NASASP-7046(11) January 1985 I Technology for tin NASA Large Space Systems

A Bibliography with Indexes

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TECHNOLOGY FOR LARGE SPACE SYSTEMS

A BIBLIOGRAPHY WITH INDEXES

Supplement 11

A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system between January 1 and June 30,1984 in

Scientific and Technical Aerospace Reports (STAR) . International Aerospace Abstracts (IA A).

Scientific and Technical Information Branch 1985 MAS National Aeronautics and Space Administration Washington, DC NOTE TO AUTHORS OF PROSPECTIVE ENTRIES:

The compilation of this bibliography results from a complete search of the STAR and IAA files. Many times a report or article is not identified because either the title, abstract, or key words did not contain appropriate words for the search. A number of words are used, but to best insure that your work is included in the bibliography, use the words Large Space Structures somewhere in your title or abstract, or include them as a key word.

This supplement is available from the National Technical Information Service (NTIS), Springfield, Virginia 22161 at the price code A07 ($14.50 domestic; $29.00 foreign). INTRODUCTION

This bibliography is designed to be helpful to the researcher and manager engaged in developing technology within the discipline areas of the Large Space Systems Technology. Also, the designers of large space systems for approved missions (in the future) will utilize the technology described in the documents referenced herein. This literature survey lists 539 reports, articles and other documents announced between January 1, 1984 and June 30, 1984 in Scientific and Technical Aerospace Reports (STAR), and International Aerospace Abstracts (IAA). The coverage includes documents that define specific missions that will require large space structures to achieve their objectives. The methods of integrating advanced technology into system configurations and ascertaining the resulting capabilities is also addressed. A wide range of structural concepts are identified. These include erectable structures which are earth fabricated and space assembled, deployable platforms and deployable antennas which are fabricated, assembled, and packaged on Earth with automatic deployment in space, and space fabricated structures which use pre-processed materials to build the structure in orbit. The supportive technology that is necessary for full utilization of these concepts is also included. These technologies are identified as analysis and design techniques, structural and thermal analysis, structural dynamics and control, electronics, advanced materials, assembly concepts, and propulsion. A General category completes the list of subjects addressed by this document. The selected items are grouped into ten categories as listed in the Table of Contents with notes regarding the scope of each category. These categories were especially selected for this publication and differ from those normally found in STAR and IAA. Each entry consists of a standard bibliographic citation accompanied by an abstract where available, and appears with the original accession numbers from the respective announcement journals. Under each of the ten categories, the entries are presented in one of two groups that appear in the following order: 1) IAA entries identified by accession number series A84-10,000 in ascending accession number order; 2) STAR entries identified by accession number series N84-10,000 in ascending accession number order. After the abstract section there are six indexes - subject, personal author, corporate source, contract number, report number, and accession number. AVAILABILITY OF CITED PUBLICATIONS

IAA ENTRIES (A84-10000 Series) All publications abstracted in this Section are available from the Technical Information Service, American Institute of Aeronautics and Astronautics, Inc. (AIAA), as follows: Paper copies of accessions are available at $8.50 per document. Microfiche*1) of documents announced in IAA are available at the rate of $4.00 per microfiche on demand. Standing order microfiche are available at the rate of $1.45 per microfiche for IAA source documents.

Minimum air-mail postage to foreign countries is $2.50 and all foreign orders are shipped on payment of pro-forma invoices.

All inquiries and requests should be addressed to AIAA Technical Information Service. Please refer to the accession number when requesting publications.

STAR ENTRIES (N84-10000 Series) One or more sources from which a document announced in STAR is available to the public is ordinarily given on the last line of the citation. The most commonly indicated sources and their acronyms or abbreviations are listed below. If the publication is available from a source other than those listed, the publisher and his address will be displayed on the availability line or in combination with the corporate source line.

Avail: NTIS. Sold by the National Technical Information Service. Prices for hard copy (HC) and microfiche (MF) are indicated by a price code preceded by the letters HC or MF in the STAR citation. Current values for the price codes are given in the tables onpageviii. Documents on microfiche are designated by a pound sign (#) following the accession number. The pound sign is used without regard to the source or quality of the microfiche. Initially distributed microfiche under the NTIS SRIM (Selected Research in Microfiche) is available at greatly reduced unit prices. For this service and for information concerning subscription to NASA printed reports, consult the NTIS Subscription Section, Springfield, Va. 22161. NOTE ON ORDERING DOCUMENTS: When ordering NASA publications (those followed by the * symbol), use the N accession number. NASA patent applications (only the specifications are offered) should be ordered by the US-Patent-Appl-SN number. Non-NASA publications (no asterisk) should be ordered by the AD, PB, or other report number shown on the last line of the citation, not by the N accession number. It is also advisable to cite the title and other bibliographic identification.

Avail: SOD (or GPO). Sold by the Superintendent of Documents, U.S. Government Printing Office, in hard copy. The current price and order number are given following the availability line. (NTIS will fill microfiche requests, as indicated above, for those documents identified by a # symbol.)

Avail: NASA Public Document Rooms. Documents so indicated may be examined at or purchased from the National Aeronautics and Space Administration, Public Document Room (Room 126), 600 Independence Ave., S.W., Washington, D.C. 20546, or public document rooms located at each of the NASA research centers, the NASA Space Technology Laboratories, and the NASA Pasadena Office at the Jet Propulsion Laboratory.

(i(1)) A microfiche is a transparent sheet cof film. 105 by 148 mm in size containing as many as 60 to 98 pages of information reduced to micro images (not to exceed 26.1 reduction). Avail: DOE Depository Libraries. Organizations in U.S. cities and abroad that maintain collections of Department of Energy reports, usually in microfiche form, are listed in Energy Research Abstracts. Services available from the DOE and its depositories are described in a booklet, DOE Technical Information Center - Its Functions and Services (TID-4660), which may be obtained without charge from the DOE Technical Information Center.

Avail: Univ. Microfilms. Documents so indicated are dissertations selected from Dissertation Abstracts and are sold by University Microfilms as xerographic copy (HC) and microfilm. All requests should cite the author and the Order Number as they appear in the citation.

Avail: USGS. Originals of many reports from the U.S. Geological Survey, which may contain color illustrations, or otherwise may not have the quality of illustrations preserved in the microfiche or facsimile reproduction, may be examined by the public at the libraries of the USGS field offices whose addresses are listed in this introduction. The libraries may be queried concerning the availability of specific documents and the possible utilization of local copying services, such as color reproduction.

Avail: HMSO. Publications of Her Majesty's Stationery Office are sold in the U.S. by Pendragon House, Inc. (PHI), Redwood City, California. The U.S. price (including a service and mailing charge) is given, or a conversion table may be obtained from PHI.

Avail: BLL (formerly NLL): British Library Lending Division, Boston Spa, Wetherby, Yorkshire, England. Photocopies available from this organization at the price shown. (If none is given, inquiry should be addressed to the BLL.)

Avail: Fachinformationszentrum, Karlsruhe. Sold by the Fachinformationszentrum Energie, Physik, Mathematik GMBH, Eggenstein Leopoldshafen, Federal Republic of Germany, at the price shown in deutschmarks (DM).

Avail: Issuing Activity, or Corporate Author, or no indication of availability. Inquiries as to the availability of these documents should be addressed to the organization shown in the citation as the corporate author of the document.

Avail: U.S. Patent and Trademark Office. Sold by Commissioner of Patents and Trademarks, U.S. Patent and Trademark Office, at the standard price of 50 cents each, postage free.

Avail: ESDU. Pricing information on specific data, computer programs, and details on ESDU topic categories can be obtained from ESDU International Ltd. Requesters in North America should use the Virginia address while all other requesters should use the London address, both of which are on page vii.

Other availabilities: If the publication is available from a source other than the above, the publisher and his address will be displayed entirely on the availability line or in combination with the corporate author line. PUBLIC COLLECTIONS OF NASA DOCUMENTS

DOMESTIC: NASA and NASA-sponsored documents and a large number of aerospace publications are available to the public for reference purposes at the library maintained by the American Institute of Aeronautics and Astronautics, Technical Information Service, 555 West 57th Street, 12th Floor, New York, New York 10019.

EUROPEAN: An extensive collection of NASA and NASA-sponsored publications is maintained by the British Library Lending Division, Boston Spa, Wetherby, Yorkshire, England for public access. The British Library Lending Division also has available many of the non-NASA publications cited in Star. European requesters may purchase facsimile copy or microfiche of NASA and NASA-sponsored documents, those identified by both the symbols # and * from ESA - Information Retrieval Service European Space Agency, 8-10 rue Mario-Nikis, 75738 Paris CEDEX 15, France.

FEDERAL DEPOSITORY LIBRARY PROGRAM

In order to provide the general public with greater access to U.S. Government publications, Congress established the Federal Depository Library Program under the Government Printing Office (GPO), with 50 regional depositories responsible for permanent retention of material, inter-library loan, and reference services. Over 1,300 other depositories also exist. A list of the regional GPO libraries appears on the inside back cover.

VI ADDRESSES OF ORGANIZATIONS

American Institute of Aeronautics and National Aeronautics and Space Astronautics Administration Technical Information Service Scientific and Technical Information 555 West 57th Street, 12th Floor Branch (NIT-1) New York, New York 10019 Washington, D.C. 20546

British Library Lending Division, National Technical Information Service Boston Spa, Wetherby, Yorkshire, 5285 Port Royal Road England Springfield, Virginia 22161

Commissioner of Patents and Pendragon House, Inc. Trademarks 899 Broadway Avenue U.S. Patent and Trademark Office Redwood City, California 94063 Washington, D.C. 20231

Department of Energy Superintendent of Documents Technical Information Center U.S. Government Printing Office P.O. Box 62 Washington, D.C. 20402 Oak Ridge, Tennessee 37830 University Microfilms ESA-lnformation Retrieval Service A Xerox Company ESRIN 300 North Zeeb Road Via Galileo Galilei Ann Arbor, Michigan 48106 00044 Frascati (Rome) Italy University Microfilms, Ltd. ESDU International, Ltd. Tylers Green 1495 Chain Bridge Road London, England McLean, Virginia 22101

U.S. Geological Survey Library ESDU International, Ltd. National Center - MS 950 251-259 Regent Street 12201 Sunrise Valley Drive London, W1R 7AD, England Reston, Virginia 22092

Fachinformationszentrum Energie, Physik, Mathematik GMBH U.S. Geological Survey Library 7514 Eggenstein Leopoldshafen 2255 North Gemini Drive Federal Republic of Germany Flagstaff, Arizona 86001

Her Majesty's Stationery Office U.S. Geological Survey P.O. Box 569, S.E. 1 345 Middlefield Road London, England Menlo Park, California 94025

NASA Scientific and Technical Information U.S. Geological Survey Library Facility Box 25046 P.O. Box 8757 Denver Federal Center, MS 914 B.W.I. Airport, Maryland 21240 Denver, Colorado 80225

VII NTIS PRICE SCHEDULES

Schedule A STANDARD PAPER COPY PRICE SCHEDULE

(Effective January 1, 1983)

Prle* Page Ring* North American Foreign Cod* Prle* Price A01 Microfiche $ 4.50 $ 8.00 A02 001-025 7.00 14.00 A03 028-050 8.50 17.00 AIM 051-075 10.00 20.00 AOS 078-100 11.50 23.00 A06 101-125 13.00 28.00

A07 126-150 14.50 29.00 AOS 151-175 16.00 32.00 A09 176-200 17.50 35.00 A10 201-225 19.00 38.00 A11 228-250 20.50 41.00

A12 251-275 22.00 44.00 A13 276-300 23.50 47.00 A14 301-325 25.00 50.00 A15 326-350 26.50 53.00 A16 351-375 28.00 56.00

A17 376-400 29.50 59.00 A18 401-425 31.00 62.00 A1B 426-450 32.50 65.00 A20 451-475 34.00 68.00 A21 476-500 35.50 71.00

A22 501-525 37.00 74.00 A23 526-550 38.50 77.00 A24 551-575 40.00 80.00 A25 576-600 41.50 83.00 A99 601-up -1 — 2

1 / Add S1.50 for each additional 25 page Increment or portion thereof for 601 pages up.

2/ Add S3.00 for each additional 25 page Increment or portion thereof for 801 pages and more.

Schedule E EXCEPTION PRICE SCHEDULE Paper Copy & Microfiche

Prle* North American Foreign Cod* Price Price E01 $ 6.50 $ 13.50 E02 7.50 15.50 EOS 9.50 19.50 £04 11.50 23.50 EOS 13.50 27.50

E06 15.50 31.50 E07 17.50 35.50 EOS 19.50 39.50 E09 21.50 43.50 £10 23.50 47.50

E11 25.50 51.50 E12 28.50 57.50 £13 31.50 63.50 £14 34.50 69.50 £15 37.50 75.50

E16 40.50 81.50 E17 43.50 88.50 £18 48.50 93.50 £19 51.50 102.50 £20 61.50 123.50

E-99 - Write tor quote

N01 35.00 45.00

VIII TABLE OF CONTENTS Page Category 01 Systems 1 Includes mission and program concepts and requirements, focus missions, conceptual studies, technology planning, systems analysis and integration, and flight experiments.

Category 02 Analysis and Design Techniques 15 Includes interactive techniques, computerized technology design and development programs, dynamic analysis techniques, environmental modeling, thermal modeling, and math modeling.

Category 03 Structural Concepts 19 Includes erectable structures (joints, struts, and columns), deployable platforms and booms, solar sail, deployable reflectors, space fabrication techniques and protrusion processing.

Category 04 Structural and Thermal Analysis 22 Includes structural analysis and design, thermal analysis and design, analysis and design techniques, and thermal control systems.

Category 05 Structural Dynamics and Control 30 Includes modeling, systems identification, attitude and control techniques, surface accuracy measurement and control techniques and systems, sensors and actuators.

Category 06 Electronics 43 Includes techniques for power and data distribution, antenna RF performance analysis, communications systems, and spacecraft charging effects.

Category 07 Advanced Materials 52 Includes matrix composites, polyimide films and thermal control coatings, bonding agents, antenna components, manufacturing techniques, and space environmental effects on materials.

Category 08 Assembly Concepts 57 Includes automated manipulator techniques, EVA, robot assembly, teleoperators, and equipment installation.

Category 09 Propulsion 61 Includes propulsion concepts and designs utilizing solar sailing, solar electric, ion, and low thrust chemical concepts.

Category 10 General 63 Includes either state-of-the-art or advanced technology which may apply to Large Space Systems and does not fit within the previous categories. Publications of conferences, seminars, and workshops are covered in this area.

Subject Index A-1 Personal Author Index B-1 Corporate Source Index C-1 Contract Number Index D-1 Report / Accession Number Index E-1 TYPICAL CITATION AND ABSTRACT FROM STAR

NASA SPONSORED DOCUMENT , | AVAILABLE ON I MICROFICHE NASA ACCESSION 11 NUMBER •*-N84-18576*# National Aeronautics and Space Administration.-. CORPORATE Washington, D. C. SOURCE TITLE SECOND ALL-UNION SEMINAR ON HYDROMECHANICS AND HEAT-MASS TRANSFER IN WEIGHTLESSNESS. ABSTRACTS OF REPORTS: TABLE OF CONTENTS / PUBLICATION AUTHORS -G. z. GERSHUNI and Y. M. ZHUKHOVITSKIY Jan. 1984^ 15 p DATE rets Trans), into ENGLISH of conf. papers, 1981 p 176-186 Seminar held in Perm, USSR, 1981 CONTRACT -(Contract NASW-3542) OR GRANT 1 MNASA-TM-77534; NAS 1.15:77534) Avail: NTIS HC A02/MF- AVAILABILITY A01 CSCL 20D SOURCE REPORT Abstracts of reports are given which were presented at the NUMBER ' Second All Union Seminar on Hydromechanics and Heat-Mass Transfer in Weightlessness. Topics inlcude: (1) features of crystallization of semiconductor materials under conditions of microacceleration; (2) experimental results of crystallization of solid solutions of CDTE-HGTE under conditions of weightlessness; (3) impurities in crystals cultivated under conditions of weightlessness; and (4) a numerical investigation of the distribution of impurities during guided crystallization of a melt B.W.

TYPICAL CITATION AND ABSTRACT FROM IAA

NASA SPONSORED DOCUMENT , AVAILABLE ON AIAA ACCESSIONII . MICROFICHE NUMBER -*-A84-11811*# Jet Propulsion Lab., California Inst. of Tech., Pasadena. TECHNOLOGY REQUIREMENTS FOR LARGE FLEXIBLE SPACED TITLE STRUCTURES AUTHORS «-B. K. WADA, R. E. FREELAND (California Institute of Technology, Jet Propulsion Laboratory, Applied Mechanics Technology Section, Pasadena, CA), and N. F. GARCIA (Lockheed Missiles and Space - AUTHOR'S Co., Inc., Sunnyvale, CA) International Astronautical Federation, AFFILIATION International Astronautical Congress,,34th, Budapest, Hungary, Oct. 10-15,1983*ff p. refs v MEETING (IAF PAPER 83-404) I Research, test, and demonstration experiments necessary for I : MEETING establishing a data base that will permit construction of large, DATE lightweight flexible space structures meeting on-orbit pointing and surface precesion criteria are discussed. Attention is focused on the wrap-rib proof-of-concept antenna structures developed from technology used on the ATS-6 satellite. The target structure will be up to 150 m in diameter or smaller, operate at RF levels, be amenable to packaging for carriage in the Shuttle bay, be capable of being ground-tested, and permit on-orbit deployment and retraction. Graphile/epoxy has been chosen as the antenna ribs material, and the antenna mesh will be gold-plated Mo wire. A 55-m diam reflector was built as proof-of-concept with ground-test capability. Tests will proceed on components, a model, the entire structure, and in-flight An analytical model has been formulated to characterize the antenna's thermal behavior. The flight test of the 55-m prototype in-orbit offers the chance to validate the analytical model and characterize the control, mechanical, and thermal characteristics of the antenna configuration. M.S.K. TECHNOLOGYFOR LARGE SPACE SYSTEMS A Bibliography (Suppl. 11)

JANUARY 1985

01 including habitabilrty, closed-loop life-support system, the scope of science application and data transfer, and the power SYSTEMS requirements. M.S.K.

Includes mission and program concepts and requirements, focus missions, conceptual studies, technology planning, systems analysis and integration, and flight experiments.

A84-11724# PAYLOAD PLACING USING AN OPERATIONAL SUPPORT A84-11731# PLATFORM APPLICATION OF A COMMON REFLECTOR CONFIGURATION J. J. RUNAVOT and O. GROSJEAN (Centre National d'Etudes TO A MULTIMISSION SATELLITE OF THE 90'S Spatiales, Toulouse, France) International Astronautical C. COUGNET, J. L PERBOS, P. SAINT-AUBERT (Matra, S.A., Federation, International Astronautical Congress, 34th, Budapest, Centre Spatiale de Toulouse, Toulouse, France), and G. Hungary, Oct. 10-15, 1983. 10 p. BERRETTA (ESA, Paris, France) International Astronautical (IAF PAPER 83-44) Federation, International Astronautical Congress, 34th, Budapest, Feasibility studies on a Hungary, Oct. 10-15, 1983. 10 p. space-platform/orbital-maneuvering-vehicle (OMV) method for (IAF PAPER 83-60) placing large (greater than 3000-kg) payloads in geosynchronous A telecommunication satellite concept is presented in which a orbit are reported. This capability is seen as required by current single reflector, common to different payloads, is applied to Ka- European plans for the period 1990-2005; an alternate procedure and Ku-band European coverage and, as a development for the currently being evaluated involves the use of an electronuclear late 1990s, C-band coverage of Africa. Attention is given to the tug. The approach considered here comprises a platform on low, configurations of the satellite and its antenna, as well as the near-equatorial orbit and a cryogenically propelled OMV capable definition of this mission and its traffic prediction analysis. No of rendezvous, docking, fuel transfer, assembly, and checking. insurmountable problems have thus far been encountered in the The payload (here, a telecommunications satellite) is launched in application of this satellite concept to the mission in question, two parts by two Ariane-type expendable rockets: the satellite and a single, long payload-fairing Ariane 4 launch appears to be itself first, and then its propulsion unit. If the propellents can be suitable. O.C. stored on the platform (from earlier operations), the maximum payload in GEO can be about 12.5 tons. This potential plus the greater flexibility and safety of this approach make it more practical, at least with current technology, than the approach using the electronuclear tug. D.G.

A84-11726*# National Aeronautics and Space Administration. Earth Resources Labs., Bay St. Louis, Miss. A84-11793*# National Aeronautics and Space Administration, OVERVIEW OF NASA SPACE STATION ACTIVITIES Washington, D. C. E. L. TILTON, III (NASA, National Space Technology Laboratories, NASA PRIORITY TECHNOLOGIES Earth Resources Laboratory, Bay St. Louis, MS) and E. B. S. R. SADIN (NASA, Office of Aeronautics and Space Technology, PRITCHARD (NASA, Langley Research Center, Hampton, VA) Washington, DC) and H. O. SLONE (NASA, Lewis Research Center, International Astronautical Federation, International Astronautical Cleveland, OH) International Astronautical Federation, Congress, 34th, Budapest, Hungary, Oct. 10-15, 1983. 12 p. International Astronautical Congress, 34th, Budapest, Hungary, Oct. (IAF PAPER 83-48) 10-15, 1983. 10 p. The architecture, functions, and human activities on-board a (IAF PAPER 83-345) space station are discussed. A manned presence is regarded as Significant research areas deserving of attention within the essential for innovative actions and successful exploitation of NASA Space Research and Technology program are discussed, weightless conditions. The station itself could be a cluster of noting that the program is pursed to strengthen the U.S. technology modules for habitation, power, operations, docking, base, improve low-cost access to space, and to aid in the expanded experimentation, and storage. Additionally, the station could provide use of space, including a space station. Study areas being pursued an interface for free-flying platforms and teleoperated satellite include new Orbiter thermal protection system materials, developing services, as well as a base for establishing space-based longer-life reusable engines, and providing the technology for orbital manufacturing facilities. NASA has projected timelines that include transfer vehicle propulsion and aeroassisted braking. Attention is initial development funding in 1987, full capabilities before the also being given to CFD techniques for entry body and rocket year 2000, and initial costs for minimum capabilities of $7.5-9 engine design, verifying the feasibility of advanced sensor concepts, billion. Architecture, mission requirements, trade-offs, and concepts defining the technology for large deployable RF antennas, and are currently being defined as a prelude to systems development. improving on-board data management systems. Of particular Attention is being given to participation by both the DoD and concern is to establish technologies which will enhance and extend other governments, and to defining the capabilities of the station. a permanent manned presence in space. M.S.K. 01 SYSTEMS

A84-11811*# Jet Propulsion Lab., California Inst. of Tech., vehicle. Consideration is devoted to management of the day-to-day Pasadena. progress of a project that involved ESA, CNES, and European TECHNOLOGY REQUIREMENTS FOR LARGE FLEXIBLE SPACE industries. Note is taken of contract features which distributed STRUCTURES authority for various management and manufacturing tasks, B. K. WADA, R. E. FREELAND (California Institute of Technology, established production and delivery schedules, specified Jet Propulsion Laboratory, Applied Mechanics Technology Section, performances, and characterized interface components. Scheduling Pasadena, CA), and N. F. GARCIA (Lockheed Missiles and Space techniques included setting margins for delivery dates in order to Co., Inc., Sunnyvale, CA) International Astronautical Federation, ameliorate the effects of the delay of delivery of any one subsystem International Astronautical Congress, 34th, Budapest, Hungary, Oct. on the project as a whole. Examples are cited from the Ariane, 10-15, 1983. 6 p. refs SPOT, and Spacelab projects. M.S.K. (IAF PAPER 83-404) Research, test, and demonstration experiments necessary for A84-15303 establishing a data base that will permit construction of large, HUMAN ORGANIZATION [ORGANISATION HUMAINE] lightweight flexible space structures meeting on-orbit pointing and M. G. DELMAS (Centre National d'Etudes Spatiales, Toulouse, surface precesion criteria are discussed. Attention is focused on France) IN: Management of large space projects; Course on the wrap-rib proof-of-concept antenna structures developed from Space Technology, Toulouse, France, May 3-14,1982, Proceedings technology used on the ATS-6 satellite. The target structure will . Toulouse, Cepadues-Editions, 1983, p. 95-108. In French. be up to 150 m in diameter or smaller, operate at RF levels, be The organizations required for a large space project are amenable to packaging for carriage in the Shuttle bay, be capable discussed, along with several of the tasks involved. A large space of being ground-tested, and permit on-orbit deployment and project is affected by its international effects, the necessary retraction. Graphite/epoxy has been chosen as the antenna ribs technical interfaces, the environments in the various countries material, and the antenna mesh will be gold-plated Mo wire. A manufacturing subsystems, and political and industrial limitations. 55-m diam reflector was built as proof-of-concept with ground-test The Telecom I project is cited as an example of a goal with capability. Tests will proceed on components, a model, the entire international implications. The participants were the client, the structure, and in-flight. An analytical model has been formulated project manager, the industries involved, the work managers, the to characterize the antenna's thermal behavior. The flight test of subcontractors, and the equipment suppliers. It was found that the 55-m prototype in-orbit offers the chance to validate the the organization was not amenable to technical hierarchies, and a analytical model and characterize the control, mechanical, and matrix organization functioned instead. A project head was thermal characteristics of the antenna configuration. M.S.K. appointed and supplied with a management structure to administer the work. The project leader coordinated the individual subprograms A84-13330 and reported directly to the governing agency. Simultaneously, a POTENTIAL MILITARY APPLICATIONS OF SPACE PLATFORMS ground station network was established for tracking and controlling AND SPACE STATIONS the satellite, as well as transmitting signals and receiving data. J. LEVY, E. RADANY, and J. TUTTLE (ORI, Inc., Silver Spring, The human interactions on an organization level were affected by MD) IN: EASCON '82; Annual Electronics and Aerospace Systems the location of authority, the dynamism of the organization, the Conference, 15th, Washington, DC, September 20-22, 1982, relations between the people involved, the management actions, Conference Record . New York, Institute of Electrical and and the experience of the participants. M.S.K. Electronics Engineers, 1982, p. 269-276. The potential applicability of space platforms and space stations A84-15304 to perform several military functions is discussed, and the role of THE CONTRACT [LE CONTRAT] man with regard to the station applications is identified. Additional M. M. VANHEMS (Centre National d'Etudes Spatiales, Toulouse, space station concepts for providing military support functions are France) IN: Management of large space projects; Course on described, and the usefulness of man in each concept is Space Technology, Toulouse, France, May 3-14,1982, Proceedings identified. Author . Toulouse, Cepadues-Editions, 1983, p. 121-140. In French. Features of contracts, negotiations, and other considerations A84-14762 which are germane to the realization of large space projects are THE TIROS-BASED ASTEROID MISSION described. The justifications, specifications, consultations, selection R. MAEHL (RCA, Astro-Electronics Div., Princeton, NJ) Spaceflight of suppliers, and negotiating considerations for contracts are (ISSN 0038-6340), vol. 25, Dec. 1983, p. 430-435. outlined. Three types of contracts are used: fixed price, controlled Mission features for a survey of the physical and chemical expenses, and incentive contracts with penalty clauses for delays. properties of asteroids that are candidates for a shift to GEO as The contracts must take account of interest, carry a bill of raw material supplies for building large space structures are particulars, detail the costs, cite administrative fees and assign described. Modified Tiros satellites could probe near-earth objects duties, and identify suppliers. Price sampling techniques are detailed in multiple-rendezvous scenarios, which would also yield data on in terms of units of account, and attention is given to methods of the evolution of the solar system. Attention would be given to modifying contracts in order to meet new or reformulated surface morphology, bulk density, density distribution, chemical and requirements, particularly those due to unanticipated cost increases mineral composition, and magnetic properties. A mission profile for supplies. M.S.K. including Shuttle launch, IDS boost, repeated orbits, and a soft landing on a single asteroid is detailed. D.H.K. A84-15305 THE PROGRESSION OF PROJECTS [LE DEROULEMENT DES A84-15301 PROJETS] MANAGEMENT OF LARGE SPACE PROJECTS; COURSE ON B. ESTADIEU (Centre National d'Etudes Spatiales, Toulouse, SPACE TECHNOLOGY, TOULOUSE, FRANCE, MAY 3-14, 1982, France) IN:.Management of large space projects; Course on PROCEEDINGS [LA GESTION DES GRANDS PRO JETS Space Technology, Toulouse, France, May 3-14,1982, Proceedings SPATIAUX; COURS DE TECHNOLOGIE SPATIALE, TOULOUSE, . Toulouse, Cepadues-Editions, 1983, p. 141-165. In French, FRANCE, MAY 3-14, 1982, EXPOSES] refs Course sponsored by the Centre National d'Etudes Spatiales. Milestones and managerial actions which are necessary during Toulouse, Cepadues-Editions, 1983, 872 p. In French and various specified phases of a large space project are explored. English. The space projects are organized by phases to coordinate Topics discussed in an 11-day course on space technology dispersed work, reduce risk, and for economic purposes such as sponsored by CNES to characterize the management techniques selecting areas needing the greatest attention. The phases include involved in the development of large space projects are presented, mission analysis, feasibility analysis, design, manufacture, with attention focused on the production of the Ariane launch production, and use. NASA avoids following the phases rigorously 01 SYSTEMS

in order to maintain flexibility during development. Industrial A84-15363 feedback is required during the different phases, as is constant COHERENT ARRAYS OF SEPARATE OPTICAL TELESCOPES monitoring of developments carried out in other countries. Reviews IN SPACE PROJECT TRIO are performed at each phase to maintain coherence in the work A. LABEYRIE (Centre d'Etudes et de Recherches Geodynamiques and assure that the goals are being met or suitably modified. The et Astronomiques, Saint-Vallier-de-Thiey, Alpes-Maritimes, France), reviews cover all aspects of the projects. M.S.K. J. KIBBLEWHITE (Cambridge University, Cambridge, England), T. DE GRAAUW, H. ROUSSEL (ESA, European Space Research and Technology Centre, Noordwijk, Netherlands), J. NOORDAM (Dwingeloo, Radiosterrewacht, Dwingeloo, Netherlands), and G. WEIGELT (Eriangen-Nuernberg, Universitaet, Erlangen, West Germany) IN: Very long baseline interferometry techniques; International Colloquium, Toulouse, France, August 31-September 2, 1982, Proceedings . Toulouse, Cepadues-Editions, 1983, p. A84-15310 477-488. MANAGEMENT OF LARGE SPACE PROJECTS - QUALITY The present investigation is concerned with optical arrays in ASSURANCE OR 'PRODUCT ASSURANCE' [GESTION DES space, taking into account floating arrays of three (Trio) or more GRANDS PROJETS SPATIAUX - ASSURANCE DE LA satellites. 'Floating arrays' consist of independent satellites which QUALITEOU 'ASSURANCE PRODUIT'] cany the optical elements separately but according to a stabilized A. DE CACQUEREY (Matra, S.A., Toulouse, France) IN: configuration. It is pointed out that floating optical arrays are Management of large space projects; Course on Space Technology, superior to rigid structures for large apertures, in the range from Toulouse, France, May 3-14, 1982, Proceedings . Toulouse, 100 m to 10 km. If they are feasible, their intrinsic modularity and Cepadues-Editions, 1983, p. 287-320. In French. flexibility should accelerate the implementation and growth of giant Quality assurance comprises predefined procedures for telescopes in space. Attention is given to the employment of obtaining products which meet all flight, ground, testing, different types of satellites, orbits, and pointing procedures, in a environmental, and performance specifications. Products for space large floating optical array. G.R. use are usually not production line items and therefore must be built right the first time, with testing covering all mechanical, A84-15634* Jet Propulsion Lab., California Inst. of Tech., electrical, thermal, radiation, and interface performance Pasadena. components. A large amount of written documentation becomes AN ADVANCED GENERATION LAND MOBILE SATELLITE necessary in order to trace the progress of development of all SYSTEM AND ITS CRITICAL TECHNOLOGIES subsystems and ameliorate any adverse effects due to the differing F. NADERI (California Institute of Technology, Jet Propulsion motivations of the industrial sector and other participants engaged Laboratory, Pasadena, CA) IN: NTC '82; National Telesystems in the enterprise. Product assurance is constrained by the large Conference, Galveston, TX, November 7-10, 1982, Conference number of interfaces within both the product, which may originate Record . New York, Institute of Electrical and Electronics Engineers, from off-the-shelf, original, and modified designs with subsystems Inc., 1982, p. B1.1.1-B1.1.8. NASA-supported research. manufactured in diverse places, and the organizations participating A conceptual design for a Land Mobile Satellite System (LMSS) in the project. M.S.K. for the 1990s is presented. LMSS involves small tranceivers accessing satellites directly, with ground reception through small car-top antennas. The satellite would have a large antenna and blanket coverage areas in the UHF. The call may originate from a home, be carried by wire to a gateway, transmitted to satellite on the S-band, converted to UHF on the satellite, and transmitted to the vehicle. The system design is constrained by the number of A84-1532S users in an area during the busiest hours, Shuttle storage, THE SPACELAB PROGRAM - THE MANAGEMENT OF THE controllability factors, and the total area served. A 55-m antenna PROGRAM, PROBLEMS ENCOUNTERED AND THE SOLUTIONS has been selected, with 87 spot beams and two 10 MHz UHF ADOPTED [LE PROGRAMME SPACELAB - LA GESTION DU bands in the 806-890 MHz band. A 17 dB interbeam isolation PROGRAMME, LES PROBLEMES RENCONTRES ET LES level is required, implying that sufficient sub-bands can be SOLUTIONS ADOPTEES] generated to assure 8265 total channels. The mobile satellite B. R. K. PFEIFFER (ESA, European Space Research and (MSAT) would have an 83 m mast lower segment, a 34 m upper Technology Centre, Noordwijk, Netherlands) IN: Management of segment, and a second, 10 m antenna made of a deployable large space projects; Course on Space Technology, Toulouse, mesh. Various antenna function modes are considered. M.S.K. France, May 3-14, 1982, Proceedings . Toulouse, Cepadues-Editions, 1983, p. 773-838. In French. A84-15695 The management techniques applied by ESA in the Spacelab SPACE OPERATIONS CENTER COMMUNICATIONS PATH (SL) development program are reviewed critically. The history, OBSCURATION objectives, and contractual responsibilities of ESA and NASA are J. R. CARL and B. P. LU (Lockheed Engineering and Management summarized, and the SL modules to besupplied by ESA are Services Co., Inc., Houston, TX) IN: NTC '82; National Telesystems characterized. The management structure is presented, with Conference, Galveston, TX; November 7-10, 1982, Conference discussion of the roles of ESA and industry, the phases of the Record . New York, Institute of Electrical and Electronics Engineers, program, the principal reviews, documentation, verification, ongoing Inc., 1982, p. F1.2.1-F1.2.5. control of specifications, quality control and security, cost control Computer assisted techniques were developed to determine and the evolution of the budget, the geographical distribution of the obscuration of a communications path caused by the physical the contracts, delay control, and configuration management. Block objects that comprise the Space Operations Center (SOC). Of diagrams, sample worksheets, graphs, and maps are provided. particular interest in this paper is the obscuration of the line-of-sight The problems of the SL program are seen as primarily technical, path from an antenna, mounted somewhere on or in the vicinity associated with an insufficient initial technical base, overly diffuse of the SOC, to a geosynchronous satellite, such as a Telemetry management control, substantial modifications during development, Data Relay Satellite. The dynamic geometry of this type of problem and contractual and economic difficulties arising from the technical makes it difficult to visualize, in a complete manner, without the problems. It is shown that the management techniques adopted aid of a computer. Blockage is shown graphically by during the second half of the program limited the cost overrun to computer-generated displays, and the percentage of time that the 40 percent of the original budget and ensured the successful path is blocked is calculated. Graphics permit a ready comparison fulfillment of the technical objectives. T.K. of one antenna location to another. Author 01 SYSTEMS

A84-18005# station with unmanned platforms and transportation-node capability LOW COST SPACE SCIEHCE AND ASTRONOMY PLATFORMS (OTV, TMS). The latter option is found most promising and IN ORBIT developed further, with consideration of the technical challenges P. M. MITCHELL (Martin Marietta Aerospace, New Orleans, LA) involved. T.K. and T. C. TAYLOR (Taylor and Associates, Inc., Wrightwood, CA) American Institute of Aeronautics and Astronautics, Aerospace A84-24634*# National Aeronautics and Space Administration, Sciences Meeting, 22nd, Reno, NV, Jan. 9-12, 1984. 12 p. refs Washington, D. C. (AIAA PAPER 84-0297) SPACE STATION ARCHITECTURAL ISSUES AS VIEWED BY Design concepts for orbital space-science or astronomy THE USER COMMUNITY - APPLICATIONS platforms utilizing the STS external propellant tank (ET) as primary W. P. RANEY (NASA, Washington, DC) IN: Space station: Policy, structure are presented. It is pointed out that the 68,000-pound, planning and utilization; Proceedings of the Symposium, Arlington, 154-ft-long, 27.5-ft-diameter ET currently attains 98 percent of VA, July 18-20,1983 . New York, American Institute of Aeronautics orbital velocity and could be placed in LEO for little additional and Astronautics, 1983, p. 139-141. cost. General modifications to the ET, such as additional wiring Potential applications of the proposed space station are briefly and tubing, the bolt-on aft cargo carrier, an environmental protection examined. Areas considered include communications (bulk traffic, system, avionics, and attitude control, are discussed. Hardware direct broadcast, and assembly of GEO platforms), earth sciences for four specific missions is described in detail: a dedicated (repair and refurbishment of long-term spacecraft), and materials commercial platform; a life-science platform with growth chambers processing. The importance of developing a comfortable habitat for algae, marine fauna, or aeroponically grown plants; a is stressed. T.K. large-deployable-reflector platform; and a gamma-ray imaging telescope. Drawings illustrating the design concepts are provided. A84-25260* D.G. THE FRANCO-GERMAN DBS PROGRAM TV-SAT/TDF-1' R. ARNIM (Eurosatellite GmbH, Munich, West Germany) IN: A84-21573 Communication Satellite Systems Conference, 10th, Orlando, FL, SPACE VEHICLES [O KOSMOLETAKH] March 19-22, 1984, Technical Papers . New York, American K. FEOKTISTOV and I. BUBNOV Moscow, Izdatel'stvo Molodaia Institute of Aeronautics and Astronautics, 1984, p. 75-83. Gvardiia, 1982, 208 p. In Russian. (AIAA PAPER 84-0661) The Soviet cosmonaut Feoktistov gives an informal, popular Governmental authorities of Germany and France have jointly sketch of his participation in the Soviet space program. Part of awarded a contract to industry for two DBS satellites, to be the book consists of a dialogue on space issues conducted with launched in 1985, which will then serve Germany and France the journalist Bubnov. Topics discussed include the development with direct-to-home broadcasting. This paper provides an overview of the first spacecraft, problems in the planning of the first manned of the background of the Franco-German program, the scope of flights and the first space stations, and the future of man in the program, its technical baseline and configuration, its delivery space. B.J. schedule, its present status, and information on the customer and contractor side. Author A84-24628*# National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. A84-25282# INTEGRATED REQUIREMENTS FOR A SPACE STATION DEVELOPMENT AND APPLICATION OF NEW TECHNOLOGIES E. B. PRITCHARD (NASA, Langley Research Center, Hampton, IN THE ESA OLYMPUS PROGRAMME VA) IN: Space station: Policy, planning and utilization; Proceedings R. BONHOMME, B. L. HERDAN, and R. STEELS (ESA, Olympus of the Symposium, Arlington, VA, July 18-20, 1983 . New York, Programme Office, Noordwijk, Netherlands) IN: Communication American Institute of Aeronautics and Astronautics, 1983, p. Satellite Systems Conference, 10th, Orlando, FL, March 19-22, 23-32. 1984, Technical Papers . New York, American Institute of The time-phased mission set developed for the proposed space Aeronautics and Astronautics, 1984, p. 249-262. station program (including the manned facility, coorbiting and (AIAA PAPER 84-0706) remote free flyers and platforms, orbital maneuvering and transfer The European Space Agency (ESA) Olympus Program systems, and storage and service facilities) by the Space Station constitutes one of the most ambitious current developments in Mission Requirements Workshop in May 1983, is presented in the communications satellite field. The development program has figures and tables and discussed. The scientific, commercial, and now been underway for nearly two years. This paper describes a technology-development proposals are characterized, and the number of the innovative features and new technologies being requirements for a station and coorbiting platform at 28.5-deg orbital incorporated in the satellite design. The latest status of design, inclination are listed for the period 1991-2000. Japanese, ESA, analysis and test of platform and payload hardware is given together and Canadian utilization is considered, special requirements are with planning for near-term future activities, and commentary on outlined, and functional characteristics are summarized. future prospects for Olympus large spacecraft derivatives. Developmental strategies to meet the concerns of the user Author community are suggested. T.K. A84-25287# A84-24633*# National Aeronautics and Space Administration, TELE-X - THE FIRST STEP IN A SATELLITE COMMUNICATIONS Washington, D. C. SYSTEM FOR THE NORDIC COUNTRIES ARCHITECTURAL OPTIONS AND DEVELOPMENT ISSUES L BACKLUND, L. ANDERSON, A. EKMAN, S. GRAHN, L. L. E. POWELL (NASA, Washington, DC) IN: Space station: Policy, JALMARSSON, and L-l. LUNDSTROM (Svenska planning and utilization; Proceedings of the Symposium, Arlington, Rymdaktiebolaget, Solna, Sweden) IN: Communication Satellite VA, July 18-20, 1983 . New York, American Institute of Aeronautics Systems Conference, 10th, Orlando, FL, March 19-22, 1984, and Astronautics, 1983, p. 131-135. Technical Papers . New York, American Institute of Aeronautics The design options for the space station are discussed in and Astronautics, 1984, p. 299-309. general terms, reflecting the approach taken by the NASA Concept (AIAA PAPER 84-0713) Development Group. Primary aims are flexibility and transparency, The development and design of Tele-X, an experimental TV to fulfill as many scientific and commercial user requirements as and telecommunications satellite to be launched in 1986 by possible and to open the station to as many new users as possible; Sweden, Norway, and Finland, are discussed. The history of the utilities, facilities, and functional support must be designed to meet cooperative R&D venture is traced from the beginning of Nordsat these aims. General architecture options considered include the studies in 1974 through the 1977 WARC frequency and orbit present STS, an extended STS, a limited-duration manned allocations and the initiation of the Viking research-satellite program transportation node with unmanned platforms, and a manned and the Tele-X program in the late 1970s. The Tele-X spacecraft 01 SYSTEMS and its payload are modified versions of the TV-Sat/TDF-1 satellite Only in a few cases - materials science and processing, and space design being completed by France and the FRG. Primary services sciences (earth observation) - can possible commercial usage be to be provided include TV (using two 230-W TWTA transponders realised. This, of course, does not exclude the creation of so-called in the 18/12-GHz bands) and data/video communication (using by-products/spin-offs which have been a feature of existing space one wide-band and one narrow-band transponder in the 14/12-GHz programmes e.g. pocket computers, microminiaturised solid state bands and serving a fully switched digital network at 64 kbit/sec electronics, quartz watches, etc. The participation of Europe in and 2 Mbit/sec). Experimental transmissions at 8, 34, and 140 developing hardware and facilities for a US Space Station is seen Mbit/sec will also be undertaken. Block diagrams, drawings, tables as a major near and long term goal. Author of performance data, and a coverage map are included. T.K. A84-27945 A84-25308# LEASECRAFT - AN INNOVATIVE SPACE VEHICLE LAND-MOBILE COMMUNICATIONS SATELLITE SYSTEM J. DESKEVICH (Fairchild Space Co., Germantown, MD) IEEE DESIGN Transactions on Aerospace and Electronic Systems (ISSN M. HORSTEIN (TRW, Inc.. TRW Space and Technology Group, 0018-9251), vol. AES-20, Jan. 1984, p. 25-37. Redondo Beach, CA) IN: Communication Satellite Systems The Leasecraft system has been developed by an American Conference, 10th, Orlando, FL, March 19-22, 1984, Technical aerospace company with the objective to further the industrialization Papers . New York, American Institute of Aeronautics and of space with its significant business potential. This system Astronautics, 1984, p. 467-475. refs comprises a low orbit space platform, an operation control center, (AIAA PAPER 84-0753) user accommodations, and services such as payload interfaces, Satellite system designs capable of providing land-mobile documentation, and ground support equipment and procedures. satellite service to a population of 350,000 radio-telephone Potential applications of Leasecraft considered are related to the subcribers are considered. The problems discussed include processing of Pharmaceuticals and materials, satellite-aided search frequency allocation, modulation, system sizing, carrier assignment, and rescue, data collection, and support of NASA's astrophysics satellite/gateway links, satellite-link design, and mobile unit antenna programs. The Leasecraft space vehicle will accommodate up to design. Data on link noise allocation and satellite-to-mobile and five modular power subsystems, including a communications and mobile-to-satellite link budgets are presented. A satellite description data handling module, a modular attitude control subsystem, a is briefly given, and the feed-cluster approach to beam formation special function module, two alternative solar array assemblies, a is summarized. Economic aspects and alternate system designs tracking and data relay satellite system antenna assembly, a are also addressed. C.D. propulsion module, and optional primary and secondary payload modules. G.R. A84-25326*# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. A84-29043* National Aeronautics and Space Administration. NASA'S GEOSTATIONARY COMMUNICATIONS PLATFORM Ames Research Center, Moffett Field, Calif. PROGRAM ENVIRONMENTAL CONTROL AND LIFE SUPPORT FOR AN J. RAMLER (NASA, Lewis Research Center, Cleveland, OH) and EVOLUTIONARY SPACE STATION R. DURRETT (NASA, Marshall Space Flight Center, Huntsville, P. D. QUATTRONE (NASA, Ames Research Center, Moffett Field, AL) IN: Communication Satellite Systems Conference, 10th, CA) and R. A. WYNVEEN (Life Systems, Inc., Cleveland, OH) Orlando, FL, March 19-22, 1984, Technical Papers . New York, AIAA, SAE, ASME, AlChE, and ASMA, Intersociety Conference American Institute of Aeronautics and Astronautics, 1984, p. on Environmental Systems, 13th, San Francisco, CA, July 11-13, 613-621. refs 1983. 18 p. refs (AIAA PAPER 84-0702) (SAE PAPER 831108) This paper reviews recent trends in communications satellites The requirements for the Space Station are being defined. and explains NASA's current interest in geostationary The Environmental Control/Life Support System (ECLSS) is one communications platforms. Large communications platforms of its 13 systems. The ECLSS is further divided into five functional capable of supporting multiple payloads with common utilities have categories. Major ones are the Air Revitalization and Water been examined in a number of studies since 1974 and appear to Reclamation Systems. The paper presents ECLSS performance offer a number of potential advantages. In 1981, an Industry Briefing requirements, average design loads and fluids interfaces. The major and Workshop sponsord by NASA focused on the institutional, cost savings of regenerable ECLSS techniques versus the open operational and technical issues that will influence the loop approach are quantified. Issues impacting ECLSS design are implementation of geostationary platforms. The workshop identified cited. Priority regenerable ECLSS developments are reviewed numerous issues and problem areas that needed more detailed including the Electrochemical CO2 Concentrator, Static Feed study. To address the issues/problems identified, a NASA Electrolyzer and Automated Control/Monitor Instrumentation. geostationary communications platform program has been Baseline and alternative approaches are cited. The ECLSS planning developed. This program is described, focusing on the initial studies issues are reviewed including functional boundaries, planning to be performed. Author schedule, technology maturity definition and technology gaps. The paper concludes with a review of water electrolysis as a Space A84-26926 Station utility impacting ECLSS design. Author EVOLUTIONARY CONCEPTS FOR A SPACE STATION AND THE RELEVANT UTILISATION POTENTIAL A84-29044* National Aeronautics and Space Administration. P. W. SHARP (ERNO Raumfahrttechnik GmbH, Bremen, West Lyndon B. Johnson Space Center, Houston, Tex. Germany) British Interplanetary Society, Journal (Space SYSTEMS ENGINEERING ASPECTS OF A PRELIMINARY Technology) (ISSN 0007-084X), vol. 37. April 1984, p. 157-162. CONCEPTUAL DESIGN OF THE SPACE STATION Two basic evolutionary concept approaches for the realisation ENVIRONMENTAL CONTROL AND LIFE SUPPORT SYSTEM of a space station are discussed in this paper. They are respectively C. H. LIN and M. S. MEYER (NASA, Johnson Space Center, the US manned station and the European unmanned station. Both Houston. TX) AIAA, SAE, ASME, AlChE, and ASMA, Intersociety concepts as detailed here are currently under investigation; the Conference on Environmental Systems, 13th, San Francisco, CA, goal of both programmes is to have an operational system early July 11-13, 1983. 19 p. in the 1990's. Even though no single space discipline can justify (SAE PAPER 831109) the establishment of such a station, it is this author's opinion that The systems engineering aspects of developing a conceptual both will be built, not in competition but as two compatible systems design of the Space Station Environmental Control and Life Support being part of a larger space infrastructure. The majority of payloads System (ECLSS) are discussed. Topics covered include defining which will utilise the facilities of the space station will be of a system requirements and groundrules for approach, formulating scientific nature e.g. life sciences, extraterrestrial research, etc. possible cycle closure options, and establishing a system-level 01 SYSTEMS mass balance on the essential materials processed in oxygen resin bed cyclic absorption/desorption systems which may furnish and water cycles. Consideration is also given to the performance CO2 removal for a regenerative space station environmental control of a system trade-off study to determine the best degree of cycle and life support system, with attention to the sizing of their closure for the ECLSS, and the construction of a conceptual design respective subsystems. The analysis includes identification of of the ECLSS with subsystem performance specifications and subsystem boundaries, which are defined as the hardware required candidate concepts. For the optimum balance between for the replacement of the nonregenerable substances otherwise development costs, technological risks, and resupply penalties, a employed in the space station system. It is found that the EDC partially closed cycle ECLSS option is suggested. C.M. concept has a far lower equivalent weight than the alternative. O.C. A84-29046* National Aeronautics and Space Administration. Lyndon B. Johnson Space Center, Houston, Tex. INTEGRATED WATER MANAGEMENT SYSTEM - DESCRIPTION AND TEST RESULTS N. C. ELDEN, H. E. WINKLER, D. F. PRICE (NASA, Johnson Space Center, Houston, TX), and R. P. REYSA (Boeing Aerospace Co., Houston, TX) AIAA, SAE, ASME, AlChE, and ASMA, A84-29056 Intersociety Conference on Environmental Systems, 13th, San PHASE CHANGE WATER RECOVERY TECHNIQUES - VAPOR Francisco, CA, July 11-13, 1983. 13 p. refs COMPRESSION DISTILLATION AND (SAE PAPER 831111) THERMOELECTRIC/MEMBRANE CONCEPTS Water recovery subsystems are being tested at the NASA F. H. SCHUBERT (Life Systems, Inc., Cleveland, OH) AIAA, Lyndon B. Johnson Space Center for Space Station use to process SAE, ASME, AlChE, and ASMA, Intersociety Conference on waste water generated from urine and wash water collection Environmental Systems, 13th, San Francisco, CA, July 11-13,1983. facilities. These subsystems are being integrated into a water 17 p. refs management system that will incorporate wash water and urine (SAE PAPER 831122) processing through the use of hyperfiltration and vapor compression The Vapor Compression Distillation (VCD) and distillation subsystems. Other hardware in the water management thermoelectric/membrane evaporation concepts, both of which system includes a whole body shower, a clothes washing facility, involve phase change recovery processes and attempt to minimize a urine collection and pretreatment unit, a recovered water the energy input/unit mass of water recovered by using heat post-treatment system, and a water quality monitor. This paper released by condensation as energy for further evaporation, are describes the integrated test configuration, pertinent performance being considered for the recovery of water from urine and other data, and feasibility and design compatibility conclusions of the waste waters in a space station regenerative life support system. integrated water management system. Author Comparisons between these alternatives are conducted in light of configurational and subsystem schematics, component sizing considerations, and projected operational characteristics. The A84-29047* Boeing Aerospace Co., Houston, Tex. thermoelectric concept is found to be 26 percent heavier, with 56 HYPERFILTRATION WASH WATER RECOVERY SUBSYSTEM - percent higher total equivalent weight and more than twice the DESIGN AND TEST RESULTS energy/unit mass of water recovered by the alternative VCD R. P. REYSA (Boeing Aerospace Co., Houston, TX), D. F. PRICE process. O.C. (NASA, Johnson Space Center, Houston, TX), T. OLCOTT (Lockheed Missiles and Space Corp., Palo Alto, CA), and J. L. GADDIS (Clemson University, Clemson, SC) AIAA, SAE, ASME, AlChE, and ASMA, Intersociety Conference on Environmental Systems, 13th, San Francisco, CA, July 11-13, 1983. 12 p. refs (SAE PAPER 831112) The Hyperfiltration Wash Water Recovery (HWWR) subsystem, A84-29666# designed to offer low-power high-volume wash water purification SERVICING VEHICLE FOR SATELLITES AND PLATFORMS IN for extended mission spacecraft, is discussed in terms of LOW EARTH ORBITS [WARTUNGSFAHRZEUG FUER preprototype design and configuration. Heated wash water SATELLITEN UND PLATTFORMEN IN NIEDRIGEN collected from the shower, hand wash, and laundry flows into a ERDUMLAUFBAHNEN] temperature-controlled (374 K) waste storage tank. Two parallel W. KLEINAU (Messerschmitt-Boelkow-Blohm GmbH, Ottobrunn, 25 micron absolute filters at the tank outlet remove large particles West Germany) Deutsche Gesellschaft fuer Luft- und Raumfahrt, from the feed stream. A positive displacement feed pump delivers Jahrestagung, Munich, West Germany, Oct. 17-19, 1983. 58 p. In wash water to the hyperfiltration module at a constant flow rate German. of 0.20 Ipm with discharge pressure variations from 4181-7239 (DGLR PAPER 83-102) Kpa. The hyperfiltration membrane module is a single-pass design A report is presented of studies which were conducted by two including 36 porous stainless steel tubes, and is designed to provide German aerospace companies. A scenario for the time period an approximate water recovery rate of 90 percent. Permeate and from 1988 to 2000 is considered, and the concept of an Interorbital brine water flows are monitored by flow meters, and removal of Transfer and Logistics Vehicle (IOTLV) for applications involving urea and ammonia is achieved by adding 15 percent NaOCI solution the low earth orbit (LEO) is presented. The IOTLV is based on to the permeate fluid stream. An alternate module design using existing European technology, and a modular concept has been two diameters of tubing (allowing a smaller pressure drop and a employed. A description is given of the individual modules of the larger membrane area) gave a superior predicted performance 'Modular Orbital Operations Systems' (MOOS). Six types of vehicles over the first module with larger tubing throughout. J.N. can be obtained for more than 16 identified missions by using six modules in appropriate combinations. The modules include the A84-29054 Modular Orbital Propulsion System (MOPS), the Modular Auxiliary ELECTROCHEMICAL AND STEARfl-DESORBED AMINE CO2 Tank System (MATS), the Modular Orbital Servicing System CONCENTRATION SUBSYSTEM COMPARISON (MOSS), the Modular Equipment and Avionics System (MEAS), D. B. HEPPNER and F. H. SCHUBERT (Life Systems, Inc., the Modular Orbital Reentry System (MORS), and the Modular Cleveland, OH) AIAA, SAE, ASME, AlChE, and ASMA, Intersociety Orbital Crew Cabin (MOCC). It is pointed out that the modular Conference on Environmental Systems, 13th, San Francisco, CA, IOTLV is cost effective with respect to total costs and yearly July 11-13, 1983. 11 p. refs maximum costs. The development can be easily assigned to (SAE PAPER 831120) different European countries and firms. It is estimated that the A comparative study has been conducted for the continuous transfer stage could be available in 1989 and the servicing vehicle Electrochemical Depolarized CO2 Concentration (EDC) and amine in 1990. G.R. 01 SYSTEMS

A84-29853* National Aeronautics and Space Administration. N84-15171*# Teledyne Brown Engineering, Huntsville, Ala Lyndon B. Johnson Space Center, Houston, Tex. Payload Missions Integration Div. HABITABILITY DESIGN ELEMENTS FOR A SPACE STATION PAYLOAD MISSIONS INTEGRATION Progress Report, 19 Sep. M. C. DALTON (NASA, Johnson Space Center, Houston, TX) IN: - 11 Nov. 1983 Space manufacturing 1983; Proceedings of the Sixth Conference, 28 Nov. 1983 52 p Princeton, NJ, May 9-12, 1983 . San Diego, CA, Univelt, Inc., (Contract NAS8-32712) 1983, p. 9-26. (NASA-CR-170949; NAS 1.26:170949; PMIC-MA03-469-29; (AAS PAPER 83-200) PO-83-506) Avail: NTIS HC A04/MF A01 CSCL 22B Habitability in space refers to the components, characteristics, Spacelab missions 1 to 3, OSTA partial payloads, Astro-1 conditions, and design parameters that go beyond but include the mission, premission definition, and mission peculiar equipment basic life sustaining requirements. Elements of habitability covered support structure are discussed. Author include internal environment, architecture, mobility and restraint, food, clothing, personal hygiene, housekeeping, communications, N84-15172*# National Aeronautics and Space Administration. and crew activities. All elements are interrelated and need to be Langley Research Center, Hampton, Va. treated as an overall discipline. Designing for a space station is AN ALTERNATE CONCEPT FOR EXPANDING MAN'S similar to designing on earth but with 'space rules' instead of PRESENCE IN SPACE ground rules. It is concluded that some habitability problems require W. R. HOOK and R. S. OSBORNE Feb. 1983 43 p refs behavioral science solutions. C.M. (NASA-TM-84617; NAS 1.15:84617) Avail: NTIS HC A03/MF A01 CSCL 22A A logical next step after shuttle is a manned orbital service system (MOSS) consisting of a two-man crew module mated with A84-29858 a propulsion module. The resulting spacecraft would remain in REUSABLE COMMERCIAL SPACE PROCESSING PLATFORMS low Earth orbit for months or years at a time conducting civil or D. E. KOELLE (Messerschmitt-Boelkow-Blohm GmbH, Ottobrunn, military satellite servicing, experimental, or applications missions West Germany) IN: Space manufacturing 1983; Proceedings of while being periodically supplied and refueled by Shuttle flights the Sixth Conference, Princeton, NJ, May 9-12, 1983 . San Diego, from the ground. The system would accumulate experience CA, Univelt, Inc., 1983, p. 119-133. invaluable to the design of future large and more expensive (AAS PAPER 83-208) spacecraft. Key features of the vehicle are versatility and mobility. The paper deals with the new concept of reusable Shuttle With Centaur-type propulsion and a large payload, the MOSS could platforms: it describes their special features and the specific leave an initial orbit of 370 km (200 nmi) altitude and inclinations applications. The first demonstration of this concept is performed up to 56 deg, make a plane change of up to + or - 14 deg, by the SPAS-01 platform developed by MBB as commercial venture, reach altitudes to 5500 km (2970 nmi), and then return the payload launched on STS-07. Reusable platforms provide advantages for to the original orbit altitude and inclination. Obviously, the size of commercial space processing operations. They provide an essential the performance envelope varies with the payload and cost reduction compared to previous alternatives, together with propulsion-unit selected. The MOSS can reach orbits and perform extended operation periods (several months) and high microgravity tasks not possible with Shuttle alone or with the much larger level. The characteristics of the EURECA platform are given and space stations currently being proposed. Author a commercial version (OMNI-SPAS) of similar performance is discussed. Finally, economic and cost aspects are dealt with for N84-15179*# National Aeronautics and Space Administration. reusable platforms as well as for future permanent space Langley Research Center, Hampton, Va. platforms. Author CAPTURE-EJECTOR SATELLITES I. O. MACCONOCHIE, C. H. ELDRED, and J. A. MARTIN Oct. 1983 23 p refs Previously announced in IAA as A82-43265 (NASA-TM-85686; NAS 1.15:85686) Avail: NTIS HC A02/MF M84-12026*# National Aeronautics and Space Administration. A01 CSCL 22B Langley Research Center, Hampton, Va. A satellite in the form of a large rotating rim which can be RESEARCH AND TECHNOLOGY, 1983 Annual Report used to boost spacecraft from low-Earth orbit to higher orbits is Nov. 1983 96 p described. The rim rotates in the plane of its orbit such that the (NASA-TM-85702; NAS 1.15:85702) Avail: NTIS HC A05/MF lower portion of the rim is traveling at suborbital velocity, while A01 CSCL 05B the upper portion is travelling at greater than orbital velocity. Highlights of major accomplishments and applications made Ascending spacecraft or payloads arrive at the lowest portion of during the past year illustrate the broad range of research and the rim at suborbital velocities, where the payloads are released technology activities at the Langley Research Center. Advances on a trajectory for higher orbits; descending payloads employ the are reported in the following areas: systems engineering and reverse procedure. Electric thrusters placed on the rim maintain operation; aeronautics; electronics; space applications; aircraft and rim rotational speed and altitude. From the standpoint of currently spacecraft structures; composite structures; laminar flow control; known materials, the capture-ejector concept may be useful for subsonic transport aircraft; and supersonic fighter concepts. relatively small velocity increments. Author Technology utilization efforts described cover a hyperthermia monitor, a lightweight composite wheelchair; and a vehicle ride N84-17211*# National Aeronautics and Space Administration. quality meter. A.R.H. Langley Research Center, Hampton, Va. STEP EXPERIMENT REQUIREMENTS M. L BRUMFIELD, comp, Jan. 1984 347 p refs Workshop held in Hampton, Va., 28 Jun. - 1 Jul. 1983 N84-14234# Committee on Science and Technology (U. S. (NASA-CP-2294; L-15733; NAS 1.55:2294) Avail: NTIS HC House). A15/MFA01 CSCL22B NASA'S SPACE STATION ACTIVITIES A plan to develop a space technology experiments platform Washington GPO 1983 161 p Hearing before the Subcomm. (STEP) was examined. NASA Langley Research Center held a on Space Sci. and Appl. of the Comm. on Sci. and Technol., 98th STEP Experiment Requirements Workshop on June 29 and 30 Congr., 1st Sess., no. 37, 2 Aug. 1983 and July 1, 1983, at which experiment proposers were invited to (GPO-27-393) Avail: Subcommittee on Space Science and present more detailed information on their experiment concept Applications and requirements. A feasibility and preliminary definition study was The status, plans, and activities associated with NASA's space conducted and the preliminary definition of STEP capabilities and station effort are reviewed. N.W. experiment concepts and expected requirements for support 01 SYSTEMS services are presented. The preliminary definition of STEP N84-17220*# Astro Research Corp., Carpinteria, Calif. capabilities based on detailed review of potential experiment THE STEP/STACBEAM EXPERIMENT TECHNOLOGY requirements is investigated. Topics discussed include: Shuttle DEVELOPMENT FOR VERY LARGE SOLAR ARRAY on-orbit dynamics; effects of the space environment on damping DEPLOYERS materials; erectable beam experiment; technology for development R. SAMUELS In NASA. Langley Research Center STEP Expt. of very large solar array deployers; thermal energy management Requirements p 135-146 Jan. 1984 refs process experiment; photovoltaic concentrater pointing dynamics Avail: NTIS HC A15/MF A01 CSCL 22B and plasma interactions; vibration isolation technology; flight tests The Stacking Triangular Articulated Compact Beam of a synthetic aperture radar antenna with use of STEP. (STACBEAM) is discussed with reference to structural testing experiments afforded by ground simulation and the Space Technology Experiments Platform (STEP). The STACBEAM lends itself to a deployment technique which offers a radical improvement N84-17212*# National Aeronautics and Space Administration. in flexible blanket solar array technology. A system for deployment Langley Research Center, Hampton, Va. and support of a solar array blanket is described which consists SPACE TECHNOLOGY EXPERIMENTS PLATFORM (STEP) of the blanket, its containment structure, the support structure OVERVIEW and its deployer, the blanket stiffening battens, and the deployable J. E. HARRIS In its STEP Expt. Requirements p 1-12 Jan. boom standoffs. In operation, the blanket is pulled out and 1984 supported by the STACBEAM which packages next to the folded Avail: NTIS HC A15/MF A01 CSCL 22B blanket. Since the STACBEAM does not rotate during extension, The Space Technology Experiments Platform (STEP) concept complete control of the blanket is maintained during extension. is summarized. It is shown that STEP is the enabling link between Deployment of this system occurs one bay at a time in a sequential the research community and the space environment made manner. The deployer provides sufficient rigidity so that beam accessible by the Space Transportation System (STS). The stiffness is not degraded during the deployment process. M.G. constituent elements of the research community are identified, the pertinent space environment attributes are listed, and the major N84-17221*# Massachusetts Inst. of Tech., Cambridge. Space guidelines applicable to establishing the specific STEP configuration Systems Lab. are identified. E.A.K. GENERAL REQUIREMENTS FOR SHUTTLE FLIGHT EXPERIMENTS E. F. CRAWLEY In NASA. Langley Research Center STEP Expt. Requirements p 147-154 Jan. 1984 N84-17213*# National Aeronautics and Space Administration. Avail: NTISHCA15/MF A01 CSCL 22A Langley Research Center, Hampton, Va. Requirements and guiding principles for flight space structures STEP MECHANICAL SYSTEMS experiments are defined. Shuttle mid-deck experiments, Space O. H. BRADLEY, JR. In its STEP Expt. Requirements p 13-34 Technology Experiments Platform (STEP) tests, and the EVA Jan. 1984 Assembly of Structures Experiment (EASE) are addressed. M.G. Avail: NTIS HC A15/MF A01 CSCL 22B The key elements in the STEP system are depicted including N84-17231*# McDonnell-Douglas Astronautics Co., Huntington the Spacelab pallet, a modular interface structure, and pallet Beach, Calif. mounted electronics. Several concepts for potential experiments STEP FLIGHT EXPERIMENTS LARGE DEPLOYABLE are illustrated. E.A.K. REFLECTOR (LDR) TELESCOPE F. C. RUNGE In NASA. Langley Research Center STEP Expt. Requirements p 257-278 Jan. 1984 N84-17215*# National Aeronautics and Space Administration. Avail: NTISHCA15/MF A01 CSCL 03A Langley Research Center, Hampton, Va. Flight testing plans for a large deployable infrared reflector STEP EXPERIMENT INTEGRATION telescope to be tested on a space platform are discussed. J. C. MOORMAN In its STEP Expt. Requirements p 47-54 Subsystem parts, subassemblies, and whole assemblies are Jan. 1984 discussed. Assurance of operational deployability, rigidization, Avail: NTIS HC A15/MF A01 CSCL 22B alignment, and serviceability will be sought. R.J.F. The space technology experiments platform (STEP) integration was examined. Topics include: experiment design, fabrication, and N84-17232*# National Aeronautics and Space Administration. assembly; experiment performance and environmental testing; Langley Research Center, Hampton, Va. STEP compatibility testing; STEP experiment integration; LARGE DEPLOYABLE ANTENNA FLIGHT EXPERIMENT FOR STS/payload requirements definition documentation. E.A.K. THE SPACE TECHNOLOGY EXPERIMENTS PLATFORM (STEP) B. C. TANKERSLY (Harris Corp.) and T. G. CAMPBELL In its STEP Expt. Requirements p 279-300 Jan. 1984 N84-17218*# National Aeronautics and Space Administration. Avail: NTIS HC A15/MF A01 CSCL 22B Langley Research Center, Hampton, Va. Spaceborne experiments to test the deployment reliability of DEPLOYABLE BEAM FLIGHT EXPERIMENT (MAST) large space antennas are discussed. Retraction, reflector surface B. R. HANKS and J. L. ALLEN, JR. In its STEP Expt. Requirements tolerance, thermal distortion, electromagnetic performance, and p 103-120 Jan. 1984 refs dynamic controls are discussed. R.J.F. Avail: NTISHCA15/MFA01 CSCL 22B Improvement of technology of space systems control is N84-17233*# Jet Propulsion Lab., California Inst. of Tech., discussed. Future space systems such as large antennas or a Pasadena. space station may have dimensions on the order of 30 m to 200 THE 55-METER-STRUCTURE FLIGHT EXPERIMENT m, yet their basic structures may be relatively lightweight and J. A. GARBA, R. FREELAND, B. K. WADA, K. J. OKEEFE flexible, making ground tests for loads, controls analyses, and (Lockheed Missile and Space Co., Sunnyvale, Calif.), and A. design verifications questionable if not impossible. Abandoning the WOODS (Lockheed Missile and Space Co., Sunnyvale, Calif.) In extensive ground test and analysis verification program that led to NASA. Langley Research Center STEP Expt. Requirements p the success of previous spacecraft is not a sensible option; making 301-310 Jan. 1984 it meaningful using current technology will require inefficient, Avail: NTISHCA15/MFA01 CSCL 22B ultraconservative structure and control designs. New test methods The verification and demonstration of the structural performance are outlined. E.A.K. related parameters for large flexible space structures are discussed. 01 SYSTEMS

The objectives are to verify the deployment repeatability of static to package within the Space Transportation System (STS) cargo surface contour, to demonstrate the feasibility of in-flight static bay. After separation, the antenna, its integral feed mast, radiometer shape correction, to verify predicted shape in a zero gravity thermal receivers, power system, and other instruments are automatically environment, to determine zero gravity structural dynamic deployed and transferred to the operational orbit The design characteristics, and to verify the instrumentation and excitation resulted in an antenna with a major antenna dimension of 120 system for in-flight measurements. R.J.F. meters, weighing 7650 kilograms, and operating at an altitude of 700 kilometers. Author N84-17234*# National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. LARGE INFLATED-ANTENNA SYSTEM N84-17947# National Aeronautics and Space Administration. W. F. HINSON and L S. KEAFER In its STEP Expt. Requirements Langley Research Center, Hampton, Va. p 311 -324 Jan. 1984 refs SPLINE-BASED ESTIMATION TECHNIQUES FOR PARAMETERS Avail: NTIS HC A15/MF A01 CSCL 22B IN ELLIPTIC DISTRIBUTED SYSTEMS It is proposed that for inflatable antenna systems, technology H. T. BANKS (Brown Univ.), P. L DANIEL (Southern Methodist feasibility can be demonstrated and parametric design and Univ.), and E. S. ARMSTRONG Jun. 1983 19 p scalability (scale factor 10 to 20) can be validated with an (Contract AF-AFOSR-0198-81; AF PROJ. 2304) experiment using a 16-m-diameter antenna attached to the Shuttle. (NASA-TM-85439; NAS 1.15:85439; AD-A135109; LCDS-83-22; The antenna configuration consists of a thin film cone and AFOSR-83-0926TR) Avail: NTIS HC A02/MF A01 CSCL 12A paraboloid held to proper shape by internal pressure and a Parameter and state estimation techniques are discussed for self-rigidizing torus. The cone and paraboloid would be made using an elliptic system arising in a developmental model for the antenna pie-shaped gores with the paraboloid being coated with aluminum surface in the Maypole Hoop/Column antenna. A computational to provide reflectivity. The torus would be constructed using an algorithm based on spline approximations for the state and elastic aluminum polyester composite that when inflated would erect to a parameters is given and numerical results obtained using this smooth shell that can withstand loads without internal pressure. algorithm are summarized. Author (GRA) R.J.F.

N84-17237*# Department of Communications, Ottawa (Ontario). Directorate of Space Mechanics. N84-18116# Committee on Science and Technology (U. S. FLIGHT TEST OF A SYNTHETIC APERTURE RADAR ANTENNA House). USING STEP NATIONAL AERONAUTICS AND SPACE ADMINISTRATION D. G. ZIMCIK, F. R. VIGERON, and S. AHMED In NASA. Langley ACT, 1985 Research Center STEP Expt. Requirements p 339-354 Jan. Washington GPO 1984 10 p A bill referred to the Comm. 1984 on Sci. and Technol., 98th Congr., 2nd Sess., 8 Feb. 1984 Avail: NTIS HC A15/MF A01 CSCL 171 Avail: US Capitol, House Document Room To establish confidence in its overall performance, credible Appropriations to the National Aeronautics and Space information on the synthetic aperture radar antenna's mechanical Administration for research and development, space flight, control properties in orbit must be obtained. However, the antenna's size, and data communications, construction of facilities, and research design, and operating environment make it difficult to simulate and program management, and for other purposes were operating conditions under 1-g Earth conditions. The Space authorized. Author Technology Experiments Platform (STEP) offers a timely opportunity to mechanically qualify and characterize the antenna design in a representative environment. The proposed experimental N84-18265*# Boeing Aerospace Co., Seattle, Wash. configuration would employ a half-system of the full-scale SPACE STATION NEEDS, ATTRIBUTES AND ARCHITECTURAL RADARSAT antenna which would be mounted on the STEP OPTIONS STUDY. VOLUME 1: EXECUTIVE STUDY Final platform in the orbiter cargo bay such that it could be deployed Report and retracted in orbit (as shown in this figure). The antenna would 21 Apr. 1983 69 p refs be subjected to typical environmental exposures while an array of (Contract NASW-3680) targets and sensors on the antenna support structure and reflecting (NASA-CR-173334; NAS 1.26:173334; D180-27477-1-VOL-1) surface are observed and monitored. In particular, the typical Avail: NTIS HC A04/MF A01 CSCL 22B environments would include deployment and retraction, dynamic Mission identification and validation, the benefits of a manned response to vehicle thruster or base exciter inputs, and thermal presence in space; attributes and architectures; time-phased soak and transient effects upon entering or exiting Earth eclipse. mission and system requirements imposed on the space station; The proposed experiment would also provide generic information orbit selection; space station architectural options; technology on the properties of targe space structures in space and on selection; and program planning are addressed. N.W. techniques to obtain the desired information. R.J.F.

N84-17248*# Martin Marietta Aerospace, Denver, Colo. TECHNOLOGY NEEDS OF ADVANCED EARTH OBSERVATION N84-18266*# Boeing Aerospace Co., Seattle, Wash. SPACECRAFT Final Report SPACE STATION NEEDS, ATTRIBUTES AND ARCHITECTURAL J. J. HERBERT. J. R. POSTUCHOW, and W. A. SCHARTEL OPTIONS STUDY. VOLUME 2: MISSION ANALYSIS Final Washington NASA Jan. 1984 261 p Report (Contract NAS1-16756) 21 Apr. 1983 412 p refs (NASA-CR-3698; NAS 1.26:3698; MCR-81-630) Avail: NTIS HC (Contract NASW-3680) A12/MF A01 CSCL 22B (NASA-CR-173333; NAS 1.26:173333; D180-27477-2-VOL-2) Remote sensing missions were synthesized which could Avail: NTIS HC A18/MF A01 CSCL 22B contribute significantly to the understanding of global environmental Space environment studies, astrophysics, Earth environment, parameters. Instruments capable of sensing important land and life sciences, and material sciences are discussed. Commercial sea parameters are combined with a large antenna designed to communication, materials processing, and Earth observation passively quantify surface emitted radiation at several wavelengths. missions are addressed. Technology development, space A conceptual design for this large deployable antenna was operations, scenarios of operational capability, mission developed. All subsystems required to make the antenna an requirements, and benefits analysis results for space-produced autonomous spacecraft were conceptually designed. The entire gallium arsenide crystals, direct broadcasting satellite systems, and package, including necessary orbit transfer propulsion, is folded a high inclination space station are covered. N.W.

9 01 SYSTEMS

N84-18267*# Boeing Aerospace Co., Seattle, Wash. gross mission model benefit derived from these capabilities is S5.9B SPACE STATION NEEDS, ATTRIBUTES AND ARCHITECTURAL without the industrial park, and S9.3B with it. Other benefits include OPTIONS STUDY. VOLUMES: REQUIREMENTS the lowering of acquisition costs for NASA and DoD space assets 21 Apr. 1983 57 p refs and a basis for broadening international participation. A.R.H. (Contract NASW-3680) (NASA-CR-173332; NAS 1.26:173332; D180-27477-3-VOL-3) Avail: NTIS HC A94/MF A01 CSCL 22B A typical system specification format is presented and N84-18271*# McDonnell-Douglas Astronautics Co., Huntington requirements are compiled. A Program Specification Tree is shown Beach, Calif. showing a high inclination space station and a low inclination SPACE STATION NEEDS, ATTRIBUTES AND ARCHITECTURAL space station with their typical element breakdown, also OPTIONS: SUMMARY BRIEFING Final Report represented along the top blocks are the interfaces with other Apr. 1983 120 p refs systems. The specification format is directed at the Low Inclination (Contract NASW-3687) space station. Author (NASA-CR-173328; NAS 1.26:173328; MDC-H0180A) Avail: NTIS HC A06/MF A01 CSCL 22B N84-18268*# Boeing Aerospace Co., Seattle, Wash. Computerized data sorting and analysis techniques were used SPACE STATION NEEDS, ATTRIBUTES AND ARCHITECTURAL with a data base accumulated in over 20 years of space station OPTIONS STUDY. VOLUME 4: ARCHITECTURAL OPTIONS, studies to evaluate candidate missions and select a final model SUBSYSTEMS, TECHNOLOGY AND PROGRAMMATICS Final of 88 missions. The social, cultural, scientific, technical, and Report commercial benefits to be accrued from each mission were 21 Apr. 1983 207 p refs identified. Requirements were determined for satellite servicing; (Contract NASW-3680) payload placement and retrieval; refueling; repair; testing; assembly; (NASA-CR-173331; NAS 1.26:173331; D180-27477-4-VOL-4) and construction. Missions drivers determined include crew, remote Avail: NTIS HC A10/MF A01 CSCL 22B manipulating system, external parts, instrumentation, extravehicular Space station architectural options, habitability considerations activity/manned maneuvering unit, and voice/video equipment. and subsystem analyses, technology, and programmatics are User interest for commercial applications were determined. Variable reviewed. The methodology employed for conceiving and defining architecture based on a modular concept with multi-use elements space station concepts is presented. As a result of this approach, is proposed. A.R.H. architectures were conceived and along with their supporting rationale are described within this portion of the report. Habitability consideration and subsystem analyses describe the human factors associated with space station operations and includes subsections N84-18272'# TRW Space Technology Labs., Redondo Beach, covering (1) data management, (2) communications and tracking, Calif. (3) environmental control and life support, (4) manipulator systems, SPACE STATION NEEDS, ATTRIBUTES AND ARCHITECTURAL (5) resupply, (6) pointing, (7) thermal management and (8) interface OPTIONS STUDY. FINAL REVIEW EXECUTIVE SUMMARY standardization. A consolidated matrix of subsystems technology BRIEFING issues as related to meeting the mission needs for a 1990's era 5 Apr. 1983 136 p refs space station is presented. Within the programmatics portion, a (Contract NASW-3681) brief description of costing and program strategies is outlined. (NASA-CR-173674; NAS 1.26:173674) Avail: NTIS HC A07/MF Author A01 CSCL 22B User needs and mission requirements, architecture and mission N84-18269*# Boeing Aerospace Co., Seattle, Wash. implementation, and program costs and benefits are discussed. SPACE STATION NEEDS, ATTRIBUTES AND ARCHITECTURAL Author OPTIONS STUDY. FINAL EXECUTIVE REVIEW 5 Apr. 1983 126 p refs (Contract NASW-3680) (NASA-CR-173335; NAS 1.26:173335; D180-27477-6) Avail: N84-18273*# Martin Marietta Aerospace, Bethesda, Md. Space NTIS HC A07/MF A01 CSCL 22B and Electronics Systems Div. Identification and validation of missions, the benefits of manned SPACE STATION NEEDS, ATTRIBUTES AND ARCHITECTURAL presence in space, attributes and architectures, space station OPTIONS STUDY. BRIEFING MATERIAL: FINAL REVIEW AND requirements, orbit selection, space station architectural options, EXECUTIVE SUMMARY technology selection, and program planning are addressed. Apr. 1983 70 p refs Sponsored in part by Department of N.W. Defense (Contract NASW-3686) N84-18270*# Grumman Aerospace Corp., Bethpage, N.Y. (NASA-CR-173321; NAS 1.26:173321; SOC-SE-02-02) Avail: SPACE STATION NEEDS, ATTRIBUTES AND ARCHITECTURAL NTIS HC A04/MF A01 CSCL 228 OPTIONS. PART 1: SUMMARY Final Briefing Report Advantages and disadvantages were assessed for configuration 9 Apr. 1983 150 p refs Prepared in cooperation with COMSAT options for a modular 14' diameter space station, a modular aft General and General Electric cargo carrier and a shuttle derived vehicle. Early, intermediate, (Contract NASW-3685) and mature configurations were defined as well as power (NASA-CR-175382; NAS 1.26:175382; SA-SSP-RP009-PT-1) requirements, heat rejection, hydrazine usage, and the external Avail: NTIS HC A07/MF A01 CSCL 228 scavenging concept. Subsystems were analyzed for propulsion, Candidate missions for the space station were subjected to an attitude control, data processing, and communications. Areas of evaluation/filtering process which included the application of uncertainties, associated costs and benefits, and the cost by phase budgetary constraints and performance of benefits analysis. Results of the modular and shuttle derived vehicle configurations were show that the initial space station should be manned, placed in a identified. Technologies assessed included solar vs nuclear; gravity 28.5 deg orbit, and provide capabilities which include a space gradient vs active control; heat pipe radiators vs fluid loops; test facility, satellite service, a transport harbor, and an observatory. distributed processors vs centralized, and modular vs shuttle A space industrial park may be added once further development derived configuration. It was determined that the early space station effort validates the cost and expanding commercial market for architecture should include: (1) reusable OTV with aerobraking; space-processed material. Using the space station as a national (2) TMS with telepresence services; (3) OTV/TMS refueling and space test facility can enhance national security, as well as servicing capability; and (4) attached research laboratories for life commercial and scientific interests alike. The potential accrued sciences and materials processing. A.R.H.

10 01 SYSTEMS

N84-18274*# Rockwell International Corp., Downey, Calif. Shuttle N84-18279*# Texas Woman's Univ., Houston. Integration and Satellite Systems Div. CREW AND LIFE SUPPORT: EVA SPACE STATION NEEDS, ATTRIBUTES, AND ARCHITECTURAL R. S. JOHNSTON In NASA. Langley Research Center Space OPTIONS STUDY Final Executive Summary Briefing Station Technol., 1983 p 25-32 Feb. 1984 6 Apr. 1983 79 p Avail: NTIS HC A09/MF A01 CSCL 22B (Contract NASW-3683) Four general recommendations by the EVA subpanel are listed (NASA-CR-173327; MAS 1.26:173327; SSD-83-0037) Avail: as follows: 1) EVA design standard document needs to be dveloped NTIS HC A05/MF A01 CSCL 22B in the next 6 to 12 months and updated as technology progresses. Recommended program architecture; missions and 2) NASA needs to couple EVA design personnel closer to the requirements, programmatic evolution; space station architecture, user community. 3) there appears to be a lack of centralized technology, and cost; and space'Station attributes and benefits NASA responsibility for the EVA community. 4) Panel activity should are discussed. N.W. continue to promote exchange of information and understanding of user problems, and to stimulate technology activity. Author N84-18275*# General Dynamics/Convair, Fort Worth, Tex. N84-18280*# General Dynamics Corp., San Diego, Calif. SPACE STATION NEEDS, ATTRIBUTES AND ARCHITECTURAL CREW AND LIFE SUPPORT: ECLSS OPTIONS. SUMMARY OF MAJOR STUDY ACTIVITIES AND G. DRAKE In NASA. Langley Research Center Space Station RESULTS. SPACE STATION PROGRAM OBSERVATIONS Final Technol., 1983 p 33-40 Feb. 1984 Briefing Report O. STEINBRONN and D. CHARHUT 5 Apr. 1983 136 p refs Avail: NTIS HC A09/MF A01 CSCL 22B The schedule NASA has proposed has four main elements. (Contract NASW-3682) The focal point of all the life support activity is demonstrator for (NASA-CR-173345; NAS 1.26:173345) Avail: NTIS HC A07/MF the initial space station. The demonstrator is composed of items A01 CSCL 22B that are ready for Phase C and D development. Technical options Space station study logic, commercial applications, total mission are scheduled during the early years to provide alternatives because set space station system, mission requirements, free flyer missions, the capability to substitute must be maintained. Growth technology a baseline time phased mission set, and space systems architecture and supporting research and technology (SR&T) will continue are discussed. N.W. throughout the program life, and as new items emerge, the space station capability will be updated. Author N84-18277*# National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. N84-18282*# Little (Arthur D.), Inc., Cambridge, Mass. SPACE STATION TECHNOLOGY, 1983 HUMAN CAPABILITIES R. L WRIGHT, ed. and C. R. MAYS, ed. Feb. 1984 189 p W. AUGERSON In NASA. Langley Research Center Space Workshop held in Williamsburg, Va., 28-31 Mar. 1983 Station Technol., 1983 p61-83 Feb. 1984 (NASA-CP-2293; L-15732; NAS 1.55:2293) Avail: NTIS HC Avail: NTIS HC A09/MF A01 CSCL 22B A09/MF A01 CSCL 22B In conclusion, habitability is more than just life support and This publication is a compilation of the panel summaries there is a substantial technology application void. Habitability needs presented in the following areas: systems/operations technology; both visibility and responsibility in the space station program to crew and life support; EVA; crew and life support: ECLSS; attitude, ensure the optimum use of man in space. In the area of work control, and stabilization; human capabilities; auxiliary propulsion; technology, IVA and EVA teleoperators and robotics should be fluid management; communications; structures and mechanisms; considered as tools and not competitors. A generic work station data management; power, and thermal control. The objective of is a contemporary of the early space stations. Flexibility of a future the workshop was to aid the Space Station Technology Steering space station requires this. Author Committee in defining and implementing a technology development program to support the establishment of a permanent human N84-18283*# Aerojet-General Corp., Sacramento, Calif. presence in space. This compilation will provide the participants AUXILIARY PROPULSION and their organizations with the information presented at this S. D. ROSENBERG In NASA. Langley Research Center Space workshop in a referenceable format. This information will establish Station Technol., 1983 p 85-87 Feb. 1984 a stepping stone for users of space station technology to develop Avail: NTIS HC A09/MF A01 CSCL 228 new technology and plan future tasks. When man is put in the loop, almost anything can happen. Caution must be exercised in permitting life cycle costs analysis N84-18278*# Boeing Aerospace Co., Seattle, Wash. to control technology investment. One of the ways of reducing SYSTEMS/OPERATIONS TECHNOLOGY cost is to stay with the old tried and true technology. However, G. R. WOODCOCK In NASA. Langley Research Center Space when requirements of a permanent space station are considered Station Technol., 1983 p 1-24 Feb. 1984 (15-year life, the issues associated with health monitoring, Avail: NTIS HC A09/MF A01 CSCL 22B maintenance, and repair), the conclusion is that very little, if The deliberations of the Systems/Operations Technology Panel anything, is really state of the art. Before investing in old are summarized. The first real question that arose was to develop technologies to make them comply with the requirements of a an understanding of what systems/operations technology is. A permanent space station, the question of whether or not it is relativelynew discipline in the NASA technology organization, worth putting the money there as opposed to advancing the state necessitates the definition of the objectives. Two objectives were of the art should be considered. Program managers and system established: (1) to make new things possible, and (2) to make designers must not make the mistake of selecting old technologies existing capabilities cost less or work better. Making new things in the belief that they are state of the art. Author possible is not really applicable in the case of a space station. Both Salyut 7 and Skylab indicate that space stations are possible N84-18284*# Martin Marietta Corp., Denver, Colo. with existing (not necessarily new) technology. There was a concern FLUID MANAGEMENT on the part of some of the penelists that work better might mean D. FESTER In NASA. Langley Research Center Space Station higher performance, and that is not necessarily the case at all. Technol., 1983 p 89-94 Feb. 1984 Work better may mean simply to provide better service to the Avail: NTIS HC A09/MF A01 CSCL 22B users of the space station at lower cost. The panel felt this to be The Fluid Management Panel's assessment of the technology a more realistic viewpoint. As evidenced from interaction with users is summarized. Since a baseline space station was not defined (and all of the contractors found this basically to be true), the as a reference guide and the results of the eight contracted space users want low cost, no schedule constraints, and no hassles. station studies were not available as input, the assessment focused Author on technology and not programmatics. The ground rules that were

11 01 SYSTEMS key to the deliberations and guided the assessment are: (1) The Ni-H2 battery concept, and the regenrative hydrogen-oxygen space station will be operational in 1991, and (2) A space-based system utilizing essentially the Shuttle orbiter type of fuel cell. OTV will be operational in 1992. Thus, the capability to transport, Author transfer, and resupply all fluids, including those for the OTV, is required in the initial space station. The only evolutionary aspect is the refinement of capability. Fluid management includes fluid transport to orbit, liquid storage/supply, fluid transfer/resupply, and N84-18290*# Lockheed Missiles and Space Co., Sunnyvale, integral thermal control. Author Calif. SPACE STATION NEEDS, ATTRIBUTES AND ARCHITECTURAL N84-18285*# TRW Electronic Systems Group, Redondo Beach, OPTIONS. VOLUME 4, ATTACHMENT 1: TASK 2 AND 3 Calif. MISSION IMPLEMENTATION AND COST Final Study Report COMMUNICATIONS 22 Apr. 1983 393 p refs G. J. BONELLE In NASA. Langley Research Center Space (Contract NASW-3684) Station Technol., 1983 p 95-108 Feb. 1984 (NASA-CR-173330; NAS 1.26:173330; Avail: NTIS HC A09/MF A01 CSCL 22B LMSC-D889718-VOL-4-ATTACH-1) Avail: NTIS HC A17/MF Communications in any system is one of the last technologies A01 CSCL 22B to be considered, and sometimes it is considered too late to impact Mission scenario analysis and architectural concepts, alternative the system. This was somewhat the impression on reviewing the systems concepts, mission operations and architectural NASA budget for two mission scenarios for the space station. development, architectural analysis trades, evolution, configuration, However, that budget fortunately was well spent, and the money and technology development are assessed. N.W. was spent to get the most benefit per dollar. Another thing that is very often forgotten is that technology is not produced in a vacuum. In fact, in conducting independent research and development N84-18291*# Lockheed Missiles and Space Co., Sunnyvale, (IR&D), the first phase is to define the requirements which must Calif. be time phased, becuase very often the conditions will change SPACE STATION NEEDS, ATTRIBUTES AND ARCHITECTURAL during the life of the system. From the requirements, a set of OPTIONS. VOLUME 2, ATTACHMENT 2: SUPPORTING DATA architectures that are at least representative of that era are AND ANALYSIS REPORTS Final Study Report produced. If the exact requirements were not established, at least 22 Apr. 1983 174 p refs boundaries are set on the requirements for that architecture. When (Contract NASW-3684) this is completed, then the technology that is really needed is (NASA-CR-173329; NAS 1.26:173329; defined. The major criticism of the work that was presented to LMSC-D889718-VOL-2-ATTACH-2) Avail: NTIS HC A08/MF the panel is the lack of a firm set of requirements. Author A01 CSCL 22B Architectural impact analysis, configuration concepts evaluation, N84-18287*# McDonnell-Douglas Astronautics Co., Huntington CADAM draining file, EVA technology needs and manned system Beach, Calif. technology requirements are provided. N.W. DATA MANAGEMENT G. LOVE In NASA. Langley Research Center Space Station Technol., 1983 p 137-154 Feb. 1984 Avail: NTIS HC A09/MF A01 CSCL 22B N84-18292*# Lockheed Missiles and Space Co., Sunnyvale, The following tasks were prioritized: software acquisition Calif. management plan; space station flight data system architectural SPACE STATION NEEDS, ATTRIBUTES AND ARCHITECTURAL study; space station user data system interface; automation of OPTIONS. VOLUME 1: EXECUTIVE SUMMARY NASA Final software development process; automation of software testing; Presentation Report distributed data base management; ADA (automated data 5 Apr. 1983 368 p refs acquisition) evaluation and transition and planning; network (Contract NASW-3684) operating system software; fault tolerant computer validation (NASA-CR-172792; NAS 1.26:172792; LMSC-D889718-VOL-1) methodology for onboard data management system; systems Avail: NTIS HC A16/MF A01 CSCL 22B integration; artificial intelligence/expert systems; space station data The uses alignment plan was implemented. The existing data network concept; space station standard interface protocols; space bank was used to define a large number of station requirements. station data networks systems; integrated software development Ten to 20 valid mission scenarios were developed. Architectural facility; and language trade studies. Author options as they are influenced by communications operations, subsystem evolvability, and required technology growth are defined. N84-18288*# Lockheed Missiles and Space Co., Sunnyvale, Costing of evolutionary concepts, alternative approaches, and Calif. options, was based on minimum design details. N.W. POWER R. CORBETT In NASA. Langley Research Center Space Station Technol., 1983 p 155-163 Feb. 1984 Avail: NTIS HC A09/MF A01 CSCL 22B N84-18293*# Lockheed Missiles and Space Co., Sunnyvale, The space station requires an increase in power or energy of Calif. at least several orders of magnitude compared to previous space SPACE STATION NEEDS, ATTRIBUTES AND ARCHITECTURAL missions. With the requirement up in the range of 10 kilowatt OPTIONS. VOLUME 1, ATTACHMENT 1: EXECUTIVE hours, this obviiously requires the development of new technology. SUMMARY NASA Final Study Report Although the power area is very well integrated in the spacecraft 22 Apr. 1983 -281 p refs itself, it represents a diverse set of components necessary for (Contract NASW-3684) energy conversion, electronics, and energy distribution. (NASA-CR-173337; NAS 1.26:173337; Considerable work is ongoing at NASA Lewis in the power devices LMSC-D889718-VOL-1-ATTACH-1) Avail: NTIS HC A13/MF development area, including transformers, large area solid-state A01 CSCL 22B chips, transistors, and fast recovery diodes. This work is oriented User alignment plan, physical and life sciences and applications, toward eventual application to both AC and DC power conversion commercial requirements national security, space operations, user approaches. In the energy storage area, there are many options needs, foreign contacts, mission scenario analysis and architectural available to fit into the space station representing various degrees concepts, alternative systems concepts, mission operations of risk and leverage combination, such as the near-term architectural development, architectural analysis trades, evolution, integral-pressure-vessel nickel hydrogen battery, an advanced configuration, and technology development are discussed. N.W.

12 01 SYSTEMS

N84-18294*# Lockheed Missiles and Space Co., Sunnyvale, companies that were asked to review it Key commercial Calif. telecommunications comments are summarized the actual SPACE STATION NEEDS, ATTRIBUTES AND ARCHITECTURAL response letters from the industry are included. A.R.H. OPTIONS. VOLUME 1, ATTACHMENT 2: SUPPORTING DATA AND ANALYSIS REPORTS Final Study Report N84-18299*# Grumman Aerospace Corp., Bethpage, N.Y. 22 Apr. 1983 402 p refs SPACE STATION NEEDS, ATTRIBUTES AND ARCHITECTURAL (Contract NASW-3684) OPTIONS. VOLUME 2, BOOK 1, PART 4: PAYLOAD ELEMENT (NASA-CR-173336; NAS 1.26:173336; MISSION DATA SHEETS Final Technical Report LMSC-D889718-VOL-1-ATTACH-2) Avail: NTIS HC A18/MF 20 Apr. 1984 299 p refs A01 CSCL 22B (Contract NASW-3685) Reference space station evolution, a contact list, a data base, (NASA-CR-173315; NAS 1.26:173315; scenarios, and subcontractor reports are considered. N.W. SA-SSP-RP008-VOL-2-BK-1-PT-4) Avail: NTIS HC A13/MF A01 CSCL 22B N84-18296*# Grumman Aerospace Corp., Bethpage, N.Y. Data sheets are presented for 11 internal payloads, 30 externally SPACE STATION NEEDS, ATTRIBUTES AND ARCHITECTURAL mounted payloads, and 46 free flyers. The importance of the space OPTIONS. VOLUME 2, BOOK 1, PART 1: MISSION station to each payload element is rated on a scale of 1 to 10. REQUIREMENTS Final Technical Report The type of experiment noncommercial science and applications, 20 Apr. 1983 210 p refs commercial, technological, and operational is indicated and the (Contract NASW-3685) payload and its objectives are described. Space is provided for (NASA-CR-173312; NAS 1.26:173312; noting requirements for power; data/communication; thermal SA-SSP-RP008-VOL-2-BK-1-PT-1) Avail: NTIS HC A10/MF A01 environment; equipment physical characteristics; crew size; and CSCL 22B service and maintenance. A.R.H. The baseline mission model used to develop the space station mission-related requirements is described as well as the 90 civil N84-18300*# Grumman Aerospace Corp., Bethpage, N.Y. missions that were evaluated, (including the 62 missions that SPACE STATION NEEDS, ATTRIBUTES AND ARCHITECTURAL formed the baseline model). Mission-related requirements for the OPTIONS. VOLUME 2, BOOK 2, PART 1: MISSION space station baseline are defined and related to space station IMPLEMENTATION CONCEPTS Final Technical Report architectural development. Mission-related sensitivity analyses are 20 Apr. 1983 188 p refs discussed. A.R.H. (Contract NASW-3685) (NASA-CR-173316; NAS 1.26:173316; N84-18297*# Grumman Aerospace Corp., Bethpage, N.Y. SA-SSP-RP008-VOL-2-BK-2-PT-1) Avail: NTIS HC A09/MF A01 SPACE STATION NEEDS, ATTRIBUTES AND ARCHITECTURAL CSCL 22B OPTIONS. VOLUME 2, BOOK 1, PART 2, TASK 1: MISSION The overall configuration and modules of the initial and evolved REQUIREMENTS Final Technical Report space station are described as well as tended industrial and polar 20 Apr. 1983 239 p refs platforms. The mass properties that are the basis for costing are (Contract NASW-3685) summarized. User friendly attributes (interfaces, resources, and (NASA-CR-173313; NAS 1.26:173313; facilities) are identified for commercial; science and applications; SA-SPP-RP008-VOL-2-BK-1-PT-2) Avail: NTIS HC A11/MF A01 industrial park; international participation; national security; and the CSCL 22B external tank option. Configuration alternates studied to determine Mission areas analyzed for input to the baseline mission model a baseline are examined. Commonality for clustered 3-man and include: (1) commercial materials processing, including 9-man stations are considered as well as the use of tethered representative missions for producing metallurgical, chemical and platforms. Requirements are indicated for electrical, communication biological products; (2) commercial Earth observation, represented and tracking; data management Subsystem requirements for by a typical carry-on mission amenable to commercialization; (3) electrical, data management, communication and tracking, solar terrestrial and resource observations including missions in environment control/life support system; and guidance navigation geoscience and scientific land observation; (4) global environment, and control subsystems are identified. A.R.H. including representative missions in meteorology, climatology, ocean science, and atmospheric science; (5) materials science, N84-18301*# Grumman Aerospace Corp., Bethpage, N.Y. including missions for measuring material properties, studying SPACE STATION NEEDS, ATTRIBUTES AND ARCHITECTURAL chemical reactions and utilizing the high vacuum-pumping capacity OPTIONS. VOLUME 2, BOOK 2, PART 2, TASK 2: of space; and (6) life sciences with experiments in biomedicine INFORMATION MANAGEMENT SYSTEM Final Technical and animal and plant biology. A.R.H. Report 20 Apr. 1983 315 p refs Prepared in cooperation with N84-18298*# Grumman Aerospace Corp., Bethpage, N.Y. General Electric Corp. SPACE STATION NEEDS, ATTRIBUTES AND ARCHITECTURAL (Contract NASW-3685) OPTIONS. VOLUME 2, BOOK 1, PART 3: MANNED SPACE (NASA-CR-173317; NAS 1.26:173317; STATION RELEVANCE TO COMMERCIAL SA-SSP-RP008-VOL-2-BK-2-PT-2) Avail: NTIS HC A14/MF A01 TELECOMMUNICATIONS SATELLITES Final Technical Report CSCL 22B 20 Apr. 1983 77 p refs , Missions to be performed, station operations and functions to (Contract NASW-3685) be carried out, and technologies anticipated during the time frame (NASA-CR-173314; NAS 1.26:173314; of the space station were examined in order to determine the SA-SSP-RP008-VOL-2-BK-1-PT-3) Avail: NTIS HC A05/MF A01 scope of the overall information management system for the space CSCL 22B station. This system comprises: (1) the data management system A document containing a forecast of satellite traffic and revelant which includes onboard computer related hardware and software technology trends to the year 2000 was prepared which includes required to assume and exercise control of all activities performed those space station capabilities and characteristics that should be on the station; (2) the communication system for both internal provided to make the station useful to commercial satellite owners. and external communications; and (3) the ground segment. The document was circulated to key representative organizations Techniques used to examine the information system from a within the commercial telecommunications satellite and related functional and performance point of view are described as well communities of interest, including spacecraft manufacturers, as the analyses performed to derive the architecture of both the commercial satellite owners, communications carriers, networks onboard data management system and the system for internal and risk insurers. The prospectus document is presented as well and external communications. These architectures are then used as the transmittal letter and the mailing list of the people and to generate a conceptual design of the onboard elements in order

13 01 SYSTEMS to determine the physical parameters (size/weight/power) of the N84-19377*# General Dynamics/Convair, Fort Worth, Tex. hardware and software. The ground segment elements are DEFINITION OF TECHNOLOGY DEVELOPMENT MISSIONS FOR summarized. A.R.H. EARLY SPACE STATIONS ORBIT TRANSFER VEHICLE SERVING. PHASE 2, TASK 1: SPACE STATION SUPPORT OF OPERATIONAL OTV SERVICING N84-18302*# Grumman Aerospace Corp., Bethpage, N.Y. Dec. 1983 245 p refs SPACE STATION NEEDS, ATTRIBUTES AND ARCHITECTURAL (Contract NAS8-35039) OPTIONS. VOLUME 2, BOOK 2, PART 3: COMMUNICATION (NASA-CR-170984; NAS 1.26:170984; GDC-SP-83-067) Avail: SYSTEM Final Technical Report NTIS HC A11 /MF A01 CSCL 22A 20 Apr. 1983 64 p refs Representative space based orbital transfer vehicles (OTV), (Contract NASW-3685) ground based vehicle turnaround assessment, functional (NASA-CR-173318; NAS 1.26:173318; operational requirements and facilities, mission turnaround SA-SSP-RP008-VOL-2-BK-2-PT-3) Avail: NTIS HC A04/MF A01 operations, a comparison of ground based versus space based CSCL 22B tasks, activation of servicing facilities prior to IOC, fleet operations Preliminary results of the study of the architecture and attributes requirements, maintenance facilities, OTV servicing facilities, space of the RF communications and tracking subsystem of the space station support requirements, and packaging for delivery are station are summarized. Only communications between the space discussed. N.W. station and other external elements such as TDRSS satellites, low-orbit spacecraft, OTV, MOTV, in the general environment of N84-20435*# Engineering and Economics Research, Inc., Vienna, the space station are considered. The RF communications Va. Data and Operations Subcommittee. subsystem attributes and characteristics are defined and analyzed STARLAB GROUND SYSTEM GUIDELINES DOCUMENT Final key issues are identified for evolution from an initial space station Report (1990) to a year 2000 space station. The mass and power F. J. HAWKINS Jan. 1984 132 p refs Sponsored in part by characteristics of the communications subsystem for the initial National Research Council of Canada and Australian Department space station are assessed as well as the impact of advanced of Science and Technology technology developments. Changes needed to the second (Contract NAS5-27617) generation TDRSS to accomodate the evolutionary space station (NASA-CR-175192; NAS 1.26:175192) Avail: NTIS HC A07/MF of the year 2000 are also identified. A.R.H. A01 CSCL 05B Starlab science objectives, ground system considerations, space N84-18303*# Grumman Aerospace Corp., Bethpage, N.Y. shuttle sortie, space platform/station, mission planning, and remote SPACE STATION NEEDS, ATTRIBUTES AND ARCHITECTURAL facilities are addressed. N.W. OPTIONS, VOLUME 2, BOOK 2, PART 4: INTERNATIONAL REPORTS Final Technical Report N84-20604*# Smithsonian Astrophysical Observatory, Cambridge, 20 Apr. 1983 172 p refs Mass. (Contract NASW-3685) A LARGE-AREA GAMMA-RAY IMAGING TELESCOPE SYSTEM (NASA-CR-173319; NAS 1.26:173319; Final Report, 24 Mar. -1 Sep. 1983 SA-SSP-RP008-VOL-2-BK-2-PT-4) Avail: NTIS HC A08/MF A01 D. G. KOCH Aug. 1983 100 p refs CSCL 22B (Contract NAS2-3743) The capabilities of the European Space Agency's SPAS and (NASA-CR-175435; NAS 1.26:175435) Avail: NTIS HC A05/MF EURECA platforms for reference payload accommodation are A01 CSCL 22A considered. The instrument pointing subsystem, the position and The concept definition of using the External Tank (ET) of the hold mount, and the antenna pointing mechanism developed by Space Shuttle as the basis for constructing a large area gamma Dornier are described. Relevant payloads for the space station ray imaging telescope in space is detailed. The telescope will be are summarized and space station accommodation aspects are used to locate and study cosmic sources of gamma rays of energy discussed. A.R.H. greater than 100 MeV. Both the telescope properties and the means whereby an ET is used for this purpose are described. A parallel is drawn between those systems that would be common N84-18304*# Grumman Aerospace Corp., Bethpage, N.Y. to both a Space Station and this ET application. In addition, those SPACE STATION NEEDS, ATTRIBUTES AND ARCHITECTURAL systems necessary for support of the telescope can form the OPTIONS, VOLUME 2, BOOK 3: COST AND PROGRAMMATICS basis for using the ET as part of the Space Station. The major Final Technical Report conclusions of this concept definition are that the ET is ideal for 20 Apr. 1983 79 p refs making into a gamma ray telescope, and that this telescope will (Contract NASW-3685) provide a substantial increase in collecting area. S.L. (NASA-CR-173320; NAS 1.26:173320; SA-SSP-RP008-VOL-2-BK-3) Avail: NTIS HC A05/MF A01 N84-20610*# Michigan State Univ., East Lansing. Dept. of CSCL 22B Botany and Plant Pathology. The cost and programmatic considerations which integrate THE ALPHA-HELIX CONCEPT: INNOVATIVE UTILIZATION OF mission requirements and architectural options into a cohesive THE SPACE STATION PROGRAM. A REPORT TO THE system for exploitation of space opportunities within affordable NATIONAL AERONAUTICAL AND SPACE ADMINISTRATION limits are discussed. The mission requirements, baseline REQUESTING ESTABLISHMENT OF A SENSORY PHYSIOLOGY architecture, a top level baseline schedule, and acquisition costs LABORATORY ON THE SPACE STATION Final Report are summarized. The work breakdown structure (WBS) used to R. S. BANDURSKI and N. SINGH 17 Oct. 1983 71 p refs structure the program, and the WBS dictionary are included. The (Contract NASW-3748) costing approach used, including the operation of the primary (NASA-CR-175436; NAS 1.26:175436) Avail: NTIS HC A04/MF costing tool, the SPACE cost model are described. The rationale A01 CSCL 22B for the choice of cost estimating relationships is given and costs A major laboratory dedicated to biological-medical research is at the module level are shown. Detailed costs at the subsystem proposed for the Space Platform. The laboratory would focus on level are shown. The baseline schedule and annual funding profiles sensor physiology and biochemistry since sensory physiology are provided. Alternate schedules are developed to provide different represents the first impact of the new space environment on living funding profiles. Alternate funding sources are discussed and organisms. Microgravity and the high radiation environment of foreign and contractor participation is outlined. The results of the space would be used to help solve the problems of prolonged benefit analysis are given and the accrued benefits deriving from sojourns in space but, more importantly, to help solve terrestrial an implemented space station program are outlined. A.R.H. problems of human health and agricultural productivity. The

14 02 ANALYSIS AND DESIGN TECHNIQUES emphasis would be on experimental use of microorganisms and that satellites are rigid. Since modern space vehicles carry small plants and small animals to minimize the space and time lightweight, flexible deployable members, this assumption can no required to use the Space Platform for maximum human betterment. longer be made. Summaries are given of the papers presented at The Alpha Helix Concept, that is, the use of the Space Platform the 10th (MACS Congress. The question whether the availability to bring experimental biomedicine to a new and extreme frontier of computers has tended to stifle fundamental mathematical is introduced so as to better understand the worldly environment. inquiries leading to elegant analytical answers is addressed. Staffing and instrumenting the Space Platform biomedical laboratory C.R. in a manner patterned after successful terrestrial sensory physiology laboratories is also proposed. Author A84-11946* Jet Propulsion Lab., California Inst. of Tech., N84-21586*# Arizona State Univ., Tempe. Dept. of Geology. Pasadena. FEASIBILITY STUDY TO CONDUCT WINDBLOWN SEDIMENT MODEL ERROR ESTIMATION FOR DISTRIBUTED SYSTEMS EXPERIMENTS ABOARD A SPACE STATION Final Report DESCRIBED BY ELLIPTIC EQUATIONS R. GREELEY and J. D. IVERSEN (Iowa State Univ., Ames) 30 G. RODRIGUEZ (California Institute of Technology, Jet Propulsion Aug. 1983 36 p refs Original contains color illustrations Laboratory, Pasadena, CA) IN: World Congress on System (Contract NASW-3741) Simulation and Scientific Computation, 10th, Montreal, Canada, (NASA-CR-175434; NAS 1.26:175434) Avail: NTIS HC A03/MF August 8-13,1982, Proceedings. Volume 3 . Montreal, International A01 CSCL 22A Association for Mathematics and Computers in Simulation, 1983, A feasibility study was undertaken to determine if a suitable p. 371-373. NASA-supported research, refs apparatus could be designed to analyze aeolian processes for A function space approach is used to develop a theory for operation in space and to assess the feasibility of conducting estimation of the errors inherent in an elliptic partial differential meaningful experiments to address key aspects of aeolian equation model for a distributed parameter system. By establishing processes. To meet this objective a prototype apparatus was knowledge of the inevitable deficiencies in the model, the error fabricated and some limited experiments were run to determine estimates provide a foundation for updating the model. The function its suitability for this application. At least three general types of space solution leads to a specification of a method for computation experiments were devised that could be carried out aboard a space of the model error estimates and development of model error station: threshold studies, swirl (dust devil) experiments, and analysis techniques for comparison between actual and estimated analyses of windblown particle trajectories. How experiments in a errors. The paper summarizes the model error estimation approach zero-g environment could advance knowledge of aeolian processes as well as an application arising in the area of modeling for static was studied. M.A.C. shape determination of large flexible systems. Author M84-21623# Consulenze General! Roma (Italy). PROPOSALS FOR ADDITIONS, MODIFICATIONS, AND NEW EXPERIMENTAL METHODS. PART 1: GROUND TESTS. PART A84-16841 2: FLIGHT TESTS A HEURISTIC METHOD FOR THE DESIGN OF MINIMUM U. PONZI In its Study on Syn. and Characterization of Large WEIGHT TRUSSES USING DISCRETE MEMBER SIZES Space Systems, Phase 2. Part 3: Expt. Design Verification Tech. D. F. YATES, T. B. BOFFEY, and A. B. TEMPLEMAN (Liverpool, te] p 170-428 Dec. 1982 refs University, Liverpool, England) Computer Methods in Applied Avail: NTIS HC A19/MF A01 Mechanics and Engineering (ISSN 0045-7825), vol. 37, March 1983, The adaptation of ground test techniques to analysis of large p. 37-55. space structures (LSS) is discussed using Space Construction This paper describes a heuristic method for obtaining an Automated Fabrication Experiment Definition Study data. Analysis approximate solution to the problem of determining the minimum of gravitational effects is emphasized, and the difficulties and weight design of a structural truss using only a discrete set of practical consequences in reducing scale when composite materials commercially available member gauges. The method treats are involved are considered. The evolution of flight tests from constraints on joint deflection as well as constraints on member aircraft to space applications is reviewed. Modeling of LSS is stress and gauge. A sufficient condition for convergence of the treated. Parameter identification approaches are compared with method to a global optimum is derived together with both an a methods which consider the model/system performance/error priori and an a posteriori bound on the approximate solution. Finally, problem as a whole. Identification algorithms and error the results obtained from applying the method to several test representations are appended. Author (ESA) problems are reported. Author

02 A84-19108 ALGORITHMS AND COMPUTATIONAL ASPECTS PERTAINING TO BLOCK DIAGONAL DOMINANCE METHODS FOR DESIGN ANALYSIS AND DESIGN TECHNIQUES OIF DECENTRALIZED FEEDBACK COMPENSATION W. H. BENNETT (U.S. Navy, Naval Research Laboratory, Includes interactive techniques, computerized technology design Washington, DC) and J. S. BARAS (Maryland, University, College and development programs, dynamic analysis techniques, Park, MD) IN: Conference on Decision and Control, 21st, Orlando, environmental modeling, thermal modeling, and math modeling. FL, December 8-10, 1982, Proceedings. Volume 1 . New York, Institute of Electrical and Electronics Engineers, 1982, p. 479-484. refs A84-11930 Reference is made to a study by Bennett and Baras (1979), in SOME ASPECTS OF SIMULATION STUDIES IN SPACECRAFT which the idea of a block diagonally dominant transfer function DYNAMICS matrix is used to provide criteria for the design of decentralized V. J. MODI (British Columbia, University, Vancouver, Canada) IN: feedback control. Computer implementable algorithms are World Congress on System Simulation and Scientific Computation, developed here for determining the block diagonal dominance 10th, Montreal, Canada, August 8-13, 1982, Proceedings. Volume condition. Consideration is given to numerical stability in developing 3 . Montreal, International Association for Mathematics and the algorithms. It is suggested that the algorithms be implemented Computers in Simulation, 1983, p. 204-206. refs in an interactive computing environment. At present, these It is pointed out that numerous investigations involving active algorithms are being integrated into an interactive package that and passive stabilization procedures and accounting for internal will be used to assess feasibility of some large space structure as well as external forces have been carried out on the assumption decentralized control schemes. C.R.

15 02 ANALYSIS AND DESIGN TECHNIQUES

A84-19129 A84-25259# MATRIX(X) - APPLICATION TO LARGE SPACE STRUCTURE UNFURLABLE OFFSET ANTENNA DESIGN FOR CONTROL DESIGN PROBLEMS MULTIPURPOSE APPLICATIONS C. GREGORY, JR., S. SHAH, and R. WALKER (Integrated Systems, W. SCHAEFER, F. DRACHENBERG, H. HERBIG, R. SCHAELLIG Inc., Palo Alto, CA) IN: Conference on Decision and Control, (Messerschmitt-Boelkow-Blohm GmbH, Ottobrunn, West Germany), 21st, Orlando, FL, December 8-10, 1982, Proceedings. Volume 2 A. FESTA, A. ROEDERER (ESA, European Space Research and . New York, Institute of Electrical and Electronics Engineers, 1982, Technology Centre, Noordwijk, Netherlands), and K. p. 912-917. refs PONTOPPIDAN (TICRA A/S, Copenhagen, Denmark) IN: Matrix(X) is a computer-aided-design system for performing the Communication Satellite Systems Conference, 10th, Orlando, FL, steps in the control design cycle starting from system modeling March 19-22, 1984, Technical Papers . New York, American to data analysis, identification, control synthesis, and simulation. Institute of Aeronautics and Astronautics, 1984, p. 64-74. In addition to a powerful matrix interpreter, the package features (AIAA PAPER 84-0659) a user-friendly environment that involves device-independent A European aerospace company has been awarded a contract graphics, state-of-the-art numerical algorithms for reliable by the European Space Agency (ESA) for the development of a computations, and user-transparent file management. A description European technological capability in the area of unfurlable is given of the design and application of Matrix(X) user interface antennas. Such antennas are to be employed by the next and numerical algorithms for large space structures. It is pointed generation of ESA communication satellites. The present out that for large space structure problems, the bulk of the investigation is concerned with the results obtained during the information involved in evaluating a control design tends to obscure first phase of the project. During the second phase, the hardware the significant performance effects unless the results are is being developed for the selected concept, and the final design summarized graphically in a way that allows the analyst to quickly of a Technology Demonstration Model (TDM) of the antenna obtain an overview of the system performance. Selected graphical reflector will be produced. Attention is given to mission examples overview results for different aspects of the design, such as for large offset deployable antennas, requirements and interfaces eigenvalue locations, controllability/observability, modal cost, and for antennas, the unfurlable reflector concepts, a thermo-structural rms errors, are illustrated. C.R. analysis of the two different reflector concepts, and the selection of the optimum concept. G.R. A84-19887# A COMPARISON OF LINEAR AND GEOMETRICALLY NONLINEAR FINITE ELEMENT ANALYSES APPLIED TO LARGE SPACE STRUCTURES A. E. CONAWAY (Alabama, University, Tuscaloosa, AL) American Institute of Aeronautics and Astronautics, Aerospace Sciences A84-25525* Brown Univ., Providence, R. I. Meeting, 22nd, Reno, NV, Jan. 9-12, 1984. 7 p. refs PARAMETER IDENTIFICATION IN CONTINUUM MODELS (AIM PAPER 84-0069) H. T. BANKS (Brown University, Providence, Rl; Southern Methodist Many of the projects which are being considered to utilize the University, Dallas, TX) and J. M. CROWLEY (U.S. Air Force special characteristics of the space environment for some Academy, Colorado Springs, CO) IN: American Control application require for their implementation a structure in space, Conference, San Francisco, CA, June 22-24, 1983, Proceedings. which, in a number of cases, may be very large. One important Volume 3 . New York, Institute of Electrical and Electronics problem regarding such structures is related to limitations on weight. Engineers, 1983, p. 997-1001. refs The resulting fairly 'flimsy' configurations require special systems (Contract NSF MCS-82-05335; AF-AFOSR-81-0198; for the control of motion in response to dynamic loads. The design DAAG29-79-C-0161; NAS1-15810; NAS1-16394) of these control systems requires information regarding the Approximation techniques for use in numerical schemes for structure's mode shapes and natural frequencies. NASA employs estimating spatially varying coefficients in continuum models such currently numerical methods based on linear behavior of the as those for Euler-Bernoulli beams are discussed. The techniques structure to derive this information. However, it is entirely possible are based on quintic spline state approximations and cubic spline that such a linear approach is not adequate because of nonlinear parameter approximations. Both theoretical and numerical results effects. The considered project had as the objective to develop a are presented. Previously announced in STAR as N83-28934 means of nonlinear analysis for a structure modeled as having an M.G. applied static load. It is found that a dependence on linear assumptions might lead to inefficient control systems. G.R.

A84-21564 FOR THE FIRST TIME [VPERVYE] A. IVANOV Moscow, Moskovskii Rabochii, 1982, 289 p. In A84-25S51* National Aeronautics and Space Administration. Russian. Langley Research Center, Hampton, Va. The author gives a personal account of his work as a spacecraft STATIC SHAPE FORMING FOR AN ELECTROSTATICALLY designer during the early years of the Soviet space program. CONTROLLED MEMBRANE MIRROR Particular consideration is given to the beginnings of the Soviet J. N. JUANG (NASA, Langley Research Center, Hampton, VA) space program; the launching of the first animal (the dog Laika) and W. HUANG (Martin Marietta Aerospace, Denver, CO) IN: into space; the flights of Luna 1, 2, and 3; and the first manned American Control Conference, San Francisco, CA, June 22-24, flight. BJ. 1983, Proceedings. Volume 3 . New York, Institute of Electrical and Electronics Engineers, 1983, p. 1310-1316. refs A design concept is described permitting the static construction A84-22131*# Teledyne Brown Engineering, Huntsville, Ala. of a flexible membrane reflector for use in a radiometer spacecraft. SPACE PLATFORM ACCOMMODATIONS The scheme utilizes electrostatic forces to actively shape the W. BAILEY (Teledyne Brown Engineering, Base Programs Div., membrane toward a specified reflector surface with a required Huntsville, AL) and M. E. NEIN (NASA, Marshall Space Flight degree of precision. The formulations of the required electrostatic Center, Advanced Systems Office, Huntsville, AL) Journal of attractive forces, and stress and strain distributed in the membrane Spacecraft and Rockets (ISSN 0002-4650), vol. 20, Nov.-Dec. 1983, are presented in this paper in terms of curvilinear coordinates. An p. 646-552. example is given to illustrate a variety of spherical membrane Previously cited in issue 23, p. 3590, Accession no. characteristics associated with different boundary conditions. A82-46489 Author

16 02 ANALYSIS AND DESIGN TECHNIQUES

N84-10114*# McDonnell-Douglas Technical Services Co., Inc., N84-17225*# Rockwell International Corp., Seal Beach, Calif. Huntsville, Ala. Shuttle Integration and Satellite Systems Div. A DEFINITION OF STS ACCOMMODATIONS FOR ATTACHED LOW CONCENTRATION RATIO SOLAR ARRAY STRUCTURAL PAYLOADS CONFIGURATION F. L ECHOLS and P. A. BROOME Sep. 1983 125 p refs S. J. NALBANDIAN In NASA. Langley Research Center STEP (Contract NAS8-32350) Expt. Requirements p 185-198 Jan. 1984 refs (NASA-CR-172223; MAS 1.26:172223) Avail: NTIS HC A06/MF Avail: NTIS HC A15/MF A01 CSCL 10A A01 CSCL 228 The design and structural properties of a low concentration An input to a study conducted to define a set of earner avionics ratio solar array are discussed. The assembled module consists for supporting large structures experiments attached to the Space of six interconnected containers which are compactly stowed in a Shuttle Orbiter is reported. The 'baseline' Orbier interface used in volume of 3.24 m(3) for delivery to orbit by the shuttle. The developing the avionics concept for the Space Technology containers deploy in accordian fashion into a rectangular area of Experiments Platform, STEP, which Langley Research Center has 19.4 x 68 meters and can be attached to the user spacecraft proposed for supporting experiments of this sort is defined. along the longitudinal centertine of the end container housing. Primarily, flight operations capabilities and considerations and the Five rotary incremental actuators requiring about 8 watts each will avionics systems capabilities that are available to a payload as a execute the 180-degree rotation at each joint Deployable masts 'mixed cargo' user of the Space Transportation System are (three per side) are used to extend endcaps from the housing in addressed. Ground operations for payload integration at Kennedy both directions. Each direction is extended by three masts requiring Space Center, and ground operations for payload support during about 780 watts for about 27 minutes. Concentrator elements are the mission are also discussed. Author extended by the endcaps and are supported by cable systems that are connected between the housings and endcaps. These power generating elements contain reflector panels which N84-14233*# Grumman Aerospace Corp., Bethpage, N.Y. concentrate light onto the solar panels consisting of an aluminum ORBITER-BASED CONSTRUCTION EQUIPMENT STUDY. THE radiator with solar cells positioned within the element base formed HPA/DTA TECHNOLOGY ADVANCEMENT PLAN by the reflectors. A flat wire harness collects the power output of Oct. 1983 15 p refs individual elements for transfer to the module container housing (Contract NAS9-16468) harnesses. M.G. (NASA-CR-174605; NAS 1.26:174605; DRL-T-1701; DRD-SE957T) Avail: NTIS HC A02/MF A01 CSCL 22B N84-17284# Contraves Corp., Zurich (Switzerland). Satellite berthing mechanism, umbilicals for fluid and electrical STUDY ON LARGE, ULTRALIGHT LONG-LIFE STRUCTURES interfaces, EVA service platform, and large mass berthing IN SPACE, PHASE 2C Final Report mechanism are discussed. Author M. C. BERNASCONI Paris ESA 2 Jul. 1983 84 p refs (Contract ESTEC-5156/82/NL-PB(SQ) N84-14759# Erno Raumfahrttechnik G.m.b.H., Bremen (West (TM-EKR3; ESA-CR(P)-1796) Avail: NTIS HC A05/MF A01 A design of an inflatable, space rigidized structure (ISRS) offset Germany). antenna reflector, its manufacturing approach, and the development SOFTWARE QUALITY ASSURANCE SPACELAB EXPERIENCE of a light weight, inflatable stabilization torus to be used for this AND FUTURE TRENDS design are described. A structural concept for a 12 m aperture R. DAVENPORT In ESA Software Eng. p 235-241 Aug. 1983 refs offset reflector was defined. A continuous fabrication method for the stabilization torus was identified. Instruments for the torus Avail: NTIS HC A13/MF A01 design which relate the mass added by the torus complex and The quality assurance plan used when developing the command the pressure level, necessary for stabilization purposes were and data management software subsystem to support the functions prepared. Tests with an unreinforced simulacrum of the inflatable of Spacelab in flight; automatic test equipment software subsystem to support the functions needed for ground checkout of Spacelab; reflector, which validate the proposed pressure prediction formulas, were performed. A development plan, leading to a ground and support software subsystem to generate and maintain a demonstration of the ISRS technology for large expandable common data base and to provide a generation mechanism for software for the other two subsystems, is outlined. The software structures is presented. Author (ESA) problem reports, unit development folders, verification control document, test data folder, acceptance data package, and N84-18457# British Aerospace Dynamics Group, Stevenage certificate of acceptance are described. Trends in developing (England). Space and Communications Div. automated software quality assurance tools are reviewed. DESIGN AND DEVELOPMENT OF AN ADVANCED SOLAR Author (ESA) ARRAY DRIVE MECHANISM J. S. SHEPPARD In ESA First European Space Mech. and Tribology Symp. p 19-26 Dec. 1983 refs N84-16427*# National Aeronautics and Space Administration. Avail: NTIS HC A10/MF A01 Langley Research Center, Hampton, Va. The design and development of a solar array drive capable of SURFACE ACCURACY MEASUREMENT SENSOR TEST ON A transferring 7kW of power or more is described. Results of 50-METER ANTENNA SURFACE MODEL functional performance and environmental tests encompassing R. B. SPIERS, E. E. BURCHER, C. W. STUMP, C. G. SAUNDERS, L-SAT/Olympus qualification levels are summarized. The drive and G. F. BROOKS (Kentron International, Inc.) Jan. 1984 32 consists of power slip ring, bearing support, drive actuator, and p refs pyfo/signal slip ring modules. Thermal vacuum, accelerated life (NASA-TM-85689; NAS 1.15:85689) Avail: NTIS HC A03/MF test, and vibration tests are satisfactory. Author (ESA) A01 CSCL 20N The Surface Accuracy Measurement Sensor (SAMS) is a N84-18475# British Aerospace Dynamics Group, Stevenage telescope with a focal plane photo electric detector that senses (England). Space and Communications Div. the lateral position of light source targets in its field of view. After BAE REACTION WHEELS FOR OLYMPUS extensive laboratory testing the engineering breadboard sensor G. J. STURTIVANT In ESA First European Space Mech. and system was installed and tested on a 30 degree segment of a Tribology Symp. p 187-192 Dec. 1983 refs 50-meter diameter, mesh surface, antenna model. Test results Avail: NTIS HC A10/MF/ A01 correlated well with the laboratory tests and indicated accuracies The design philosophy and achievements of the Olympus of approximately 0.59 arc seconds at 21 meters range. Test results reaction wheel are presented. The design incorporates a compliant are presented and recommendations given for sensor bearing preload arrangement which reduces the launch phase loads improvements. S.L. applied to the bearings. The fiber optic commutation sensor system

17 02 ANALYSIS AND DESIGN TECHNIQUES is described, together with the four-phase brushless, ironless dc N84-21624# Consulenze General! Roma (Italy). electric motor which achieves a very low output torque ripple. STUDY ON SYNTHESIS AND CHARACTERIZATION OF LARGE Author (ESA) SPACE SYSTEMS, PHASE 2. PART 1: ASSESSMENT OF DESIGN VERIFICATION ANALYTICAL METHODS. VOLUME 1: MECHANICAL DESIGN Final Report C. ARDUINI and U. PONZI Paris ESA Dec. 1982 480 p refs 5 Vol. (Contract ESTEC-4348/80/NL-AK(SC)) N84-20621 Purdue Univ., Lafayette, Ind. (ESA-CR(P)-1779-VOL-1) Avail: NTIS HC A21/MF A01 ANALYSIS OF LARGE SPACE STRUCTURES Ph.D. Thesis Softwares for large spacecraft structural dynamic/control S. ABRATE 1983 182 p dynamic verification are reviewed. The ASKA, NASTRAN, SPAR, Avail: Univ. Microfilms Order No. DA8400322 DISCOS, and N-BOD programs are described. Decoupling, Typically, large space structures are latticed beams or plates substructuring, and the effects of structural symmetry are made up of a very large number of elements assembled in a discussed. For mechanical design verification, orbital flight periodic pattern with overall dimensions possibly measured in miles. conditions replace launch stresses tolerance as the main criterion. Efficient dynamic models are needed for design optimization, and For thermal design, verifying thermal deformations is paramount control problems. Harmonic wave propagation analysis is used to for large space structures. Software for design verification of these determine the limits of applicability of the simple continuum models. structures should integrate thermal and mechanical parameters Several equivalent continuum models are developed and evaluated into an interactive scheme. Author (ESA) comparatively. The range of validity of these continuum models is established in terms of wavelength. The presence of modes which are not predicted by the simple models is detected by considering a typical cell of the original structure. Procedures for including N84-21625# Consulenze General! Roma (Italy). damping in the simple models are presented. Viscous, hysteretic, STUDY ON SYNTHESIS AND CHARACTERIZATION OF LARGE and a three parameter type damping models are discussed. The SPACE SYSTEMS, PHASE 2. PART 1: ASSESSMENT OF analysis of geometrically nonlinear trusses is performed, and the DESIGN VERIFICATION ANALYTICAL METHODS. VOLUME 2: continuum beam models are shown to be efficient and accurate THERMAL DESIGN Final Report for both static and dynamic problems. Dissert. Abstr. C. ARDUINI and U. PONZI Paris ESA Dec. 1983 411 p refs 5 Vol. (Contract ESTEC-4348/80/NL-AL(SC)) (ESA-CR(P)-1779-VOL-2) Avail: NTIS HC A18/MF A01 Thermal design verification of large space systems through software evaluation was studied. The analytical methods were N84-21607*# National Aeronautics and Space Administration. summarized with special emphasis on the Lockheed orbital heat Marshall Space Flight Center, Huntsville, Ala. rate package, the thermal radiation analysis system, NASTRAN TETHERS IN SPACE: BIRTH AND GROWTH OF A NEW thermal analyzer, and the simplified shuttle payload thermal AVENUE TO SPACE UTILIZATION analyzer. Basic concepts of thermodynamic modeling and structural G. VONTIESENHAUSEN Feb. 1984 33 p refs characteristics were included along with the relevant equilibrium (NASA-TM-82571; NAS 1.15:82571) Avail: NTIS HC A03/MF equations. M.A.C. A01 CSCL 22B The evolution of the ideas of tether applications in space are traced from its origin in the last century past a dormant period of N84-22179*# National Aeronautics and Space Administration. sixty-five years to the mid-seventies. At that time as a consequence Langley Research Center, Hampton, Va. of major revival efforts, NASA entered into serious investigations COMPUTER-AIDED GEOMETRY MODELING of the theoretical and practical feasibility of a large number of J. N, SHOOSMITH, comp. and R. E. FULTON, comp. tethered concepts in space. These efforts culminated in the Washington Mar. 1984 387 p refs Symp. held in Hampton, establishment of the Tethered Satellite System Project now at Va., 20-22 Apr. 1983 NASA in the advanced development phase. Extensive planning (NASA-CP-2272; L-15618; NAS 1.55:2272) Avail: NTIS HC efforts are described, first, through a Tether Applications in Space A17/MFA01 CSCL 12A Workshop which generated additional concepts and provided Techniques in computer-aided geometry modeling and their overall assessments and recommendations to NASA, and then application are addressed. Mathematical modeling, solid geometry through a NASA inter-center Tether Applications in Space Task models, management of geometric data, development of geometry Group which generated a four year program plan in the areas of standards,, and interactive and graphic procedures are discussed. further studies, technology, work and science and applications of The applications include aeronautical and aerospace structures tethers in space. An outlook into the future of tether applications design, fluid flow modeling, and gas turbine design. that approaches some of the goals of the early visionaries is offered. Author N84-22191*# National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. INTERACTIVE GEOMETRY MODELING OF SPACE STATION CONCEPTUAL DESIGNS Abstract Only N84-21620# Consulenze General! Roma (Italy). D. D. DERYDER, M. J. FEREBEE, JR., and M. L. MCMILLIN In STUDY ON SYNTHESIS AND CHARACTERIZATION OF LARGE its Computer-Aided Geometry Modeling p 101-102 Mar. 1984 SPACE SYSTEMS, PHASE 2. PART 3: EXPERIMENTAL DESIGN Avail: NTISHC A17/MFA01 CSCL 09B VERIFICATION TECHNIQUES Final Report With the advent of a serious interest in the design and C. ARDUINI and U. PONZI Paris ESA Dec. 1982 428 p implementaton of a low-Earth orbit, manned space station, the refs 5 Vol. need has arisen to rapidly synthesize, characterize, and analyze (Contract ESTEC-4348/80/NL-AK(SC)) many conceptual designs. Because the manual generation and (ESA-CR(P)-1779-VOL-5) Avail: NTIS HC A19/MF A01 analysis of a mathematical design model could consume many Ground and flight tests of large space structures are discussed. man-months, an interactive modeling and analysis capability is Thermal balance tests, thermal cycle tests, the effects of scale sought. This poster session will demonstrate the activities and reductions, and gravitational effects are considered. Static, current capabilities at NASA LaRC that could support the modeling dynamic, and modal structural analysis techniques are reviewed. analysis of space station conceptual designs. Author

18 03 STRUCTURAL CONCEPTS

N84-22224*# National Aeronautics and Space Administration. A84-21517# Langley Research Center, Hampton, Va. THE BEAM-LIKE BEHAVIOR OF SPACE TRUSSES MATHEMATICAL SYNTHESIZATION OF COMPLEX J. D. RENTON (Oxford University, Oxford, England) AIAA Journal STRUCTURES (ISSN 0001-1452), vol. 22, Feb. 1984, p. 273-280. refs L B. GARRETT In its Computer-Aided Geometry Modeling p A general approach is developed for determining the overall 389-398 Mar. 1984 refs elastic behavior of space trusses. This is done by casting the Avail: NTIS HC A17/MF A01 CSCL 12A matrix equations for pin-ended bars in a suitable algebraic form A mathematical synthesization approach for rapidly modeling and using them to construct the finite difference equations for the and analyzing complex structures comprised of hundreds or truss under examination. Characteristic solutions of the thousands of repeating individual structural members, homogeneous form of these equations are found in terms of simple interconnecting hardware, and other components was described. polynomial functions. These correspond to the resultant forces The techniques are applicable to any structure with repeating and moments applied to the truss. All other modes decay toward structural members. The capabilities are embodied within the these characteristic deflections. This means that the internal loads Interactive Design and Evaluation of Advanced Spacecraft (IDEAS) in the truss can be estimated from the resultant applied loading, computer-aided design system. IDEAS has a full range of integrated even when the truss is not statically determinate. Also, the spacecraft modeling, design, analysis, performance, and cost characteristic response yields elastic properties akin to the axial, estimating capabilities which include about 40 technical program torsional, bending, and shear stiffness of beams, although in some and executive, data base, and file management systems. With cases these effects are coupled. Values for a number of common IDEAS, a single user at an interactive terminal can create, design, space trusses are listed. It is also shown how the method may analyze, and conduct parametric studies of Earth orbiting spacecraft be used to give the natural frequencies of vibration of such in a timely, cost-efficient manner. The system is particularly useful structures. Author in the conceptual design phases of advanced space missions when a multiplicity of concepts must be evaluated. The IDEAS interactive A84-22153# finite-element modeling capabilities are discussed. The DESIGN AND DEVELOPMENT OF THE INTELSAT V mathematical synthesization programs were structured not only to GRAPHITE-EPOXY CENTRAL THRUST TUBE provide a detailed finite-element model of the structure but also N. BARBERIS (Ford Aerospace and Communications Corp., Palo to automatically perform the many auxiliary computations needed Alto, CA), M. ZILANI, and C. GABRIEL (SocieteNationale to analyze the spacecraft in its orbital operational environment. Industrielle Aerospatiale, Cannes, France) (Structures, Structural MAC. Dynamics and Materials Conference, 23rd, New Orleans, LA, May 10-12, 1982, Collection of Technical Papers. Part 2, p. 594-602) Journal of Spacecraft and Rockets (ISSN 0022-4650), vol. 21, Jan.-Feb. 1983, p. 55-60. Research sponsored by the International 03 Telecommunications Satellite Organization. Previously cited in issue 13, p. 2030, Accession no. A82-30189 STRUCTURAL CONCEPTS A84-22859# Includes erectable structures (joints, struts, and columns), LOCAL STABILITY OF SANDWICH STRUCTURES WITH THIN deployable platforms and booms, solar sail, deployable reflectors, FIBRE REINFORCED FACE SKINS FOR SPACE APPLICATION space fabrication techniques, and protrusion processing. H. BANSEMIR and K. PFEIFER (Messerschmitt-Boelkow-Blohm GmbH, Munich, West Germany) Society for the Advancement of Material and Process Engineering, Technology Conference on A84-10141*# California Univ., Los Angeles. Engineering with Composites, 3rd, London, England, Mar. 14-16, APPROXIMATIONS METHOD FOR SPACE FRAME SYNTHESIS 1983, Paper. 32 p. W. C. MILLS-CURRAN, R. V. LUST, and L. A. SCHMIT (California, (MBB-UD-381-83-OE) University, Los Angeles, CA) (Structures, Structural Dynamics Sandwich structures with thin carbon and aramid epoxy face and Materials Conference, 23rd, New Orleans, LA, May 10-12, skins are used in the INTELSAT V, INTELSAT VI, OTS and EXOSAT 1982, Collection of Technical Papers, Part 2, p. 187-200) AIAA solar arrays. Structural instability of these structures can manifest Journal (ISSN 0001-1452), vol. 21, Nov. 1983, p. 1571-1580. itself in a number of different modes. The ultimate compressive refs stresses are defined by wrinkling stresses. These are related to a (Contract NSG-1490) mode with short wave lengths in the face sheets. A theory of Previously cited in issue 13, p. 2109, Accession no. general stability is derived and the theoretical stresses are A82-30149 compared with test values. Author

A84-11922 A84-22965* Hughes Aircraft Co., Los Angeles, Calif. ANALYSIS AND DESIGN OF LEAF-SPRING FLEXIBLE JOINTS WELDED SOLAR CELL INTERCONNECTION FOR DRIVING GYROSCOPIC ROTORS E. J. STOFEL, E. R. BROWNE, R. A. MEESE, and G. J. VENDURA J. L. SCIESZKO and W. M. MANSOUR (Rio de Janeiro, (Hughes Aircraft Co., Space and Communications Group, Los Universidade Federal, Rio de Janeiro, Brazil) IN: World Congress Angeles, CA) IN: Photovoltaic Specialists Conference, 16th, San on System Simulation and Scientific Computation, 10th, Montreal, Diego, CA, September 27-30, 1982, Conference Record . New Canada, August 8-13, 1982, Proceedings. Volume 2 . Montreal, York, Institute of Electrical and Electronics Engineers, 1982, p. International Association for Mathematics and Computers in 45-50. Simulation, 1983, p. 155, 156. (Contract JPL-956038) The present investigation is concerned with the development The efficiency of the welding of solar-cell interconnects is of algorithms for the exact solution of the nonlinear mathematical compared with the efficiency of soldering such interconnects, and model which governs the static performance of the flexible joint the cases in which welding may be superior are examined. employed to drive gyroscopic rotors. The constructed mathematical Emphasis is placed on ultrasonic welding; attention is given to model takes into account the relationships between the internal the solar-cell welding machine, the application of the welding forces and the deflections in each leaf. The model has nonlinear process to different solar-cell configurations, producibility, and characteristics. The derived computing algorithm was implemented long-life performance of welded interconnects. Much of the present in a routine to evaluate the stress levels and buckling loads for work has been directed toward providing increased confidence in the joints. Attention is given to the case where the two leaves the reliability of welding using conditions approximating those that are identical, and some typical plots. G.R. would occur with large-scale array production. It is concluded that

19 03 STRUCTURAL CONCEPTS there is as yet insufficient data to determine which of three methods design of a ground test article for future development testing. (soldering, parallel gap welding, and ultrasonic welding) provides This design is representative of a prototype square-truss, single-fold the longest-duration solar panel life. B.J. building-block design that can construct deployable platform structures. This prototype design was selected through a A84-23366# comprehensive and traceable selection process applied to eight OPTIMIZATION OF SHALLOW TRUSSES AGAINST LIMIT POINT competitive designs. The selection process compared the INSTABILITY competitive designs according to seven major selection criteria, M. P. KAMAT (Virginia Polytechnic Institute and State University, i.e., design versatility, cost, thermal stability, meteoroid impact Blacksburg, VA), N. S. KNOT, and V. B. VENKAYYA (USAF, Flight significance, reliability, performance predictability, and orbiter Dynamics Laboratory, Wright-Patterson AFB, OH) AIAA Journal integration suitability. In support of the foregoing, a materials data (ISSN 0001-1452), vol. 22, March 1984, p. 403-408. refs base, and platform systems technology development needs were The problem of the maximization of the critical load (limit point established. An erectable design of an OTV hangar was selected instability) of shallow space trusses of constant volume or weight and recommended for further design development. This design is considered. Exact solutions being possible in simple cases, a was selected from five study-developed competitive single-fold and detailed investigation of the question of the uniqueness of the double-fold designs including hard-shell and inflatable designs. optimum designs for two- and four-bar shallow truss problems is Also, two deployable manned module configurations, i.e., a carried out. The optimized trusses satisfy the constant-strain energy hard-shell and an inflatable design were each developed to the density criteria and the load maximization problem is verified to same requirements as the composite of two Space station baseline be the dual of the minimization of the total potential energy. habitat modules. N.W. Author N84-10176*# Rockwell International Corp., Downey, Calif. Shuttle A84-25258# Integration and Satellite Systems Div. A DEPLOYABLE 30/20 GHZ MULTIBEAM OFFSET ANTENNA DEVELOPMENT OF DEPLOYABLE STRUCTURES FOR LARGE B. ABT (Domier System GmbH, Friedrichshafen, West Germany) SPACE PLATFORMS. VOLUME 2: DESIGN DEVELOPMENT and H. WOLLENHAUPT (ANT Nachrichtentechnik GmbH, Final Report Backnang, West Germany) IN: Communication Satellite Systems H. S. GREENBERG Oct. 1983 183 p refs Conference, 10th, Orlando, FL, March 19-22, 1984, Technical (Contract NAS8-34677) Papers . New York, American Institute of Aeronautics and (NASA-CR-170914; NAS 1.26:170914; SSD-83-0094-2-VOL-2) Astronautics, 1984, p. 54-63. Research supported by the Avail: NTIS HC A09/MF A01 CSCL 228 Bundesministerium fuer Forschung und Technologie. Design evolution, test article design, test article mass properties, (AIAA PAPER 84-0658) and structural analysis of deployable platform systems are This paper presents the results of a feasibility study for the discussed. Orbit transfer vehicle (OTV) hangar development, OTV design of a 30/20 GHz multibeam satellite antenna with bandwidth hangar concept selection, and manned module development are of 2.5 GHz and for a continuous coverage of West Germany, discussed. Deployable platform systems requirements, material including West Berlin. The required dual offset Cassegrain reflector data base, technology development needs, concept selection and system has a precision deployable (rigid panels) main reflector deployable volume enclosures are also discussed. N.W. with a diameter of 4.7 m. The continuous coverage requires an edge gain of at least 47 dB. To maintain a high decoupling between N84-11199 Columbia Univ., New York. the individual earth stations in different zones, a pointing accuracy ACTUATOR PLACEMENT CONSIDERATIONS FOR THE of better than 0.3 deg RMS has to be achieved. This can only be CONTROL OF LARGE SPACE STRUCTURES Ph.D. Thesis realized by a closed loop RF-tracking system with a low power R. E. LINDBERG 1982 126 p refs consumption pointing mechanism. Author Avail: Univ. Microfilms Order No. DA8307603 The problem of actuator placement for the control of distributed A84-29862 parameter systems such as large flexible space structures is THE DEVELOPMENT OF A COMPOSITE BEAM BUILDING considered. Focus is placed first on the concept of the degree of MACHINE FOR ON-SITE CONSTRUCTION OF LARGE SPACE controllability. The behavior of the degree of controllability and its STRUCTURES approximation is considered via application to simple problems for W. B. GOLDSWORTHY (Goldsworthy Engineering, Inc., Torrance, which the exact value may be computed. The upper bound CA) IN: Space manufacturing 1983; Proceedings of the Sixth approximation is found to be particularly exact for harmonic systems Conference, Princeton, NJ, May 9-12, 1983 . San Diego, CA, and an acceptable approximation for lightly damped systems. A Univelt, Inc., 1983, p. 177-182. refs method is proposed for avoiding the unacceptable behavior of (AAS PAPER 83-217) the approximation in the neighborhood of a problem containing Composites will be favored for beam construction in space for repeated roots. The divergence of the upper bound approximation two reasons. The first is the need for materials of low density in the problem of a double integral plant motivates the development and high strength in projects where the cost of trannsportation of a new lower bound approximation based on discretization of will be dominant. The second is the requirement that the material the continuous time system. Dissert. Abstr. have a zero thermal coefficient of expansion. An outline is presented of material selection and the development of prototype N84-14561 Nebraska Univ., Lincoln. feasibility demonstration equipment for continuously producing, in NEW ELEMENTS FOR ANALYSIS OF SPACE FRAMES WITH space, triangular truss beams 1 -112 meters on a side with closed TAPERED MEMBERS Ph.D. Thesis beam caps. C.R. Y. W. LEE 1983 204 p Avail: Univ. Microfilms Order No. DA8314904 N84-10175*# Rockwell International Corp., Downey, Calif. Shuttle The closed forms of the linear stiffness matrix, geometric Integration and Satellite Systems Div. stiffness matrix, displacement functions and equivalent nodal loads DEVELOPMENT OF DEPLOYABLE STRUCTURES FOR LARGE are developed for analyses of space structures containing linearly SPACE PLATFORM SYSTEMS. VOLUME 1: EXECUTIVE tapered members with cross sections of thin-walled tubes, solid SUMMARY Final Report rectangles and l-sections. The series expansion forms of these H. S. GREENBERG Oct. 1983 27 p refs are also developed because they avoid numerical failure in (Contract NAS8-34677) structural analyses under extremely small taper. The cross sectional (NASA-CR-170913; NAS 1.26:170913; SSD-83-0094-1-VOL-1) properties are closely approximated by the ordering process if the Avail: NTIS HC A03/MF A01 CSCL 22B geometric properties along the member do not follow a simple The preponderance of study effort was devoted toward the power law. Then, solutions are obtained by direct integration of deployable platform systems study which culminated in the detailed the differential equations for displacements and the moment area

20 03 STRUCTURAL CONCEPTS theorem. The elements presented can be used for the linear stability examined in developing the design concept are: (1) the support and the large deflection analysis of tapered and prismatic structure of the station be stiff enough to preclude the need for members. Dissert. Abstr. an elaborate on-orbit system to control structural response, (2) the station support structure and solar power system be compatible N84-17226*# Rockwell International Corp., Downey, Calif. Shuttle with existing technology, and (3) the station be capable of growing Integration and Satellite Systems Div. in a systematic modular fashion. The concept is developed around DEVELOPMENT OF TEST ARTICLE BUILDING BLOCK (TABS) the assembly of truss platforms by pressure-suited astronauts FOR DEPLOYABLE PLATFORM SYSTEMS operating in extravehicular activity (EVA), assisted by a machine H. S. GREENBERG and R. T. BARBOUR In NASA. Langley (Assembly and Transport Vehicle, ATV) to position the astronauts Research Center STEP Expt. Requirements p 199-210 Jan. at joint locations where they latch truss members in place. The 1984 ATV is a mobile platform that is attached to and moves on the Avail: NTIS HC A15/MF A01 CSCL 22B station support structure using pegs attached to each truss joint The concept of a Test Article Building Block (TABB) is The operation of the ATV is described and a number of conceptual described. The TABB is a ground test article that is representative configurations for potential space stations are developed. Author of a future building block that can be used to construct LEO and GEO deployable space platforms for communications and scientific N84-19899# Concordia Univ., Montreal (Quebec). Dept. of payloads. This building block contains a main housing within which Mechanical Engineering. the entire structure, utilities, and deployment/retraction mechanism COMPUTER AIDED SYNTHESIS OF A SATELLITE ANTENNA are stowed during launch. The end adapter secures the foregoing STRUCTURE WITH PROBABILISTIC CONSTRAINTS components to the housing during launch. The main housing and V. K. JHA (SPAR Aerospace Ltd.), T. S. SANKAR, and R. B. adapter provide the necessary building-block-to-building-block BHAT In Shock and Vibration Inform. Center The Shock and attachments for automatically deployable platforms. Removal from Vibration Bull., part 3 p 79-89 May 1983 refs the shuttle cargo bay can be accomplished with the remote Avail: SVIC, Code 5804, Naval Research Lab., Washington, D.C. manipulator system (RMS) and/or the handling and positioning 20375 CSCL 20M aid (HAPA). In this concept, all the electrical connections are in The satellite antenna structures have to be designed to place prior to launch with automatic latches for payload attachment withstand the severe environmental conditions encountered by the provided on either the end adapters or housings. The housings satellite without failure, and hence they have to be designed with also can contain orbiter docking ports for payload installation and very strict reliability requirements. At the same time these structures maintenance. M.G. should be as light as possible, in weight, to minimize the cost of launching the satellites into space. A computer aided design N84-18286*# General Electric Co., Philadelphia, Pa. procedure capable of meeting these design requirements in STRUCTURES AND MECHANISMS presented. The procedure involves synthesis of a finite element D. PURDY In NASA. Langley Research Center Space Station analysis program capable of analyzing complex structures and a Technol., 1983 p 109-135 Feb. 1984 state of the art optimization algorithm into one unified design Avail: NTIS HC A09/MF A01 CSCL 22B system. This system is used for designing antenna structures Structures, materials, and mechanisms is one of the older subjected to random excitations and having design requirements technologies in the aerospace business. The Structures, Materials, specified in a probabilistic manner. An approach is presented to and Mechanisms Panel was divided into the four basic categories handle probabilistic design requirements. The design of a typical that fit the overall responsibilities of the panel: materials, satellite antenna structure realized using the proposed design mechanisms, structural design, and analysis. Author procedure is presented. Starting from the best guessed design, a saving of 43% in weight is demonstrated. The proposed system N84-18680*# Old Dominion Univ., Norfolk, Va. Dept. of is very versatile and the possibilities of extending it for designing Mechanical Engineering and Mechanics. other complex structures are also discussed. M.G. COMPONENT MODE SYNTHESIS AND LARGE DEFLECTION VIBRATIONS OF COMPLEX STRUCTURES Final Report, 1 Nov. N84-21608*# National Aeronautics and Space Administration. 1982 - 31 Oct 1983 Langley Research Center, Hampton, Va. C. MEI Feb. 1984 16 p refs OPERATIONAL MODULES FOR SPACE STATION (Contract NAG 1-301) CONSTRUCTION (NASA-CR-173338; NAS 1.26:173338) Avail: NTIS HC A02/MF L R. JACKSON, P. L. MOSES (Kentron International, Inc.), S. J. A01 CSCL 20K SCOTT (Kentron International, Inc.), and M. L BLOSSER Apr. The accuracy of the NASTRAN modal synthesis analysis was 1984 34 p refs assessed by comparing it with full structure NASTRAN and nine (NASA-TM-85772; NAS 1.15:85772) Avail: NTIS HC A03/MF other modal synthesis results using a nine-bay truss. A NASTRAN A01 CSCL 22B component mode transient response analysis was also performed Identification of an effective space construction concept is a on the free-free truss structure. A finite element method was current objective of NASA studies. One concept, described in this developed for nonlinear vibration of beam structures subjected to memorandum, consists of repetitive use of operational modules, harmonic excitation. Longitudinal deformation and inertia are both which minimizes on-orbit stay time for the shuttle. A space station included in the formula. Tables show the finite element free vibration constructed of operational modules may benefit from fabrication results with and without considering the effects of longitudinal and system checkout in ground-based facilities, and since the deformation and inertia as well as the frequency ratios for a simply modules are the primary structure of the space station, a minimum supported and a clamped beam subjected to a uniform harmonic of additional structure, and trips and on-orbit stay time of the force. A.R.H. shuttle are required. Author

N84-19395*# National Aeronautics and Space Administration. N84-21615# Consulenze General! Roma (Italy). Langley Research Center, Hampton, Va. FINITE ELEMENT FORMULATIONS FOR TENSIONED A MANNED-MACHINE SPACE STATION CONSTRUCTION MEMBERS CONCEPT S. SGUBINI In its Study on Syn. and Characterization of Large M. M. MIKULAS, JR., H. G. BUSH, R. E. WALLSOM, J. T. DORSEY, Space Systems, Phase 2. Part 2: Proposals for Additions, and M. D. RHODES Feb. 1984 33 p refs Modifications and New Anal. Methods, Vol. 1 p 277-360 Dec. (NASA-TM-85762; NAS 1.15:85762) Avail: NTIS HC A03/MF 1982 refs A01 CSCL 22B Avail: NTIS HC A16/MF A01 A design concept for the construction of a permanent manned The geometrical stiffness matrices are evaluated for typical space station is developed and discussed. The main considerations structures, and the effects of shear deformations and rotary inertia

21 03 STRUCTURAL CONCEPTS on large space structure design are discussed. In plane and 04 longitudinal deformations, and beam torque moment coupling with all other displacements are considered. Analysis shows that these STRUCTURAL AND THERMAL ANALYSIS effects are small, but not negligible. Evaluation of the geometrical stiffness matn'x of a square section beam reveals that axial and shear force effects can be of the same order of magnitude with Includes structural analysis and design, thermal analysis and slender beams. Author (ESA) design, analysis and design techniques, and thermal control systems.

A84-10224 SPACECRAFT THERMAL CONTROL, DESIGN, AND OPERATION H. E. COLLICOTT, ED. (Boeing Co., Seattle, WA) and P. E. BAUER, ED. (McDonnell Douglas Astronautics Co., St. Louis, MO) New M84-21914# Technische Univ., Hanover (West Germany), lost, York, American Institute of Aeronautics and Astronautics (Progress fuer Statik. in Astronautics and Aeronautics. Volume 86), 1983, 371 p. GEOMETRICALLY NONLINEAR ANALYSIS OF BEAM-IN-SPACE Requirements and challenges concerning military spacecraft STRUCTURES Thesis thermal management are considered along with a Shuttle Orbiter G. LUMPE 15 Dec. 1982 107 p refs In GERMAN; ENGLISH thermal control postflight evaluation, the orbital test satellite thermal summary experience after 31/2 years in orbit, the thermal design and (MITT-28; ISSN-0073-0300) Avail: NTIS HC A06/MF A01 experiment thermal integration of the long duration exposure facility, A finite element concept for complex beam-in-space structures and satellite thermal design and analyses for expendable and based on large displacement and small strain theory is developed. Shuttle launch environments. Topics related to subsystem and Derivation of a beam theory from the three dimensional theory components are discussed, taking into account the with consistent approaches and error estimations combined with thermo-mechanical design and analysis system for a 76-in. separation of rigid body motion and actual deformation allowed parabolic antenna reflector, the thermodynamic optimization of a the derivation of a simple tangent stiffness matrix which takes cryogenic storage system for minimum boiloff, and a molecular into account geometrically nonlinear effects. The magnitude of absorption cryogenic cooler for liquid hydrogen propulsion system. error is a function of element length. The rotation of each cross Subjects concerned with material properties and interfaces are section is described by an orthogonal tensor as a rotation about explored along with finite-element analysis techniques. A one skew axis to avoid nonsymmetric stiffness matrices. The range description of heat pipes is also provided, giving attention to of application includes hinge fitting combination, shear deformation, osmotic pumped heat pipes for large space platforms, the and hindered torsion. For cable-roll-connections, a simple algorithm development of a double-wall artery high-capacity heat pipe, and which overcomes the difficult kinematic relations of cable rolls by the Marangoni effect. No individual items are abstracted in this energetical considerations is presented. Efficiency of the volume G.R. computation method is demonstrated by the example of a tower crane. Author (ESA) A84-10440 THERMAL CONTROL OF TUBULAR COMPOSITE STRUCTURES IN SPACE ENVIRONMENT R. D. KARAM (Fairchild Space Co., Germantown, MD) IN: Composite structures 2; Proceedings of the Second International Conference, Paisley, Scotland, September 14-16, 1983 . London, Applied Science Publishers, 1983, p. 235-248. refs Thermal control of spacecraft tubular composites is discussed. N84-22225*# National Aeronautics and Space Administration. The equations used to calculate orbital temperatures are presented Langley Research Center, Hampton, Va. with a description of the design techniques which limit temperature GEOMETRIC MODELING OF LARGE SPACE ANTENNA excursions and associated distortions. Laminate fiber orientation DEPLOYMENT Abstract Only is related to heat transfer characteristics, and it is shown that J, NAZEMETZ (Oklahoma State Univ.), K. SAGE (Kentron orientations selected to yield high axial strength and least thermal International), R. L. GATES (Computer Services Corp.), and D. D. deformations will generally lead to excessive fin effect heat losses. DERYDER In its Computer-Aided Geometry Modeling p 399 A perforation procedure is proposed to eliminate in-plane Mar. 1984 deflections in a space environment independently of laminate Avail: NTIS HC A17/MF A01 CSCL 09B construction. The lamination sequence may then be optimized to A dynamic visualization of large antenna deployment was meet strength and heat loss requirements. Author created to be used as a precursor to further analysis of the structure as it is being deployed. The configuration chosen for this A84-11814# investigation was a box-truss structure consisting of a large reflector THERMO-MECHANICAL BEHAVIOUR OF CFRP TUBES FOR 60 meters wide by 120 meters long with a 120-meter mast. The SPACE STRUCTURES entire space structure is folded and compressed into a container G. REIBALDI (ESA, Mechanical Systems Div., Noordwijk, 17.8 meters long by 3.75 meters in diameter for transportation to Netherlands) International Astronautical Federation, International orbit by the Space Transportation System (STS). A geometric model Astronautical Congress, 34th, Budapest, Hungary, Oct. 10-15,1983. of this structure was created using an interactive solid modeling 16 p. refs . package. The building blocks of the structure are boxes and (IAF PAPER 83-417) cylinders which are put together to form elements connected by Relationships between the coefficient of thermal expansion joints and hinges. The elements, joints, and hinges make up the (CTE), thermal cycling, and microcracking were obtained box-truss structure. The geometric model was then passed to the experimentally for carbon fiber reinforced tubes considered by the MOVIE.BYU software package. The 'utility' module of this program ESA as candidates for space structural components. Tests were was used to manipulate the elements of the structure to represent performed on the mechanical properties, outgassing, thermal 13 different stages of deployment. The 'animate' command was expansion, fast thermal cycling tolerance, and microcracking, and then used to create a smooth sequence between stages. Each also on the long-term durability of the tubes to all the test stresses. step in the sequence was recorded on magnetic tape and a short The CTE decreased with decreasing temperature and increases movie was produced. M.A.C. in thermal cycling. The variation in the CTS decreased with

22 04 STRUCTURAL AND THERMAL ANALYSIS increased thermal cycling, after which the material became more an actual test structure under development at the Charles Stark homogeneous. Microcracks appeared after thermal cycling and Draper Laboratories. Author the density of microcracks also increased in proportion to the number of thermal cycles. CTE decreased with increases in the number of microcracks, while the mechanical properties remained relatively constant independent of the number of thermal cycles. More extensive tests are recommended to validate the CFRP tubes A84-17910# for 30,000 thermal cycles expected to be encountered by the SPACECRAFT THERMAL DESIGN USING INTERACTIVE EURECA free-flying platform in a 500-600 km orbit. M.S.K. GRAPHICS M. S. CROUTHAMEL (RCA Advanced Technology Laboratories, A84-14050* National Aeronautics and Space Administration. Camden, NJ) American Institute of Aeronautics and Astronautics, Langley Research Center, Hampton, Va. Aerospace Sciences Meeting, 22nd, Reno, NV, Jan. 9-12, 1984. 8 BUCKLING AND VIBRATION OF ANY PRISMATIC ASSEMBLY P- OF SHEAR AND COMPRESSION LOADED ANISOTROPIC (AIAA PAPER 84-0143) PLATES WITH AN ARBITRARY SUPPORTING STRUCTURE This paper describes the thermal analysis of a geosynchronous M. S. ANDERSON (NASA, Langley Research Center, Structural communications satellite in launch configuration. PATRAN was Concepts Branch, Hampton, VA), F. W. WILLIAMS (University of used as the interactive solid geometry modeler. Some PATRAN Wales Institute of Science and Technology, Cardiff, Wales), and models were coupled to the TRASYS thermal radiation analyzer C. J. WRIGHT (british Aerospace PLC, Bristol, England) to determine radiative couplings and environmental inputs. Other International Journal of Mechanical Sciences (ISSN 0020-7403), PATRAN models were coupled to SINDA to determine conductive vol. 25, no. 8, 1983, p. 585-596. refs couplings and thermal masses. Finally, the TRASYS and SINDA (Contract NCCW-000002) inputs from PATRAN were combined to determine transient and The computer program designated 'VIPASA', which accurately steady-state temperature distributions. Author treats buckling and vibration in prismatic plate assemblies with a response that varies sinusoidally in the longitudinal direction, has been found to be limited by the production of an in-plane shear loading of component plates that produces skewed mode shapes. These do not conform to desired support conditions. This problem is presently overcome through a coupling of the VIPASA stiffness A84-17911*# Washington Univ., Seattle. matrices for different wavelength responses by means of the RADIATION-CONDUCTION INTERACTION IN LARGE SPACE Lagrangian Multipliers method. The theory extends to supports at STRUCTURES arbitrary locations, and even to the support provided by any elastic A. F. EMERY, H. R. MORTAZAVI, and S. O. SMITH (Washington, structure. The generality and capabilities of VIPASA have been University, Seattle, WA) American Institute of Aeronautics and retained in the computer program designated 'VICON', which Astronautics, Aerospace Sciences Meeting, 22nd, Reno, NV, Jan. permits constraints and a supporting structure consisting of any 9-12, 1984. 9 p. refs number of transverse beam columns. O.C. (Contract NAG1-41) (AIAA PAPER 84-0144) A84-17850# The effects of a penumbra due to the long wave radiation WEIGHT CHARACTERISTICS OF FUTURE SPACECRAFT emitted by the earth or to solar energy reflected from the earth THERMAL MANAGEMENT SYSTEMS on temperature distributions, deflections and stresses in plates J. W. SHEFFIELD (Missouri-Rolla, University, Rolla, MO) and V. J. are studied to determine their importance in the design of space VAN GRIETHUYSEN (USAF, Wright Aeronautical Laboratories, structures. An examination of the state of stress in a thin plate Wright-Patterson AFB, OH) American Institute of Aeronautics exposed to the sun suggests that deflections are only slightly and Astronautics, Aerospace Sciences Meeting, 22nd, Reno, NV, modified by the penumbra, but that stresses in the vicinity of the Jan. 9-12, 1984. 6 p. refs shadow line are more affected. Even with the smoothing due to (AIAA PAPER 84-0054) the penumbra, these stresses should be considered in the design This paper presents the results of an investigation on the weight of space structures. A simple relationship is given by which albedo characteristics of future spacecraft thermal management systems. viewfactors can be easily derived from the direct viewfactor, thus The sensitivity of the thermal management system weight to the simplifying the radiation analysis. Author performance requirements of both evolutionary and revolutionary spacecraft .missions has been studied. A numerical analysis modeling the transient heat flow through the thermal management system was performed. The performance parameters included the peak thermal load, the peak-to-average thermal load ratio and A84-21284# length of peak load. In addition the sensitivity of the thermal MULTI-MEGAWATT SPACE POWER THERMAL MANAGEMENT management system weight to the choice of phase change material SYSTEM REQUIREMENTS for heat storage was determined via a heat of fusion parametric R. T. TAUSSIG (Mathematical Sciences Northwest, Inc., Bellevue, analysis. Author WA) American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting, 22nd, Reno, NV, Jan. 9-12, 1984. 7 A84-17853# P- STRUCTURAL PARAMETER IDENTIFICATION FOR FLEXIBLE (AIAA PAPER 84-0056) SPACECRAFT Multi-megawatt space power systems will require a novel S. L HENDRICKS, S. M. HAYES, and J. L JUNKINS (Virginia approach to manage the enormous amounts of waste heat Polytechnic Institute and State University, Blacksburg, VA) generated. Mission constraints such as average and peak power American Institute of Aeronautics and Astronautics, Aerospace requirements, power system duty cycle, on-board end use power Sciences Meeting, 22nd, Reno, NV, Jan. 9-12, 1984. 5 p. requirements, and mission lifetime, orbit parameters, maneuver and USAF-supported research, refs attitude control accelerations, speed of deployment, and other (AIAA PAPER 84-0060) related requirements are used to define the amounts, temperatures, A system identification procedure applicable to large flexible and temporal duration of waste heat production. These quantities spacecraft is presented. An iteration scheme is used to obtain are then applied to the design and optimization of a thermal best estimates for a small set of key system parameters so that management system based on a thermal bus. Applications include the predicted natural frequencies and damping factors agree with 100 kw to 1 MW space platforms and burst mode missions requiring measured values. Numerical simulations are presented based on up to several hundred MW of electric power. Author

23 04 STRUCTURAL AND THERMAL ANALYSIS

A84-28237 A84-29067 THERMAL-MECHANICAL BEHAVIOR OF THERMAL CONTROL OF THE TETHERED SATELLITE GRAPHITE/MAGNESIUM COMPOSITES MODULE B. J. MACLEAN and M. S. MISRA (Martin Marietta Aerospace, G. BORRIELLO and G. PELLIS (Aeritalia S.p.A., Turin, Italy) AIAA, Denver, CO) IN: Mechanical behavior of metal-matrix composites; SAE, ASME, AlChE, and ASMA, Intersociety Conference on Proceedings of the Symposium, Dallas, TX, February 16-18, 1982 Environmental Systems, 13th, San Francisco, CA, July 11-13,1983. . Warrendale, PA, The Metallurgical Society of AIME, 1983, p. 11 p. 195-212. refs (SAE PAPER 831138) Continuous-filament, graphite-reinforced magnesium composites Thermal analytical modeling plays an important role in the exhibit exceptional unidirectional mechanical properties fo their design, development and evaluation of the Space Shuttle's weight. For aerospace applications requiring high modulus, Tethered Satellite System (TSS) module, which in accomodating light-weight, thermal deformation-resistant materials, Gr/Mg a wide range of experiments and instruments requires variable promises substantial payoffs, and is compared to other more thermal control features. The TSS design approach to thermal conventional materials. Single-ply and 3-ply VSB32/AZ91C/AZ31B control encompasses external and internal coatings, control of panels and single ply VS0054/AZ91C/AZ31B panels were thermally conductive paths, the use of multilayer insulation blankets, evaluated. NDI techniques of X-radiography, ultrasonic C-scan, and and electrical heaters. Standard thermal computer programs are liquid penetrant were used to assess filament collimation, face used to evaluate spacecraft radiative exchange, quantify heat flux sheet disbonds, and sheet tears or pitting, respectively. Ambient impingements on surfaces, and predict resulting temperature temperature tensile testing yielded longitudinal elastic modulus variations, at various Space Shuttle Orbiter orientations with respect values predicted by the rule-of-mixtures (32.4 Msi for 28.4 to solar flux. O.C. volume-percent Pitch 100 Gr/Mg) and ultimate tensile strengths of better than 83 ksi. Failure analysis and fractography were then conducted to determine failure modes. Author

A84-29071 THE THERMAL DESIGN OF THE EUROPEAN COMPLEMENT OF FSLP A84-29032* National Aeronautics and Space Administration. U. LAUX (ERNO Raumfahrttechnik GmbH, Bremen, West Lyndon B. Johnson Space Center, Houston, Tex. Germany) AIAA, SAE, ASME, AlChE, and ASMA, Intersociety THERMAL MANAGEMENT SYSTEM TECHNOLOGY Conference on Environmental Systems, 13th, San Francisco, CA, DEVELOPMENT FOR SPACE STATION APPLICATIONS July 11-13, 1983. 11 p. J. G. RANKIN and P. F. MARSHALL (NASA, Johnson Space Center, (SAE PAPER 831144) Houston, TX) AIAA, SAE, ASME, AlChE, and ASMA, Intersociety Due to the unique requirements of the First Spacelab Mission, Conference on Environmental Systems, 13th, San Francisco, CA, extensive analytical efforts have had to be made to determine July 11-13, 1983. 14 p. refs instrument rack thermal characteristics. In the case of Space (SAE PAPER 831097) Shuttle Orbiter cargo bay-located payloads, such analytical studies A short discussion of the history to date of the NASA thermal can be less demanding provided that the instrumentation whose management system technology development program is thermal control is in question employs the Shuttle's Freon-cooling presented, and the current status of several ongoing studies and loop and makes effective use of thermal insulation. In the case of hardware demonstration tasks is reported. One element of complex experiment configurations, additional systems for the technology that is required for long-life, high-power orbital optimal control of human contact areas rather than heat rejection platforms/stations that is being developed is heat rejection and a capabilities must be developed. It is noted that the thermal space-constructable radiator system. Aspects of this project include insulation practices developed for the European Bridge Assembly high-efficiency fin concepts, a heat pipe quick-disconnect device, yield both higher thermal performance and greater integration high-capacity heat pipes, and an alternate interface heat exchanger flexibility. O.C. design. In the area of heat acquisition and transport, developments in a pumped two-phase transport loop, a capillary pumped transport loop using the concept of thermal utility are reported. An example of a thermal management system concept is provided. J.N. A84-29076* United Technologies Corp., Windsor Locks, Conn. REGENERABLE NON-VENTING THERMAL CONTROL SUBSYSTEM FOR EXTRAVEHICULAR ACTIVITY A84-29036 G. J. ROEBELEN, JR., K. J. DRESSER, E. W. HODGSON, JR. A CONTACT CONDUCTANCE INTERFACE FOR A SPACE (United Technologies Corp., Hamilton, Standard Div., Windsor CONSTRUCTABLE HEAT PIPE RADIATOR Locks, CT), and C. LIN (NASA, Johnson Space Center, Houston, J. A. OREN and M. L FLEMING (Vought Corp., Dallas, TX) AIAA, TX) AIAA, SAE, ASME, AlChE, and ASMA, Intersociety SAE, ASME, AlChE, and ASMA, Intersociety Conference on Conference on Environmental Systems, 13th, San Francisco, CA, Environmental Systems, 13th, San Francisco, CA, July 11-13, 1983. July 11-13, 1983. 15 p. 11 p. (Contract NAS9-16609) (SAE PAPER 831101) (SAE PAPER 831151) The design, development, feasibility demonstration, and testing Extravehicular Mobility Unit heat rejection requirements have of a prototype heat exchanger device which will provide an interface been formulated for both Space Shuttle Orbiter and space station with a spacecraft thermal control subsystem at a regenerable npnventing thermal sink (RNTS) applications, where connectable/disconnectable joint is described. The approach taken the former involve nonventing extravehicular activity (EVA) missions involves pressurized clamping of a segmented cylindrical heat and the latter both nonventing and regenerable EVA. The present exchanger on the outside of a round heat pipe evaporator section, conceptual study notes that while the exclusive use of thermal and is intended to provide a contact heat exchanger which could storage is suitable for the Space Shuttle mission, space station be connected or disconnected without breaking of fluid systems requirements are best satisfied by a hybrid system which combines in the assembly/dissembly of radiator panels. The heat pipe thermal storage with radiator and heat pump. The Space Shuttle radiators are 9 to 18 m in length and use a single high-capacity RNTS thermal control subsystem's thermal storage unit uses water heat pipe attached to a fin 15 to 30 cm wide. In testing, thermal as a phase change medium. It is noted that the same heat storage conductance across the interface of 8500 w/sq m-deg C and unit can satisfy the Space Shuttle and space station overall conductance of 4300 w/sq m-deg C were obtained. J.N. requirements. O.C.

24 04 STRUCTURAL AND THERMAL ANALYSIS

N84-11200 Messerschmitt-Boelkow-Blohm G.m.b.H., Ottobrunn N84-16509# Sandia Labs., Livermore, Calif. Systems Evaluation (West Germany). Betriebsbereich. Div. SPACECRAFT THERMAL CONTROL SELECTION FOR SEVEN SODIUM HEAT TRANSFER SYSTEM MODELING YEARS OF LIFETIME IN SYNCHRONOUS ORBIT A. F. BAKER and M. E. FEWELL (Sandia Labs., Albuquerque, N. L PREUSS 1982 16 p Presented at 55th AGARD/SMP Mex.) 1983 6 p refs Presented at the ASME Winter Ann. Panel Meeting/Specialists Meeting on Environ. Effects on Mater, Meeting, Boston, 13-18 Nov. 1983 for Space Appl., Toronto, 19-24 Sep. 1982 (Contract DE-AC04-76DP-00789) (MBB-UR-584-82-OE) Avail: Issuing Activity (DE84-002051; SAND-83-1631C; CONF-831111-9) Avail: NTIS Nonconductive and conductive flexible second surface mirrors HC A02/MF A01 (SSM) with interference filters on top for satellite use are presented. The sodium heat transfer system of the international energy The SSM composition is analyzed and defined. The optimization agency (IEA) small solar power systems (SSPS) central receiver procedure for the SSM is outlined. The qualification of the SSM system (CRS), which includes the heliostat field, receiver, hot and on laboratory scale for synchronous orbit is demonstrated. cold storage vessels, and sodium/water steam generator was Handling, application and performance specifications are given. modeled. The computer code SOLTES (simulator of large thermal Author (ESA) energy systems), was used to model this system. The results from SOLTES are compared to measured data. DOE

N84-15329*# National Aeronautics and Space Administration. N84-16565*# Old Dominion Univ., Norfolk, Va. Dept. of Goddard Space Flight Center, Greenbelt, Md. Mechanical Engineering and Mechanics. NASA NEEDS AND TRENDS IN CRYOGENIC COOLING SELF-SHADOWING OF ORBITING TRUSSES Progress Report A. SHERMAN In its Refrig. for for Cryogenic Sensors p 13-27 J. MAHANEY and E. A. THORNTON Aug. 1983 48 p Dec. 1983 refs (Contract NAG 1-257) Avail: NTIS HC A19/MF A01 CSCL 20L (NASA-CR-173215; NAS 1.26:173215) Avail: NTIS HC A03/MF Projected NASA needs in spaceborne cryogenic systems and A01 CSCL 131 recent results of NASA cryogenic cooling technology efforts in The approach used to assess shadowing reductions on the infrared astronomy, X-ray astronomy, gamma ray astronomy, liquid heating of orbiting trusses involves determining the heating rates helium and space stations are discussed. R.J.F. with slender member shadowing effects included and then obtaining the thermal response of the shadowed member. Steps taken to identify shadowers, find locations where shadowing occurs and calculate shadow intensity are listed. The finite element thermal N84-15426*# National Aeronautics and Space Administration. structural analysis of cable stiffened space structure is delineated Langley Research Center, Hampton, Va. and the exact solution of the caternary problem is given. Typical THERMAL ANALYSIS RESEARCH APPLICABLE TO SPACE cable surface heating rates are plotted. The structural analysis STATION TECHNOLOGY NEEDS includes large deformation (nonlinear), thermal effect, and the H. M. ADELMAN Apr. 1983 53 p Presented at the Space pretension effect. Displacements and stresses are computed at State Technol. Workshop, Williamsburg, Va., 28-31 Mar. 1983 different orbital positions for an orbit. A.R.H. (NASA-TM-84658; NAS 1.15:84658) Avail: NTIS HC A04/MF A01 CSCL 20D N84-17222*# National Aeronautics and Space Administration. Thermal analysis, optimization, and software research and Goddard Space Flight Center, Greenbelt, Md. development at the NASA Langley Research Center which is THERMAL ENERGY MANAGEMENT PROCESS EXPERIMENT applicable to analytical design calculations for space station S. OLLENDORF In NASA. Langley Research Center STEP structures are summarized. Topics discussed include integrated Expt. Requirements p 161-163 Jan. 1984 thermal-structural software, improved thermal radiation analysis, Avail: NTIS HC A15/MF A01 CSCL 22B solution techniques for transient temperatures, unified The thermal energy management processes experiment (TEMP) thermal-structural finite elements, thermal structural sensitivity will demonstrate that through the use of two-phase flow technology, analysis and optimization, and concept and performance analysis thermal systems can be significantly enhanced by increasing heat for heat pipes. Author transport capabilities at reduced power consumption while operating within narrow temperature limits. It has been noted that such phenomena as excess fluid puddling, priming, stratification, and N84-15562# National Centre of Tribology, Risley (England). surface tension effects all tend to mask the performance of European Space Tribology Lab. two-phase flow systems in a 1-g field. The flight experiment THERMAL CONDUCTANCE AND TORQUE OF THIN SECTION approach would be to attack the experiment to an appropriate FOUR-POINT CONTACT BALL BEARINGS IN VACUUM mounting surface with a 15 to 20 meter effective length and provide R. A. ROWNTREE and M. J. TODD Paris ESA Mar. 1983 a heat input and output station in the form of heaters and a 57 p refs radiator. Using environmental data, the size, location, and (Contract ESTEC-4099/79/NL-PP(SQ) orientation of the experiment can be optimized. The approach (ESA-ESTL-54; ESA-CR(P)-1772) Avail: NTIS HC A04/MF A01 would be to provide a self-contained panel and mount it to the Ball bearings for the L-SAT antenna pointing mechanism (APM) STEP through a frame. A small electronics package would be were tested in vacuum with external diameter clearance (i.e., free developed to interface with the STEP avionics for command and fit rings) and held in-situ with clamp rings. The influence of speed, data handling. During the flight, heaters on the evaporator will be temperature, internal preload, axial ring clamping force, lubricant exercised to determine performance. Flight data will be evaluated and cage type was examined. As the inner race becomes warmer against the ground tests to determine any anomalous behavior. than the outer, the conductance increases linearly with the M.G. temperature difference, whereas the increase in torque is almost a square law relation. With a colder inner race, the bearing develops N84-18289*# Grumman Aerospace Corp., Bethpage, N.Y. internal diametral clearance and thus gives low conductance and THERMAL CONTROL a small constant torque. Bearing torque and conductance are also B. HASLETT In NASA. Langley Research Center Space Station shown to be dependent on axial clamping force, internal preload Technol., 1983 p 165-186 Feb. 1984 and lubricant quantity. Hysteresis effects of temperature on Avail: NTIS HC A09/MF A01 CSCL 22B conductance and torque, and the contribution of the cage to the There are basically three key ingredients to the thermal control overall bearing torque are noted. By suitable selection of internal system for any large space platform or space station. These are preload and clamping force, the design requirements for L-SAT heat rejection (from a centralized radiator or from body mounted APM bearings can be achieved. Author (ESA) radiators), heat acquisition (from payloads), and heat transport

25 04 STRUCTURAL AND THERMAL ANALYSIS

(via a transport loop to the radiator). The echnical approach in into existing conventional solar simulation facilities. It was assessed the heat rejection area is to construct the radiator from individual by using a telecommunication satellite model with typical radiator elements so that it can be built on-orbit, is very insensitive to faces. Comparison of the mathematical model and test model meteoroid and debris hazards, and is repairable. In the area of temperatures is considered acceptable, allowing for the difference thermal acquisition and transport an added effort to better between infrared and solar simulation. Author (ESA) understand two phase flow in zero gravity by analysis and testing is suggested. Author N84-19400# European Space Research and Technology Center, Noordwijk (Netherlands). N84-18576*# National Aeronautics and Space Administration, IRSIM: A PROGRAM FOR THE CALCULATION OF INFRARED Washington, D. C. FLUX INTENSITY INCIDENT ON A SPACECRAFT INSIDE A SECOND ALL-UNION SEMINAR ON HYDROMECHANICS AND TEST CHAMBER HEAT-MASS TRANSFER IN WEIGHTLESSNESS. ABSTRACTS R. P. ROGERS In ESA Environ, and Thermal Control Systems OF REPORTS: TABLE OF CONTENTS for Space Vehicles p 27-37 Dec. 1983 refs G. Z. GERSHUNI and Y. M. ZHUKHOVITSKIY Jan. 1984 15 p Avail: NTIS HC A25/MF A01 refs Transl. into ENGLISH of conf. papers, 1981 p 176-186 A computer program which calculates the infrared flux intensity Seminar held in Perm, USSR, 1981 received by a specimen in a test chamber is described. Illumination (Contract NASW-3542) by an array of infrared lamps in thermal testing of spacecraft too (NASA-TM-77534; NAS 1.15:77534) Avail: NTIS HC A02/MF large for conventional solar simulators is considered. The code is A01 CSCL 20D used to decide on a sensor/baffle/lamp arrangement at an early Abstracts of reports are given which were presented at the stage in the test process; and to help resolve discrepancies Second All Union Seminar on Hydromechanics and Heat-Mass observed in the test measurements. The modelling of the NOSAT Transfer in Weightlessness. Topics inlcude: (1) features of dummy spacecraft is described. Author (ESA) crystallization of semiconductor materials under conditions of microacceleration; (2) experimental results of crystallization of solid N84-19401# European Space Agency, Paris (France). solutions of CDTE-HGTE under conditions of weightlessness; (3) THERMAL CYCLING TESTS IN SPACE ENVIRONMENT impurities in crystals cultivated under conditions of weightlessness; SIMULATION CHAMBERS [LES ESSAIS DE CYCLAGES and (4) a numerical investigation of the distribution of impurities THERMIQUES DANS LES CHAMBRES DE SIMULATION during guided crystallization of a melt. B.W. SPATIALE] C. POUX (Intespace, Toulouse) In its Environ, and Thermal N84-19396# European Space Agency, Paris (France). Control Systems for Space Vehicles p 39-42 Dec. 1983 In ENVIRONMENTAL AND THERMAL CONTROL SYSTEMS FOR FRENCH SPACE VEHICLES Avail: NTIS HC A25/MF A01 T. D. GUYENNE, ed. and J. J. HUNT, ed. Dec. 1983 576 p Thermal cycling/thermal vacuum test facilities to simulate space refs Partly in FRENCH and ENGLISH Proc. of Intern. Symp., environments are described. Solar simulation at 1400 W/sqm is Toulouse, 4-7 Oct. 1983; sponsored by CNES and ESA Original possible. Thermal cycling test temperatures can vary from 100 to contains color illustrations 360 K. Thermal vacuum test temperatures between -60 and +55 (ESA-SP-200; ISSN-0379-6566) Avail: NTIS HC A25/MF A01; C are achieved. Infrared tests using 500 W quartz lamps are ESA, Paris FF 250, Member States, AU, CN and NO (+20% carried out. The vacuum chambers allow a main satellite spherical others) body of 3 m diameter, or a deployed configuration of 6 m diameter, Spacecraft thermal testing, thermal control technology, thermal 7 m height, to be tested. Author (ESA) control design, cryogenics, and thermal analysis were discussed. Environmental control systems for space stations and platforms, N84-19402*# National Aeronautics and Space Administration. and in flight experience were considered. Goddard Space Flight Center, Greenbelt, Md. RECENT AND PLANNED DEVELOPMENTS AT THE GODDARD N84-19398# Aeritalia S.p.A., Torino (Italy). SPACE FLIGHT CENTER IN THERMAL CONTROL DEVELOPMENT OF A SPACECRAFT INFRARED TEST TECHNOLOGY TECHNIQUE AS AN ALTERNATIVE TO SOLAR SIMULATION: S. OLLENDORF In ESA Environ, and Thermal Control Systems FIRST STEPS ON L-SAT THERMAL MODEL for Space Vehicles p 45-51 Dec. 1983 refs P. MESSIDORO, D. BOGGIATTO, M. PATACCIA, and P. Avail: NTIS HC A25/MF A01 BURATTI In ESA Environ, and Thermal Control Systems for Thermal control technology for advanced spacecraft and space Space Vehicles p 11-17 Dec. 1983 refs stations is presented. Results of proof of concept two phase Avail: NTIS HC A25/MF A01 laboratory devices indicate that large amounts of energy (1 to 2 The L-Sat satellite was used for an off-line investigation to kw) can- be transported long distances (10 to 20 m) with very develop an infrared test technique alternative to solar simulation, small temperature differences. An evolutionary test bed for because of its large size and the presence of heat pipes on its advanced development of thermal technology, which provides data north/south radiators. The infrared test set-up facility and test on components and systems for space station designs is described. sequence; lamp characteristics; surface property measurements; Results of the STS-3 Thermal Canister Experiment show that the flux calculation; flux measurement; power control system; lamp rig enclosure held simulated instruments to + or - 1 C over a wide design; and test prediction and correlation are described. range of thermal environments. Author (ESA) Improvements to the test technique are suggested. Author (ESA) N84-19405# Aeritalia S.p.A., Torino (Italy). Space Sector. HEAT PIPES FOR THE L-SAT COMMUNICATIONS MODULE N84-19399# European Space Research and Technology Center, RADIATORS Noordwijk (Netherlands). M. PAPACCIA, V. PEROTTO, B. SESSIONS, and H. KREEB SPACECRAFT THERMAL BALANCE TESTING USING (Dornier-Werke G.m.b.H., Friedrichshafen, West Germany) In ESA INFRARED LAMPS ON A DUMMY SPACECRAFT Environ, and Thermal Control Systems for Space Vehicles p 67-74 G. B. T. TAN and J. B. WALKER In ESA Environ, and Thermal Dec. 1983 refs Control Systems for Space Vehicles p 19-25 Dec. 1983 refs Avail: NTIS HC A25/MF A01 Avail: NTIS HC A25/MF A01 Constant conductance aluminum axial groove ammonia heat The use of tungsten lamp infrared sources placed in close pipes for L-SAT 1 north/south radiators were developed. proximity to a spacecraft undergoing thermal balance testing is Twenty-four pipes on the south radiator and 38 on the north reject discussed. The technique has economic advantages for thermal directly imposed heat loads of 600 W and 700 W, respectively. balance testing of spaceborne objects which are too large to fit Pipe inner diameter is 5.0 mm, outer square dimension = 9.0

26 04 STRUCTURAL AND THERMAL ANALYSIS mm. Integral fins provide equipment mounting support and control was manufactured. The TDM consists of radiator panels increased thermal efficiency. Pipe lengths range from 0.72 m to (1.2 x 1.85 m), Spacelab type piping, fluid loop servicer with pump 1.238 m. The L-SAT honeycomb radiators offer up to 5.23 sqm package, thermal control valves (bypass and flow metering) and a radiating area each (2.1 x 2.58 m less the solar array drive microprocessor based electronic control unit. Studies leading to mechanism). To establish the manufacturing techniques for the the definition of the TDM; the design and manufacturing activities heat pipe radiators and to acquire confidence in the analytical of the components; and the test program are described. modeling approach, a development model heat pipe radiator Author (ESA) measuring 0.8 m x 1.6 m with ten 1.5 m long heat pipes was tested in a vacuum chamber. Author (ESA) N84-19444# Aeritalia S.p.A., Torino (Italy). Space Sector. THERMAL CONTROL OF TETHERED SATELLITE IN A VERY W84-19406# Royal Netherlands Aircraft Factories Fokker, LOW ALTITUDE AERODYNAMIC MISSION Schiphol-Oost. Space Div. G. BORRIELLO, C. CHIARELLI, G. PELLIS, and F. A VARIABLE CONDUCTANCE HEAT PIPE (VCHP) RADIATOR AL-ASTRABADI In ESA Environ, and Thermal Control Systems SYSTEM FOR COMMUNICATIONS PAYLOADS for Space Vehicles p 407-416 Dec. 1983 refs N. H. PENNINGS and C. J. SAVAGE (ESTEC, Noorwidjk, Avail: NTIS HC A25/MF A01 Netherlands) In ESA Environ, and Thermal Control Systems for Aerodynamic heating rates that a very low altitude satellite Space Vehicles p 75-81 Dec. 1983 Sponsored by ESTEC (100 km) can experience were calculated. A theoretical analysis, Avail: NTIS HC A25/MF A01 evaluating Knudsen number for flow regimes from free molecular A thermal control system to support the development of a to transition, is presented. Although it is not possible to predict multibeam antenna array system for communication satellites is with high confidence level the heating rates in transition flow discussed. Trade-off shows that for the antenna power amplifiers regimes, the analysis data can be used to facilitate theoretical a system using variable conductance heat pipes (VCHPs) is the development. Metallic and ceramic thermal shields to protect the optimum heat rejection system. The VCHP-concept is compared satellite primary structure were investigated. Conventional design with louvers, phase change materials, feedback controlled heat methods are proposed to control internal unit temperature. pipes, and heaters. With passively controlled reservoirs and subject Author (ESA) to a factor of 3 variation in the power dissipation, the VCHP concept features a temperature range of 10 to 50 C. The system N84-19449# Lockheed Missiles and Space Co., Palo Alto, Calif. is suitable for all spacecraft with remote dissipating and radiating EFFECTS OF COMBINED ULTRAVIOLET AND OXYGEN elements. Author (ESA) PLASMA ENVIRONMENT ON SPACECRAFT THERMAL CONTROL MATERIALS N84-19414# Aeritalia S.p.A., Torino (Italy). M. MCCARGO, R. E. DAMMANN, J. C. ROBINSON, and R. J. THE THERMAL DESIGN OF L-SAT LARGE MILLIGAN In ESA Environ, and Thermal Control Systems for TELECOMMUNICATION SATELLITE Space Vehicles p 447-454 Dec. 1983 refs Sponsored by D. BOGGIATTO, E. COLIZZI, R. VENERI, and E. SACCHI In Lockheed Palo Alto Research Laboratory Directorate ESA Environ, and Thermal Control Systems for Space Vehicles Avail: NTIS HC A25/MF A01 p 149-159 Dec. 1983 refs Sponsored by ESA and British A laboratory plasma reactor was built to study the effects on Aerospace Dynamics Group surface properties of materials flown in space shuttle cargo bays Avail: NTIS HC A25/MF A01 of the interaction of the surfaces with atomic oxygen in low Earth The passive thermal control design of the L-SAT series of orbit. The apparatus, the effects of oxygen plasma plus ultraviolet satellites is outlined. Multilayer insulation blankets, heaters, thermal radiation on thermal control materials, changes in optical properties, doubters, paints, and thermal fillers/stand offs are supplemented and rate of weight loss are described. Results show that UV effects by constant conductance heat pipes, electrically conductive coated are negligible in all cases, and that changes are due to the oxygen second surface mirrors, and a multilayer insulation outer layer. environment. Author (ESA) The heat rejection philosophy is standard for a three axis stabilized geostationary satellite, with external appendages insulated from M84-19454# Centre National d'Etudes Spatiales, Toulouse the spacecraft body. Author (ESA) (France). A MALTESE CROSS SHAPED MOBILE THERMAL CONTROL N84-19423# Institute of Space and Astronautical Science, Tokyo SHUTTER [VOLET MOBILE DE CONTROLE THERMIQUE DU (Japan). TYPE CROIX DE RflALTE] THERMOFLUIDYNAMICS OF HEAT PIPES I. ALET In ESA Environ, and Thermal Control Systems for K. OSHIMA and M. MURAKAMI (Tsukuba University, Japan) In Space Vehicles p 477-480 Dec. 1983 In FRENCH ESA Environ, and Thermal Control Systems for Space Vehicles Avail: NTIS HC A25/MF A01 p 231-234 Dec. 1983 refs The advantages of a Maltese cross shaped shutter over Avail: NTIS HC A25/MF A01 Venetian blind type systems for satellite thermal control are The operation of high heat flux heat pipes is analyzed using a described. It has low power consumption, is mechanically simple, thermodynamic phase diagram, and the gasdynamic heat pipe and can be used against the Sun. Its low surface efficiency makes which uses the gasdynamic effect of the vapor flow for pumping it unsuitable for geostationary telecommunication satellites, but up the liquid onto the evaporator is discussed. A space station presents no problems in low Earth orbit. Thermal, vibration, and thermal control system using the gasdynamic heat pipe is shock tests demonstrate its robustness and reliability. introduced. This system does not need any external force and is Author (ESA) self-controlled. It ensures high system reliability as well as wide design flexibility. Author (ESA) M84-19458# European Space Research and Technology Center, Noordwijk (Netherlands). N84-19434# Aeritalia S.p.A., Torino (Italy). System THE LARGE SPACE SIMULATOR (LSS) AT ESA/ESTEC (A Engineering-Space Sector. SUMMARY OF THE MAIN CHARACTERISTICS) DESIGN AND MANUFACTURING OF A HEAT REJECTION P. W. BRINKMANN In ESA Environ, and Thermal Control Systems SYSTEM FOR ADVANCED THERMAL CONTROL for Space Vehicles p 501-503 Dec. 1983 refs L. BUSSOLINO and J. P. BOUCHEZ (ESTEC, Noordwijk, Avail: NTIS HC A25/MF A01 Netherlands) In ESA Environ, and Thermal Control System for Parameters of ESA's Space Simulator for thermal balance tests Space Vehicles p 329-335 Dec. 1983 refs on satellites and satellite equipment with large geometries are Avail: NTIS HC A25/MF A01 listed. A vertical main chamber and horizontal auxiliary chamber A Technology Demonstration Model (TDM) of a heat rejection are interfaced by a 8 m dia nozzle. Main chamber and nozzle will system dedicated to advanced spacecraft and payload thermal be equipped with a shroud lining the complete chamber surface,

27 04 STRUCTURAL AND THERMAL ANALYSIS while the shroud elements in the auxiliary chamber have the form N84-20624*# Vought Corp., Dallas, Tex. of light baffles. The collimation mirror is suspended from the rear FLEXIBLE RADIATOR SYSTEM: EXECUTIVE SUMMARY stiffening ring of the auxiliary chamber. A spout provides the J. R. OREN and R. L. COX 30 Oct. 1982 49 p interface between the vacuum chamber and the lamp house. The (Contract NAS9-14776) lamp house contains 19 lamp modules, collection optics and (NASA-CR-171766; NAS 1.26:171766; REPT-2-19200/3R-1062B) transfer optics and provides a protective environment for all optical Avail: NTIS HC A03/MF A01 CSCL 22B elements. The test articles can be mounted on a vibration-free A full scale prototype flexible radiator panel was designed, support platform (eventually via a motion simulator) or suspended built and tested. The panel, has approximately 173 sq ft of radiating from support lugs in the upper part of the main chamber. area and is designed to reject 1.33 kW of heat to a 0 F sink with Author (ESA) a 100 F fluid inlet. The panel is constructed from a flexible Teflon/silver mesh fin surrounding 1/8 inch Teflon tubes. The prototype panel is stowed on a 10 inch diameter by 4 foot wide N84-19906# National Space Development Agency, Tokyo drum. (It rolls up to a diameter of 17 inches when fully stowed). (Japan). Deployment of the soft tube prototype is via two four inch diameter EVALUATION OF MODAL TESTING TECHNIQUES FOR Kevlar/Mylar inflation tubes with flat springs incorporated in each SPACECRAFT STRUCTURES tube. Nitrogen is normally used for the deployment with K. SHIRAKI and H. MITSUMA In Shock and Vibration Inform. approximately 1 psi required. The springs retract the panels when Center The Shock and Vibration Bull., part 3 p 161-170 May the inflation tubes are deflated. Another method of deployment 1983 refs available for the soft tube flexible is a motor driven deployable Avail: SVIC, Code 5804, Naval Research Lab., Washington, D.C. boom. This eliminates the need for expendables when the panel 20375 CSCL 22B area is varied during the mission for heat load control. The soft A comparative study of modal testing techniques with a base tube panel is designed for a 90% probability of no punctured classical sine sweep and random test methods based upon digital tube in a 30 day mission. The acceptable working fluids for this analysis techniques are compared by measuring transfer functions soft tube flexible are Coolanol 15, Coolanol 20 and Glycol/water of a simple beam specimen. For the random test data, modal (a eutectic mixture). S.L. analyses were performed using two kinds of analyzers, for two steps of input levels, respectively. The modal parameters obtained by both analyzers were in good agreement. And the structural response nonlinear characteristics due to the input level change were investigated. An example of the application of these techniques to the development of the Engineering Test Satellite 3 is shown. M.G. N84-21613# Consulenze General! Roma (Italy). COMPUTING THE RADIATION PRESSURE FORCES BY ADAPTING THERMAL DESIGN VERIFICATION SOFTWARES Final Report N84-20622*# Vought Corp., Dallas, Tex. C. ARDUINI In its Study on Syn. and Characterization of Large FLEXIBLE RADIATOR THERMAL VACUUM TEST REPORT Space Systems, Phase 2. Part 2: Proposals for Additions, J. A. OREN and C. W. HIXON 29 Oct. 1982 103 p refs Modifications, and New Anal. Methods, Vol. 1 p 169-208 Dec. (Contract NAS9-14776) 1982 (NASA-CR-171764; NAS 1.26:171764; REPT-2-32300/IR-03) Avail: NTIS HC A16/MF A01 Avail: NTIS HC A06/MF A01 CSCL 22B Formulas for computing radiation forces on large space Two flexible, deployable/retraction radiators were designed and structures are provided, and insertion of the formulas in thermal fabricated. The two radiator panels are distinguishable by their softwares is indicated. Radiation coming directly from the Sun or mission life design. One panel is designed with a 90 percent Earth, and direct reflection of this impinging radiation are probability of withstanding the micrometeoroid environment of a considered. Except for thermal radiation, all cases can be covered low earth orbit for 30 days. This panel is designated the soft tube by a single program run, and with a model limited to the spacecraft radiator after the PFA Teflon tubes which distribute the transport external surfaces. Formulas for general reflected flux distribution fluid over the panel. The second panel is designed with armored are generated. The formulas are specialized for diffuse, specular, flow tubes to withstand the same micrometeoroid environment for and specular-diffuse reflection. Applications for Sun primary 5 years. It is designated the hard tube radiator after its stainless reflection are treated. Author (ESA) steel flow tubes. The thermal performance of the radiators was tested under anticipated environmental conditions. The two deployment systems of the radiators were evaluated in a thermal vacuum environment. S.L.

N84-20623*# Vought Corp., Dallas, Tex. N84-21614# Consulenze General! Roma (Italy). FLEXIBLE RADIATOR SYSTEM SIMPLIFIED MODELS AND COMPUTATIONAL SCHEMES OF J. A. OREN 30 Oct. 1982 82 p refs THE AERODYNAMIC LOAD (Contract NAS9-14776) U. PONZI In its Study on Syn. and Characterization of Large (NASA-CR-171765; NAS 1.26:171765; REPT-2-19200/3R-1195B) Space Systems, Phase 2. Part 2: Proposals for Additions, Avail: NTIS HC A05/MF A01 CSCL 22B Modifications and New Anal. Methods, Vol. 1 p 209-276 Dec. The soft tube radiator subsystem is described including 1982 refs applicable system requirements, the design and limitations of the Avail: NTIS HC A16/MF A01 subsystem components, and the panel manufacturing method. The A scheme for computing the aerodynamic load on large space soft tube radiator subsystem is applicable to payloads requiring 1 structures during the preliminary design phase is outlined. The to 12 kW of heat rejection for orbital lifetimes per mission of 30 scheme is based on simplified interaction models able to reduce days or less. The flexible radiator stowage volume required is the aerodynamic aspect of the problem into a simple form with a about 60% and the system weight is about 40% of an equivalent reasonable accuracy; and the adaptation and/or use .of existing heat rejection rigid panel. The cost should also be considerably softwares in order to solve the geometrical implications. The less. The flexible radiator is particularly suited to shuttle orbrter Lockheed orbital heat rate program, the Thermal Radiation Analysis sortie payloads and also whose mission lengths do not exceed System program, and the Simplified Shuttle Payload Thermal the 30 day design life. A.R.H. Analyzer are described. Author (ESA)

28 04 STRUCTURAL AND THERMAL ANALYSIS

N84-21616# Consulenze General! Roma (Italy). N84-21619# Consulenze General! Roma (Italy). STUDY ON SYNTHESIS AND CHARACTERIZATION OF LARGE INTERACTIVE STRUCTURAL-THERMAL-CONTROL SPACE SYSTEMS, PHASE 2. PART 2: PROPOSALS FOR ANALYTICAL FORMULATIONS Rnal Report ADDITIONS, MODIFICATIONS AND NEW ANALYTICAL C. ARDUINI In its Study on Syn. and Characterization of Large METHODS, VOLUME 2 Final Report Space Systems, Phase 2. Part 2: Proposals for Additions, C. ANDUINI and U. PONZI Paris ESA Dec. 1982 368 p Modifications and New Anal. Methods, Vol. 2 p 171-368 Dec. refs 5 Vol. 1982 refs (Contract ESTEC-4348/80/NL-AK(SC)) Avail: NTIS HC A16/MF A01 (ESA-CR(P)-1779-VOL-4) Avail: NTIS HC A16/MF A01 The suitability of analytic solutions for large space structure Thermal design verification of large open truss structures of interactive thermal control dynamic problems was studied for the large spacecraft (the local approach and the shadow problem); case of a beam subjected to the thermal environment of space, computational savings in view factor evaluation by node and possibly actively controlled by sensors and actuators. It is prescreening; analytical formulations of the interactive structural shown that the basic interactive equations can be constructed in thermal control problem (thermostructural self excitation); and a variety of conditions based on a menu of component terms design oriented control theories in continuous models are derived from basic theories and limited special developments, such discussed. as a thermal theory of the beam. The approach is limited, however, to considering a fixed, generally simple, geometry, although the size can be increased by adding modes without changing the reduced size model. Author (ESA)

N84-21617# Consulenze General! Roma (Italy). THERMAL DESIGN VERIFICATION OF THE LARGE OPEN TRUSS STRUCTURES. THE LOCAL APPROACH AND THE SHADOW PROBLEM Final Report C. ARDUINI In its Study on Syn. and Characterization of Large N84-21621# Consulenze General! Roma (Italy). Space Systems, Phase 2. Part 2: Proposals for Additions, ASSESSMENT OF THE EXISTING GROUND TEST Modifications and New Anal. Methods, Vol. 2 p 13-120 Dec. TECHNOLOGY AND CONFRONTING WITH THE LARGE SPACE 1982 refs STRUCTURES (LSS) REQUIREMENTS. EXPERIMENTAL Avail: NTIS HC A16/MF A01 TECHNIQUES IN STRUCTURAL ANALYSIS For large space structure thermal design verification, an U. PONZI and A. AGNENI In its Study on Syn. and Characterization approximation which considers a single bay (or a module made of Large Space Systems, Phase 2. Part 3: Expt. Design Verification by a finite number of bays) as isolated from the rest of the system Tech. te] p 13-103 Dec. 1982 refs (the "local" approach) was suggested. Conditions under which Avail: NTIS HC A19/MF A01 the approximation is acceptable; and expressing heat input to the Static, dynamic and modal structural analysis of large space isolated bay, while not considering all the complex shadow effects structures (LSS) on ground are discussed. Standard excitation tests, of the complete system, are discussed. Analysis shows that the and the effect of the surrounding fluid in vibration are reviewed. local approach causes appreciable errors only at the boundaries, For LSS ground testing, constraints due to the large size; to the and considerably reduces computational loads. The method can peculiar physics of the problem; and originating from the Earth also be applied when both trusses and finite bodies are present. environment are the most important. These constraints act in For these systems an iterative scheme which solves in one step general all together, so that the effect of one factor is exasperated the system of the main bodies only (taking truss temperatures to by the presence of the remaining ones. The combination size-gravity be known) and in a successive step solves the truss, using the is the most significant example. Size constraints are best tackled local approach (taking main body temperature as known) is by partial model methods for static tests and reconstruction of proposed. Author (ESA) the behavior of the entire system by modal synthesis for dynamic tests. Investigation of physics related constraints is severely limited by scarcity of data on large configurations. Earth environment effects can be assessed by comparing the effect, e.g., gravity with each experimental parameter. Author (ESA) N84-21618# Consulenze General! Roma (Italy). COMPUTATIONAL SAVINGS IN VIEW FACTOR EVALUATION ON MODE PRESCREENING Final Report S. SGUBINI and C. ARDUINI In its Study on Syn. and Characterization of Large Space Systems, Phase 2. Part 2: Proposals for Additions, Modifications and New Anal. Methods, Vol. 2 p 121-170 Dec. 1982 refs N84-21622# Consulenze General! Roma (Italy). Avail: NTIS HC A16/MF A01 ASSESSMENT OF THE EXISTING GROUND TEST Criteria for reducing the number of view factors of each node TECHNOLOGY AND CONFRONTING WITH THE LARGE SPACE with respect to the surroundings to the absolute minimum STRUCTURES (LSS) REQUIREMENTS. THERMAL TEST compatible with a prescribed accuracy for large space structures TECHNIQUES thermal design verification; and minimizing the number of elements U. PONZI In its Study on Syn. and Characterization of Large required per node for a given accuracy are discussed. A multiple Space Systems, Phase 2. Part 3: Expt. Design Verification Tech. screening technique, using the Simplified Shuttle Payload Thermal te] p 104-169 Dec. 1982 refs Analyzer (SSPTA) program, is investigated. The SSPTA contains Avail: NTISHCA19/MFA01 a mixed surface-contour integral type view factor routine. Additional Thermal balance and thermal cycle ground testing of large surfaces can be screened out after the shadow check, if a space structures is reviewed. Scale reduction is identified as the substantial blockage is detected. Computation of view factors major problem. For the combined dynamical - radiation - thermal - among the remaining nodes can be effected, after the appropriate structural problem, no length-scaling appears possible. For the number of elements in the node is selected, in agreement with combined radiation - thermal - structural problem (statistically the desired accuracy. It is shown that this procedure can drastically distorting structures) slight length-scaling is possible. For uncoupled reduce the total number of elements in large systems, being radiation - distortion, full length-scaling is possible. Simulation equivalent, from the radiative point of view only, to a local approach, methods and facilities for solar radiation characteristics; albedo without however any arbitrary substructure isolation. and Earth radiation; vacuum; heat sink; and spacecraft mounting Author (ESA) are reviewed. Author (ESA)

29 04 STRUCTURAL AND THERMAL ANALYSIS

W84-21626# Deutsche Forschungs- und Versuchsanstalt fuer reported. Specimens 15 mm wide and 250, 300, or 400 mm long Luft- und Raumfahrt, Goettingen (West Germany). Inst. fuer with 8 or 16 laminations and different laminate layups were Aeroelastik. subjected to flexure-modulus and flexural-strength tests at DEVELOPMENT OF PROCEDURES FOR COMPONENT MODE excitation frequencies of 5-350 Hz and temperatures of 25-120 C SYNTHESIS Final Report in an environmental chamber at 0.001 tore. The results are A. BERTRAM and P. CONRAD Paris ESA 15 Mar. 1983 presented graphically. The frequency effect on the damping 163 p rets coefficient is found to be minimal, while a correlation between (Contract ESTEC-4350/80/NL-PP; DFVLR-232-11; stiffness factors (due to layup sequences) and damping and a DFVLR-3-719-101) significant increase in damping above 90 C are observed. (DFVLR-IB-232-82-C-09; ESA-CR(P)-1826) Avail: NTIS HC Glass-fiber damping coefficients are shown to be higher than those A08/MF A01 of carbon fibers overall. These results are in good agreement The requirements of a rational, cost effective component mode with numerical calculations based on classical laminate theory. synthesis were established by performing modal coupling analyses An analysis of the bounds on the complex viscoelastic moduli on a spacecraft model composed of two modules with a highly based on the correspondence principle is presented, and the redundant interface. Parameter studies defined criteria for the bounds calculated are compared to the measured values. T.K. selection of the most suitable mode sets, the definition of boundary conditions, the number of modes and the accuracy of the mathematical mass model. Finite element models of the actual structure were used. The studies reveal the dynamic behavior of a structure with complicated interfaces, and enable optimum test boundary conditions to be defined. Author (ESA) A84-11932 HARDWARE SIMULATION OF SPACECRAFT DYNAMICS AND CONTROL 05 K. REINEL (Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt, Oberpfaffenhofen, West Germany) IN: World STRUCTURAL DYNAMICS AND CONTROL Congress on System Simulation and Scientific Computation, 10th, Montreal, Canada, August 8-13, 1982, Proceedings. Volume 3 . Montreal, International Association for Mathematics and Computers Includes modeling, systems identification, attitude and control in Simulation, 1983, p. 210-212. refs techniques and systems, surface accuracy measurement and An overview is given of the hardware simulation activities of control techniques and systems, sensors, and actuators. the spaceflight dynamics section at the German Space Operation Center. Two simulation methods for spacecraft attitude control hardware are discussed. Air-bearing simulation is used mainly for A84-10956# verifying the spacecraft dynamics and for identifying the A METHODOLOGY TO INCLUDE STATIC AND KINETIC mathematical model of actuators and torque generators. It is noted FRICTION EFFECTS IN SPACE SHUTTLE PAYLOAD that disturbance torques in the laboratory and time-consuming TRANSIENT LOADS ANALYSIS adjustments of the platform limit the air-bearing simulation to small E. E. HENKEL, J. E. MISEL, and D. H. FREDERICK (Rockwell angle motion and preferably to tests that require the actuator International Corp., Shuttle Integration and Satellite Systems Div., hardware in the loop. The servo-driven motion simulator is Downey, CA) IN: Shuttle Environment and Operations Meeting, controlled by computer and readily allows changes in the spacecraft Washington, DC, October 31-November 2, 1983, Collection of configuration and the control system during the design and Technical Papers . New York, American Institute of Aeronautics development phases. System tests of the attitude determination and Astronautics, 1983, p. 171-177. refs control are therefore performed to advantage on the three-axes (AIAA PAPER 83-2654) motion simulator as soon as the actuators and the control torques This paper presents a methodology that includes both static can be modeled mathematically. Large angle motion is limited and kinetic friction effects for Space Shuttle payload transient only by the freedom of the gimbal system. C.R. loads. The methodology employs a residual flexibility correction to the normal modes of vibration. An alteration to the dynamic finite difference equations of motion is discussed which allows one to include friction effects at reasonable cost for large structural systems such as the Space Shuttle. Numerical results of an idealized and highly simplified structural transient response problem are included to demonstrate the completeness of the approach. A84-11933 The extension of the basic NASTRAN nonlinear methodology is ON MODELING AND SIMULATION OF THE DYNAMICS OF presented through several stages of development to the point TETHER CONNECTED SATELLITE SYSTEMS where constraint equations and residual flexibility effects are V. J. MODI (British Columbia, University, Vancouver, Canada), A. incorporated. It is shown how residual flexibilities improve the K. MISRA (McGill University, Montreal, Canada), and D. M. XU accuracy of the forced dynamic response for payloads mounted IN: World Congress on System Simulation and Scientific in the orbiter vehicle. Data are presented to demonstrate the Computation, 10th, Montreal, Canada, August 8-13, 1982, possible impact of transient friction loads to the payload designer. Proceedings. Volume 3 . Montreal, International Association for Author Mathematics and Computers in Simulation, 1983, p. 217-219. refs A84-11815# A general dynamical model for a system consisting of two TESTS AND PREDICTION OF COMPOSITE MATERIAL satellites connected by a tether is presented. Three dimensional VISCOELASTIC BEHAVIOUR FOR LARGE SPACE large rotational motion, longitudinal as well as transverse vibrations STRUCTURE of the tether treated as a continuum, eccentricity of the orbit and L B. CREMA, R. BARBONI, A. CASTELLANI (Roma, Universita, aerodynamic drag in a rotating oblate atmosphere are taken into Rome, Italy), and I. PERONI International Astronautical Federation, account. Equations of motion are obtained using a Lagrangian International Astronautical Congress, 34th, Budapest, Hungary, Oct. formulation. As the frequencies associated with rotational and 10-15, 1983. 13 p. refs vibrational motions differ by orders of magnitude. Gear's method (IAF PAPER 83-418) is used for numerical integration. Attention is focused on the Experimental and analytical investigations of the damping dynamics during retrieval of a subsatellite to the Shuttle and behavior of glass-fiber and carbon-fiber reinforced composites are schemes for successful retrieval are suggested. Author

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A84-11934 rotor's momentum escalates, a larger number of modes are required ATTITUDE CONTROL AND DYNAMICS OF THE SPACE to construct a truncated model having a prespecified accuracy. A OPERATIONS CENTER controller is designed on the basis of the 'minimum error excitation' G. C. MCGEE and A. M. ANDRONIKOU (Rockwell International approach, which is found to be almost as effective as an optimal Corp., Space Operations/Integration and Satellite Systems Div., state feedback controller. The destabilizing influence of the Downey, CA) IN: World Congress on System Simulation and truncated modes is exposed by utilizing the robustness inequalities Scientific Computation, 10th, Montreal, Canada, August 8-13, 1982, available in the literature. Author Proceedings. Volume 3 . Montreal, International Association for Mathematics and Computers in Simulation, 1983, p. 222-224. A84-12489# Attitude control of the Space Operations Center (SOC) when it TORQUE FROM SOLAR RADIATION PRESSURE GRADIENT is visited by the Shuttle orbiter has been studied in order to identify DURING ECLIPSE the constraining requirements. A computer simulation of spacecraft G. B. SINCARSIN and P. C. HUGHES (Toronto, University, Toronto, disturbances was employed as an important element of the study, Canada) Journal of Guidance, Control, and Dynamics (ISSN and time histories of control capabilities were developed. Results 0731-5090), vol. 6, Nov.-Dec. 1983, p. 511-517. Sponsorship: show that the propulsion and momentum storage requirements Natural Sciences and Engineering Research Council of Canada. are achievable without undue spacecraft design impact if the refs prescribed approaches are used. Author (Contract NSERC-A-4183) Previously cited in issue 20, p. 3159, Accession no. A84-11945 A82-40433 AGGREGATE MODELS FOR DISTRIBUTED PARAMETER SYSTEMS WITH APPLICATIONS TO FLEXIBLE AIR AND A84-13320 SPACECRAFT T. L. JOHNSON (Bolt Beranek and Newman, Inc., Cambridge, THE TOYSAT STRUCTURAL CONTROL EXPERIMENT MA) IN: World Congress on System Simulation and Scientific J. A. BREAKWELL (Lockheed Research Laboratories, Palo Alto, CA) and G. J. CHAMBERS (Lockheed Missiles and Space Co.. Computation, 10th, Montreal, Canada, August 8-13, 1982, Proceedings. Volume 3 . Montreal, International Association for Inc., Sunnyvale, CA) Journal of the Astronautical Sciences (ISSN Mathematics and Computers in Simulation, 1983, p. 365-367. 0021-9142), vol. 31, July-Sept. 1983, p. 441-454. Research refs supported by the Lockheed Independent Research and Development Program, refs Even though the method of aggregation based on sensor and actuator influences presented here has been developed with a The hardware setup and experimental results of the Toysat view to large space structure applications, it is of more general structural control experiment are described in this paper. The applicability. Unlike most aggregation methods, which attempt to experiment is designed to test theoretical analyses and hypotheses concerning the application of modern control methods to the control preserve the plant dynamics, the proposed method first attempts to preserve input-output coupling; in this way, the order of the of a flexible structure. Linear-quadratic-Gaussian (LOG) optimal reduced model is related to the sum of the number of synthetic estimation and control algorithms are tested on the experimental inputs and outputs, which is assumed to be much smaller than hardware and shown to have desirable stability properties and the order of the dynamics. Although general guidelines for controller reasonable robustness characteristics. Author design compatibility with the method are given, the aggregation method is not restricted to any particular control design algorithm. A84-13321 One important property is that the effect of model truncation can A HARDWARE DEMONSTRATION OF CONTROL FOR A be precalculated independently of the feedback gains employed FLEXIBLE OFFSET-FEED ANTENNA in the controller. Results are presented for general linear R. D. BAULDRY, G. J. CHAMBERS, K. F. JOHANSEN, N. C. time-invariant multivariable systems, and a description is given of NGUYEN (Lockheed Missiles and Space Co., Inc., Sunnyvale, CA), further results that can be obtained specifically for structural J. A. BREAKWELL, and D. B. SCHAECHTER (Lockheed Research models. C.R. Laboratories, Palo Alto, CA) Journal of the Astronautical Sciences (ISSN 0021-9142), vol. 31, July-Sept. 1983, p. 455-470. Research A84-12483# supported by the Lockheed Independent Research and SATELLITE ATTITUDE DYNAMICS AND CONTROL IN THE Development Program. PRESENCE OF ENVIRONMENTAL TORQUES - A BRIEF A hardware model of a flexible offset-feed antenna has been SURVEY constructed in the laboratory in order to validate the applicability S. K. SHRIVASTAVA (British Columbia, University, Vancouver, of modern control theory to the control of flexible structures Canada) and V. J. MODI (Indian Institute of Science, Bangalore, involving realistic space hardware. In the model, principal control India) Journal of Guidance, Control, and Dynamics (ISSN actuation is provided by a cluster of three control-moment gyros; 0731-5090), vol. 6, Nov.-Dec. 1983, p. 461-471. refs sensing is provided by three rate-gyros, ten distributed Previously cited in issue 20, p. 3157, Accession no. accelerometers, and two laser attitude sensing devices. Optimal A82-40002 estimation algorithms and optimal control laws have been successfully implemented with an array processor to control this A84-12488# multi-input, multi-output, high-order system. The laboratory DYNAMICS AND CONTROL OF A DEFORMABLE GYROSTAT, hardware, the dynamics of the antenna, and the control approach UTILIZING CONTINUUM VEHICLE MODES used are discussed in detail, and recent closed-loop control results H. B. HABLANI (Rockwell International Corp., Seal Beach, CA) are reported. V.L. Journal of Guidance, Control, and Dynamics (ISSN 0731-5090), vol. 6, Nov.-Dec. 1983, p. 499-510. Research supported by the A84-15785 U.S. National Research Council, refs GEODETIC CONTROL OF THE REFLECTORS OF LARGE The paper deals with dynamics of a specific gyroscopic flexible ANTENNAS [GEODEZICHESKII KONTROL' REFLEKTOROV spacecraft and with synthesis of its controller. The infinite number BOL'SHIKH ANTENN] of associated gyroscopic modes are shown to have alternately a G. A. TEREKHOVA Geodeziia i Kartografiia (ISSN 0016-7126), precession parallel and antiparallel to the stored momentum. Sept. 1983, p. 12-17. In Russian, refs Dependence of mode shapes on the rotor's momentum is Attention is given to the precise geodetic control and adjustment investigated. Identities based on the vehicle's momentum and of large-antenna reflectors intended for radio astronomy and space inertia considerations are devised. The stochastic response analysis communications. A number of control methods are examined, with of the spacecraft subject to arbitrary excitation permits a 'modal attention given to hardware realizations, main characteristics, and cost analysis' of the vehicle. These developments show that, as practical applications. B.J.

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A84-16885 A84-17369# INSTABILITY ANALYSIS OF SPACE TRUSSES A FLEXIBLE STRUCTURE CONTROLLER DESIGN METHOD A. K. NOOR and J. M. PETERS (George Washington University, USING MODE RESIDUALIZATION AND OUTPUT FEEDBACK Hampton, VA) Computer Methods in Applied Mechanics and J. A. BOSSI (Washington, University, Seattle, WA) and G. A. PRICE Engineering (ISSN 0045-7825), vol. 40, Oct. 1983, p. 199-218. (Boeing Aerospace Co., Seattle, WA) (Guidance and Control refs Conference, San Diego, CA, August 9-11, 1982, Collection of Reduction methods and computational procedures are Technical Papers, p. 388-393) Journal of Guidance, Control, and presented for the instability analysis of space trusses with both Dynamics (ISSN 0731-5090), vol. 7, Jan.-Feb. 1984, p. 125-127. geometric and material nonlinearities subjected to combined loads. refs A mixed formulation is used with the fundamental unknowns Previously cited in issue 19, p. 2997, Accession no. consisting of both the member forces and the joint displacements. A82-38966 The governing equations of the truss consist of the two sets of member constitutive relations and joint equilibrium equations. The A84-17370# vector of fundamental unknowns is expressed as a linear COMMENTS ON 'DYNAMICS OF A SPACECRAFT DURING combination of a small number of path derivatives (derivatives of EXTENSION OF FLEXIBLE APPENDAGES' nodal displacements and member forces with respect to path M. S. JANKOVIC (Dome Petroleum, Ltd., Calgary, Alberta, parameters), and a Bubnov-Galerkin technique is used to Canada) Journal of Guidance, Control, and Dynamics (ISSN approximate the governing equations by a small system of algebraic 0731-5090), vol. 7, Jan.-Feb. 1984, p. 128. equations. The reduced equations are then used to determine the stability boundary and trace the nonlinear equilibrium paths. The A84-17854# potential of the proposed approach is discussed and its ON THE DYNAMICS OF A SUBSATELLITE SYSTEM effectiveness is demonstrated by means of numerical examples SUPPORTED BY TWO TETHERS of space trusses with combined geometric and material A. K. MISRA and G. S. DIAMOND (McGill University, Montreal, nonlinearities. The constitutive relations in these examples are Canada) American Institute of Aeronautics and Astronautics, assumed, for convenience, to be represented by Ramberg-Osgood Aerospace Sciences Meeting, 22nd, Reno, NV, Jan. 9-12, 1984. 6 polynomials. Author p. (AIAA PAPER 84-0062) The dynamics of a subsatellite system connected to a main orbiter by two extensible but massless tethers is studied. The points of attachment of these two tethers are offset from the A84-17355*# Jet Propulsion Lab., California Inst. of Tech., centre of mass of the orbiter. Both constant length and retrieval Pasadena. cases are considered. Lagrangian formulation for constrained SCIENCE PLATFORM AND ATTITUDE SUBSYSTEM IN-FLIGHT systems is used to derive the nonlinear equations of motion. These CALIBRATION FOR THE GALILEO SPACECRAFT along with the constraint equations are solved numerically. It is S. A. HAYATI and J. Y. LAI (California Institute of Technology, .noted that the rotational motion in the plane of the attachment Jet Propulsion Laboratory, Pasadena, CA) (Guidance and Control points can be damped quite effectively using a simple control Conference, Albuquerque, NM, August 19-21, 1981, Collection of scheme. Comparisons are made with the single tether case. A Technical Papers, p. 500-512) Journal of Guidance, Control, and two tether system has superior rotational behaviour, but seems to Dynamics (ISSN 0731-5090), vol. 7, Jan.-Feb. 1984, p. 29-35. have disadvantages as far as longitudinal oscillations are NASA-supported research. concerned. Author Previously cited in issue 21, p. 3640, Accession no. A81-44136 A84-17866# CONTROL OF LARGE SPACE STRUCTURES W. J. JASPER (Hughes Aircraft Co., Space and Communications Group, El Segundo, CA) American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting, 22nd, Reno, NV, Jan. 9-12, 1984. 5 p. A84-17359# (AIAA PAPER 84-0081) SEMIAUTONOMOUS STATIONKEEPING OF In the presence of disturbances, large flexible space structures GEOSYNCHRONOUS SATELLITES will exhibit excessive vibration which, in the case of a space C. C. CHAO (Aerospace Corp., Astrodynamics Dept., El Segundo, antenna, will degrade its pointing and focusing abilities. A velocity CA) Journal of Guidance, Control, and Dynamics (ISSN output feedback control system will augment damping to selected 0731-5090), vol. 7, Jan.-Feb. 1984, p. 57-61. Research sponsored modes of vibration. The performance of the design derived from by the Aerospace Corp. refs a reduced order model is degraded when evaluated on a higher (Contract F04701-82-C-0083) order model. This paper addresses this problem, and discusses a Previously cited in issue 19, p. 2992, Accession no. way to minimize performance degradation due to unmodelled A82-38883 dynamics. A numerical example is then given. Author

A84-18060# AEROELASTIC STABILITY AND RESPONSE OF FLEXIBLE TACTICAL WEAPONS A84-17361*# Jet Propulsion Lab., California Inst. of Tech., P. CRIMI (Avco Corp., Avco Systems Div., Wilmington, MA) Pasadena. American Institute of Aeronautics and Astronautics, Aerospace DYNAMICS AND CONTROL OF A LARGE SPACE ANTENNA Sciences Meeting, 22nd, Reno, NV, Jan. 9-12, 1984. 9 p. refs S. J. WANG and J. M. CAMERON (California Institute of (AIAA PAPER 84-0392) Technology, Jet Propulsion Laboratory, Control and Energy Static and dynamic aeroelastic characteristics of flexible tactical Conversion Div., Pasadena, CA) (Guidance and Control weapons are investigated analytically. Formulation of the static Conference, San Diego, CA, August 9-11, 1982, Collection of problem uses finite beam elements to model the vehicle and local Technical Papers, p. 394-402) Journal of Guidance, Control, and linearization to represent the aerodynamic loading. Analyses of a Dynamics (ISSN 0731-5090), vol. 7, Jan.-Feb. 1984, p. 69-76. representative configuration define the effects of bending stiffness, NASA-supported research, refs spin rate and dynamic pressure on divergence and static Previously cited in issue 19, p. 2997, Accession no. longitudinal stability. The dynamic problem is formulated in A82-38967 body-fixed coordinates using complex variables. Effects of velocity,

32 05 STRUCTURAL DYNAMICS AND CONTROL spin rate and bending frequency on dynamic response and flutter the form of a rigid central section with two flexible solar panels are investigated. Author cantilevered from it C.R.

A84-18168# A84-19128 A DESIGN STRATEGY FOR MULTIPLE PAYLOAD POINTING NUMBER CRUNCHING ON THE ACOSS MODEL NO. 2 FROM A THREE AXIS STABILIZED SPACECRAFT R. GRAN and M. ROSSI (Grumman Aerospace Corp., Research J. R. VELMAN and W. L BURKETT, JR. (Hughes Aircraft Co., and Development Center, Bethpage, NY) IN: Conference on Los Angeles, CA) American Institute of Aeronautics and Decision and Control, 21st, Orlando, FL, December 8-10, 1982, Astronautics, Aerospace Sciences Meeting, 22nd, Reno, NV, Jan. Proceedings. Volume 2 . New York, Institute of Electrical and 9-12, 1984. 8 p. Electronics Engineers, 1982, p. 909-911. (AIAA PAPER 84-0566) The spacecraft model called ACOSS Model Number 2 was When multiple articulated payloads are carried on a spacecraft, used to develop a control system design for large space structures each payload may have separate pointing performance that have certain desirable characteristics. To achieve these requirements on agility, accuracy, and pointing stability. By using characteristics, the control design approach used here is based synergetic combinations of sensors and actuators, the controller on an optimal reduced order control design technique that explicitly design for each loop may be nearly decoupled from the remaining computes the minimum of an expected quadratic cost function loop designs. The physical rational of the decoupling approach is using a numerical search algorithm. The algorithm, developed by given, and its power is demonstrated by the performance of a Rossi (1972), uses an explicit calculation of the gradient and sample design. The example includes the effects of actuator Hessian tensors to guide a second order search. The algorithm imperfections and non-linearities, and many flexible modes. The and the 'number crunching' on the ACOSS model are both approach provides a simple direct means of designing multtvariable described. Author controllers tailored to mission requirements. Author A84-19675# A84-19056* Rensselaer Polytechnic Inst., Troy, N. Y. ATTITUDE STABILITY FOR THE YAW-WHEEL CLASS OF THE SPATIAL ORDER REDUCTION PROBLEM AND ITS EFFECT ORBITING GYROSTATS ON ADAPTIVE CONTROL OF DISTRIBUTED PARAMETER P. C. HUGHES (Toronto, University, Toronto, Canada) Canadian SYSTEMS Aeronautics and Space Journal (ISSN 0008-2821), vol. 29, Sept. M. J. BALAS (Rensselaer Polytechnic Institute, Troy, NY) IN: 1983, p. 268-281. Research supported by the Natural Science Conference on Decision and Control, 21 st, Orlando, FL, December and Engineering Research Council of Canada, refs 8-10,1982, Proceedings. Volume 1 . New York, Institute of Electrical Motivated by the attitude stabilization of large, multibeam and Electronics Engineers, 1982, p. 30-32. refs communcations satellites, the neoclassical problem of a rigid (Contract NSF ECS-80-16173; NAG1-171) gyrostat in a circular orbit is considered. It is shown that the inclusion of a yaw wheel into the design can lead to a steady A84-19118 gyroscopic torque that is equal and opposite to the steady MULTIVARIABLE DIRECT ADAPTIVE CONTROL FOR A gravity-gradient external torque about the roll axis. This particular GENERAL CLASS OF TIME-VARYING COMMANDS class of gyrostat equilibrium has not previously been studied in I. BAR-KAMA and H. KAUFMAN (Rensselaer Polytechnic Institute, detail. Representative stability diagrams are presented which show Troy, NY) IN: Conference on Decision and Control, 21st, Orlando, that most (but not all) such equilibria are unstable. Author FL, December 8-10, 1982, Proceedings. Volume 2 . New York, Institute of Electrical and Electronics Engineers, 1982, p. 750, A84-19728 751. refs PERIODIC OSCILLATIONS OF A GYROSTAT SATELLITE WITH (Contract NSF ECS-80-16173) RESPECT TO THE CENTERS OF MASS IN A CIRCULAR ORBIT Direct multivariable model reference adaptive control [PERIODICHESKIE KOLEBANIIA SPUTNIKA-GIROSTATA (DMMRAC) procedures which are especially suitable for large scale OTNOSITEL'NO TSENTRA MASS NA KRUGOVOI ORBITE] structures (LSS) were in the past shown to be feasible provided V. V. SAZONOV Kosmicheskie Issledovaniia (ISSN 0023-4206), that the input commands were constant. In this paper the feasibility vol. 21, Nov.-Dec. 1983, p. 838-850. In Russian, refs of the MMRAC algorithms is extended to a large class of The system of differential equations of motion of a gyrostat time-variable input commands. Author satellite with respect to the center of mass under the effect of gravity moment in circular orbit is considered. It is assumed that A84-19127 the intrinsic kinetic moment of the gyrostat is large and that the A LARGE SPACE STRUCTURE BENCHMARK PROBLEM - system contains a large parameter. A search is made for symmetric ACOSS MODEL NO. 2 periodic solutions of this system, close to the periodic solutions T. C. HENDERSON (Charles Stark Draper Labortory, Inc., of a degenerate system, obtained from the initial system when Cambridge, MA) IN: Conference on Decision and Control, 21st, the large parameter is equal to infinity. The solutions are obtained Orlando, FL, December 8-10, 1982, Proceedings. Volume 2 . New in formal series in whole negative powers of the large parameter, York, Institute of Electrical and Electronics Engineers, 1982, p. and are analyzed numerically. B.J. 905-908. Attention is called to the need for a universal system model in A84-20047# order to assess the performance, sensitivity, and hardware DETERMINATION OF CRITICAL PARAMETERS IN LARGE requirements of the various active structural control methods being FLEXIBLE SPACE STRUCTURES WITH UNCERTAIN MODAL developed. The design of the model described here, ACOSS Model DATA No. 2 (ACOSS denoting active control of large space structures), R. K. YEDAVALLI (Stevens Institute of Technology, Hoboken, NJ) incorporates certain desired features into the overall system and R. E. SKELTON (Purdue University, West Lafayette, IN) characteristics. The structural design is based on realistic sizes ASME, Transactions, Journal of Dynamic Systems, Measurement, and weights, and the model has a simple unclassified optical system and Control (ISSN 0022-0434), vol. 105, Dec. 1983, p. 238-244. with associated performance measures and tolerances. It also has refs a set of disturbances that are typical of equipment vibration and This paper addresses the problem of control design for large attitude control. The model comprises two subsystems: an optical flexible space structures with uncertain modal data. The concepts support structure and an equipment section. These are connected of modal cost analysis are applied to flexible space structures by springs at three points, allowing either passive or active vibration with these uncertain parameters: modal damping, modal isolation. The optical support structure contains four optical frequencies, and mode shapes at actuator (sensor) locations. A surfaces that are assumed to be rigid and kinematically mounted quadratic function of displacements and displacement rates is used on the structure, it is assumed that the equipment section takes as a performance metric. In this case, it is possible to obtain

33 05 STRUCTURAL DYNAMICS AND CONTROL explicit formulas for the cost contributions labeled 'modal costs' A84-24991*# RCA Astro-Electronics Div., Princeton, N. J. and 'parameter costs.' This type of cost decomposition analysis A DEGREE OF CONTROLLABILITY DEFINITION - by which one can determine the significant modes and parameters FUNDAMENTAL CONCEPTS AND APPLICATION TO MODAL can be useful in model reduction, parameter estimation, and SYSTEMS structure redesign. The proposed technique is applied to the C. N. VISWANATHAN (RCA, Astro-Electronics Div., Princeton, NJ), 'Purdue Model,' a generic model for a two-dimensional flexible R. W. LONGMAN (Columbia University, New York, NY), and P. structure. Author W. LIKINS (Lehigh University, Bethlehem, PA) Journal of Guidance, Control, and Dynamics (ISSN 0731-5090), vol. 7, Mar.-Apr. 1984, p. 222-230. refs (Contract NAS8-32212) Starting from basic physical considerations, this paper develops A84-21237 a concept of the degree of controllability of a control system, and VIBRATION CHARACTERISTICS OF SELF-EXPANDING then develops numerical methods to generate approximate values STAYED COLUMNS FOR USE IN SPACE of the degree of controllability for any linear time-invariant system. J. R. BANERJEE and F. W. WILLIAMS (University of Wales Institute In many problems, such as the control of future, very large, flexible of Science and Technology, Cardiff, Wales) Journal of Sound spacecraft and certain chemical process control problems, the and Vibration (ISSN 0022-460X), vol. 90, Sept. 22,1983, p. 245-261. question of how to choose the number and locations of the control Research supported by the Science and Engineering Research system actuators is an important one. The results obtained here Council, refs offer the control system designer a tool which allows him to rank Reference is made to the report by Belvin (1982) which the effectiveness of alternative actuator distributions, and hence presented experimental and theoretical results obtained at NASA to choose the actuator locations on a rational basis. The degree for the free vibration of a stayed column. Exact theoretical results of controllability is shown to take a particularly simple form when are given here, including natural frequencies and mode types not the dynamic equations of a satellite are in second-order modal given in the NASA results. A substitute column method is employed form. The degree of controllability concept has still other to achieve economy and a much deeper understanding of the fundamental uses - it allows one to study the system structural modes. An alternative design is proposed which implements recent relations between the various inputs and outputs of a linear system, developments in the design method and has a graphite epoxy which has applications to decoupling and model reduction. core. The proposed design has the advantage that its stay Author dominated frequencies are higher than those for the NASA column. C.R. A84-24995# IDENTIFICATION OF LARGE FLEXIBLE STRUCTURES MASS/STIFFNESS AND DAMPING FROM ON-ORBIT EXPERIMENTS S. L. HENDRICKS, S. RAJARAM, M. P. KAMAT, and J. L. JUNKINS A84-21285# (Virginia Polytechnic Institute and State University, Blacksburg, TRANSIENT DYNAMICS DURING THE ORBITER BASED VA) Journal of Guidance, Control, and Dynamics (ISSN DEPLOYMENT OF FLEXIBLE MEMBERS 0731-5090), vol. 7, Mar.-Apr. 1984, p. 244, 245. V. J. MODI (British Columbia, University, Vancouver, Canada) and Previously cited in issue 19, p. 2993, Accession no. A. M. IBRAHIM American Institute of Aeronautics and Astronautics, A82-38859 Aerospace Sciences Meeting, 22nd, Reno, NV, Jan. 9-12, 1984. 11 p. refs A84-25291# (AIAA PAPER 84-0061) EVOLUTION OF EUROPEAN TELECOMMUNICATION The paper presents a general formulation for studying librational SATELLITE POINTING PERFORMANCE dynamics of a large class of spacecraft during deployment of N. BINGHAM, A. D. CRAIG, and L FLOOK (British Aerospace flexible members. It is applicable to a variety of mission ranging PLC, Dynamics Group, Stevehage, Herts., England) IN: from deployment of antennas, booms and solar panels to Communication Satellite Systems Conference, 10th, Orlando, FL, manufacturing of trusses for space platforms using the Space March 19-22, 1984, Technical Papers . New York, American Shuttle. The governing nonlinear, nonautonomous and coupled Institute of Aeronautics and Astronautics, 1984, p. 336-344. refs equations of motion are extremely difficult to solve even with the (AIAA PAPER 84-0725) help of a computer, not to mention the cost involved. To get The pointing performance of a range of European some appreciation as to the complex interactions between flexibility, communications satellite projects is reviewed. The main factors deployment and attitude dynamics as well as to help pursue stability contributing to the overall beam pointing error are discussed, and control analysis, the equations are linearized about their emphasizing the satellite attitude error. Attitude control concepts nominal deflected equilibrium configuration. The procedure is adopted for ESA satellites are addressed, discussing the reasons applied to the Space Shuttle based deployment of plate-like for the choices and describing the systems in terms of hardware members. Results suggest substantial influence of the inertia and control algorithms. The discussion is limited to on-station parameter, flexural rigidity of the appendages, orbit eccentricity, modes. Finally, the improvement achievable in beam pointing by deployment velocity, initial conditions, etc. on the system response. using an RF sensor/antenna-pointing mechanism control loop is This would indicate additional demand on the orbiter's control considered. C.D. system during construction of space-platforms. . Author A84-25496* Rensselaer Polytechnic Inst., Troy, N. Y. SOME APPLICATIONS OF DIRECT ADAPTIVE CONTROL TO LARGE STRUCTURAL SYSTEMS I. BAR-KANA and H. KAUFMAN (Rennselaer Polytechnic Institute, A84-24990# Troy, NY) IN: American Control Conference, San Francisco, CA, ON THE NUMBER AND PLACEMENT OF ACTUATORS FOR June 22-24, 1983, Proceedings. Volume 2 . New York, Institute of INDEPENDENT MODAL SPACE CONTROL Electrical and Electronics Engineers, 1983, p. 573, 574. R. E. LINDBERG, JR. (U.S. Navy, Naval Research Laboratory, (Contract NSF ECS-80-16173; NAG1-171) Washington, DC) and R. W. LONGMAN (Columbia University, New Direct multivariable model reference adaptive control York, NY) Journal of Guidance, Control, and Dynamics (ISSN (DMMRAC) applications are considered with a representative 0731-5090), vol. 7, Mar.-Apr. 1984, p. 215-221. refs example of a large structural system (LSS). Such applications have Previously cited in issue 19, p. 2994, Accession no. in the past been shown to be feasible for multivariable systems, A82-38874 provided that there exists a constant feedback gain matrix such

34 05 STRUCTURAL DYNAMICS AND CONTROL

that the resulting input-output transfer function is (simply) positive A84-26717 real. Author A SIMULATOR TO STUDY DYNAMIC INTERACTION OF THE SPACE SHUTTLE ON-ORBIT FLIGHT CONTROL SYSTEM WITH DEPLOYED FLEXIBLE PAYLOADS S. S. DAVID and L L. SACKETT (Charles Stark Draper Laboratory, A84-25516 Inc., Cambridge, MA) IN: Digital Avionics Systems Conference, CONTROLLABILITY AND OBSERVABILITY CRITERIA FOR 5th, Seattle, WA, October 31-November 3, 1983, Proceedings . MULTIVARIABLE LINEAR SECOND-ORDER MODELS New York, Institute of Electrical and Electronics Engineers, 1983, A. J. LAUB (Southern California, University, Los Angeles, CA) and p. 5.3.1-5.3.9. refs W. F. ARNOLD (U.S. Naval Weapons Center, China Lake, CA) A series of studies was undertaken to investigate the effects IN: American Control Conference, San Francisco, CA, June 22-24, of the Space Shuttle's on-orbit flight control system (FCS) 1983, Proceedings. Volume 3 . New York, Institute of Electrical dynamically interacting with the Orbiter and deployed flexible and Electronics Engineers, 1983, p. 925, 926. refs payloads. In order to support these studies, an existing digital (Contract DAAG29-81-K-0131) simulator was modified to include elastic body effects and finite Criteria are discussed for the determination of controllability, element modal parameters. The simulator provides a closed-loop stabilizability, observability, or detectability of linear second-order simulation of the flight software interacting with detailed models multivariable models of, for example, large space structures. An of the Shuttle vehicle and flight environment. The simulator and initial modal transformation is not required and the criteria are the modifications implemented to support these studies are thus applicable to models with arbitrary damping coefficients. described. Assumptions, design considerations, features, and Moreover, the criteria are modal in the sense that some or all of limitations are discussed. Recent studies, where dynamic the modes may be tested for controllability or observability. This interactions between the Orbiter/FCS and deployed payloads were aspect has advantages if not all the modes are known or easily examined, illustrate the use of the simulator's range of model computable. The criteria are further illustrated for a number of fidelity and diagnostic capability. Author important special cases in a series of corollaries. Author A84-26845 STABILITY OF LARGE FLEXIBLE DAMPED SPACECRAFT MODELED AS ELASTIC CONTINUA A84-25552* Jet Propulsion Lab., California Inst. of Tech., P. K. MAHARANA and S. K. SHRIVASTAVA (Indian Institute of Pasadena. Science, Bangalore, India) Acta Astronautica (ISSN 0094-5765), USE OF ELECTROMAGNETIC MODELS IN THE OPTIMAL vol. 11, Feb. 1984, p. 103-109. refs CONTROL OF LARGE SPACE ANTENNAS Vibrational stability of a large flexible, structurally damped F. MANSHADI and M. HAMIDI (California Institute of Technology, spacecraft subject to large rigid body rotations is analyzed modeling Jet Propulsion Laboratory, Pasadena, CA) IN: American Control the system as an elastic continuum. Using solution of rigid body Conference, San Francisco, CA, June 22-24, 1983, Proceedings. attitude motion under torque free conditions and modal analysis, Volume 3 . New York, Institute of Electrical and Electronics the vibrational equations are reduced to ordinary differential Engineers, 1983, p. 1317-1323. NASA-supported research, refs equations with time-varying coefficients. Stability analysis is carried A general approach to the optimal control of large space out using Floquet theory and Sonin-Polya theorem. The cases of antennas based on their RF/structural characteristics is described. spinning and non-spinning spacecraft idealized as a flexible The approach consists of defining a cost functional based on the beam/plate undergoing simple structural vibration are analyzed in degradation of the RF performance of the antenna and using the detail. The critical damping required for stabilizatioon is shown to structural model as the dynamic system. The method is applied be a function of the spacecraft's inertia radio and the level of to the design of an optimal controller for a 55-m, wrap-rib offset-fed disturbance. Author antenna. Simulation results show that control energy consumption is reduced to aproximately one third of the energy used to achieve A84-26977 the same RF performance with traditional control strategies. MOTION OF A SYMMETRIC SATELLITE ABOUT THE CENTER Author OF MASS IN CIRCULAR ORBIT IN THE PRESENCE OF FLEXIBLE VISCOELASTIC RODS [DVIZHENIE SIMMETRICHNOGO SPUTNIKA VOKRUG TSENTRA MASS NA KRUGOVOI ORBITE PRI NALICHII GIBKIKH VIAZKOUPRUGIKH A84-25586 STERZHNEI] NUMERICAL SOLUTION OF SEVERAL CLASSES OF N. E. BOLOTINA and V. G. VILKE Kosmicheskie Issledovaniia NONLINEAR FLEXIBLE SHELL THEORY PROBLEMS (ISSN 0023-4206), vol. 22, Jan.-Feb. 1984, p. 13-19. In Russian. [CHISLENNOE RESHENIE NEKOTORYKH KLASSOV An averaging method in canonical variables is used to obtain NELINEINYKH ZADACH TEORII GIBKIKH OBOLOCHEK] approximate equations describing the evolution of the rotational IA. M. GRIGORENKO (Akademiia Nauk Ukrainskoi SSR, Institut motion of a symmetric satellite with two flexible viscoelastic rods. Mekhaniki, Kiev, Ukrainian SSR) Vychislitel'naia i Prikladnaia The solution obtained corresponds to the rotation of the satellite Matematika (ISSN 0321-4117), no. 50, 1983, p. 73-83. In about the symmetry axis, which coincides with the normal to the Russian, refs orbit; since the satellite is symmetric, its angular velocity does not Approaches to the solution of nonlinear boundary-value have to coincide with the orbital angular velocity. In the problems describing the stress-strained state of several classes approximation considered, the rods remain rectilinear and there is of thin flexible multilayered shells with orthotropic plies of variable no energy dissipation. B.J. thickness are presented. The solution of one-dimensional nonlinear boundary-value problems for deformations in the subcritical region A84-27934*# Indian Inst. of Science, Bangalore. is obtained by linearization, reduction to 'a system of nonlinear CONTROL STRUCTURE INTERACTIONS IN LARGE SPACE equations and a Cauchy problem, and solution continuation by STRUCTURES ANALYSIS USING ENERGY APPROACH parameter. A modification of the method of reduction to nonlinear S. K. SHRIVASTAVA (Indian Institute of Science, Bangalore, India), equations and a Cauchy problem is used to solve one-dimensional R. C. RIED (NASA, Johnson Space Center, Structures and problems of nonlinear deformation in supercritical regions. Mechanics Div., Houston, TX), and M. G. MANOHARAN Two-dimensional problems of nonaxisymmetric deformation of Aeronautical Society of India, Journal (ISSN 0001-9267), vol. 35, shells of revolution with variable rigidity are considered. The results May 1983, p. 59-67. Research supported by the U.S. National of solutions of nonlinear problems for axisymmetric deformations Research Council, refs of conical and ellipsoidal shells and for asymmetric deformations A simple energy approach to study the problem of control of spherical shells are presented. J.N. structure interactions in large space structures is presented. For

35 05 STRUCTURAL DYNAMICS AND CONTROL the illustrative cases of free-free beam and free rectangular plate, demonstrated. Results include control maneuvers from one state the vibrational energy imparted during operation of constant and to another such as rest to rest and spin to rest, which effectively pulsed thrusters is found in a nondimensional form. Then based justify the 'solutions developed in this paper. Author on a parametric study, suggestions are made on the choice of the thruster location and parameters to minimize the control structure interactions. Author N84-10173*# Howard Univ., Washington, D. C. A84-29143# THE DYNAMICS AND CONTROL OF LARGE FLEXIBLE SPACE ON TRANSIENT DYNAMICS AND STABILITY OF LARGE SPACE STRUCTURES, 6 Final Report STRUCTURES P. M. BAINUM Sep. 1983 101 p refs V. J. MODI (British Columbia, University, Vancouver, Canada) IN: (Contract NSG-1414) U.S. National Congress of Applied Mechanics, 9th, Ithaca, NY, (NASA-CR-174450; NAS 1.26:174450) Avail: NTIS HC A06/MF June 21-25, 1982, Proceedings . New York, American Society of A01 CSCL 22B Mechanical Engineers, 1982, p. 249-258. Sponsorship: Natural The controls analysis based on a truncated finite element model Sciences and Engineering Research Council of Canada, refs of the 122m. Hoop/Column Antenna System focuses on an analysis (Contract NSERC-A-2181; NSERC-G-0662; NSERC-A-0967) of the controllability as well as the synthesis of control laws. Graph Results of a study aimed at assessing dynamical response theoretic techniques are employed to consider controllability for and stability of orbiting spacecraft during deployment and/or different combinations of number and locations of actuators. Control retrieval of mass elements leading to time dependent inertias are law synthesis is based on an application of the linear regulator presented. In particular two classes of problems are discussed: theory as well as pole placement techniques. Placement of an (1) flexible beam type appendages such as solar panels, antennas, actuator on the hoop can result in a noticeable improvement in preassembled trusses, etc., deploying from a space platform in the transient characteristics. The problem of orientation and shape an orbit; and (2) Space Shuttle-based tethered systems. The study control of an orbiting flexible beam, previously examined, is now suggests that with critical combinations of parameters the systems extended to include the influence of solar radiation environmental can become unstable; however, suitable control strategies are forces. For extremely flexible thin structures modification of control available which can restore stability. The analysis is relevant to laws may be required and techniques for accomplishing this are construction of the proposed Space Operations Center (SOC), explained. Effects of environmental torques are also included in tethered rescue systems, retrieval of satellites for servicing, previously developed models of orbiting flexible thin platforms. repositioning of space platform based telescopes, and similar B.W. situations involving interactions between transient inertias, flexibility, and system response. Author N84-11195# RAND Corp., Santa Monica, Calif. A84-29145# THE FLEXURAL BEHAVIOR OF PACSAT (PASSIVE MULTIBODY DYNAMICS - ANALYSIS OF FLEXIBILITY COMMUNICATION SATELLITE) IN ORBIT Interim Report EFFECTS W. SOLLFREY Feb. 1983 131 p refs R. L HUSTON (Cincinnati, University, Cincinnati, OH) IN: U.S. (Contract MDA903-82-C-0068; ARPA ORDER 3584-7) National Congress of Applied Mechanics, 9th, Ithaca, NY, June (AD-A131406; RAND/R-2936-ARPA; LC-83-570; 21-25, 1982, Proceedings . New York, American Society of ISBN-0-8330-0490-5) Avail: NTIS HC A07/MF A01 CSCL 22B Mechanical Engineers, 1982, p. 265-271. refs This report presents an analysis of the libration and vibration (Contract N00014-76-C-0139; NSF MEA-81-01110) of a passive communications satellite known as PACSAT. It (AD-A132533) addresses the effects of various disturbing mechanical forces on This paper discusses flexibility effects in multibody systems. It verticality and straightness. Phenomena considered include orbital presents a procedure for the efficient analysis of these effects in ellipticity, earth oblateness, solar and lunar gravity, radiation large systems containing many bodies. This procedure uses Kane's pressure, micrometeorial impacts, and thermal bending effects. dynamical equations, Euler parameters, generalized speeds, The last two are the most important. It is concluded that the relative coordinates, finite-segment modelling, and matrix-structural flexural misbehavior of PACSAT in orbit is such that it is most methods. It is a computer-oriented method with the governing improbable that the present design (unsupported linear array) can equations written in algorithmic form. The procedure is applicable perform its communications functions. Author (GRA) with multibody systems consisting of linked bodies in an 'open-tree' structure. It has specific applications with robots, flexible manipulators, antennae, and human body models. Author N84-12222 Stanford Univ., Calif. A84-29471*# National Aeronautics and Space Administration. CONTROL OF FLEXIBLE SPACECRAFT BY OPTIMAL MODEL Langley Research Center, Hampton, Va. FOLLOWING Ph.D. Thesis CLOSED-FORM SOLUTIONS FOR FEEDBACK CONTROL WITH J. A. QUIRK 1983 244 p TERMINAL CONSTRAINTS Avail: Univ. Microfilms Order No. DA8307199 J.-N. JUANG (NASA, Langley Research Center, Hampton, VA), J. Spacecraft flexibility resulting from increased size and D. TURNER, and H. M. CHUN (Charles Stark Draper Laboratory, light-weight design techniques significantly increases the interaction Inc., Cambridge, MA) Virginia Polytechnic Institute and State between the structural bending modes and the vehicle control University and American Institute of Aeronautics and Astronautics, system. The subject of this thesis is the use of the unique properties Symposium on Dynamics and Control of Large Flexible Structures, of Optimal Model Following (OMF) to simplify the controller design 4th, Blacksburg, VA, June 6-8, 1983, Paper. 17 p. refs process for flexible spacecraft. Model following controllers force The problem of closed-loop control of maneuvers between two the plant states to follow the dynamics of a model which states for linear dynamical systems, subject to an arbitrarily incorporates the system performance specifications. OMF, model specified terminal state, is considered. The feedback controller following using a linear quadratic cost function, trades off the design is based on finite-time quadratic regulator theory. degree of dynamics matching with the control effort utilized. As Closed-form expressions for the optimal control law are developed. part of this thesis, an OMF controller design program was Solutions are presented for both conventional and smoothed developed. OMF controllers were designed for three examples: control profiles with fixed and/or free end condition problems. In altitude control of a flexible spacecraft, pointing of a camera the maneuvers using control-rate penalties, smooth profiles are package on a flexible appendage, and control of a spacecraft generated throughout the maneuvers, in the sense that the initial based on the Galileo vehicle. The performance characteristics of condition jump discontinuities have been eliminated. Several the OMF designs were compared to those of optimal controllers. examples involving large-angle maneuvers of a spacecraft are Dissert. Abstr.

36 05 STRUCTURAL DYNAMICS AND CONTROL

N84-12234*# National Aeronautics and Space Administration. Space Platform, either of the above IPACS concepts are Marshall Space Flight Center, Huntsville, Ala. adequate. E.A.K. SPACE STATION ATTITUDE CONTROL SYSTEM CONCEPT AND REQUIREMENTS N84-12243*# National Aeronautics and Space Administration. P. D. NICAISE In NASA. Langley Research Center Integrated Langley Research Center, Hampton, Va. Flywheel Technol., 1983 p 63-69 Dec. 1983 refs ADVANCED CONTROL AND POWER SYSTEM (ACAPS) Avail: NTIS HC A10/MF A01 CSCL 22B TECHNOLOGY PROGRAM There is currently no single Space Station configuration which C. R. KECKLER and N. J. GROOM In its Integrated Flywheel is accepted as a baseline. However, the latest approach is toward Technol., 1983 p 141-156 Dec. 1983 refs symmetry in both geometry and mass distribution. This minimizes Avail: NTIS HC A10/MF A01 CSCL 22B aerodynamic and gravity gradient torques. Solar arrays and The advanced control and power system (ACAPS) program is radiators drive the configuration strongly. One axis of the solar to establish the technology necessary to satisfy space station arrays needs to be perpendicular to the orbit plane, and the and related large space structures requirements for efficient, geometric and principal axis should remain common along this reliable, and cost effective energy storage and attitude control. axis to minimize secular torques. The need for both inertial and Technology advances in the area of integrated flywheel systems earth-fixed modes drives the structure of the Station toward a capable of performing the dual functions of energy storage and disk-like shape in the orbital plane. Author attitude control are outlined. E.A.K.

N84-12235*# National Aeronautics and Space Administration. N84-12245*# National Aeronautics and Space Administration. Lyndon B. Johnson Space Center, Houston, Tex. Marshall Space Flight Center, Huntsville, Ala. THE BOEING FLYWHEEL STUDY IPACS GUIDANCE NAVIGATION AND CONTROL SYSTEM R. R. RICE In NASA. Langley Research Center Integrated CONSIDERATIONS AND TEST ACTIVITIES Flywheel Technol., 1983 p 71-76 Dec. 1983 refs H. J. BUCHANAN In NASA. Langley Research Center Integrated Avail: NTIS HC A10/MF A01 CSCL 10C Flywheel Technol., 1983 p 165-168 Dec. 1983 The major features of the history of the Boeing flywheel were Avail: NTIS HC A10/MF A01 CSCL 17G studied. The analysis of the regenerative fuel cell was started as The MSFC facility proposed for the Space Station Attitude an outgrowth of the original Boeing study of the Space Operations Control Simulator which consists of a large three degree of freedom Center, and was completed in November 1982 with the publication table driven by computer controlled hydraulic actuators designed of the final report number D180-27160-1. The current flywheel to give high bandwidth and extremely fine control through large effort attempts to study the integrated flywheel using the same angles is outlined. The facility includes star and solar simulators ground rules that were used on the fuel cell study. Author providing collimated light with the spectral content and intensity typical of Earth orbit. E.A.K.

N84-12236*# National Aeronautics and Space Administration. N84-13608*# National Aeronautics and Space Administration. Lyndon B. Johnson Space Center, Houston, Tex. Langley Research Center, Hampton, Va. SPACE STATION CONTROL REQUIREMENTS AND FLYWHEEL STABILITY, VIBRATION AND PASSIVE DAMPING OF SYSTEM WEIGHTS FOR COMBINED MOMENTUM AND ENERGY PARTIALLY RESTRAINED IMPERFECT COLUMNS STORAGE Z. RAZZAQ, R. T. VOLAND, H. G. BUSH, and M. M. MIKULAS, F. M. ELAM In NASA. Langley Research Center Integrated JR. Oct. 1983 38 p refs Flywheel Technol., 1983 p 77-92 Dec. 1983 refs (NASA-TM-85697; NAS 1.15:85697) Avail: NTIS HC A03/MF Avail: NTIS HC A10/MF A01 CSCL 10C A01 CSCL 20K The specifications of the flywheel system for momentum storage A theoretical and experimental study of slender tubular columns and vehicle torquing are somewhat dependent upon the attitude for possible use in space structures is conducted in the presence control requirements of the space station in orbit. As a ground of partial rotational end restraints. Explicit formulas are derived rule, the flywheel system will be sized large enough to provide all for computing the buckling load and the lowest natural frequency attitude maneuvers, if practical, to avoid or minimize turning on of perfectly straight uniform elastic members with rotational end the reaction control system (RCS). The RCS, whenever used, restraints possessing linear moment-rotation characteristics. An expels expensive mass and tends to contaminate optical surfaces exact solution in the form of a transcendental equation, and a of the vehicle. The vehicle rate and acceleration specifications of numerical solution using second-order finite-differences are also 0.10 deg/sec and 0.01 deg/square sec are tentative, and may be presented. The presence of an initial imperfection is also reduced if lesser values are more practical for flywheel design. incorporated into the numerical procedure. Vibration tests are For local vertical attitude hold, the average attitude error should conducted on an imperfect tubular steel member in the absence be zero, and not the classical 1 degree, since control moment of an axial load. A damping concept consisting of a string-mass gyro (CMG) gimbal angles provide an exact reference feedback assembly is explored. Three passive damping configurations for gravity gradient momentum. Docking presents a problem for involving combinations of three lead shots were investigated. The docking transients and attitude alignment which will require use of three lead shot configurations provided considerably greater the RCS. Author damping than the single lead shot. Author

M84-12238*# National Aeronautics and Space Administration. N84-14235 California Univ., Los Angeles. Marshall Space Flight Center, Huntsville, Ala. ACTIVE CONTROL OF LARGE FLEXIBLE SPACE STRUCTURES IPACS ATTITUDE CONTROL TECHNOLOGY Ph.D. Thesis CONSIDERATIONS M. K. MACKAY 1983 260 p L. BRANDON In NASA. Langley Research Center Integrated Avail: Univ. Microfilms Order No. DA8314665 Flywheel Technol., 1983 p 99-104 Dec. 1983 The control of a large flexible space structure using a finite Avail: NTIS HC A10/MF A01 CSCL 22B number of controls and observations is considered. The control Larger facilities or the Space Station and its evolutionary problem is formulated as an optimal stochastic regulator. Various versions are considered for the control bandwidth which will evolve assumptions are made concerning the natural damping in the to lower values, probably in the 0.01 to 0.1 hertz range. An system. This leads to semigroup representations for the open loop integrated power attitude control systems (IPACS) unit that system which are uniformly exponentially stable and compact, incorporates conventional mechanical bearings to have a bandwidth uniformly exponentially stable and noncompact, strongly stable, of 4-10 hertz is expected. If the IPACS unit incorporates the and unitary (no natural damping). New sufficient conditions are advanced technology magnetic bearing, a bandwidth of 1.2 hertz given for the existence of a solution to the control problem for is expected. It is found that for the Space Station or even the the strongly stable and unitary cases. The solution to the control

37 05 STRUCTURAL DYNAMICS AND CONTROL problem is obtained in terms of the compensator, i.e., the optimal analyzed. Results show that the only suitable damping model is linear operator mapping the observations to the control. Both time the viscous damping model. For response analysis with adapted domain and frequency domain representations for the compensator modal viscous damping values the response of a structure may are given and its modal approximation is studied. The general be predicted with adequate accuracy if a derived coupling criteria theory is applied to a space structure modeled as a rigid central is not violated. Otherwise the response should be predicted with body with two flexible appendages (cantilevered beams). a corrective method or the exact analysis with complex Dissert. Abstr. eigenmodes. Damping prediction methods for system damping from substructure damping are far more sensitive to the damping N84-14546# Virginia Polytechnic Inst. and State Univ., Blacksburg. characteristics of the substructures than response analysis Dept. of Aerospace and Ocean Engineering. methods. Because of damping coupling effects nonproportional EXPERIMENTAL STUDY OF ACTIVE VIBRATION CONTROL damping characteristics have to be incorporated in these system Annual Report, 15 Mar. 1982-14 Mar. 1983 damping prediction methods. Damping estimation methods are not W. L HALLAUER, JR. 15 Apr. 1983 11 p adequate for damping prediction; system identification must be (Contract AF-AFOSR-0217-82; AF PROJ. 2307) applied. Differences between random and harmonic test methods (AD-A133818; AFOSR-83-0855TR) Avail: NTIS HCA02/MFA01 are treated and system identification with random response data CSCL 20K is discussed. Author (ESA) Control system hardware, including velocity sensors, force actuators, and analog circuitry, has been designed, fabricated, calibrated, and tested in operation. Active vibration control in the forms of direct-velocity-feedback control and modal-space control N84-15840 Rensselaer Polytechnic Inst., Troy, N. Y. has been implemented on a dynamically uncomplicated beam-cable DIRECT MULTIVARIABLE MODEL REFERENCE ADAPTIVE structure, and theorectical simulations of the structure-control CONTROL WITH APPLICATIONS TO LARGE STRUCTURAL dynamics have been completed. Either correlation between SYSTEMS Ph.D. Thesis experiment and theory has been satisfactory, or the reasons for I. BAR-KANA 1983 253 p unsatisfactory correlation have become clear so that corrections Avail: Univ. Microfilms Order No. DA8321179 can be made in the future. A dynamically complicated, The need for adaptive control of any system arises because variable-geometry plane grid structure intended for control of ignorance of the systems internal structure and critical parameter experiments has been built and analyzed experimentally and values, as well as changing control regimes. A large scale system theoretically for its modes of vibration. The initial versions of both is substantially more susceptible to these problems. Although the actual structure and its theorectical model was unsatisfactory considerable progress has been made in designing Model in some respects, and necessary improvements are almost Reference adaptive controllers for unknown single input single completed at this writing. Finally, the tasks of subcontractor HR output control systems, little progress has been made toward Textron are almost completed. They consist of a study of the extension of these ideas to the multi-input multi-output techniques known as component cost analysis and modal cost (multivariable) case. Furthermore, most adaptive control procedures analysis and a preliminary study of issues involved in the testing need the order of the (assumably unknown) controlled plant and of active vibration control systems of full-size satellite structures, use a reference model of the same order as the plant for most specifically whether testing should be conducted on the implementation of the adaptive algorithm. Direct Multivariable Model ground or in orbit. Author (GRA) Reference Adaptive Control (DMMRAC) procedures which do not require explicit parameter identification or a reference model of N84-15181# TRW Space Technology Labs., Redondo Beach, the same order as the plant seem to be especially attractive for Calif. the control of large structural systems. However, in the past they ACOSS FOURTEEN (ACTIVE CONTROL OF SPACE were shown to only be feasible for systems which satisfy the STRUCTURES) Final Technical Report, 23 Jun. 1981-30 Oct. strictly positive realness condition. Dissert. Abstr. 1982 R. J. BENHABIB, H. K. FLASHNER, and F. C. TUNG Mar. 1983 260 p (Contract F30602-81-C-0194; DARPA ORDER 3654; AF PROJ. N84-16056*# Alabama Univ., Huntsville. Dept. of Aerospace C654) Engineering. (AD-A133411; RADC-TR-83-51) Avail: NTIS HCA12/MFA01 FINITE ELEMENT ANALYSIS OF A DEPLOYABLE SPACE CSCL 22B STRUCTURE ACOSS Fourteen is one of a series of studies for the G. E. WEEKS In its Res. Rept.: 1983 NASA/ASEE Summer development of a unified structural dynamics and control Faculty Fellowship Program 24 p Dec. 1983 refs technology base to support future development of large space Avail: NTIS HC A99/MF A01 CSCL 20K systems. The major emphasis in these studies in the past has The dynamic characteristics of the Solar Array Flight Experiment been on generic control law development for active vibration (SAFE) structure during deployment and retraction are investigated. suppression. The emphasis is now shifting towards hardware The SAFE structure consists of a deployable mast with an attached development and experimental verification of the technology. solar blanket designed with accordion type folds to permit ACOSS Fourteen studies the definition, design and plan for an packaging in a small volume. The planar form of the blanket on-orbit, Shuttle-based Proof of Concept demonstration and stability geometry during deployment is maintained by a blanket enduring designs which extend previous designs and treat tension/guidewire system. Structurally, the mast is modeled as an noncolocated actuator-sensor control systems, while remaining Euler beam column with inplane and out of plane bending and insensitive to modal truncation and inaccurate structural models. finite torsional stiffness. For out of plane motion, the blanket is Author (GRA) modeled as .a distributed mass uniformly supported by the three guidewires. For inplane motion the blanket displacements are N84-15182# Dornier-Werke G.m.b.H., Friedrichshafen (West assumed to vary linearly from the mast base to the mast tip. The Germany). mathematical model uses a virtual work formulation, required STUDY ON DAMPING REPRESENTATION RELATED TO because the axial loading on the mast is nonconservative, SPACECRAFT STRUCTURAL DESIGN Final Report combined with assumed beam modes to derive the differential E. HILBRANDT Paris ESA Feb. 1983 210 p refs equations of motion. Consideration of the time dependent boundary (Contract ESTEC-4435/80/NL-AK(SQ) conditions results in an infinite set of ODE with time dependent (EMSB-18/83; ESA-CR(P)-1770) Avail: NTIS HC A10/MF A01 coefficients. Finally, correlation of mast tip accelerations to mast Damping representation models for spacecraft dynamic base bending moments for specified modal motions are indicated. response analysis, and system damping prediction methods were M.G.

38 05 STRUCTURAL DYNAMICS AND CONTROL

N84-16232# Institute de Pesquisas Espaciais, Sao Jose dos which in turn causes the spin rate ripple, ultimately limited by Campos (Brazil). damping in the ribbon and spacecraft is shown. It is indicated SENSITIVITY ANALYSIS OF THE INFLUENCE OF THE that qualitative increase in the oscillation period and the thermal FLEXIBILITY OF SOLAR PANELS ON THE ATTITUDE lag is fundamental for the period increase, found that numerical DYNAMICS OF ARTIFICIAL SATELLITES [ANALISE DE parameter values required to agree with in orbit initial exponential SENSITIVIDADE DA INFLUENCIA DA FLEXIBILIDADE DE build up are reasonable; those required for the ripple period are APENDICES SOBRE A DINAMICA DA ATITUDE DE SATELITES somewhat extreme. E.A.K. ARTIFICIAL] D. L FERREIRA, P. T. D. M. LOURENCAO. and O. M. NETO M84-17227*# Rockwell International Corp., Downey, Calif. Shuttle Jun. 1983 12 p refs In PORTUGUESE; ENGLISH summary Integration and Satellite Systems Div. Presented at the 7th Brazil. Mech. Eng. Conf., COBEM 83, A DEPLOYABLE STRUCTURE AND SOLAR ARRAY CONTROLS Uberiandia, Minas Gerais. 13-16 Dec. 1983 EXPERIMENT FOR STEP (INPE-2763-PRE/337) Avail: NTIS HC A02/MF A01 T. S. NISHIMOTO In NASA. Langley Research Center STEP The motion of a spin-stabilized satellite, having two flexible Expt. Requirements p 211-220 Jan. 1984 solar panels was studied. The equations of motion are attained Avail: NTISHCA15/MFA01 CSCL 22B using the Lagrangian formalism and the assumed modes method. A candidate configuration for a controls experiment on the The influence of the flexibility is studied using the eigenvalue and Space Technology Experiments Platform (STEP) is described. The eigenvector sensitivity. The pole allocation technique is used to elements of the experiment are the mast, the solar array, and an minimize the effects of elasticity on the rigid body motion. articulation module between the two. The characteristic dimensions Author are very compatible for integration on a pallet such a STEP'S proposed configuration. The controls' objective would be the N84-16246*# Virginia Univ., Chariottesville. Dept. of Mechanical measurement of orbiter interaction as well as the system and Aerospace Engineering. identification of the appendages. The flight experiment configuration DIGITAL CONTROL SYSTEM FOR SPACE STRUCTURAL would also provide a test bed for various active vibration controls DAMPERS Semiannual Progress Report concepts. The instrumentation being considered would measure J. K. HAVILAND Jan. 1984 27 p refs accelerations, strains, displacements, and temperatures. The (Contract NAG 1-349) deployable mast has eight elements defining a structural bay. (NASA-CR-175355; MAS 1.26:175355; UVA/52824/MAE84/101) Uniaxial measurements would be required to define loads at a Avail: NTIS HC A03/MF A01 CSCL 22B cross section of the structure. Displacements due to thermal A recently developed concept for a damper was improved by distortion of the mast and the local state of the solar concentrator adding a small taper to the proof-mass, and using a proximeter to may be measured by an optical ranging technique from the orbiter determine position. Also, an experimental damper was built using an flight deck. M.G. a three-inch stroke in place of the standard one-inch stroke. The analog controller initially used was replaced by an independent N84-17228*# National Aeronautics and Space Administration. digital controller slaved to a TRS-80 Model I computer, which Langley Research Center, Hampton, Va. also serves as a highly effective, low-cost development system. VIBRATION ISOLATION TECHNOLOGY EXPERIMENT An overall system concept for the use of proof-mass dampers is C. R. KECKLER In its STEP Expt. Requirements p 221-230 presented. A.R.H. Jan. 1984 refs Avail: NTIS HC A15/MF A01 CSCL 22B N84-16248*# Massachusetts Inst. of Tech., Cambridge. Dept. The objectives of the vibration isolation technology experiment of Aeronautics and Astronautics. are to demonstrate the viability of the magnetic suspension RELIABILITY ISSUES IN ACTIVE CONTROL OF LARGE technology in providing the isolation of large structures elements FLEXIBLE SPACE STRUCTURES Semiannual Status Report, from the external environment and to quantify the degree of 16 May - 15 Nov. 1983 isolation provided by this system. The approach proposed for this W. E. VANDERVELDE 23 Nov. 1983 8 p experiment is to mount a six-degrees-of-freedom magnetic bearing (Contract NAG1-126) suspension system at the free end of a shuttle-attached flexible (NASA-CR-175341; NAS 1.26:175341) Avail: NTIS HC A02/MF structure such as MAST. The disturbance generator, located on A01 CSCL 22B top of the isolation system, will be energized at selected and The unreliability of control system components was investigated broadband frequencies to simulate a typical spacecraft vibration in our attempt to deal with that problem. This matter is of concern environment. Sensors located on the isolation system and the in large space structure control because of the large number of flexible structures element will be used to quantify the degree of components required to achieve specified performance in some isolation provided by this system. M.G. situations, and the long operating period required between maintenance visits. The detection and isolation of component N84-17229*# National Aeronautics and Space Administration. failures during system operation, and algorithms for reconfiguring Langley Research Center, Hampton, Va. control systems following detection and isolation of a failure were INTEGRATED POWER/ATTITUDE CONTROL SYSTEM (IPACS) emphasized. S.L. TECHNOLOGY EXPERIMENT C. R. KECKLER In its STEP Expt. Requirements p 231-240 N84-16249*# National Aeronautics and Space Administration. Jan. 1984 refs Goddard Space Flight Center, Greenbelt, Md. Avail: NTISHC A15/MFA01 CSCL 22B THERMALLY INDUCED SPIN RATE RIPPLE ON SPACECRAFT An experiment is proposed that will perform the tasks associated WITH LONG RADIAL APPENDAGES with the control and energy storage/power generation functions J. V. FEDOR Aug. 1983 29 p refs attendant to space operations. It was shown in past studies that (NASA-TM-85058; NAS 1.15:85058) Avail: NTIS HC A03/MF the integration of these functions into one system can result in A01 CSCL 22B significant weight, volume, and cost savings. The Integrated A thermally induced spin rate ripple hypothesis is proposed to Power/Attitude Control System (IPACS) concept is discussed. explain the spin rate anomaly observed on ISEE-B. It involves the During orbit day, power is derived from the solar cell arrays and, two radial 14.5 meter beryllium copper tape ribbons going in and after appropriate conditioning, is used to operate the spacecraft out of the spacecraft hub shadow. A thermal lag time constant is subsystems, including the control system. In conventional applied to the thermally induced ribbon displacements which perturb approaches, a part of the collected solar energy is stored in a the spin rate. It is inferred that the averaged thermally induced bank of batteries to permit operation of the vehicle's systems ribbon displacements are coupled to the ribbon angular motion. A during orbit night. In the IPACS concept, the solar energy is stored possible exponential build up of the inplane motion of the ribbon in the spinning flywheels of the control system in the form of

39 05 STRUCTURAL DYNAMICS AND CONTROL kinetic energy. During orbit night, the wheels are despun and, application of this new model to a study of the behavior of a through the use of a wheel-shaft mounted generator, power is broken tether near the Shuttle are described. A reel control generated for the onboard subsystems. Operating these flywheels algorithm developed by SAO and examples of its use are described, over a 50-percent speed variation permits the extraction of 75 including an example which also demonstrates the use of the percent of the stored energy while at the same time preserving tether in transferring a heavy payload from a low-orbiting Shuttle 50 percent of the momentum capacity for control of the vehicle. to a high circular orbit. Capture of a low-orbiting payload by a Batteries can therefore be eliminated and significant weight and Space Station in high circular orbit is described. Energy transfer volume savings realized. R.J.F. within a dumbbell-type spacecraft by cyclical reeling operations or gravitational effects on the natural elasticity of the connecting N84-17230*# General Electric Co., Philadelphia, Pa. Space tether, it is shown, can circularize the orbit of the spacecraft. Systems Div. N.W. INVESTIGATION OF ARTICULATED PANEL DYNAMICS C. V. STAHLE, JR. In NASA. Langley Research Center STEP N84-18262*# Virginia Polytechnic Inst. and State Univ., Expt. Requirements p 241-255 Jan. 1984 Blacksburg. Dept. of Engineering Science and Mechanics. Avail: NTIS HC A15/MF A01 CSCL 22B CONTROL OF LARGE FLEXIBLE SPACECRAFT BY THE An articulated panel dynamics experiment to evaluate present INDEPENDENT MODAL-SPACE CONTROL METHOD Interim analysis and ground test methods as well as damping effectiveness Report is proposed. The experiment uses an existing panel design which L. MEIROVITCH and J. SHENAR Washington NASA Jan. was extensively analyzed and tested. These data provide a firm 1984 212 p refs basis for evaluating the adequacy of panel analysis and ground (Contract NAG 1-225) test methodology. The key issues for future large space structure (NASA-CR-3760; NAS 1.26:3760) Avail: NTIS HC A10/MF A01 panel designs are addressed: the critical launch transient and CSCL 22B vibroacoustic loading; the deployment analysis adequacy including The problem of control of a large-order flexible structure in air and gravitational effects; and the orbital resonant frequencies the form of a plate-like lattice by the Independent Modal-Space and mode shapes of deployed panel assemblies. By using an Control (IMSC) method is presented. The equations of motion are existing mature design that was thoroughly tested, the effort can first transformed to the modal space, thus obtaining internal (plant) focus on correlation of actual flight results with existing predictions. decoupling of the system. Then, the control laws are designed in A second panel assembly incorporating passive damping is the modal space for each mode separately, so that the modal proposed to provide a direct measure of damped panel benefits equations of motion are rendered externally (controller) decoupled. that can be obtained. These benefits include: reduced launch loads This complete decoupling applies both to rigid-body modes and and responses; and highly damped deployed modes. Existing elastic modes. The application of linear optimal control, in space-qualified viscoelastic epoxy, in combination with composite conjunction with a quadratic performance index, is first reviewed. materials or an alternate more effective damping material, will be A solution for high-order systems is proposed here by the IMSC used. R.J.F. method, whereby the problem is reduced to a number of modal minimum-fuel problems for the controlled modes. Author N84-17241# Institut National de Recherche d'lnformatique et d'Automatique, Rocquencourt (France). N84-18281*# Lockheed Missiles and Space Co., Sunnyvale, VALIDATION METHODS FOR MATHEMATICAL MODELS OF Calif. FLEXIBLE SATELLITE DYNAMICS Final Report [METHODES ATTITUDE, CONTROL AND STABILIZATION DE VALIDATION DES MODELES MATHEMATIQUES EN B. G. MORAIS In NASA. Langley Research Center Space DYNAMIQUE DES SATELLITES NON RIGIDES] Station Technol., 1983 p 41-60 Feb. 1984 C. A. DARMON Paris ESA 1983 303 p refs In FRENCH Avail: NTIS HC A09/MF A01 CSCL 22B (Contract ESTEC-2991 /76/NL-AK(SC)) In the area of control, several problems can arise during the (ESA-CR(P)-1794) Avail: NTIS HC A14/MF A01 evolution of the space station. These incude: 1) the use of multiple The linear equations of the dynamics of a rotating or three or articulated flexible bodies; 2) the need for distributed cntrol for axis stabilized satellite are analyzed, using a second order maneuvering and maintaining altitude; 3) hierarchical control to Lagrange, a frequential, modal and a variable state model. Satellite automate and manage control systems; 4) structual control (from sensor equations are solved. It is shown that satellite nonvibration the standpoint of appendage stamping; isolation, and possible figure modes are not observed by accelerometers and gyrometers. A control); 5) cntrol position and orientation for component modules fast Fourier transformation nonparametric method which identifies during construction (an evolutionary requirement); 6) control during system order is presented. Parameter identification conditions for docking and undocking operations; and 7) the normal requirements a second order model are established, and a maximum likelihood for stablity and control during systems operations. In addition, there estimate algorithm for model parameters is described. An algorithm are a number of key technology concerns, such as significant which identifies modal vectors and frequencies which intervene in landing modes which tend to be closely spaced and distributed the mode model as state variables, and second order model widely, distributed sensors and actuators which are collecated, matrices for each observable mode is shown. Author (ESA) and the wide distribution of landing modes that must be reduced from a dimensional standpoint. Author N84-17251 *# Smithsonian Astrophysical Observatory, Cambridge, Mass. N84-18311# Draper (Charles Stark) Lab., Inc., Cambridge, INVESTIGATION OF ELECTRODYNAMIC STABILIZATION AND Mass. CONTROL OF LONG ORBITING TETHERS Final Report, 13 Sep. ACOSS ELEVEN (ACTIVE CONTROL OF SPACE STRUCTURES), 1982 - 12 Sep. 1983 VOLUME 1 Interim Report, Apr. - Nov. 1982 G. COLOMBO (Padova Univ., Italy) and D. ARNOLD Jan. 1984 E. FOGEL, D, R. HEGG, H. MCCLAMROCH, and J. C. LIN Griffiss 159 p refs AFB, N.Y. RADC Jul. 1983 140 p 2 Vol. (Contract NAS8-35036) (Contract F30602-81-C-0180; AF PROJ. C655) (NASA-CR-170972; NAS 1.26:170972) Avail: NTIS HC A08/MF (AD-A135675; CSDL-R-1598-VOL-1; RADC-TR-83-158-VOL-1) A01 CSCL 22B Avail: NTIS HC A07/MF A01 CSCL 22A The state-of-the-art in tether modelling among participants in This volume documents the progress made in four principal the Tethered Satellite System (TSS) Program, the slack tether areas during this reporting period: (1) The difficulties encountered and its behavior, and certain advanced applications of the tether in the Large Space Structure (LSS) system identification were to problems in orbital mechanics are identified. The features and studied. Focusing on the high-resolution identification problem, a applications of the TSS software set are reviewed. Modelling the procedure for identifying lightly damped, closely spaced modes is slack tether analytically with as many as 50 mass points and the derived; (2) Two approaches to the incorporation of actuator.

40 05 STRUCTURAL DYNAMICS AND CONTROL dynamics and the role of actuator transducers in LSS vibration N84-19383# Institute de Pesquisas Espaciais, Sao Jose dos control were explored; (3) A modal dashpot/modal spring control Campos (Brazil). design is presented; and (4) A controlled experiment for the ACOSS CAPTURE OF SATELLITE STABILIZED BY GRAVITY GRADIENT design is proposed in which each principal element in the overall WITH A FLEXIBLE MAST DURING AND AFTER DEPLOYMENT synthesis process is systematically examined. Author (GRA) [ANALISE DO PROBLEMA DE CAPTURA DE UM SATELITE ESTABILIZADO POR GRADIENTE DE GRAVIDADE COM MASTRO FLEXIVEL DURANTE E APOS A FASE DE ESTICAMENTO] N84-18312# Draper (Charles Stark) Lab.. Inc., Cambridge, D. L FERREIRA, P. T. D. M. LOURENCAO, and S. A. TAVARES Mass. May 1983 11 p refs In PORTUGUESE; ENGLISH summary ACOSS ELEVEN (ACTIVE CONTROL OF SPACE STRUCTURES), Presented at the 7th Brazilian Congr. of Mech. Engr., COBEM 83, VOLUME 2 Interim Report, Jun. - Nov. 1982 Uberiandia. Brazil, 13-16 Dec. 1983 T. H. BROOKS and D. ANDING Griffiss AFB, N.Y. RADC (INPE-2749-PRE/325) Avail: NTIS HC A02/MF A01 Jul. 1983 148 p 2 Vol. The capture of the nominal equilibrium position of a gravity (Contract F30602-81-C-0180; AF PROJ. C655) gradient stabilized satellite with flexible and extensible appendages (AD-A135676; CSDL-R-1598-VOL-2; RADC-TR-83-158-VOL-2) is considered. The initial conditions, for which the capture is Avail: NTIS HC A07/MF A01 CSCL 22A possible, are studied noting that there is a large variation in the In analysis and simulation of Space-based Surveillance System parameters such as deployment velocity center of massa positions, Performance, a key variable is the scene/sensor interaction, under etc. The objective is to evaluate the influence of the boom flexibility subcontract to CSDL, Photon Research Associates has developed on the librational movement of the rigid body. The study is based a software package capable of generating and manipulating on the Lagrangena formulation and on the method of assumed terrestrial scene data sets as a function of major surveillance modes. Author system and mission parameters. This report documents the details of this simulation, called Genesis, which has now been incorporated N84-19392*# Bendix Corp., Teterboro, N.J. Guidance Systems into the Draper Integrated Simulations. Author (GRA) Div. MODULAR DESIGN ATTITUDE CONTROL SYSTEM Final Report F. D. CHICHESTER 24 Jan. 1984 71 p refs N84-18313# Air Force Academy, Colo. (Contract NAS8-33979) SCALE MODEL TESTING FOR CONTROL SYSTEM (NASA-CR-170996; NAS 1.26:170996) Avail: NTIS HC A04/MF PARAMETERS OF LARGE STRUCTURES Final Report, Aug. A01 CSCL 22B 1982 - Aug. 1983 The problem of applying modular attitude control to a rigid R. T. EVANS. B. J. SIMMONS, S. M. BROWN, D. A. ERCHINGER, body-flexible suspension model of a flexible spacecraft with some and M. E. MATHEWS Oct. 1983 35 p state variables inaccessible was addressed by developing a (Contract AF PROJ. 2308) sequence of single axis models and generating a series of reduced (AD-A135652; FJSRL-TR-83-0011) Avail: NTIS HC A03/MF state linear observers of minimum order to reconstruct those scalar A01 CSCL 22B state variables that were inaccessible. The specific single axis The premise is made that as an alternate to or enhancement models treated consisted of two, three and four rigid bodies, to finite element analysis of a large complex structure, scale model respectively, interconnected by a flexible shaft passing through tests can provide useful parameters for control system design. the mass centers of the bodies. Reduced state linear observers The objective is to minimize risks associated with expensive of all orders up to one less than the total number of scalar state construction of large complex space structures by better predictions variables were generated for each of the three single axis models of the associated structural dynamics. This report covers cited. Author construction of scale models, and comparison of scale model parameters to the full size structure. A comparison of the results N84-19394*# Avco Systems Div., Lowell, Mass. obtained for three scale models yields general relationships that MAINTENANCE AND OPERATIONAL ENHANCEMENT OF THE can be applied to future large complex structure development FLEXIBLE SPACECRAFT DYNAMICS PROGRAM Final Report and to a conclusion that structural characteristics pertaining to 9 Sep. 1983 38 p refs control system parameters can be determined from scale model (Contract NAS5-27466) tests. GRA (NASA-CR-175211; NAS 1.26:175211) Avail: NTIS HC A03/MF A01 CSCL 22B The modifications and additions made to the Flexible Spacecraft Dynamics (FSD) Program under contract NAS5-27466 are N84-18987# California Univ., Los Angeles. Dept. of System described. The principal addition to the program was the capability Science. •to simulate a two axis gimble platform despin control system using RESEARCH ON BOUNDARY FEEDBACK AND CONTROL the vibration damper degree of freedom for the azimuth gimble. THEORIES, 1978 - 1983 Final Report, 2 Jan. 1982 - 31 Mar. The details of the modifications made to the FSD Program are 1983 presented. Modifications to existing subroutines are briefly A. V. BALAKRISHNAN Mar. 1983 16 p described and a detailed description of new subroutines is given. (Contract AF-AFOSR-3550-78; AF PROJ. 2304) In addition, the program variables in new labelled COMMON blocks (AD-A136531; AFOSR-83-1240TR) Avail: NTIS HC A02/MF are described in detail. New input symbols for the FSD Program A01 CSCL 12A are described. Author During the period of this grant, topics investigated included: nonlinear white noise theory; stabilization of distributed parameter N84-19464# Air Force Inst. of Tech., Wright-Patterson AFB, systems by boundary feedback; system modeling and identification; Ohio. School of Engineering. control of flexible flight vehicles; random fields, filtering and DECENTRALIZED CONTROL OF A LARGE SPACE STRUCTURE estimation; control of randomly varying systems; and control of USING DIRECT OUTPUT FEEDBACK M.S. Thesis large space structures. Thirty technical papers were produced with D. V. THYFAULT Dec. 1983 140 p titles including: active control of airfoils in unsteady aerodynamics; (AD-A136781; AFIT/GA/AA/83D-8) Avail: NTIS HC A07/MF identification of aircraft parameters in turbulence with nonrational A01 CSCL 12A spectra; Aircraft performance modelling, theory and some Direct output feedback control methods are used to develop a preliminary results; and active control of large flexible space multiple-input multiple-output controller. The controller is then structures. GRA applied to the Charles Stark Draper Laboratory 2 (CSDL 2) model.

41 05 STRUCTURAL DYNAMICS AND CONTROL

The CSDL 2 model is a sophisticated optical space structure N84-20625*# Bendix Corp., Teterboro, N.J. Guidance Systems representative of large flexible space structures. This model Div. consists ol 59 nodes and 23 lumped masses. The beam elements EXHIBIT D MODULAR DESIGN ATTITUDE CONTROL SYSTEM are fully connected and may support axial, transverse, and torsional STUDY Progress Report, Jan. - Feb. 1984 deformations. NASTRAN is employed to generate modal F. CHICHESTER Feb. 1984 69 p refs approximations of the model as well as the mode shapes and (Contract NAS8-33979) frequencies of the resulting modes. Of the numerous modes (NASA-CR-170993; NAS 1.26:170993) Avail: NTIS HC A04/MF available for the model, only the first 36 modes are utilized and A01 CSCL 22B implemented in the controller. The control problem is formulated A dynamically equivalent four body approximation of the in state space form and direct output feedback is implemented. NASTRAN finite element model supplied for hybrid deployable The state is represented as modal amplitudes and rates. System truss to support the digital computer simulation of the ten body outputs are obtained by rate sensors and control is applied by model of the flexible space platform that incorporates the four point force actuators. GRA body truss model were investigated. Coefficients for sensitivity of state variables of the linearized model of the three axes rotational dynamics of the prototype flexible spacecraft were generated with respect to the model's parameters. Software changes required to N84-19465# Air Force Inst. of Tech., Wright-Patterson AFB, accomodate addition of another rigid body to the five body model Ohio. School of Engineering. of the rotational dynamics of the prototype flexible spacecraft were THE EFFECT OF MASS AND STIFFNESS CHANGES ON THE evaluated. S.L. DAMPING FACTOR IN A LARGE SPACE STRUCTURE AS REPRESENTED BY THE CSDL 2 MODEL M.S. Thesis D. E. OLSEN Dec. 1983 132 p (AD-A136984; AFIT/GSO/AA/83D-2) Avail: NTIS HC A07/MF A01 CSCL 22B N84-20627*# Howard Univ., Washington, D. C. Dept. of This investigation was undertaken to determine the sensitivity Mechanical Engineering. of the damping factor in a large space structure (LSS) to small ENVIRONMENTAL EFFECTS ON THE DYNAMICS AND changes in nonstructural mass and structural element stiffness. CONTROL OF AN ORBITING LARGE FLEXIBLE ANTENNA Revision 3 of the ACOSS 2 model, developed by the Charles SYSTEM Stark Drapes Laboratory, Inc. (CSDL), was used as the model of R. KRISHNA and P. M. BAINUM 1984 10 p refs Proposed the LSS. Various combinations of the mirror masses in this large for Presentation at the 35th Intern. Astronautical Congr., Lausanne, space telescope were varied by up to 10%, selected structural Switzerland, 7-13 Oct. 1984 elements were stiffened by increasing their cross-sectional areas (Contract NSG-1414) by 10 and 50%, and, finally, two structural elements in the middle (NASA-CR-175448; NAS 1.26:175448) Avail: NTIS HC A02/MF of the telescope were stiffened to represent the addition of a A01 CSCL 22B lumped mass located away from the control system sensors and Solar radiation pressure on the vibrating antenna structure, actuators. A control system of 21 collocated sensors and actuators, temperature gradients induced by solar heating, and stabilizing positioned at the top and bottom of the telescope, was used in gravity-gradient torques were considered when the linear regulator this analysis. The analysis was accomplished using NASTRAN for theory was used to obtain orientation and shape control of a the finite element analysis, and, after selecting certain vibration hoop/column antenna system being considered for the land mobile modes for further study, the complex conjugate pairs used to satellite system. A finite element model of the antenna system determine the damping factors were calculated. The results indicate which includes all six rigid modes and seven flexible modes was that the damping factors for the CSDL model are quite sensitive used. Results show that the environmental disturbances affect to small perturbations and that it is very difficult to predict the only the rigid modes of the structure. The effect of solar radiation effect that a perturbation to the model will have on the damping pressure interacting with the vibrating system is smaller than the factors. GRA solar radiation pressure acting on the thermally deformed structure. To reduce control effort in order to maintain shape and orientation, thermal deformations must be minimized in the preliminary design N84-19900# Concordia Univ., Montreal (Quebec). Dept. of of the system. A.R.H. Mechanical Engineering. DYNAMIC BEHAVIOUR OF A SATELLITE ANTENNA STRUCTURE IN RANDOM VIBRATION ENVIRONMENT V. K. JHA (SPAR Aerospace Ltd.), T. S. SANDAR, and R. B. BHAT In Shock and Vibration Inform. Center The Shock and N84-20880*# National Aeronautics and Space Administration. Vibration Bull., part3 p 91-103 May 1983 refs Langley Research Center, Hampton, Va. Avail: SVIC, Code 5804, Naval Research Lab., Washington, D.C. STATIC AND DYNAMIC STRUCTURAL-SENSITIVITY 20375 CSCL 20K DERIVATIVE CALCULATIONS IN THE FINITE-ELEMENT-BASED Satellite antenna structures are often subjected to random ENGINEERING ANALYSIS LANGUAGE (EAL) SYSTEM excitations with power spectra densities varying in an arbitrary C. J. CAMARDA and H. M. ADELMAN Mar. 1984 80 p refs manner in the frequency domain. A mathematical model for (NASA-TM-85743; L-15659; NAS 1.15:85743) Avail: NTIS HC effectively describing such excitations is proposed in order to A05/MF A01 CSCL 20K compute the dynamic response of the antenna structure. The The implementation of static and dynamic structural-sensitivity mathematical model of the excitation is developed analytically by derivative calculations in a general purpose, finite-element computer enveloping the profile of the power spectral densities by linear program denoted the Engineering Analysis Language (EAL) System segments of varying slopes. The validity of the proposed is described. Derivatives are calculated with respect to structural mathematical model is experimentally verified. The dynamic parameters, specifically, member sectional properties including response of the satellite antenna structure is obtained using the thicknesses, cross-sectional areas, and moments of inertia. proposed mathematical model for the excitation. The finite element Derivatives are obtained for displacements, stresses, vibration program SPAR was used as the main frame for this dynamic frequencies and mode shapes, and buckling loads and mode response analysis. The eigenvalues and mode shapes along with shapes. Three methods for calculating derivatives are implemented displacements and stresses for the antenna structure subjected (analytical, semianalytical, and finite differences), and comparisons to random excitations encountered during normal operation are of computer time and accuracy are made. Results are presented presented, employing the proposed mathematical model for the for four examples: a swept wing, a box beam, a stiffened cylinder excitations. M.G. with a cutout, and a space radiometer-antenna truss. Author

42 06 ELECTRONICS

N84-21172# Stevens Inst. of Tech., Hoboken, N. J. Dept. of N84-21612# Consulenze General! Roma (Italy). Mechanical Engineering. THE SOLUTION OF THE DYNAMIC PROBLEM OF THE TIME DOMAIN ANALYSIS AND SYNTHESIS OF ROBUST PERIODIC STRUCTURES BY CYCLOSYMMETRIC TECHNIQUE CONTROLLERS FOR LARGE SCALE LOG (LINEAR Final Report QUADRATIC GAUSSIAN) REGULATORS Final Report, 1 Sep. C. ARDUINI In its Study on Syn. and Characterization of Large 1982 - 31 Aug. 1983 Space Systems, Phase 2. Part 2: Proposals for Additions, R. K. YEDAVALLI. R. N. SHANBHAG. and J. IRUDAYASAMY 31 Modifications and New Anal. Methods, Vol. 1 p 13-168 Dec. Aug. 1983 56 p 1982 refs (Contract AF-83-0139; AF PROJ. 2304) Avail: NTIS HC A16/MF A01 (AD-A137760; AFOSR-84-0040TR) Avail: NTIS HC A04/MF The cyclosymmetric approach is advocated for the large space A01 CSCL 12A structure eigenvalue problem. The method treats The aspect of robustness for linear multivariable systems is noncyclosymmetric systems as perturbations of a basic analyzed in time domain. Both stability robustness and performance cyclosymmetric system. Noncyclosymmetry is assumed to reside robustness are combinedly considered to meet stability and in the boundary conditions only. The original set of equations is performance requirements. First a stability robustness condition in reduced to a formally cyclosymmetric system by including all the time domain (in terms of eigenvalues) is presented and examples deviations in the load vector (F)- All the unknowns are obtained are given which indicate that the proposed robustness condition as functions of F, but since F also depends on the unknowns, is less conservative then the corresponding frequency domain the solution is really a reformulation of the problem. System condition as well as another recently proposed time domain cyclosymmetry is estimated a posteriori by comparing its modal condition, both given in terms of singular values. Next a technique shapes to those of the cyclosymmetric boundary conditions. The is presented to further reduce the conservatism of the proposed method is particularly good for higher frequency modes, but also condition. A design algorithm that incorporates both stability gives good results for frequencies as low as the fundamental, robustness and performance robustness into the design procedure and for any number of bays. It can be applied to multisymmetric suggested in the summer faculty program report, is modified with systems. Author (ESA) the help of new definitions of robustness indices. Computer software to implement the algorithm is presented along with simple examples to illustrate the concepts. Based on the experience gained by the minigrant research, areas of future research are 06 recommended. Author (GRA) ELECTRONICS

Includes techniques for power and data distribution, antenna RF performance analysis, communications systems, and spacecraft charging effects. N84-21604# European Space Agency, Paris (France). DERIVATION AND COMBINATION OF IMPEDANCE MATRICES FOR FLEXIBLE SATELLITES A84-10016# E. CRELLIN (ESTEC, Noorwidjk, Netherlands) and F. JANSSENS SPACE STATION DATA MANAGEMENT • A SYSTEM EVOLVING (ESTEC, Noorwidjk, Netherlands) Nov. 1983 107 p refs FROM CHANGING REQUIREMENTS AND A DYNAMIC (ESA-STR-209; ISSN-0379-4067) Avail: NTIS HC A06/MF A01 TECHNOLOGY BASE The concept of the impedance matrix of a "dynamical system W. C. MOSLEY (General Electric Co., Space Systems Div., Valley is presented as a tool for the study of the small vibrations about Forge, PA) IN: Computers in Aerospace Conference, 4th, Hartford, equilibrium of a satellite with flexible appendages (attitude CT, October 24-26, 1983, Collection of Technical Papers . New dynamics). A method which avoids the derivation of the equations York, American Institute of Aeronautics and Astronautics, 1983, p. of motion of the global system and does not require discretization 101-109. of the flexible appendage a priori is developed. The impedance of (AIAA PAPER 83-2338) the global system enables the study of the attitude dynamics and An assessment is made of the data management system it can be constructed, in a systematic way, from the subsystem requirements, and consequent architectural properties, of a impedances. Impedances for typical subsystems of spinning prospective Space Station data system.These requirements are satellites are derived. The method of combination of the subsystem shaped by such factors as an operational lifetime that will span impedances is used to derive global system impedances for GEOS, several generations of technology, and the ability to accomodate ISPM, ISEE-B, ESRO-4 and IMP-J satellites. Author (ESA) evolutionary growth. The architectural features that must be emphasized include modularity, to achieve functional autonomy, flexibility of application, testability, transparency of technological modification, and standardization. It is noted that software verification and validation tools offer the greatest potential return on investment of any of the data management system technology areas in which accelerated development can be undertaken. N84-21611# Consulenze General! Roma (Italy). Generally, it is judged that the technology base for the initial STUDY ON SYNTHESIS AND CHARACTERIZATION OF LARGE configuration of the Space Station data system is currently SPACE SYSTEMS, PHASE 2. PART 2: PROPOSALS FOR available. O.C. ADDITIONS, MODIFICATIONS AND NEW ANALYTICAL METHODS, VOLUME 1 Final Report A84-10025# C. ARDUINI and U. PON2I Paris ESA Dec. 1982 360 p A VOICE INTERACTIVE SYSTEM FOR AIDING AND refs 5 Vol. DOCUMENTATION OF SPACE-BASED TASKS (Contract ESTEC-4348/80/NL-AK(SC)) V. RILEY and R. VESTEWIG (Honeywell Systems and Research (ESA-CR(P)-1779-VOL-3) Avail: NTIS HC A16/MF A01 Center, Minneapolis, MN) IN: Computers in Aerospace For large space structure design, solution of the dynamic Conference, 4th, Hartford, CT, October 24-26, 1983, Collection of problems of the periodic structures by cyclosymmetric technique Technical Papers . New York, American Institute of Aeronautics is discussed. Computing radiation forces by adapting thermal design and Astronautics, 1983, p. 171-177. verification softwares is considered. Simplified models and (AIAA PAPER 83-2355) computational schemes for the aerodynamic load are outlined. The application of a voice-interactive maintenance-aiding device Finite element formulations for tensioned members are evaluated. (VIMAD) to the performance assembly and maintenance tasks in

43 06 ELECTRONICS space is considered. The problems presented by the complexity kW output, stowage in the Shuttle for launch, and the deployment of the tasks to be performed, by the crew limitations of space scenario. Choices will be made between concentrator and panel missions, by the space environment in general, and by the further configurations, the structural materials, and the concentrator restrictions of extravehicular activities are reviewed. VIMAD has designs. Modular units are favored if retraction of the array is not been developed for ground use and comprises a helmet-mounted, a factor. It is noted that the solar array is preferred to nuclear hand-held, or full-size portable display unit linked by RF or cable turboelectric configurations for the 100 kW space station power to a computer or microcomputer controlling the presentation of supply. M.S.K. video or audio information. User command is by voice or portable keyboard, and the instructions and diagrams are stored on A84-11823# random-access video and audio disks. The modifications in MANAGEMENT OF THE RADIOLINK OF THE SOLAR SAIL software and hardware which might be needed to adapt VIMAD SPACECRAFT BY RADIO-AMATEURS to space use are discussed, taking the need for task documentation J. Y. PRADO, A. PERRET, and J. VILLAEYS (Union pour la into account, and the advantages and feasibility of a VIMAD-type Promotion de la Propulsion Photonique, Venerque, Haute-Garonne, system are demonstrated. T.K. France) International Astronautical Federation, International Astronautical Congress, 34th, Budapest, Hungary, Oct. 10-15,1983. A84-10396# 4 p. EXPERIMENT DATA COMMUNICATIONS (48 MBIT/S) (IAF PAPER 83-447) BETWEEN SPACELAB, THE SPACE SHUTTLE AND THE The progress of the technical studies being performed as a GROUND prelude to the construction of solar sail vehicles for a race to the R. J. SELG (ESA, Spacelab Sustaining Engineering Div., Cocoa moon is assessed. The designs of the sail are guided by the Beach, FL) and G. A. WEIJERS (ESA, Spacelab Sustaining necessity of making them very large and very light, as well as of Engineering Div., Noordwijk, Netherlands) ESA Bulletin (ISSN reflective materials. Attention is being given to the optimized control 0376-4265), no. 35. Aug. 1983, p. 34-39. of the sails in order to configure the trajectory and gain or lose Tests have been performed at Johnson Space Center in speed as needed. The manufacture and launch of a solar sail is Houston to verify the end-to-end data-transmission performance projected to cost $2.5-5 million, and is planned to reach operation of the NASA Space Transportation System's high-rate data by 1986-87. The sails will be constructed of aluminized plastic downlink (48 Mbit/s) with the European Spacelab multiplexing and films a few microns thick. Three sails can be launched in three demultiplexing equipment to be used at the link's input and output. separate modules in the lower part of the Ariane 3 or 4 fairing The aims of the tests were to check equipment compatibility and and placed in near-GEO by a kick motor. Ground control will the overall performance of the link and to establish operational guide the unfurling of the sails, which will be equipped to telemeter procedures and constraints in time for the first Spacelab flight. attitude data. Each sail will weigh about 170 kg, and commands Author will be issued at amateur radio wavelengths. M.S.K.

A84-11816*# National Aeronautics and Space Administration, A84-13521# Washington, D. C. EVALUATION OF BUS IMPEDANCE ON THE SPOT HIGH CAPACITY POWER SYSTEMS FOR SPACE MULTIMISSION PLATFORM J. P. MULLIN and J. H. AMBRUS (NASA, Space Energy Conversion A. CAPEL (ESA, Earth Observation Programme Office, Toulouse, Office, Washington, DC) International Astronautical Federation, France) and A. BARNABA (Centre National d'Etudes Spatiales, International Astronautical Congress, 34th, Budapest, Hungary, Oct. Toulouse, France) ESA Journal (ISSN 0379-2285), vol. 7, no. 3. 10-15, 1983. 5 p. 1983, p. 277-298. refs (IAF PAPER 83-421) A numerical model for the performance of a boost-type regulator Candidate high-power supply systems for future space missions for solar-array voltage regulation through shunting excess energy are discussed. Solar cells, particularly made from GaAs materials, into dissipative elements or shorting the array strings is presented. are projected to be amenable large arrays that will have a 10 yr Equations and variable waveforms which define static operation lifetime with a 15 percent efficiency at the end. Concentrator arrays are described and a dynamic model is configured using the using GaAs cells could furnish over 200 W/sq m with 100 suns current-injection principle. The resulting small-signal equivalent irradiance. Different battery systems, other than the present model is tested against operation of a breadboard model and low-power NiCd storage systems, will be required, and could be verified, and further confirmed in comparison with the unit in the either fuel cell systems or NIH2 batteries. The flywheel also offers SPOT power system. Note is taken of the bus impedance in the promise, especially if integrated within the attitude control system. three boost sections of the SPOT power circuitry. Attention is Solar thermal systems are also possible, featuring SiGe also given to the effect of batteries wired in parallel to the user thermocouples, or boron alloys or rare earth calcogenides in load. M.S.K. thermoelectric generators or thermionic converters equipped with alkali metal elements. Mechanical systems, notably the Brayton A84-15623 cycle engine, offer multihundredwatt performance and higher, with NTC '82; NATIONAL TELESYSTEMS CONFERENCE, at least 3.5 yr lifetimes. Experimentation is still needed to GALVESTON, TX, NOVEMBER 7-10, 1982, CONFERENCE characterize the power supply interaction with the spacecraft RECORD environment and to design efficient and long-lasting radiators if Conference sponsored by the Institute of Electrical and Electronics heat engines are implemented. M.S.K. Engineers. New York, Institute of Electrical and Electronics Engineers, Inc., 1982, 515 p. A84-11817# Topics of interest in the aerospace and electronic systems PHOTOVOLTAIC SOLAR ARRAYS LEADING TO A CANDIDATE fields, such as space communications and digital avionics, are SPACE POWER SYSTEM IN THE REGIME BEYOND 100 KW explored. Attention is given to digital avionic analysis and design, W. WESTPHAL and J. RATH (Telefunken AG, Wedel, West and to 30/20 GHz technology advances. Land mobile satellite Germany) International Astronautical Federation, International system design concepts and technologies are discussed, as are Astronautical Congress, 34th, Budapest, Hungary, Oct. 10-15,1983. communications, microwaves, and tracking systems for space, 27 p. launch vehicles for communications satellites, and civil and military (IAF PAPER 83-422) applications of the GPS. Optical communications potentialities, Design and technology considerations for a solar array power theory, and technologies are examined, and consideration is supply for the manned space station are discussed. The system devoted to robotics, image coding advances, and advanced would provide up to 100 kW peak and 40 kW continuous if batteries concepts in communications. The DBS system is described, are provided. Currently unanswered problems are the interactions together with computer simulations of telecommunication systems, between the array and the station or platform, expansion to 260 remote sensing systems, and linearization of satellite

44 06 ELECTRONICS communication. Offshore communications are investigated, as are presented, and monolithic phased array technology is noted to optical processing of RF signals, communications and tracking for fail to meet a need for multiaccess capabilities. M.S.K. the Shuttle, and potential design and performance features of a space station. M.S.K.

A84-15639*# National Aeronautics and Space Administration. Lyndon B. Johnson Space Center, Houston, Tex. A84-15642*# National Aeronautics and Space Administration. SPACE STATION COMMUNICATIONS AND TRACKING Lyndon B. Johnson Space Center, Houston, Tex. EQUIPMENT MANAGEMENT/CONTROL SYSTEM APPLICATION OF BEAM POWER TECHNOLOGY TO A SPACE M. H. KAPELL and J. W. SEYL (NASA, Johnson Space Center. STATION Houston, TX) IN: NTC '82; National Telesystems Conference, G. D. ARNDT and J. H. SUDDATH (NASA, Johnson Space Center, Galveston, TX, November 7-10, 1982, Conference Record . New Houston, TX) IN: NTC '82; National Telesystems Conference, York, Institute of Electrical and Electronics Engineers, Inc., 1982, Galveston, TX, November 7-10, 1982, Conference Record . New p. B2.1.1-B2.1.8. York, Institute of Electrical and Electronics Engineers, Inc., 1982, Design details of a communications and tracking (C and T) p. B2.4.1-B2.4.5. refs local area network and the distribution system requirements for The feasibility and performance parameters for beam microwave the prospective space station are described. The hardware will be power supplies from a space station to nearby orbiting satellites constructed of LRUs, including those for baseband, RF, and are examined. A 5.8 GHz transmission frequency is found suitable antenna subsystems. It is noted that the C and T equipment must for beaming 1-10 kW over a distance of 1-10 km. The antenna be routed throughout the station to accommodate growth of the could have a 15 m diameter, a 64 kW output, provide uniform station. Configurations of the C and T modules will therefore be illumination, and have a retrodirecth/e phase control system. A dependent .on the function of the space station module where LEO to ground demonstration project is described, involving power they are located. A block diagram is provided of a sample C and levels of 0.0025 mW/sq cm and yielding 202 W at a 100 x 100 T hardware distribution configuration. A topology and protocol will m rectenna. M.S.K. be needed to accommodate new terminals, wide bandwidths, bidirectional message transmission, and distributed functioning. Consideration will be given to collisions occurring in the data transmission channels. M.S.K.

A84-15640* National Aeronautics and Space Administration. A84-15643* Lockheed Engineering and Management Services Lyndon B. Johnson Space Center, Houston, Tex. Co., Inc., Houston, Tex. COMMUNICATIONS, TRACKING, AND DOCKING ON THE A COMMUNICATIONS SYSTEM CONCEPTUAL DESIGN FOR A SPACE STATION LOW EARTH ORBITING MANNED SPACE STATION H. O. ERWIN (NASA, Johnson Space Center, Houston, TX), M. K. TU (Lockheed Engineering and Management Services Co., Inc., H. CODEN, and F. W. SCHOLL (Codenoll Technology Corp., New Houston, TX), W. E. TEASDALE, and R. J. ZIMMERMAN (NASA, York, NY) IN: NTC '82; National Telesystems Conference, Johnson Space Center, Houston, TX) IN: NTC '82; National Galveston, TX; November 7-10, 1982, Conference Record . New Telesystems Conference, Galveston, TX, November 7-10, 1982, York, Institute of Electrical and Electronics Engineers, Inc., 1982, Conference Record . New York, Institute of Electrical and p. B2.2.1-B2.2.5. Electronics Engineers, Inc., 1982, p. B2.5.1-B2.5.19. Many of the communications, tracking, and docking functions The results of a NASA study on the design of the on a large manned orbiting Space Station - one that is modular communications system for a space station RF communications and made of metal - will have to be performed by optical systems system are reported. The system requirements, ground rules, and out of necessity. This paper discusses four practical approaches assumptions are detailed, together with the overall configuration, to accomplishing Space Station functions using optical the relay satellite links, and the forward and return links. The communications technology. It also provides the results of operational modes are surveyed for voice and data transmission preliminary experiments involved in the design of particular systems. performances, as well as links to unmanned orbital transfer Major operational factors considered in each system design include: vehicles. Tradeoff studies are yet to be performed for system (a) electromagnetic interference problems, (b) data bandwidth growth, video data compression, multiaccess communications, requirements, (c) zero-gravity operations, (d) free-space operations, optical or conventional functioning, and the necessary antenna (e) data security, and (f) modular expansion of the Space Station systems. M.S.K. structure. The technologies discussed are the following: (a) local infrared communications, (b) optical tracking and docking techniques, (c) long distance free space optical communications, and (d) local area optical networks. Author A84-15671 A84-15641 AUTONOMOUS NAVIGATION OF GEOSYNCHRONOUS MULTIBEAM PHASED ARRAYS - APPLICATION TO SATELLITES USING THE NAVSTAR GLOBAL POSITIONING SOC/FREE-FLYER COMMUNICATION SYSTEM SYSTEM J. S. RICE and J. H. OTT (Novar Electronics Corp., Barberton, P. JORGENSEN (Aerospace Corp. El Segundo, CA) IN: NTC'82; OH) IN: NTC '82; National Telesystems Conference, Galveston, National Telesystems Conference, Galveston, TX, November 7-10, TX, November 7-10,1982, Conference Record . New York, Institute 1982, Conference Record . New York, Institute of Electrical and of Electrical and Electronics Engineers, Inc., 1982, p. Electronics Engineers, Inc., 1982, p. D2.3.1-D2.3.6. B2.3.1-B2.3.5. Special problems arise in connection with the navigation of Features of a multibeam design for control and communications geosynchronous satellites using the Navstar/Global Positioning between a NASA space station and up to 10 free-flying platforms System (GPS). A user's set on a geosynchronous satellite, unlike are described. Performance demands permit high gain narrow the near earth user, can never perform the required measurements beams at long range and low gain wide beams at short range. to four GPS satellites simultaneously. The present investigation is Interterometric phase control would form the transmit and receive concerned with the consequences of this situation for the navigation beams based on measurements made by the free-flyers using of the geosynchronous satellites. It s found that despite the limited reference signals beamed from no more than three locations on visibility of Navstar/GPS satellites to user satellites at the space station's phased array. Nonlinear polarization is geosynchroous altitude, GPS can provide autonomous navigation expected, and multiple antennas will be included on the station to of geosynchronous satellites with an accuracy of the order of 100 prevent signal blocking. Calculations for the phased array are m. G.R.

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A84-17743 A84-19169 NARROW MULTIBEAM SATELLITE GROUND STATION SAMPLED DATA CONTROL OF LARGE SPACE STRUCTURES ANTENNA EMPLOYING A LINEAR ARRAY WITH A USING CONSTANT GAIN VELOCITY FEEDBACK - A NEGATIVE GEOSYNCHRONOUS ARC COVERAGE OF 60 DEG. II - VIEW ANTENNA DESIGN N. H. MCCLAMROCH (Michigan, University, Ann Arbor, Ml) IN: M. J. GANS and N. AMITAY (Bell Radio Research Laboratory, Conference on Decision and Control, 21st, Orlando, FL, December Holmdel, NJ) IEEE Transactions on Antennas and Propagation 8-10,1982, Proceedings. Volume 3 . New York, Institute of Electrical (ISSN 0018-926X), vol. AP-31, Nov. 1983, p. 966-972. refs and Electronics Engineers, 1982, p. 1279, 1280. A dually polarized narrow (less than 0.5 deg) beam antenna A framework is developed for sampled data control of large which provides a geosynchronous arc coverage of 60 deg is space structures, in terms of discrete time recursive equations in proposed and analyzed. To track the geosynchronous arc second order form. This framework is used to analyze the simplest accurately, the properly oriented antenna produces a conically control scheme where the loop is closed using constant gain output scanned beam by means of a linear array of feed horns with bias velocity feedback. It is shown that the closed loop is stable if the ccut apertures illuminating a pair of parabolic cylinder reflectors in feedback gain is positive definite and not too large, and if the an imaging arrangement. This design, with reduced size array and output velocity feedback is properly specified. Properties of such singly curved reflectors, is relatively simple to construct. a stabilizing controller establish the advantage of analog control Calculations for a 0.35 deg beamwidth Ku band earth station of the form considered. Author antenna show a 0.05 deg pointing accuracy with scan loss due to aberrations less than 1 dB and little pattern degradation throughout the scan region. For multiple beam capability, a Rotman lens is proposed and analyzed as a means of exciting the feed array. It allows communication with multiple satellites spaced as close as 1 deg. Author A84-20583 POTENTIAL OF MINICOMPUTER-ARRAY PROCESSOR SYSTEM FOR NONLINEAR FINITE-ELEMENT ANALYSIS G. A. STROHKORB and A. K. NOOR (George Washington University, Hampton, VA) Computers and Structures (ISSN 0045-7949), vol. 18, no. 4, 1984, p. 703-718. refs A84-18025*# Systems Science and Software, La Jolla, Calif. The potential of using a minicomputer/array-processor system PLASMA SHEATH STRUCTURE SURROUNDING A LARGE for the efficient solution of large-scale, nonlinear, finite-element POWERED SPACECRAFT problems is studied. A Prime 750 is used as the host computer, M. J. MANDELL, G. A. JONGEWARD, and I. KATZ (System, and a software simulator residing on the Prime is employed to Science and Software, La Jolla, CA) American Institute of assess the performance of the Floating Point Systems AP-120B Aeronautics and Astronautics, Aerospace Sciences Meeting, 22nd, array processor. Major hardware characteristics of the system such Reno, NV, Jan. 9-12, 1984. 5 p. refs as virtual memory and parallel and pipeline processing are (Contract NAS3-23058) reviewed, and the interplay between various hardware components (AIAA PAPER 84-0329) is examined. Effective use of the minicomputer/array-processor Various factors determining the floating potential of a highly system for nonlinear analysis requires the following: (1) proper biased (about 4-kV) spacecraft in low earth orbit are discussed. selection of the computational procedure and the capability to While the common rule of thumb (90 percent negative; 10 percent vectorize the numerical algorithms; (2) reduction of input-output positive) is usually a good guide, different biasing and grounding operations; and (3) overlapping host and array-processor patterns can lead to high positive potentials. The NASCAP/LEO operations. A detailed discussion is given of techniques to code can be used to predict spacecraft floating potential for accomplish each of these tasks. Two benchmark problems with complex three-dimensional spacecraft. Author 1715 and 3230 degrees of freedom, respectively, are selected to measure the anticipated gain in speed obtained by using the proposed algorithms on the array processor. Previously announced in STAR as N83-27259 S.L

A84-18394*# National Aeronautics and Space Administration. Marshall Space Flight Center, Huntsville, Ala. A PROGRAMMABLE POWER PROCESSOR FOR HIGH POWER SPACE APPLICATIONS A84-20647 J, R. LANIER, JR., J. R. GRAVES, R. E. KAPUSTKA, and J. R. IMPROVED ORBIT UTILIZATION USING AUXILIARY FEEDS IN BUSH, JR. (NASA, Marshall Space Flight Center, Huntsville, AL) EXISTING EARTH TERMINALS IN: PESC '82; Annual Power Electronics Specialists Conference, J. ARNBAK, M. H. A. J. HERBEN, and R. A. C. M. VAN 13th, Cambridge, MA, June 14-17, 1982, Record . New York, SPAENDONK (Eindhoven, Technische Hogeschool, Eindhoven, Institute of Electrical and Electronics Engineers, 1982, p. Netherlands) Space Communication and Broadcasting (ISSN 331-340. refs 0167-9368), vol. 1, Dec. 1983, p. 405-416. refs A Programmable Power Processor (P3) has been developed While geostationary orbit crowding has begun to restrict further for application in future large space power systems. The P3 is development of the satellite communications bands, and the capable of operation over a wide range of input voltage (26 to investment in existing earth terminals discourages antenna 375 Vdc) and output voltage (24 to 180 Vdc). The peak output replacements for the achievement of lower sidelobe envelopes, power capability is 18 kW (180 V at 100 A). The output the E-W stationkeeping tolerance was suffciently tightened in 1979 characteristics of the P3 can be programmed to any voltage and/or to make feasible the coordination of two potentially interfering current level within the limits of the processor and may be controlled satellite networks through specific sidelobe reductions at the as a function of internal or external parameters. Seven breadboard appropriate earth terminals. This may be achieved by a simple P3s and one 'flight-type' engineering model P3 have been built retrofit of these terminals which are found to constrain orbit and tested both individually and in electrical power systems. The occupancy. Attention is presently given to the state of programmable feature allows the P3 to be used in a variety of interferometric sidelobe suppression by auxiliary feeds in applications by changing the output characteristics. Test results, double-reflector antenna systems, in view of feed geometry, orbital including efficiency at various input/output combinations, transient spacing between satellites, required excitation levels, and system response, and output impedance, are presented. Author bandwidth. O.C.

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A84-20709 array wing that has been built for NASA-MSFC and of (b) the DIELECTRIC CHARGING IN SPACE - GROUND TEST DATA supporting structure and data acquisition system (DAS) which, with AND MODEL VERIFICATION the wing, will be flown in the Shuttle as an experiment in 1984. V. W. PINE, B. L BEERS, and S. T. IVES (Beers Associates, Inc., The experiment will verify the dynamics, thermodynamic, and Reston, VA) (IEEE, U.S. Defense Nuclear Agency, NASA, et al., electrical performance predictions of the array wing and will Annual Conference on Nuclear and Space Radiation Effects, demonstrate the structural capability of the array wing for Orbiter Gatlinburg, TN, July 18-21, 1983) IEEE Transactions on Nuclear launch and re-entry environments. The experiment hardware Science (ISSN 0018-9499). vol. NS-30, Dec. 1983, p. 4290-4295. verification program was designed to minimize costs and risk of refs experiment performance degradation while maintaining Shuttle and A computational model of the charging of dielectrics by electron crew safety. The previous full-scale wing hardware tests included irradiation has been verified by comparison with ground-based test an extension mast water table test and wing testing for random data. Recent improvements to the model are described briefly. vibration, thermal vacuum, and acoustic environments. The results Model calculations are compared with a variety of ground-based of these tests were used to define wing design modifications and test data. The test data span a range of electron energies, from to scope the test program for the experiment hardware. Author a few keV to beyond 1 MeV. Several experimental configurations are examined. Agreement between computational and experimental A84-22962 results is good. Author TECHNICAL ASPECTS OF THE INTELSAT V SOLAR ARRAY H. E. POLLARD and W. R. BARON (Ford Aerospace and A84-22958* Jet Propulsion Lab., California Inst. of Tech., Communications Corp., Palo Alto, CA) IN: Photovoltaic Specialists Pasadena. Conference, 16th, San Diego, CA, September 27-30, 1982, NEW DIRECTIONS IN SOLAR ARRAY DEVELOPMENT Conference Record . New York, Institute of Electrical and J. SCOTT-MONCK (California Institute of Technology, Jet Electronics Engineers, 1982, p. 31-35. Propulsion Laboratory, Pasadena, CA) IN: Photovoltaic Specialists The Intelsat V solar array is the largest rigid solar array used Conference. 16th, San Diego, CA, September 27-30, 1982, for a commercial communication satellite. This paper describes Conference Record . New York, Institute of Electrical and salient technology applications of the electrical design, Electronics Engineers, 1982, p. 7-12. NASA-supported research, development and manufacture of the Intelsat V solar array. The refs circuits including cells, interconnects and wiring are being A broad overview is presented of current and near-term solar assembled using solderiess welding techniques; the first solar array array technology that could be suitable for space use. Particular of this size to do so. Special welding process controls are described consideration is given to such advanced concepts as high power including monitor of electrical pulse, resistance and head pressure arrays, concentrator arrays, and ultrathin solar cell arrays. It is which provide the quality control to assure satisfactory welds. With concluded that if such ambitious concepts as geosynchronous the extensive use of solderiess cells, various techniques were space platforms, orbital space stations, and alternate forms of employed to ensure humidity resistance. The use of the Scanning propulsion are realized, the type of new technology described in Auger Microprobe as well as X-ray fluorescence for Palladium this paper may find acceptance for space. B.J. measurements are summarized. The electrical and environmental test program for the project is reviewed. Author A84-22959 TECHNOLOGY COMPONENTS OF SOLAR ARRAYS FOR SPACE PLATFORMS A84-22963* Lockheed Missiles and Space Co., Sunnyvale, K. BOGUS (ESA, European Space Research and Technology Calif. Centre, Noordwijk, Netherlands) IN: Photovoltaic Specialists NEW COMPONENT DEVELOPMENT FOR MULTI-100 KW Conference, 16th, San Diego, CA, September 27-30, 1982, LOW-COST SOLAR ARRAY APPLICATIONS Conference Record . New York, Institute of Electrical and G. J. PACK and J. A. MANN (Lockheed Missiles and Space Co., Electronics Engineers, 1982, p. 13-20. refs Inc., Sunnyvale, CA) IN: Photovoltaic Specialists Conference, It is noted that the European Space Photovoltaics Program 16th, San Diego, CA, September 27-30, 1982, Conference Record responds to the near-future needs of space platform missions. . New York, Institute of Electrical and Electronics Engineers, 1982, The chosen approach is characterized by emphasis on silicon-cell p. 36-38. Research supported by the Lockheed Missiles and Space optimization, development of long-life contact systems, and Co. commonality for different applications. Space platform concepts in (Contract NAS8-32981) the framework of the European space program are categorized Studies of the cost and performance of flexible arrays have into four classes containing near-term missions and follow-up shown that the most dramatic reductions in the $/Watt figure of generations: retrievable LEO platforms; long-life LEO platforms for merit are achieved by increasing performance. An examination of earth observation and astronomy; power module systems; and those properties that contribute to array performance indicated geostationary telecommunication platforms. The requirements on areas where radical changes in current design practice and the solar array subsystem in each of these classes are identified, philosophy would result in significant cost and performance impacts. leading to a definition of PV technology development requirements. To take advantage of the predicted cost reductions, modules were Current space PV technology activities in Europe which respond fabricated and tested that had ultra-thin superstrates as a load to these requirements are discussed, and future space platform carrying member and large area dielectric wraparound (DWA), applications are examined. B.J. gridded back surface and copper contacted solar cells. Author

A84-22961* Lockheed Missiles and Space Co., Sunnyvale, A84-22979* Applied Solar Energy Corp., City of Industry, Calif. Calif. LARGE AREA, LOW COST SPACE SOLAR CELLS SOLAR ARRAY SHUTTLE FLIGHT EXPERIMENT - HARDWARE J. KUKULKA and P. A. ILES (Applied Solar Energy Corp., City of DEVELOPMENT AND TESTING Industry, CA) IN: Photovoltaic Specialists Conference, 16th, San R. V. ELMS (Lockheed Missiles and Space Co., Inc., Sunnyvale, Diego, CA, September 27-30, 1982, Conference Record . New CA), H. C. HILL, and L. E. YOUNG (NASA, Marshall Space Flight York, Institute of Electrical and Electronics Engineers, 1982, p. Center, Huntsville, AL) IN: Photovoltaic Specialists Conference, 146-149. 16th, San Diego, CA, September 27-30, 1982, Conference Record (Contract NAS9-16440) . New York, Institute of Electrical and Electronics Engineers, 1982, This paper describes cost effective production-ready space solar p. 25-30. cells which can meet the requirements for use on the Space (Contract NAS8-31352) Shuttle and other large space missions. Actual yield and This paper reports on the fabrication and ground testing of (a) performance data for these cells, as well as cost comparisons a large area, light-weight, flexible substrate developmental solar between these and standard space cells are included. Author

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A84-22982 and for fixing error tolerances. The simulation method is based MECHANICAL WRAPAROUND CONTACTED CELL FOR LOW on discretizing the aperture so that the geometric form and the COST SPACE ARRAYS energy distribution of the sending antenna can assume arbitrary N. MARDESICH, D. JOSLIN, and D. MICHAELS (Spectrolab, Inc., profiles. C.D. Sylmar, CA) IN: Photovoltaic Specialists Conference, 16th, San Diego, CA, September 27-30, 1982, Conference Record . New York, Institute of Electrical and Electronics Engineers, 1982, p. A84-28067 160-163. CHARACTERISTICS OF THE MICROPROCESSOR The paper presents the advantages, performance, reliability and IMPLEMENTATION OF ALGORITHMS FOR THE PROCESSING cost of a mechanical wraparound contact on a large area solar OF RADIO SIGNALS AND NOISE IN LARGE ANTENNA ARRAYS cell. The wraparound contact consists of a silver ribbon laminated [OSOBENNOSTI MIKROPROTSESSORNOI REALIZATSII to the metallization on the back of a solar cell with an insulating ALGORITMOV OBRABOTKI RADIOSIGNALOV I POMEKH V acrylic-Kapton-acrylic sandwich and wrapped around the edge to BOL'SHIKH ANTENNYKH RESHETKAKH] the N+ metallization and welded. The wraparound contact can V. V. POPOVSKII and E. I. GLUSHANKOV Radioelektronika increase the cell cost by approximately 20 percent, which must (ISSN 0021-3470), vol. 27, March 1984, p. 51-53. In Russian. be offset by the panel assembly savings. Author refs

A84-22997# PREDICTION OF SOLAR CELL PERFORMANCE IN SPACE A84-29861 R. L. STATLER and D. H. WALKER (U.S. Navy, Naval Research TELECOMMUNICATION SYSTEMS FOR LARGE-SCALE SPACE Laboratory, Washington, DC) IN: Photovoltaic Specialists MANUFACTURING ACTIVITY Conference, 16th, San Diego, CA, September 27-30, 1982, D. OLMSTEAD (Stanford University, Stanford, CA) and M. A. Conference Record . New York, Institute of Electrical and ROTHBLATT (Schnader, Harrison, Segal and Lewis, Washington, Electronics Engineers, 1982, p. 301-306. Navy-supported DC) IN: Space manufacturing 1983; Proceedings of the Sixth research. Conference, Princeton, NJ, May 9-12, 1983 . San Diego, CA, Predicting solar array performance with a high degree of Univelt, Inc., 1983, p. 157-175. accuracy is of critical importance to the success of space missions. (AAS PAPER 83-216) This calculation is influenced by a large number of variables and Telecommunication systems for large-scale manufacturing parameters. Consequently, the accurate prediction becomes very activity are analyzed in terms of probable requirements, available difficult and safety margins must be assigned because of unknown frequency resources and desired network architecture. Separate factors relating to incomplete description of the behavior of the analysis is provided for space manufacturing activity in earth orbit materials and components in the solar array. This paper discusses and in deep space. The paper suggests various design alternatives two factors which are important in such predictions. The first is a for meeting dispersed space communications requirements and description of the gradual deterioration of the optical transmissivity considers interface options with terrestrial networks. The paper of the coverglass and its adhesive layer, using data derived from recommends adoption of a TDMA-based architecture and suggests the solar cell experiment on the Naval Research Laboratory NTS-2 spectrum allocation priorities for intersatellite and space operation satellite. The magnitude of this effect is shown through the radio services. Author interpretation of satellite data. The second factor is temperature enhanced radiation damage which was observed during radiation experiments at low dose rates on silicon solar cells. The observed N84-12233*# National Aeronautics and Space Administration. radiation damage is shown to be strongly dependent on the Lyndon B. Johnson Space Center, Houston, Tex. temperature of the silicon cells during irradiation. The magnitude SPACE STATION ENERGY SIZING of this effect is shown in its influence on the interpretation of R. R. RICE In NASA. Langley Research Center Integrated satellite data. Author Flywheel Technol., 1983 p 57-62 Dec. 1983 Avail: NTISHCA10/MFA01 CSCL 22B A84-25306# A general schematic for a space station power system is MSAT MOBILE COMMUNICATION DEMONSTRATION described. The major items of interest in the power system are SATELLITE SYSTEM AND BUS TRADEOFF CONSIDERATIONS the solar array, transfer devices, energy storage, and conversion R. D. CASWELL (Department of Communications, Communications equipment. Each item will have losses associated with it and must Research Centre, Ottawa, Canada) and A. M. KIDD (Spar be utilized in any sizing study, and can be used as a checklist for Aerospace, Ltd., Montreal, Canada) IN: Communication Satellite itemizing the various system components. Author Systems Conference, 10th, Orlando, FL, March 19-22, 1984, Technical Papers . New York, American Institute of Aeronautics and Astronautics, 1984, p. 450-458. refs N84-12246*# National Aeronautics and Space Administration. (AIAA PAPER 84-0751) Goddard Space Flight Center, Greenbelt, Md. ASSESSMENT OF POTENTIAL FOR BATTERIES IN SPACE A84-26516# APPLICATIONS RADIATION CHARACTERISTICS OF ARRAY ANTENNAS WITH F. E. FORD In NASA. Langley Research Center Integrated DISTURBED APERTURE COVERAGE Flywheel Technol., 1983 p 171-174 Dec. 1983 [STRAHLUNGSCHARAKTERISTIK VON ARRAY-ANTENNEN Avail: NTISHCA10/MFA01 CSCL 10C MIT GESTOERTER APERTURBELEGUNG] Different battery technologies for energy storage in space E. FLOERY and W. RIEDLER (Graz, Technische Universitaet, Graz, missions were examined. One of the best ways of the possibilities Austria) (International Union of Radio Science and of high energy density batteries were determined by looking at Nachrichtentechnische Gesellschaft, Gemeinsame Tagung, more conventional batteries (i.e., lead-acid, nickel-cadmium, Kleinheubach, West Germany, Oct. 3-7, 1983) Kleinheubacher nickel-hydrogen, etc.). The theoretical specific energy density for Berichte (ISSN 0343-5725), vol. 27, 1984, p. 243-252. In German. state of the art batteries and the usable energy density for a Research supported by the Fonds zur Foerderung der reasonable life expectancy are outlined. The most mature of these wissenschaftlichen Forschung. refs couples is lead acid, which achieves nearly 20% of its theoretical A numerical simulation of the effect of disturbances in the capacity. The nickel-cadmium couple, has matured to where the ideal aperture coverage of phased array antennas on the radiation active capacity is 17% of its theoretical capacity. The achievements geometry is presented. The microwave radiation energy distribution are used to measure the practicality of more advanced batteries in the near-earth region provides an important criterion for and to estimate what is needed for future high power space determining the energy threshold value of ionospheric modification systems. E.A.K.

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N84-12634*# TRW Space Technology Labs.. Redondo Beach, N84-14395# General Research Corp., Santa Barbara, Calif. Calif. Power Sources Engineering Dept. RF SYSTEMS IN SPACE. VOLUME 1: SPACE ANTENNAS STUDY OF MULTI-KILOWATT SOLAR ARRAYS FOR EARTH FREQUENCY (SARF) SIMULATION Final Technical Report ORBIT APPLICATIONS Final Report, 19 Nov. 1980 - 30 Jun. A. C. LUDWIG, J. R. FREEMAN, and J. D. CAPP Griffiss AFB, 1983 N.Y. RADC Apr. 1983 253 p R.E.PATTERSON 15 Oct. 1983 200 p refs (Contract F30602-81-C-0119; AF PROJ. 4506) (Contract NAS8-34131) (AD-A133734; RADC-TR-83-91-VOL-1) Avail: NTIS (NASA-CR-170939; MAS 1.26:170939; REPT-38172-6001-UE-00) HCA12/MFA01 CSCL 171 Avail: NTIS HC A09/MF A01 CSCL 10A The main objective of this effort was to develop a computer A miniaturized Cassegrainian concentrator (MCC) solar array based analytical capability for simulating the RF performance of concept is being developed with the objective of significantly large space-based radar (SBR) systems. The model is capable of reducing the recurring cost of multikilowatt solar arrays. The desired simulating corporate and space fed aperture. The model also can cost reduction is obtained as a result of using very small high simulate multibeam feeds, cluster/point feeds, corporate feed and efficiency solar cells in conjuction with low cost optics. The MCC various aperture distributions. The simulation is capable of single element concept incident slar radiation is reflected rom a accepting Draper Labs structural data and antenna current data primary parabolic reflector to a secondary hyperbolic reflector and from Atlantic Research Corporation's (ARC) First Approximation finally to a 4 millimeter diameter solar cell. A light catcher cone is Methods (FAM) and Higher Approximation Methods (HAM) models. used to improve off axis performance. The solar cell is mounted In addition there is a routine to input various apertures surface to a heat fin. An element is approximately 13 millimeters thick distortions which causes the elements in the array to be displaced which permits efficient launch stowage of the concentrator system from the ideal location on a planar lattice. These were analyses panels without complex optical component deployments or looking at calibration/compensation techniques for large aperture retractions. The MCC elements are packed in bays within graphite space radars. Passive, space fed lens SBR designs were epoxy frames and are electrically connected into appropriate investigated. The survivability of an SBR system was analyzed. series-parallel circuits. A MCC sngle element with a 21 sq cm The design of ground based SBR validation experiments for large entrance aperture and a 20 efficient, 0.25 sq cm gallium arsenide aperture SBR concepts were investigated. SBR designs were solar cell has the same power output as 30 sq cm of 11-percent investigated for ground target detection. GRA efficiency (at 68 C) silicon solar cells. S.C.L N84-14761# Dornier-Werke G.m.b.H., Friedrichshafen (West Germany). MODERN SOFTWARE DEVELOPMENT TOOLS IN SPACE N84-12653# Istituto di Ricerca e Tecnologia per lo Studio del PROJECTS ON THE EXAMPLE OF A SPACELAB Plasma Nello Spazio, Frascati (Italy). EXPERIMENT ORBITING WIRE AS A DYNAMO: AUXILIARY POWER O. NEFF, R. SCHMIDT, and H. J. SCHNEIDER In ESA Software POSSIBILITIES FOR SPACE PLATFORMS Eng. p 257-259 Aug. 1983 G. MASTRANTONIO Mar. 1983 12 p refs Sponsored by Avail: NTIS HC A13/MF A01 CNR The life cycle of the software for a Spacelab experiment is (IFSI-83-3) Avail: NTIS HC A02/MF A01 outlined. Typical software requirements for spacecraft experiments, A technique to short circuit the electric field set up by the and software development tools used in this project are presented. Earth's magnetic field in an orbiting metal wire, so that energy The program design language; the real time language PEARL for can be extracted is described. Useful powers of 3 kw for wire programming; and a powerful debugging system, which can also length 1 km, 4 mm in diameter and for external load equal to the be used for test and operation of the complete experiment are wire resistance are predicted. By varying the wire length as well described. An implementation of the compiler and real time as its cross-section low-voltage, high current (and vice-versa) needs operating system, resulting in very efficient object code is can be met. Author (ESA) demonstrated. Author (ESA)

N84-15386# Fondazione Ugo Bordoni, Rome (Italy). THE SMALL TRANSMITTER RECEIVER STATIONS IN THE N84-14394# General Research Corp., Santa Barbara, Calif. SIRIO EXPERIMENT [LE PICCOLE STAZIONI RF SYSTEMS IN SPACE. VOLUME 2: SPACE-BASED RADAR RICETRASMITTENTI NELL'ESPERIMENTO SIRIO] ANALYSES Final Technical Report P. LOMBARDI, P. MIGLIORINI. and E. SAGGESE (Telespazio A. V. MRSTIK, D. BESTE, R. J. BARTEK, and P. M. PAZICK S.p.A.) Oct. 1982 12 p In ITALIAN Submitted for Griffiss AFB, N.Y. RADC Apr. 1983 213 p publication (Contract F30602-81-C-0119; AF PROJ. 4506) (FUB-50-1982) Avail: NTIS HC A02/MF A01 (AD-A133735; RADC-TR-83-91-VOL-2) Avail: NTIS Experiments related to the utilization of 3m antenna transmitter HCA10/MFA01 CSCL 171 receiver stations are discussed. The stations can transmit or receive The main objective of this effort was to develop a computer via the Sirio satellite either 64 k bit/sec or 2.048 Mbit/sec data based analytical capability for simulating the RF performance of rates from or to similar stations or large antenna (17m) stations. large space-based radar (SBR) systems. The model is capable of System operation was tested using large antenna transmitters and simulating corporate and space fed aperture. The model also can small antenna receivers. With clear sky conditions a 0.0000001 simulate multibeam feeds, cluster/point feeds, corporate feed and error rate is feasible. The influence of rain events with alternations various aperture distributions. .The simulation is capable of of the order on up to 12 dB is discussed. Author (ESA) accepting Draper Labs structural data and antenna current data from Atlantic Research Corporation's (ARC) First Approximation N84-15970 Colorado State Univ., Fort Collins. Methods (FAM) and Higher Approximation Methods (HAM) models. CURRENT COLLECTION FROM THE SPACE PLASMA In addition there is a routine to input various apertures surface THROUGH DEFECTS IN HIGH VOLTAGE SOLAR ARRAY distortions which causes the elements in the arrays to be displaced INSULATION Ph.D. Thesis from the ideal location on a planar lattice. There were analyses R. P. STILLWELL 1983 129 p looking at calibration/compensation techniques for large aperture Avail: Univ. Microfilms Order No. DA8317838 space radars. Passive, space fed lens SBR designs were For spacecraft operation in the near earth environment, solar investigated. The survivability of an SBR system was analyzed. cell arrays constitute the major source of reliable long-term power. The design of ground based SBR validation experiments for large Optimization of mass and power efficiency results in a general aperture SBR concepts were investigated. SBR designs were requirement for high voltage solar arrays. The space plasma investigated for ground target detection. GRA environment, though, can result in large currents being collected

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by exposed solar cells. The solution of a protective covering of attached to the Shuttle? Does the outgassing of moisture from transparent insulation is not a complete solution, inasmuch as 0.3-mil Kapton film affect its reflector capability? A box ring truss defects in the insulation result in anomalously large currents being support structure and an automatic sequence deployment system collected through the defects. Tests simulating the electron are discussed. R.J.F. collection from small defects in an insulation have shown that there are two major collection modes. The first mode involves N84-17236*# National Aeronautics and Space Administration. current enhancement by means of a surface phenomenon involving Langley Research Center, Hampton, Va. the surrounding insulator. In the second mode the current collecton MICROWAVE REFLECTOR CHARACTERIZATION USING is enhanced by vaporization and ionization of the insulator material, SIMPLE INSTRUMENTS IN EVA in addition to the surface enhancement of the first mode. J. W. GOSLEE In its STEP Expt. Requirements p 333-338 Dissert. Abstr. Jan. 1984 Avail: NTIS HC A15/MF A01 CSCL 20N N84-16247*# National Aeronautics and Space Administration. An antenna with rigid panels which can be measured under Lewis Research Center, Cleveland, Ohio. ground conditions, carried to space in a packaged condition, RADIATING DIPOLE MODEL OF INTERFERENCE INDUCED IN deployed into a form similar to the Earth-measured one, measured SPACECRAFT CIRCUITRY BY SURFACE DISCHARGES under space conditions, restowed, and brought back to Earth so R. N. METZ (Colby College) Jan. 1984 7p refs that the original measurements can be verified is the type being (NASA-TP-2240; E-1775; MAS 1.60:2240) Avail: NTIS HC proposed for this experiment. The antenna chosen will be measured A02/MF A01 CSCL 22B under ground conditions, carried aloft, deployed into its antenna Spacecraft in geosynchronous orbit can be charged electrically shape, lifted by the remote manipulator system to a position where to high voltages by interaction with the space plasma. Differential it can be sighted by two astronauts at the two theodolites, and charging of spacecraft surfaces leads to arc and blowoff held there until the surface characterization can be completed. discharging. The discharges are thought to upset interior, An alternate method would be to use photogrammetry and take computer-level circuitry. In addition to capacitive or electrostatic pictures of the surface from the payload handling station. After effects, significant inductive and less significant radiative effects the surface characterization is completed, the antenna will be folded of these discharges exist and can be modeled in a dipole and restowed into the Shuttle bay for return to Earth. The surface approximation. Flight measurements suggest source frequencies characterization will be repeated on Earth after its return for of 5 to 50 MHz. Laboratory tests indicate source current strengths verification both of the original measurement taken on Earth and of several amperes. Electrical and magnetic fields at distances of the measurement taken in space. R.J.F. many centimeters from such sources can be as large as tens of volts per meter and meter squared, respectively. Estimates of field N84-17254# Aerospace Corp., Los Angeles, Calif. attenuation by spacecraft walls and structures suggest that interior A REVIEW OF SCATHA SATELLITE RESULTS: CHARGING fields may be appreciable if electromagnetic shielding is much AND DISCHARGING thinner than about 0.025 mm (1 mil). Pickup of such fields by J. F. FENNELL, H. C. KOONS, M. S. LEUNG, and P. F. MIZERA wires and cables interconnecting circuit components could be a In ESA Spacecraft/Plasma Interactions and their Influence on source of interference signals of several volts amplitude. Author Field and Particle Meas. p 3-11 Nov. 1983 refs (Contract AF-F04701-82-C-0083) N84-17224*# General Dynamics Corp., San Diego, Calif. Avail: NTIS HC A10/MF A01 PHOTOVOLTAIC CONCENTRATOR POINTING DYNAMICS AND Results from the SCATHA satellite charging monitors and PLASMA INTERACTION STUDY discharge detectors are summarized. The data show that surface T. G. STERN In NASA. Langley Research Center STEP Expt. charging, near synchronous altitudes, occurs preferentially in the Requirements p 177-184 Jan. 1984 midnight to local morning sectors. Evidence for bulk charging by Avail: NTIS HC A15/MF A01 CSCL 20! energetic electrons is also observed. Material charging data show The objectives of this experiment are to use the Space that there is a marked increase in bulk conductivity of Technology Experiments Platform (STEP) system to demonstrate solar-illuminated Kapton with exposure time in the space vacuum. the viability of concentrator photovoltaic arrays by: (1) configuring Teflon accumulates a permanent charge which slowly increases a deployable mast on the STEP pallet with concentrator mass with time. A quartz cloth material charges to higher than expected models and some active photovoltaic modules; (2) measuring the levels. Statistical analysis of the surface charging and the resultant array pointing dynamics under normal rotation as well as discharges and noise generation shows a close association with disturbance conditions; (3) performing an array plasma interaction each other. Discharges are ascribed to possible bulk charging. experiment to determine the steady-state plasma losses under The signal amplitudes of the discharges are discussed and the various voltage conditions; and (4) providing active distributed temporal character of the discharge signal is shown. control of the support truss to determine the improvement in Author (ESA) dynamic response. Experiment approach and test control and instrumentation are described. M.G. N84-17269*# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. N84-17235*# National Aeronautics and Space Administration. THE ROLE OF POTENTIAL BARRIER FORMATION IN Langley Research Center, Hampton, Va. SPACECRAFT CHARGING ADAPTIVE MICROWAVE REFLECTOR C. K. PURVIS In ESA Spacecraft/Plasma Interactions and their J. W. GOSLEE In its STEP Expt. Requirements p 325-331 Influence on Field and Particle Meas. p 115-124 Nov. 1983 Jan. 1984 refs refs Previously announced as N83-35005 Avail: NTIS HC A15/MF A01 CSCL 20N Avail: NTIS HC A10/MF A01 CSCL 22B As an interim step in going to the 100-meter reflector that was The role of potential barrier formation in spacecraft charging evaluated, a 5-meter reflector is proposed to test the electrostatic at geosynchronous orbit is discussed. Sudden dramatic shifts in concept under space conditions. Some of the issues which require structure potential at eclipse entry and exit, and in response to the space environment for evaluation are the following questions: injections of hot plasma during eclipse do not indicate the Can deployment of a box ring structure with a thin film reflector magnitude of differential charging. All daylight charging and some attached be manually deployed? In the absence of humidity, can long-term eclipse charging is barrier dominated. Shaded or low a 0.3-mil aluminized Kapton film reflector be formed by the yield surfaces charge negatively, forming vacuum potential barriers electrostatic process suitable for antenna applications? Can the which suppress emission of photoelectrons and secondary photogrammetric process be used to evaluate the reflector surface electrons, causing the spacecraft to charge negatively. This with pictures taken from the payload handling station? Can the process, which is configuration and material dependent, limits the space charging effect be evaluated with the 5-meter reflector magnitude of insulator-negative differential charging to values

50 06 ELECTRONICS substantially lower than supposed, and allows the possibility of is that there may be other controller structures which do better. insulator-positive differential charging. Discharges are less GRA energetic and more localized than supposed. If the spacecraft changes its potential when electrons are emitted in a discharge, then when the structure is driven positive, electron emission should cease. Author (ESA) N84-18458# Contraves Corp., Zurich (Switzerland). Dept EKR. SPACE TELESCOPE: SOLAR ARRAY PRIMARY DEVELOPMENT MECHANISM N84-17431*# UnCom Corp., Los Angeles, Calif. A. VEIT and D. CHANDLER In ESA First European Space USER MANUAL OF THE CATSS SYSTEM (VERSION 1.0) Mech. and Tribology Symp. p 27-34 Dec. 1983 COMMUNICATION ANALYSIS TOOL FOR SPACE STATION Avail: NTIS HC A10/MF A01 Interim Report A Primary Deployment Mechanism (PDM) powered by redundant C. S. TSANG, Y. T. SU. and W. C. LINDSEY Nov. 1983 45 p stepper motors was developed for the primary deploy and stow (Contract NAS9-16868) operations of the Space Telescope solar array. The mechanism (NASA-CR-171728; NAS 1.26:171728; TR-1183-8314) Avail: locks the array boom in the deployed position and releases the NTIS HC A03/MF A01 CSCL 17B boom at the end of mission for restowing before capture and The Communication Analysis Tool for the Space Station Earth return via space shuttle. Due to a continual growth in the (CATSS) is a FORTRAN language software package capable of design load of the PDM, the system exhibited instabilities. A predicting the communications links performance for the Space redesign introduced a planetary gear train between the motors Station (SS) communication and tracking (C & T) system. An and the primary lever arms. This results in a very stable system, interactive software package was currently developed to run on allowing for increase in system load if required. Three flight models the DEC/VAX computers. The CATSS models and evaluates the were successfully tested. Acceptance testing, besides ambient various C & T links of the SS, which includes the modulation operational tests, included vibration and thermal vacuum tests with schemes such as Binary-Phase-Shift-Keying (BPSK), BPSK with operational testing being included in the thermal vacuum Direct Sequence Spread Spectrum (PN/BPSK), and M-ary environment. Author (ESA) Frequency-Shift-Keying with Frequency Hopping (FH/MFSK). Optical Space Communication link is also included. CATSS is a C & T system engineering tool used to predict and analyze the system performance for different link environment. Identification N84-18532# National Telecommunications and .Information of system weaknesses is achieved through evaluation of Administration, Annapolis, Md. performance with varying system parameters. System tradeoff for ASSESSMENT OF SATELLITE POWER FLUX-DENSITY LIMITS different values of system parameters are made based on the IN THE 2025-2300 MHZ FREQUENCY RANGE, PART 1 performance prediction. Author A. FARRAR Oct. 1983 67 p refs (PB84-129402; NTIA/REPT-83-135) Avail: NTIS HC A04/MF N84-17436*# Old Dominion Univ., Norfolk, Va. Dept. of Electrical A01 CSCL 17B Engineering. An assessment of the line-of-sight (LOS) power flux-density AIRBORNE ANTENNA PATTERN CALCULATIONS Final Report, (pfd) limits for satellites operating in the 2025-2300 MHz frequency 1 Nov. 1982 - 31 Oct. 1983 range was conducted. Two computer models were used in the A. B. BAGHERIAN and R. R. MIELKE Dec. 1983 106 p refs analysis. Modifications to these models were suggested in order (Contract NSG-1655) to enhance their accuracy in the evaluation of the pfd limits in (NASA-CR-173284; NAS 1.26:173284) Avail: NTIS HC A06/MF this and other shared bands. Distinctions were made between the A01 CSCL 20N satellites in geostationary satellite orbit and those in Use of calculation program START and modeling program P nongeostationary orbits. Two different sets of limits were calculated, 3D to produce radiation patterns of antennas mounted on a space one for the satellites in the geostationary satellite orbit and the station is discussed. Basic components of two space stations in other for the satellites in nongeostationary satellite orbits. These the early design stage are simulated and radiation patterns for limits were calculated using the technical characteristics of antennas mounted on the modules are presented. Author equipment in the 2025-2300 MHz frequency range. The preliminary calculations using the existing computer models indicate that the pfd limits for the satellites operating in this frequency range may N84-17931# Air Force Inst. of Tech., Wright-Patterson AFB, be relaxed. • GRA Ohio. SELECTION OF NOISY SENSORS AND ACTUATORS FOR REGULATION OF LINEAR SYSTEMS Ph.D. Thesis M. L. DELORENZO Aug. 1983 254 p W84-19382*# National Aeronautics and Space Administration. (AD-A135442; AFIT/CI/NR-83-59D) Avail: NTIS HC A12/MF Goddard Space Flight Center, Greenbelt, Md. A01 CSCL 12A SPACELAB DATA PROCESSING FACILITY This research has developed and tested an algorithm which 1983 27 p refs Original document contains color illustrations aids the controls engineer in placing sensors and actuators in a (NASA-TM-85556; NAS 1.15:85556) Avail: NTIS HC A03/MF linear system to best achieve a set of variance specifications on A01 CSCL 14B the outputs and inputs of the system. The term best achieve has The Spacelab Data Processing Facility (SDPF) processes, been defined to be the sensor and actuator configuration which monitors, and accounts for the payload data from Spacelab and enables a controller to do either of the following: Meet the input other Shuttle missions and forwards relevant data to various user specifications while minimizing a sum of output variances facilities worldwide. The SLDPF is divided into the Spacelab Input normalized by their specification (i.e. input-constrained solution), Processing System (SIPS) and the Spacelab Output Processing or meet the output specifications while minimizing a sum of input System (SOPS). The SIPS division demultiplexes, synchronizes, variances normalized by their specification (i.e., output-constrained time tags, quality checks, accounts for the data, and formats the solution). The approach taken to solve this sensor and actuator data onto tapes. The SOPS division further edits, blocks, formats, selection (SAS) problem was to use LOG (Linear Quadratic and records the data on tape for shipment to users. User Gaussian) theory to specify a structure for the controller, and experiments must conform to the Spacelab's onboard High Rate then develop an algorithm (SASLQG) that places sensors and Multiplexer (HRM) format for maximum process ability. Audio, actuators in this controller structure to achieve either the analog, instrumentation, high density, experiment data, input/output input-constrained or output-constrained solution. The main data, quality control and accounting, and experimental channel advantage of this approach is the mathematical ease which LOG tapes along with a variety of spacelab ancillary tapes are provided theory addresses variance constraints, and the main disadvantage to the user by SLDPF. M.A.C.

51 06 ELECTRONICS

N84-19463# Air Force Geophysics Lab., Hanscom AFB, Mass. 07 SHEATH IONIZATION MODEL OF BEAM EMISSIONS FROM LARGE SPACECRAFTS ADVANCED MATERIALS S. T. LAI, H. A. COHEN, K. H. BHAVNANI (Radex, Inc.), and M. F. TAUTZ (Radex, Inc.) 30 Dec. 1983 14 p Presented at the Spacecraft Environ. Interactions Technol. Conf., Colorado Springs, Includes matrix composites, polyimide films, thermal control 4-6 Oct. 1983 coatings, bonding agents, antenna components, manufacturing (Contract AF PROJ. 7661) techniques, and space environmental effects on materials. (AD-A137181; AFGL-TR-83-0331) Avail: NTIS HC A02/MF A01 CSCL 22A An analytical model of the charging of a spacecraft emitting A84-10949*# Monsanto Research Corp., St. Louis, Mo. electron and ion beams has been applied to the case of large EROSION OF MYLAR AND PROTECTION BY THIN METAL spacecraft. In this model, ionization occurs in the sheath due to FILMS the return current. Charge neutralization of spherical space charge P. FRAUNDORF (Monsanto Research Center, St. Louis, Mo), D. flow is examined by solving analytical equations numerically. LINDSTROM, S. SANDFORD, P. SWAN, R. WALKER, E. ZINNER Parametric studies of potential large spacecraft are performed. As (Washington University, St. Louis, MO), and N. PAILER in the case of small spacecraft, the ions created in the sheath by (Max-Planck-lnstitut fuer Kemphysik, Heidelberg, West Germany) the returning current play a large role in determining spacecraft IN: Shuttle Environment and Operations Meeting, Washington, DC, potential. Author (GRA) October 31-November 2, 1983, Collection of Technical Papers . New York, American Institute of Aeronautics and Astronautics, 1983, p. 131-137. refs (Contract NAGW-122) (AIAA PAPER 83-2636) Mylar strips, 2.5 microns thick, uncoated and coated with 50A, 100A and 200A of Al, Pd, and Au/Pd were exposed on STS-5 in order to measure the erosion of mylar and to test means of protecting thin plastic foils commonly used for space experiments in low earth orbit. Analysis by optical microscopy, SEM and STEM investigation, EDX measurements, FTIR spectroscopy and weight loss measurements showed that while up to 75 percent of the uncoated mylar was eroded during exposure, thin coatings of the above metals can protect mylar for integrated oxygen-fluxes of at least 10 to the 21st atoms/sq cm. Author

A84-17108 NEW FABRIC STRUCTURES OF CARBON FIBER A. NISHIMURA, N. UEDA, and H. S. MATSUDA (Toray Industries, Inc., Olsu, Shiga, Japan) IN: Materials and processes - Continuing innovations; Proceedings of the Twenty-eighth National SAMPE Symposium and Exhibition, Anaheim, CA, April 12-14,1983 . Azusa, CA, Society for the Advancement of Material and Process Engineering, 1983, p. 71-88. Carbon fiber fabric has been increasingly used as a reinforcing intermediate material in the fields of aircraft and aerospace materials that require high performance; and is becoming one of the basic reinforcing materials for composites. A drawback of N84-21781# Mission Research Corp., Santa Barbara, Calif. conventional fabric, however, is in lower transfer ratio of the THE EFFECTS OF APERTURE ANTENNAS AFTER SIGNAL properties to those of the composites. This is a result of carbon PROPAGATION THROUGH ANISOTROPIC IONIZED MEDIA fiber bend (crimp), caused by the alternate crossing of warp and D. L KNEPP 1 Mar. 1983 76 p weft yarns which induce stress concentration. In order to solve (Contract DNA001-81-C-0006; S99-QAXH) the problem, a new fabric structure, that is, bi-directional noncrimp (AD-A138286; AD-E301332; MRC-R-744; DNA-TR-81-254) Avail: carbo fiber fabrics have been developed. In this paper, attention NTIS HC A05/MF A01 CSCL 20N is given to test results obtained from extensive studies of noncrimp Because of the large ranges involved, a space based search fabrics; that is, optimum design of fabric construction and effect and track radar requires a large aperture antenna to increase the of the construction to mechanical properties. The carbon fiber energy collected and to create a narrow beam for accurate angle investigated includes the newly developed high strain type having measurements and for resistance to localized jammers. This report more than 1.7 percent ultimate strain. Author gives the effects of such an antenna on measurements of received power, decorrelation time (or distance), mean time delay, time A84-17120 delay jitter and coherence bandwidth after propagation of the radar FIELD REPAIR OF GRAPHITE EPOXY SKIN PANELS ON THE signal through a strongly disturbed transionospheric propagation SPACESHIP COLUMBIA channel. It is shown that aperture averaging can reduce observed W. A. HENRY (Rockwell International Corp., Space Transportation signal power, increase observed decorrelation time and can be a and Systems Group, Downey, CA) IN: Materials and processes - significant factor in reducing the time delay jitter observed at the Continuing innovations; Proceedings of the Twenty-eighth National antenna output. As part of this analysis an analytic solution is SAMPE Symposium and Exhibition, Anaheim, CA, April 12-14,1983 obtained for the two-position, two-frequency mutual coherence . Azusa, CA, Society for the Advancement of Material and Process function for spherical wave propagation in the strong scatter limit. Engineering, 1983, p. 249-257. Transmitter and receiver are located in free-space on opposite Prior to and during the first four test flights of the spaceship sides of a thick slab containing anisotropic electron density Columbia, structural deficiencies as well as flight damages to the irregularities that are elongated in the direction parallel to the aft propulsion subsystem orbital maneuvering and reaction control magnetic field. The orientation of the magnetic result is used to subsystems pods graphite epoxy (G/ep) skin panels were determine the effect of an antenna aperture as a function of strengthened and repaired with beefup straps and doubters bonded geometry relative to the magnetic field. GRA in place at Kennedy Space Center. This is a delineation of the

52 07 ADVANCED MATERIALS structural modifications and double repairs made on these skin fabricated using standard ED clad material for comparison to panels. It includes a discussion of failure causes and descriptions, laminate with high-temperature elongation (HTE) copper foil. The inspections, development of bonding techniques and procedures, test panels were subjected to process variations throughout the installation of beefups and repair doublers, and bonding procedure stages of fabrication to determine the failure mechanism. Author modifications resulting from problems encountered in the field. It highlights the evolution of the procedure from that developed in A84-17768 the laboratory to modifications made in the field to eliminate MATERIALS AND CONSTRUCTION TECHNIQUES FOR LARGE problems encountered during field installation of beefups and SPACECRAFT STRUCTURES [WERKSTOFFE UND BAUWEISEN repairs. The beefup and repair procedures developed in the GROSSER RAUMFAHRTSTRUKTUREN) laboratory and modified in the field prior to and during the early W. HARTUNG (Deutsche Forschungs- und Versuchsanstalt fuer flights of Columbia have become the standard procedures for all Luft- und Raumfahrt, Institut fuer Strukturmechanik, Brunswick, OMS/RCS pod field repairs. Author West Germany) DFVLR-Nachrichten (ISSN 0011-4901). vol. 40, Nov. 1983, p. 26-29. In German. A84-17151 The current status of DFVLR research on CFRP materials and ADVANCED COMPOSITE ANTENNA REFLECTORS FOR designs for large structures (such as a communications platform) COMMUNICATIONS SATELLITES to be built from modular subassemblies in orbit is reviewed. The R. N. GOUNDER, C. F. SHU, and B. D. JACOBS (RCA, Astro pilot studies assume a platform lifetime of 10-20 yr and use slender, Electronics Div., Princeton, NJ) IN: Materials and processes - thin-walled profiled bars as primary construction elements. Thermal Continuing innovations; Proceedings of the Twenty-eighth National cyclic tests show that epoxide-resin CFRP elements maintain SAMPE Symposium and Exhibition, Anaheim, CA, April 12-14,1983 tensile strength at 80 percent or better after 3480 cycles but . Azusa, CA, Society for the Advancement of Material and Process suffer some loss of stiffness. Exposure during 27 h to an Engineering, 1983, p. 678-686. electron-radiation dose greater than that predicted for the platform This paper discusses advanced composites applications to lifetime produces no detrimental effect on CFRP performance. communications antenna reflectors used on RCA-built satellites. Overall, the applicability of CFRP to these structures has been Various types of reflector systems and their specific materials and confirmed. Since the structural designs themselves cannot be structures requirements are reviewed. The mechanical design, effectively tested on earth, modal survey tests using new software analysis, and test results for the different types of advanced (incorporating phase-resonance and phase-separation phenomena) composite reflectors are presented. The specific problems and mathematical simulations of the larger structures are being associated with deployable, frequency-reuse, gridded Kevlar developed. T.K. reflectors and large, deployable, high-frequency graphite reflectors are discussed in greater detail. Novel design concepts for the A84-18159# control of thermal distortions in deployable, composite reflectors REACTIONS OF HIGH VELOCITY ATOMIC OXYGEN WITH are presented. Author CARBON G. S. ARNOLD and D. R. PEPLINSKI (Aerospace Corp., Chemistry A84-17174 and Physics Laboratory, El Segundo, CA) American Institute of USING THE OUTGASSING TEST TO SCREEN MATERIALS FOR Aeronautics and Astronautics, Aerospace Sciences Meeting, 22nd, CONTAMINATION POTENTIAL Reno, NV, Jan. 9-12, 1984. 6 p. Research supported by the R. MOSS (Ford Aerospace and Communications Corp., Western Aerospace Corp. refs Development Laboratories Div., Palo Alto, CA) IN: Materials and (AIAA PAPER 84-0549) processes - Continuing innovations; Proceedings of the A spacecraft in low earth orbit experiences bombardment by Twenty-eighth National SAMPE Symposium and Exhibition, fast oxygen atoms by virtue of its own orbital velocity. Direct, Anaheim, CA, April 12-14, 1983 . Azusa, CA, Society for the dramatic observations on the Space Shuttle, as well as indirect Advancement of Material and Process Engineering, 1983, p. evidence from a number of Space Division and NASA spacecraft, 1045-1056. refs have revealed some of the effects which this bombardment can The standard outgassing test method, ASTM E-595, and the produce. The high velocity at which atoms strike surfaces on orbit apparatus used are described, and results of internal and round has resulted in gas-solid chemistry not observed in the thermal robin inter-laboratory tests are reviewed. It is shown that the ASTM interactions of oxygen atoms with surfaces and has apparently E-595 outgassing test is an accurate, reproducible method for accelerated the rates of some more familiar processes. The screening organic materials for contamination. Normal acceptance phenomenology of oxygen atom collisions with surfaces is levels of 1.0 percent TML and 0.10 percent VCM are realistic for completely unstudied at these high collision velocities (2-8 km/sec). the initial screening of materials. More than 90 percent of materials This paper discusses the reactions between oxygen atoms and can be expected to clearly pass or fail the 1.0 and 0.10 percent carbon films at collision velocities of 3.5 km/sec. It is found that limits. Round robin tests confirm that different laboratories testing there is no apparent translational energy enhancement of reaction the same material can expect the same accept/reject results. probability at this collision velocity. Results are compared to on-orbit The test is not operator sensitive. V.L. rates. Author

A84-17200 A84-19912*# National Aeronautics and Space Administration. CRACKED INNER LAYER FOIL IN HIGH-DENSITY MULTILAYER Lyndon B. Johnson Space Center, Houston, Tex. PRINTED WIRING BOARDS LOW EARTH ORBIT ATOMIC OXYGEN EFFECTS ON G. R. PAUL (McDonnell Douglas Astronautics Co., Huntington SURFACES Beach, CA) IN: Materials and processes - Continuing innovations; L J. LEGER, J. T. VISENTINE, and J. F. KUMINECZ (NASA, Proceedings of the Twenty-eighth National SAMPE Symposium Johnson Space Center, Houston, TX) American Institute of and Exhibition, Anaheim, CA, April 12-14,1983 . Azusa, CA, Society Aeronautics and Astronautics, Aerospace Sciences Meeting, 22nd, for the Advancement of Material and Process Engineering, 1983, Reno, NV, Jan. 9-12, 1984. 9 p. refs p. 1399-1405. refs (AIAA PAPER 84-0548) A study has been undertaken to establish why foil cracks occur Significant effects have been observed on surfaces in the at the internal foil planes of multilayer boards (MLBs) fabricated Shuttle Orbiter payload bay and on some experiments due to with standard 1- and 2-oz electrodeposited (ED) copper foil. The exposure to the LEO environment. These effects, which are foil cracking was observed during the testing of high-density MLBs predominantly manifested as surface recession and therefore mass and following the thermal stress requirements similar to loss, appear to arise from oxidation from exposure to atomic MIL-P-55110C. but at 500 F. Metallographic analysis indicated that oxygen, the major LEO component. Rates of interaction were layers one and two and/or nine and ten of a typical 10-layer MLB measured on two experiments for a large group of materials and were most susceptible to thermal shock damage. Test panels were specifically for thin organic films, and are in the range of 2-3x10

53 07 ADVANCED MATERIALS to the 24th cu cm/atom. These rates are large enough to present A84-24508 significant problems for solar arrays which use similar thin films ASSESSMENT OF RELIABILITY OF CERAMIC MATERIALS for solar-cell support. Author J. E. RITTER, JR. (Massachusetts, University, Amherst, MA) IN: Fracture mechanics of ceramics. Volume 5 - Surface flaws, statistics, and microcracking . New York, Plenum Press, 1983, p. A84-20682* Jet Propulsion Lab., California Inst. of Tech., 227-251. refs Pasadena. The reliability analysis of ceramic components must take into SIMULATED SPACE RADIATION EFFECTS ON DIELECTRICS account the variability and time-dependency of strength. The AND COATINGS techniques and concepts of fracture mechanics can be used for F. L. BOUQUET, A. PHILLIPS (California Institute of Technology, purposes of design to estimate the allowable stress and expected Jet Propulsion Laboratory, Pasadena, CA), and D. A. RUSSELL lifetime of a component in service. This is accomplished by (Boeing Radiation Effects Laboratory, Seattle, WA) (IEEE, U.S. estimating the initial crack size in the material and the time required Defense Nuclear Agency, NASA, et al., Annual Conference on for the crack to grow from its initial size to a final critical size. Nuclear and Space Radiation Effects, Gatlinburg, TN, July 18-21, The application of fracture mechanics theory appropriate for 1983) IEEE Transactions on Nuclear Science (ISSN 0018-9499), carrying out a reliability analysis is reviewed and successful vol. NS-30, Dec. 1983, p. 4090-4093. NASA-supported research, applications of this theory are discussed. Limitations of the theory refs and methods for overcoming these limitations are then presented. Simulation tests of space radiation have been performed for Author specific organic and inorganic materials. The test results for fifteen materials exposed to protons and five exposed to electrons are presented. Author

A84-21775 A84-28242 THE EFFECT OF PRESSURE AND TEMPERATURE ON SIC-REINFORCED-ALUMINUM ALLOYS FOR AEROSPACE TIME-DEPENDENT CHANGES IN GRAPHITE/EPOXY APPLICATIONS COMPOSITES BELOW THE GLASS TRANSITION B. J. MACLEAN and M. S. MISRA (Martin Marietta Aerospace, J. MIJOVIC and R. C. LIANG (New York, Polytechnic Institute, Denver, CO) IN: Mechanical behavior of metal-matrix composites; Brooklyn, NY) Polymer Engineering and Science (ISSN Proceedings of the Symposium, Dallas, TX, February 16-18, 1982 0032-3888), vol. 24, no. 1, Jan. 1984, p. 57-66. refs . Warrendale, PA, The Metallurgical Society of AIME, 1983, p. (Contract NSF MEA-81-20211) 301-320. Effects of pressure and temperature on time-dependent The aluminum alloys 6061 and 2024, reinforced with SiC changes in physical/mechanical properties of graphite/epoxy whiskers or particulates, were tested for tensile, fatigue, impact composites were investigated. Samples were cut from the toughness, and thermal expansion properties. Substantial eight-ply-thick laminates of commercially used composites, improvements in modulus, strength, and fatigue resistance were post-cured, and then quenched to environments of various observed when compared to the metal-matrix composite's wrought temperature and pressure. Time-dependent changes in their alloy counterpart. Depending on the degree of hot-working, elastic properties were analyzed by thermal and thermomechanical moduli on the order of 18 x 10 to the 6th psi (124 GPa) are (dynamic mechanical) measurements. An increase in the possible with tensile strengths of greater than 70,000 psi (480 glass-transition temperature was found to occur as a function of MPa). Enhanced strength and stiffness evolve at the expense of time. The rate of this process was enhanced by an increase in elongation and impact toughness. Microstructure and fractography temperature and/or a decrease in pressure. An explanation was reveal the relation between reinforcement/matrix homogeneity and offered in terms of types and mechanisms of molecular events isotropy of properties. The coefficient of thermal expansion is seen that occur in the glassy state. Time-dependent decrease in free to decrease from a nominal value of 13 x 10 to the -6th in./in. F volume (and enthalpy) takes place but is not the sole mechanism to 8 x 10 to the -6th in./in. F. ' Author responsible for the observed increase in T(g). After a certain period of time (which depends on T and P of the environment), additional crosslinking appears to take place. Author

A84-24501 A84-28458* Jet Propulsion Lab., California Inst. of Tech., FRACTURE MECHANICS OF CERAMICS. VOLUME 5 - SURFACE Pasadena. FLAWS, STATISTICS, AND MICROCRACKING EVALUATION OF SPACECRAFT MATERIALS AND PROCESSES R. C. BRADT, ED. (Pennsylvania State University, University Park, FOR 'OPTICAL DEGRADATION POTENTIAL PA), A. G. EVANS, ED. (California, University, Berkeley, CA), D. T. ODONNELL (California Institute of Technology, Jet Propulsion P. H. HASSELMAN, ED. (Virginia Polytechnic Institute and State Laboratory, Applied Mechanics Technology Section, Pasadena, University, Blacksburg, VA), and F. F. LANGE, ED. (Rockwell CA) IN: Spacecraft contamination environment; Proceedings of International Science Center, Thousand Oaks, CA) New York, the Meeting, Arlington, VA, May 4-6, 1982 . Bellingham, WA, SPIE Plenum Press, 1983, 706 p. - The International Society for Optical Engineering, 1983, p. Among the topics discussed are interface crack extension with 65-71. refs friction, the indentation fracture toughness of brittle materials with (Contract JPL-955426) Palmquist cracks, the surface and subsurface fracture of alpha-SIC A Wide Field Planetary Camera instrument with wide wavelength single crystals, brittle material deformation and cracking during sensitive Charged Coupled Device detectors has been designed high temperature scratching, ceramic material reliability and built for employment in space. The contamination potential of assessment, a probabilistic framework for structural design, the the spacecraft hardware is determined by the outgassing measurement and implications of the stress corrosion limit, a characteristics of the selected materials and the effect of the universal materials function for subcritical crack extension, and performed processing procedures. An investigation was conducted the fracture of piezoelectric materials. Also discussed are the to provide for more selective material screening with respect to fracture statistics of multiple flaw distributions, reliability contamination potential and to develop an optical effects data improvements for hot pressed silicon nitride, ceramic microcracking base. In the investigation, a series of thermogravimetric, residual mechanisms, statistical aspects of grain boundary cracking in gas, Micro-Volatile Condensible Material (VCM), and Vacuum ceramics and rocks, the fracture behavior of glass matrix/glass Optical Degradation tests were performed. The results of the particle composites, and limitations and challenges found in the Micro-VCM testing of four epoxy adhesive systems are presented application of fracture mechanics to ceramics. O.C. in tables. G.R. 07 ADVANCED MATERIALS

A84-28553* Jet Propulsion Lab., California Inst. of Tech., theorem is written in the Stieltjes convolution notation, and Pasadena. variations in displacement, velocity, stress and strain yield the ELECTRICALLY CONDUCTIVE BLACK OPTICAL PAINT appropriate characteristic equations. A finite element analysis based M. M. BIRNBAUM, E. C. METZLER, and E. L CLELAND (California on the theorem is presented for flexible four bar linkages Institute of Technology, Jet Propulsion Laboratory, Pasadena, CA) constructed from graphite-epoxy laminates, and the results are IN: Scattering in optical materials; Proceedings of the Meeting, compared with experimental data. Author San Diego, CA, August 25-27, 1982 . Bellingham, WA, SPIE - The International Society for Optical Engineering, 1983, p. 60-70. A84-29565# NASA-supported research, refs HIGHER TEMPERATURE COMPOSITE JOINTS SURVIVE An electrically conductive flat black paint has been developed ELIMINATION TESTS for use on the Galileo spacecraft which will orbit Jupiter in the V. WIGOTSKY Aerospace America (ISSN 0740-722X), vol. 22, late 1980s. The paint, designed for equipment operating in Feb. 1984, p. 32, 35. high-energy radiation fields, has multipurpose functions. Its Design and preliminary test results for four types of electrical conductivity keeps differential charging of the spacecraft graphite/polyimide joints for aerospace vehicles are discussed. external surfaces and equipment to a minimum, preventing the Different designs of joints made from Celion 3000 and buildup of electrostatic fields and arcing. Its flat black aspect 6000/PMR-15 graphite in a polyimide matrix over a minimizes the effects of stray light and unwanted reflectances, polyimide/fiberglass honeycomb core were subjected to when used in optical instruments and on sunshades. Its blackness temperatures ranging from -250 to 600 F to reveal information is suitable, also, for thermal control, when the paint is put on about laminate net tension strength, the relative worth of separately spacecraft surfaces. The paint has good adherence properties, as bonded or cocured doublers, and the importance of bonding measured by tape tests, when applied properly to a surface. The attachment angles to the joint. In static tests it was discovered electrically conductive paint which was developed has the following that one bolted design type had cover failures outside the joint characteristics: an electrical resistivity of 5 x 10 to the 7th ohms area at an average of 97 percent of the design load; T-shape, per square; a visual light total reflectance of approximately 5 and L-shape design types met or exceeded design requirements; percent; an infrared reflectance of 0.13 measured over a spectrum and a sandwiched, straight joint design type was dropped because from 10 to the (-5.5) power to 0.001 meter; a solar absorptivity, of difficulties in bonding its parts together. Diagrams are presented alpha-s, of 0.93, and a thermal emissivity, epsilon, of 0.87, resulting which describe the different design types in detail. I.H. in an alpha-s/epsilon of 1.07. The formula for making the paint and the process for applying it are described. Author A84-29572# A84-28900 GRAPHITE/POLYIMIDE JOINTS EXTEND TEMPERATURE EFFECT OF TEMPERATURE, MOISTURE AND RADIATION LIMITS EXPOSURES ON COMPOSITE MECHANICAL PROPERTIES V. WIGOTSKY Aerospace America (ISSN 0740-722X), vol. 22, V. F. MAZZIO (General Electric Co., Space Div., Valley Forge, March 1984, p. 29-31. PA) and G. HUBER (Cincinnati Testing Laboratories, Inc., Cincinnati, After extensive testing, an American aerospace company has OH) SAMPE Journal (ISSN 0091-1062), vol. 20, Mar.-Apr. 1984, found four graphite/polyimide joint designs for which the 350 F p. 14, 15, 18 (4 ff.). temperature limit of epoxy-matrix could be raised to 550 F. The (Contract F33615-79-C-5114) bonded and bolted joints are designed for loads encountered by A program was conducted to determine the effects of electron control surfaces of advanced aerospace vehicles. However, there beam radiation, moisture, and temperature exposure on the are certain problems because static and fatigue testing revealed mechanical properties of advanced composites. The composite a wide variation in failure loads and modes among different systems evaluated were three graphite/epoxy materials specimens. The reasons for these variations are discussed, taking (P-75-S/CE339, GY70/X30, and T300/934) and one Kevlar/epoxy into account deficiencies in gripping of the test specimen, the system (Kevlar 49/5209). The environmental conditions evaluated shelf life of resin, and the role of the nadic ester. G.R. were three levels of radiation exposure (between 3 x 10 to the 8th and 3 x 10 to the 9th rads), moisture saturation at 90 percent N84-11220*# National Aeronautics and Space Administration. R.H. and 160 F, and combined moisture and space environmental Langley Research Center, Hampton, Va. exposure. High and low dose rate exposure of PS75-S/CE339 SURFACE ANALYSIS OF GRAPHITE FIBER REINFORCED resulted in improved properties due to postcuring effects. Kevlar POLYIMIDE COMPOSITES 49/5209 showed no apparent effects from radiation when D. L. MESSICK (Virginia Polytechnic Inst. and State Univ., compared with baseline properties. P75-S/CE339 tensile Blacksburg), D. J. PROGAR, and J. P. WIGHTMAN Oct. 1983 specimens exposed to combined moisture and space environment 21 p refs Presented at the 15th Natl. SAMPE Tech. Conf., and tested at elevated temperature showed a decrease in modulus Cincinnati, 4-6 Oct. 1983 and strength; Kevlar 49/5209 showed a slight reduction in tensile (Contract NAG 1-248) properties. V.L. (NASA-TM-85700; NAS 1.15:85700) Avail: NTIS HC A02/MF A01 CSCL11D A84-29101# Several techniques have been used to establish the effect of A VARIATIONAL THEOREM FOR THE VISCOELASTODYNAMIC different surface pretreatments on graphite-polyimide composites. ANALYSIS OF HIGH-SPEED LINKAGE MACHINERY Composites were prepared from Celion 6000 graphite fibers and FABRICATED FROM COMPOSITE MATERIALS the polyimide LARC-160. Pretreatments included mechanical B. S. THOMPSON (Michigan State University, East Lansing, Ml) abrasion, chemical etching and light irradiation. Scanning electron and C. K. SUNG American Society of Mechanical Engineers, microscopy (SEM) and X-ray photoelectron spectroscopy (XPS) Design and Production Engineering Technical Conference, were used in the analysis. Contact angle of five different liquids Dearborn, Ml, Sept. 11-14, 1983. 7 p. refs of varying surface tensions were measured on the composites. (Contract NSF MEA-82-16777) SEM results showed polymer-rich peaks and polymer-poor valleys (ASME PAPER 83-DET-6) conforming to the pattern of the release cloth used durng The dynamic analysis of high-speed linkage machinery fabrication. Mechanically treated and light irradiated samples fabricated from viscoelastic composite materials requires the showed varying degrees of polymer peak removal, with some construction of appropriate equations of motion and boundary degradation down to the graphite fibers. Minimal changes in surface conditions for the members of the mechanism. In order to establish topography were observed on concentrations of surface fluorine these equations, a variational theorem is presented herein by even after pretreatment. The light irradiation pretreatment was most considering the motion of a continuum having dynamic viscoelastic effective at reducing surface fluorine concentrations whereas deformations superimposed on a general rigid-body motion. The chemical pretreatment was the least effective. Critical surface

55 07 ADVANCED MATERIALS

tensions correlated directly with the surface fluorine to carbon N84-17293*# Rensselaer Polytechnic Inst., Troy, N. Y. ratios as calculated from XPS. Author COMPOSITE STRUCTURAL MATERIALS Semiannual Progress Report, 30 Apr. - 30 Sep. 1983 G. S. ANSELL, R. G. LOEWY, and S. E. WIBERLEY Dec. 1983 N84-11595*# Martin Marietta Corp., Denver, Colo. 190 p EVALUATION AND PREDICTION OF LONG-TERM (Contract NGL-33-018-003) ENVIRONMENTAL EFFECTS OF NONMETALLIC MATERIALS, (NASA-CR-173259; NAS 1.26:173259; SAPR-45) Avail: NTIS SECOND PHASE Final Report HCA09/MFA01 CSCL 11D Sep. 1983 46 p rels Progress and plans are reported for investigations of: (1) the (Contract NAS8-33578) mechanical properties of high performance carbon fibers; (2) fatigue (NASA-CR-170915; MAS 1.26:170915; MCR-83-643) Avail: in composite materials; (3) moisture and temperature effects on NTIS HC A03/MF A01 CSCL 138 the mechanical properties of graphite-epoxy laminates; (4) the Changes in the functional properties of a number of nonmetallic theory of inhomogeneous swelling in epoxy resin; (5) numerical materials were evaluated experimentally as a function of simulated studies of the micromechanics of composite fracture; (6) free edge space environments and to use such data to develop models for failures of composite laminates; (7) analysis of unbalanced accelerated test methods useful for predicting such behavioral laminates; (8) compact lug design; (9) quantification of changes. The effects of changed particle irradiations on candidate Saint-Venant's principles for a general prismatic member; (10) space materials are evaluated. N.W. variation of resin properties through the thickness of cured samples; and (11) the wing fuselage ensemble of the RP-1 and RP-2 sailplanes. A.R.H. N84-16037*# Mississippi State Univ., State College. Dept. of Chemical Engineering. N84-18416# Erno Raumfahrttechnik G.m.b.H., Bremen (West AN EVALUATION OF TECHROLL SEAL FLEXIBLE JOINT Germany). Structures Dept. MATERIAL INTEGRITY CONTROL OF CARBON FIBER REINFORCED W. B. HALL In Alabama Univ. Res. Rept.: 1983 NASA/ASEE PLASTICS STRUCTURAL ELEMENTS, PHASE 1 REPORT Summer Faculty Fellowship Program 18 p Dec. 1983 W. H. PAUL and D. WAGNER Paris ESA 8 Apr. 1983 342 Avail: NTIS HC A99/MF A01 CSCL 11A p refs This study evaluated the materials utilized in the flexible joint (Contract ESA-4442/80/NL-AK(SC)) for possible failure modes. Studies undertaken included effect of (TB-TS-11-01/82-A; ESA-CR(P)-1778) Avail: NTISHCA15/MF temperature on the strength of the system, effect of fatigue on A01 the strength of the system, thermogravimetric analysis, An integrity control program for CFRP structural elements, to thermochemical analysis, differential scanning calorimeter analysis, avoid catastrophic failures due to propagation of defects and dynamic mechanical analysis, and peel test. These studies indicate imperfections inherent in FRPs is established. Based upon the that if the joint failed due to a materials deficiency, the most experience with fracture control of elements made from .likely mode was excessive temperature in the joint. In addition, homogeneous materials, the control logic applicable to safety the joint material is susceptible to fatigue damage which could relevant elements is determined and consequences in application have been a contributing factor. B.W. through all project phases are considered. Problems in defining adequate acceptance/rejection criteria for quality assurance are identified, given the difficulties in determination of local inter and N84-17217*# Dayton Univ., Ohio. Research Inst. intra laminary stresses at notches and defects. The THE EFFECTS OF THE SPACE ENVIRONMENT ON DAMPING phenomenological approach to relate damage propagation under MATERIALS AND DAMPING DESIGNS ON FLEXIBLE operational conditions to initial gross stresses cannot describe STRUCTURES the real process: cracking, especially delamination, results in a M. F. KLUESENER In NASA. Langley Research Center STEP significant change of stresses in individual layers. A tranfer matrix Expt. Requirements p 79-102 Jan. 1984 refs analytical method is proposed. Author (ESA) Avail: NTIS HC A15/MF A01 CSCL 20K The effects of space environments on damping materials and N84-21290*# Perkin-Elmer Corp., Danbury, Conn. Space Science damping designs on flexible structures were investigated. The Div. following items were examined: damping of flexible spacecraft OPTICAL COATING IN SPACE Final Report appendages; composite loss factor (n sub s) vs. time in high A. N. BUNNER 27 Oct. 1983 83 p refs vacuum for clamped test beams and damping of flexible structures. (Contract NASW-3753) The STEP experiments show inherent damping of flexible structures (NASA-CR-175441; NAS 1.26:175441; ER-591; REPT-2983-81) in space effective possible damping design configurations for space Avail:' NTIS HC A05/MF A01 CSCL 20F structures, effects of passively damped components on the system A technological appraisal of the steps required to approach loss factor of flexible structures and the effect of space environment the goal of in-situ optical coating, cleaning and re-coating the on properties of damping materials. E.A.K. optical elements of a remote telescope in space is reported. Emphasis is placed on the high ultraviolet throughput that a telescope using bare aluminum mirrors would offer. A preliminary N84-17253# European Space Agency, Paris (France). design is suggested for an Orbital Coating Laboratory to answer SPACECRAFT/PLASMA INTERACTIONS AND THEIR basic technical questions. Author INFLUENCE ON FIELD AND PARTICLE MEASUREMENTS A. PEDERSEN, ed., D. GUYENNE, ed., and J. HUNT, ed. Nov. N84-21675# Fulmer Research Inst. Ltd., Stoke Poges 1983 217 p refs Proc. of 17th ESLAB Symp., Noordwijk, (England). • Netherlands, 13-16 Sep. 1983 REVIEW REPORT OF THE THIRD YEAR'S ACTIVITIES ON THE (ESA-SP-198; ISSN-0379-6566) Avail: NTIS HC A10/MF AOV, STUDY SURVEY OF ADVANCED MATERIALS ESA, Paris FF 140 Member States, AU, CN and NO (+20% D. P. BASHFORD Paris ESA 14 Sep. 1983 12 p others) (Contract ESA-4389/80/NL-AK(SC)) The effect of spacecraft-plasma interactions on plasma and (R878; ESA-CR(P)-1838) Avail: NTIS HC A02/MF A01 electric field measurements was discussed, using results from Mechanical test methods applicable to carbon fiber reinforced Voyager, SCATHA, ISEE, and GEOS satellite missions, and space plastics (CFRP) were investigated. Moisture absorption and residual shuttle flights. Spacecraft charging and impact ionization during stresses in CFRP were studied. Epoxy resins suitable for space Halley's comet flyby missions were considered. Means of controlling structure applications as matrices for fiber reinforced composites spacecraft surface potentials were examined. were examined. Author (ESA)

56 08 ASSEMBLY CONCEPTS

08 A84-15667* Lockheed Engineering and Management Services Co., Inc., Houston, Tex. ASSEMBLY CONCEPTS KNOWLEDGE BASED SYSTEMS FOR INTELLIGENT ROBOTICS N. S. RAJARAM (Lockheed Engineering and Management Services Includes automated manipulator techniques, EVA, robot assembly, Co., Inc., Houston, TX) IN: NTC '82; National Telesystems teleoperators, and equipment installation. Conference, Galveston, TX, November 7-10, 1982, Conference Record . New York, Institute of Electrical and Electronics Engineers, Inc., 1982, p. D1.1.1-D1.1.4. refs A83-44602 (Contract NAS9-15800) CANADARM AND THE SPACE SHUTTLE It is pointed out that the construction of large space platforms, B. A. AIKENHEAD (National Aeronautical Establishment, Ottawa, such as space stations, has to be earned out in the outer space Canada), R. G. DANIELL, and F. M. DAVIS (SPAR Aerospace. environment. As it is extremely expensive to support human workers Ltd., Toronto, Canada) Journal of Vacuum Science and in space for large periods, the only feasible solution appears to Technology A (ISSN 0734-2101), vol. 1, Apr.-June 1983, pt. 1, p. be related to the development and deployment of highly capable 126-132. Research supported by the National Research Council robots for most of the tasks. Robots for space applications will of Canada. have to possess characteristics which are very different from those The remote manipulator system designed for the Space Shuttle needed by robots in industry. The present investigation is concerned is discussed. The system requirements and environment are with the needs of space robotics and the technologies which can summarized, and the manipulator arm assembly and its installation be of assistance to meet these needs, giving particular attention in the Orbiter, the joint assemblies, the end effector, and the wrist to knowledge bases. 'Intelligent' robots are required for the solution roll joint are discussed. The system uses brushless dc servomotors of arising problems. The collection of facts and rules needed for to drive the six joints and the end effector in a variety of control accomplishing such solutions form the 'knowledge base' of the modes which provide both manual and automatic control of the system. G.R. arm functions. Allowances made for the vacuum environment are addressed, and proof of compliance with requirements is considered. C.D. A84-21486 THE SHUTTLE REMOTE MANIPULATOR SYSTEM: CANADARM - A ROBOT ARM IN SPACE C. G. J. WAGNER-BARTAK (Spar Aerospace, Ltd., Mississauga, A84-10070*# National Aeronautics and Space Administration. Ontario, Canada) (United Nations, Symposium on Solar Energy Langley Research Center, Hampton, Va. from Space, Vienna, Austria, Aug. 9-21, 1982) Space Solar Power A SYSTEM FOR INTELLIGENT TELEOPERATION RESEARCH Review (ISSN 0191-9067), vol. 4, no. 1-2, 1983, p. 131-142. N. E. ORLANDO (NASA, Langley Research Center, Hampton, The diversity of automated tasks required by the Space Shuttle VA) American Institute of Aeronautics and Astronautics, has prompted critical consideration of both artificial intelligence Computers in Aerospace Conference, 4th, Hartford, CT, Oct. 24-26, and the man/machine relationship, resulting in the development 1983. 7 p. refs of the Shuttle's Remote Manipulator System (RMS). This system (AIAA PAPER 83-2376) provides interactive computer and human control, so that either The Automation Technology Branch of NASA Langley Research can possess executive system management. For the 'astroworker', Center is developing a research capability in the field of artificial the RMS constitutes a dextrous cybernetic system that intelligence, particularly as applicable in teleoperator/robotics electronically and mechanically increases physical strength, development for remote space operations. As a testbed for sensory perception, and dimensions of reach. It is the first experimentation in these areas, a system concept has been generation of space-based robotic manipulators that will eventually developed and is being implemented. This system termed DAISIE become the workhorses of space-based industrialization. Attention (Distributed Artificially Intelligent System for Interacting with the is given to the development status of the RMS, as well as the Environment), interfaces the key processes of perception, extrapolation of its technology to future orbital robotics for reasoning, and manipulation by linking hardware sensors and manufacturing, auxiliary power source deployment, and platform manipulators to a modular artificial intelligence (Al) software system construction in solar power conversion projects. O.C. in a hierarchical control structure. Verification experiments have been performed: one experiment used a blocksworld database and planner embedded in the DAISIE system to intelligently A84-22336# manipulate a simple physical environment; the other experiment REMOTE MANIPULATORS IN SPACE implemented a joint-space collision avoidance algorithm. Continued P. S. MATTHEWS, B. R. HILL (Spar Aerospace, Ltd., Remote system development is planned. Author Manipulator Systems Div., Toronto, Canada), and C. G. WAGNER-BARTAK IN: Manufacturing in space; Proceedings of the Winter Annual Meeting, Boston, MA, November 13-18, 1983 . New York, American Society of Mechanical Engineers, 1983, p. A84-11935 101-112. SIMULATION OF THE MOTION OF A SHUTTLE-ATTACHED The role of manipulators in space and the major design FLEXIBLE MANIPULATOR ARM challenges of the current Remote Manipulator System (RMS) are R. A. MILLER, W. R. GRAHAM, and F. R. VIGNERON (Department treated. The RMS, operated by both man-in-the-loop and of Communications, Ottawa, Canada) IN: World Congress on preprogrammed control, manipulates a maximum 30,000 kg System Simulation and Scientific Computation, 10th, Montreal, payload, 18.3 m in length and 4.5 m in diameter. End point accuracy Canada, August 8-13, 1982, Proceedings. Volume 3 . Montreal, is in the order of + or - 5 cm and + or -1 deg when automatically International Association for Mathematics and Computers in controlled and better than + or - 1-1/2 cm when operator Simulation, 1983, p. 225-227. controlled. RMS functions discussed include the future deployment An overview of the Shuttle's Remote Manipulator Control of on-orbit. Shuttle tended platforms such as Eureca and System is presented, followed by a description of a two-joint, Leasecraft, where robotic technology will exploit the constant two-link model of the arm used to study its flexible behavior. Two microgravity environment for manufacturing processes. In the methods of modelling link flexibility are formulated. Non real-time future, control systems will only be provided with tasks; and real-time simulations are described, and conclusions regarding manipulators will effect obstacle-avoiding, automatic interfacing of the arm's flexible behavior and the simulation methodology are tools and spacecraft with, fully sensate hands that include force presented. Author and visual/proximity sensing. C.M.

57 08 ASSEMBLY CONCEPTS

A84-22337# The methodology can easily be transferred to more complex AUTOMATION, ROBOTICS, AND MACHINE INTELLIGENCE problems in the future. The applications of artificial intelligence SYSTEMS (ARAMIS) IN SPACE MANUFACTURING techniques in diagnosis and treatment of robot system failures D. G. STUART (MIT, Cambridge, MA) IN: Manufacturing in space; are examined, including decision systems, production systems, and Proceedings of the Winter Annual Meeting, Boston, MA, November logical-proof systems. Finally, existing plan-synthesis methods are 13-18, 1983 . New York, American Society of Mechanical examined in detail and an algorithm that generalizes the NOAH Engineers, 1983, p. 113-126. refs system is proposed. C.M. Two studies are reviewed, one on the design of a space manufacturing facility (SMF), and the other on automation, robotics, A84-28523* National Aeronautics and Space Administration. and machine intelligence systems (ARAMIS) for space applications. Langley Research Center, Hampton, Va. The overall design of the SMF is described, as well as examples NASA RESEARCH IN TELEOPERATION AND ROBOTICS of space-specific production processes and equipment. A A. J. MEINTEL, JR. (NASA, Langley Research Center, Automation systematic method to evaluate ARAMIS options for tasks in space Technology Branch, Hampton, VA) and R. L. LARSEN (NASA, is presented. Promising ARAMIS options are described for Computer Science and Electronics Office, Washington, DC) IN: mechanical actuation tasks, monitoring and control tasks, decision Robotics and industrial inspection; Proceedings of the Meeting, and planning tasks, and fault diagnosis and handling tasks. San Diego, CA, August 24-27, 1982 . Bellingham, WA, SPIE - The Author International Society for Optical Engineering, 1983, p. 22-30. refs A84-25484* Honeywell, Inc., Clearwater, Fla. Increased automation is necessary in future NASA missions. MANIPULATOR INTERACTIVE DESIGN WITH Drivers for automation include constrained funding and physical INTERCONNECTED FLEXIBLE ELEMENTS resources as well as mission capabilities not achievable through R. P. SINGH (Honeywell, Inc., Clearwater, FL) and P. W. LIKINS conventional means. The application of emerging technology in (Lehigh University, Bethlehem, PA) IN: American Control manipulators and machine intelligence will enable the development Conference, San Francisco, CA, June 22-24, 1983, Proceedings. of robotic devices remotely commanded by human operators to Volume 2 . New York, Institute of Electrical and Electronics increase man's productivity in space. The Office of Aeronautics Engineers, 1983, p. 505-512. NASA-sponsored research, refs and Space Technology (OAST) has established a program for This paper describes the development of an analysis tool for research in teleoperation and robotics. The program's near-term the interactive design of control systems for manipulators and focus is a Remote Orbital Servicing System (ROSS). The longer similar electro-mechanical systems amenable to representation as range goals include: (1) basic research in autonomous operations, structures in a topological chain. The chain consists of a series of (2) human factors research on the man-machine interface to remote elastic bodies subject to small deformations and arbitrary systems, and (3) system integration and analysis of advanced displacements. The bodies are connected by hinges which permit concepts. This paper reviews the current NASA research and kinematic constraints, control, or relative motion with six degrees technology and considers future work needed to meet the OAST of freedom. The equations of motion for the chain configuration goals. Author are derived via Kane's method, extended for application to interconnected flexible bodies with time-varying boundary A84-28541 conditions. A corresponding set of modal coordinates has been APPLICATION OF LASER INTERFEROMETRY TO ROBOTICS selected. The motion equations are imbedded within a simulation R. H. ANDERSON, C. W. GILLARD, and C.-C. HUANG (Lockheed that transforms the vector-dyadic equations into scalar form for Missiles and Space Co., Inc., Space Systems Div., Sunnyvale, numerical integration. The simulation also includes a linear, CA) IN: Robotics and industrial inspection; Proceedings of the time-invariant controler specified in transfer function format and a Meeting, San Diego, CA, August 24-27, 1982 . Bellingham, WA, set of sensors and actuators that interface between the structure SPIE - The International Society for Optical Engineering, 1983, p. and controller. The simulation is driven by an interactive set-up 207-213. refs program resulting in an easy-to-use analysis tool. Author The application of a two-color CO2 laser system and a HeNe phase modulated system to the positioning and control of robots A84-25531 is discussed. The CO2 laser system has a 0.03 micron precision DYNAMICS OF NONRIGID ARTICULATED ROBOT LINKAGES for aligning optical elements, and the HeNe phase modulated R. P. JUDD and D. R. FALKENBURG (Oakland University, system has a 25 micron precision for measuring and controlling Rochester, Ml) IN: American Control Conference, San Francisco, large antennas. If incorporated into robotics, laser metrology would CA, June 22-24,1983, Proceedings. Volume 3 . New York, Institute permit unsophisticated robots (unaffected by temperature or stress) of Electrical and Electronics Engineers, 1983, p. 1045-1049. to perform high-precision work. The recommended primary distance refs measuring system for robotics is the multichannel interferometer This paper presents the kinematic and dynamic analysis of an in 'addition to a modulated subcarrier for absolute distance n-link manipulator with flexible members. The deformation of a measurement updates. Other recommendations include beam relay link from its rigid body position is modeled by a homogeneous by stationary and tracking mirrors, and a retroreflector target transformation. The dynamic equations are obtained using an attached to the robot as close as possible to the tool. C.M. Euler-Lagrange formulation. These equations are compared to those describing a rigid link mechanism. Author A84-44183*# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. A84-25828 ON MODELING DILUTION JET FLOWFIELDS STUDY OF ARTIFICIAL INTELLIGENCE TECHNIQUES - J. D. HOLDEMAN (NASA, Lewis Research Center, Cleveland, OH) REALIZATION OF A HIGHLY AUTONOMOUS EXPERIMENTAL and R. SRINIVASAN (Garrett Turbine Engine Co., Phoenix. AZ) ROBOT SYSTEM [CONTRIBUTION AL'ETUDE DE TECHNIQUES AIAA, SAE, and ASME, Joint Propulsion Conference, 20th, D'INTELLIGENCE ARTIFICIELLE - REALISATION D'UN Cincinnati, OH, June 11-13, 1984. 13 p. Previously announced in SYSTEME ROBOTIQUE EXPERIMENTAL AGRANDE STAR as N84-25713. refs AUTONOMIE] (AIAA PAPER 84-1379) A. LANUSSE Toulouse III, Universite, Docteur-lngenieur Thesis, This paper compares temperature field measurements from 1983, 179 p. In French, refs selected experiments on a single row, and opposed rows, of jets Artificial intelligence research is conducted to develop a injected into a ducted crossflow with profiles calculated using an robotized assembly system capable of implementing short or long empirical model based on assumed vertical profile similarity and production series with small variations. A flexible multirobot superposition, and distributions calculated with a 3-D elliptic code multisensor assembly cell is defined and realized. Integration of using a standard K-E turbulence model. The empirical model software programs effects the development of the NNS system. predictions are very good within the range of the generating

58 08 ASSEMBLY CONCEPTS experiments, and the numerical model results, although exhibiting projections for advances in these technologies over the next too little mixing, correctly describe the effects of the principal flow decade are included. Author and geometric variables. Author N84-11761*# National Aeronautics and Space Administration. N84-10582*# Massachusetts Inst. of Tech., Cambridge. Space Marshall Space Flight Center, Huntsville, Ala SELF-LOCKING TELESCOPING MANIPULATOR ARM Patent Systems Lab. Application SPACE APPLICATIONS OF AUTOMATION, ROBOTICS AND M. F. NESMITH, inventor (to NASA) 30 Sep. 1983 14 p MACHINE INTELLIGENCE SYSTEMS (ARAMIS). VOLUME 3, (NASA-CASE-MFS-25906-1; US-PATENT-APPL-SN-537757) PHASE 2: EXECUTIVE SUMMARY Final Report Avail: NTIS HC A02/MF A01 CSCL 05H D. L. AKIN, M. L MINSKY, E. D. THIEL, and C. R. KURTZMAN A telescoping manipulator arm and pivotable finger assembly Washington NASA Oct. 1983 42 p refs are disclosed. The telescoping arm assembly includes a generally (Contract NAS8-34381) T-shaped arm having three outwardly extending fingers guided on (NASA-CR-3736; NAS 1.26:3736; SSL-32-83-VOL-3-PHASE-2) Avail: NTIS HC A03/MF A01 CSCL 05H the grooved roller guides to compensate for environmental variations. The pivotable finger assembly includes four pivoting The field of telepresence is defined, and overviews of those fingers. Arcuate teeth are formed on the ends of the fingers. A capabilities that are now available, and those that will be required rack having teeth on four sides meshes with each one of the to support a NASA telepresence effort are provided. Investigation fingers. One surface of the rack includes teeth along its entire of NASA's plans and goals with regard to telepresence, extensive surface which mesh with teeth of the finger. The teeth at the literature search for materials relating to relevant technologies, a remote end of the rack engage teeth of a gear wheel. NASA description of these technologies and their state of the art, and projections for advances in these technologies are included. Several space projects are examined in detail to determine what N84-13208*# Essex Corp., Huntsville, Ala. capabilities are required of a telepresence system in order to ANALYSIS OF LARGE SPACE STRUCTURES ASSEMBLY: accomplish various tasks, such as servicing and assembly. The MAN/MACHINE ASSEMBLY ANALYSIS Final Report key operational and technological areas are identified, conclusions Washington NASA Dec. 1983 172 p refs and recommendations are made for further research, and an (Contract NAS8-32989) example developmental program leading to an operational (NASA-CR-3751; NAS 1.26:3751; H-83-03) Avail: NTIS HC telepresence servicer is presented. Author A08/MF A01 CSCL 22A Procedures for analyzing large space structures assembly via three primary modes: manual, remote and automated are outlined. N84-10583*# Massachusetts Inst. of Tech., Cambridge. Space Data bases on each of the assembly modes and a general data Systems Lab. base on the shuttle capabilities to support structures assembly SPACE APPLICATIONS OF AUTOMATION, ROBOTICS AND are presented. Task element times and structure assembly MACHINE INTELLIGENCE SYSTEMS (ARAMIS), PHASE 2. component costs are given to provide a basis for determining the VOLUME 1: TELEPRESENCE TECHNOLOGY BASE comparative economics of assembly alternatives. The lessons DEVELOPMENT Final Report learned from simulations of space structures assembly are D. L AKIN, M. L. MINSKY, E. D. THIEL, and C. R. KURTZMAN detailed. Author Oct. 1983 106 p refs (Contract NAS8-34381) N84-16250*# National Aeronautics and Space Administration. (NASA-CR-3734; NAS 1.26:3734; SSL-30-83) Avail: NTIS HC Langley Research Center, Hampton, Va. A06/MFA01 CSCL05H SYNCHRONOUSLY DEPLOYABLE TRUSS STRUCTURE Patent The field of telepresence is defined, and overviews of those Application capabilities that are now available, and those that will be required H. G. BUSH, M. M. MIKULAS, JR., and R. E. WALLSOM, inventors to support a NASA telepresence effort are provided. Investigation (to NASA) (Kentron International, Inc., Hampton, Va.) 30 Nov. of NASA's plans and goals with regard to telepresence, extensive 1983 15 p literature search for materials relating to relevant technologies, a (NASA-CASE-LAR-13117-1; US-PATENT-APPL-SN-556512) description of these technologies and their state of the art, and Avail: NTIS HC A02/MF A01 CSCL 22B projections for advances in these technologies over the next A collapsible-expandable truss structure is disclosed which decade are included. Several space projects are examined in detail includes two space surface truss layers with an attached core to determine what capabilities are required of a telepresence layer. The surface truss layers are composed of several linear system in order to accomplish various tasks, such as servicing struts arranged in multiple triangular configurations. Each linear and assembly. The key operational and technological areas are strut is hinged at its center and hingedly connected at each end identified, conclusions and recommendations are made for further to a nodular joint. A passive spring serves as the expansion force research, and an example developmental program is presented, to move the folded struts from a stowed collapsed position to a leading to an operational telepresence servicer. Author deployed operative final truss configuration. A damper controls the rate of spring expansion for synchronized deployment of the N84-10584*# Massachusetts Inst. of Tech., Cambridge. Space truss as the folded configuration is released for deployment by Systems Lab. restraint belts that synchronously extend under the control of motor SPACE APPLICATIONS OF AUTOMATION, ROBOTICS AND driven spools. NASA MACHINE INTELLIGENCE SYSTEMS (ARAMIS), PHASE 2. VOLUME 2: TELEPRESENCE PROJECT APPLICATIONS Final N84-16807# Naval Academy, Annapolis, Md. Dept. of Weapons Report and Systems Engineering. D. L. AKIN, M. L. MINSKY, E. D. THIEL, and C. R. KURTZMAN STABILITY ENHANCEMENT OF A FLEXIBLE ROBOT Washington NASA Oct. 1983 116p refs MANIPULATOR Final Report, 1982 - 1983 (Contract NAS8-34381) T. D. LOOKE 24 Jun. 1983 115 p (NASA-CR-3735; NAS 1.26:3735; SSL-31-83) Avail: NTIS HC (AD-A134185; USNA-TSPR-126) Avail: NTIS HC A06/MF A01 A06/MF A01 CSCL 05H CSCL12A The field of telepresence is defined and overviews of those A computer software programming technique was developed capabilities that are now available, and those that will be required to compensate a highly oscillatory robot system controlled by a to support a NASA telepresence effort are provided. Investigation bang-bang input. The assumptions that the system was linear and of NASA' plans and goals with regard to telepresence, extensive had lumped parameter characteristics allowed a fifth order, literature search for materials relating to relevant technologies, a simplified dynamic model to be derived. Analysis using frequency description of these technologies and their state of the art, and response methods led to further simplification of the model to a

59 08 ASSEMBLY CONCEPTS third order system. Based on the third order model, a technique two flexible links are developed. Kinematics of both the rotary was developed which would compensate the system with a form joint motion and the link deformation are described by 4x4 of deadbeat control. Simulation of the model driven by the transformation matrices. The link deflection is assumed small so compensated bang-bang input verified the deadbeat response. The that the link transformation can be composed of summations of technique was implemented on an 8080-based microcomputer assumed link shapes. The resulting equations are presented as system which controlled the input. Actual system response to the scalar and 4x4 matrix operations ready for programming. compensated input was observed to be essentially free of the Author (GRA) undesirable oscillatory motions, thus yielding an apparently rigid system. Author (GRA)

N84-17219*# National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. ERECTABLE BEAM EXPERIMENT W. L. HEARD, JR. In its STEP Expt. Requirements p 121-134 Jan. 1984 Avail: NTIS HC A15/MF A01 CSCL 22B The erectable beam applicability to the MAST/STEP experiment is summarized. High manual assembly rates were demonstrated N84-20626*# National Aeronautics and Space Administration. in neutral buoyancy tests and it is suggested that use of an Langley Research Center, Hampton, Va. erectable beam would eliminate extension/retraction complexity CONSTRUCTION CONCEPT FOR ERECTING AN OFFSET-FED associated with deployable beams. The erectable beam assembly ANTENNA aid is easily adaptable to general truss configurations and structural M.D.RHODES Mar. 1984 20 p refs appendages could be accommodated with the use of actuators. (NASA-TM-85774; NAS 1.15:85774) Avail: NTIS HC A02/MF The ACCESS flight experiment precedes MAST by 2 to 3 years A01 CSCL 22B and will provide mature, space proven assembly/disassembly A design concept for the construction of an offset-fed antenna technology on which to base the MAST experiment. E.A.K. is discussed. Antennas of this type are of interest for space applications because the configuration eliminates the effects of N84-20175*# Stanford Univ., Calif. feed and feed-support blockage. The proposed construction PRECISE CONTROL OF FLEXIBLE MANIPULATORS concept is developed around the assembly of a stiff truss Semiannual Progress Report substructure by pressure-suited astronauts operating in R. H. CANNON, JR. Mar. 1984 36 p refs extravehicular activity (EVA) assisted by a mobile platform that (Contract NAG 1-322) moves along the structure to position the astronauts at joint (NASA-CR-175389; NAS 1.26:175389) Avail: NTIS HC A03/MF locations where they can latch members in place. Construction A01 CSCL 05H can be accomplished from the shuttle cargo bay in the course of Experimental apparatus were developed for physically testing a normal flight or from a space station platform. The concepts control systems for pointing flexible structures, such as limber demonstrates the versatility of machine assisted manned assembly spacecraft, for the case that control actuators cannot be collocated and is only one of many potential applications. Author with sensors. Structural damping ratios are less than 0.003, each basic configuration of sensor/actuator noncollocation is available, and inertias can be halved or doubled abruptly during control maneuvers, thereby imposing, in particular, a sudden reversal in the plant's pole-zero sequence. First experimental results are presented, including stable control with both collocation and noncollocation. Author

N84-20316# Carnegie-Mellon Univ., Pittsburgh, Pa. Robotics Inst. RECURSIVE LAGRANGIAN DYNAMICS OF FLEXIBLE N84-20857*# Massachusetts Inst. of Tech., Cambridge. Dept. MANIPULATOR ARMS VIA TRANSFORMATION MATRICES of Ocean Engineering. Interim Technical Report FEASIBILITY OF REMOTELY MANIPULATED WELDING IN W. J. BOOK Dec. 1983 28 p SPACE. A STEP IN THE DEVELOPMENT OF NOVEL JOINING (AD-A137345; CMU-RI-TR-83-23) Avail: NTIS HC A03/MF A01 TECHNOLOGIES Final Report CSCL 12A K.' MASUBUCHI, J. E. AGAPAKIS, A. DEBICCARI, and C. Improving the performance of most engineering systems VONALT Sep. 1983 260 p refs requires the ability to model the system's behavior with improved (Contract NASW-3740) accuracy. The evolution of the mechanical arm from teleoperator (NASA-CR-175437; NAS 1.26:175437) Avail: NTIS HC A12/MF and crane to present day industrial and space robots and large A01 CSCL 131 space manipulators is no exception. Initial simple kinematic and In order to establish permanent human presence in space dynamic models are no longer adequate to improve performance technologies of constructing and repairing space stations and other in the most critical applications. Both the mechanical system and space structures must be developed. Most construction jobs are control system require improved models for design simulation. performed on earth and the fabricated modules will then be Proposed new control algorithms require dynamic models for delivered to space by the Space Shuttle. Only limited final assembly control calculation. Planning and programming activities as well jobs, which are primarily mechanical fastening, will be performed as man-in-the-loop simulation also require accurate models of the on site in space. Such fabrication plans, however, limit the designs arms. Accuracy is usually acquired at some cost The application of these structures, because each module must fit inside the of mechanical arms to economically sensitive endeavors in industry transport vehicle and must withstand launching stresses which and space also gives incentive to improve the efficiency of the are considerably high. Large-scale utilization of space necessitates formulation and simulation of dynamic models. Control algorithms more extensive construction work on site. Furthermore, continuous and man-in-the-loop simulation require real time calculation of operations of space stations and other structures require dynamic behavior. Formulation of the dynamics in an easy to maintenance and repairs of structural components as well as of understand conceptual approach is also important if maximum use tools and equipment on these space structures. Metal joining of the results is to be obtained. The nonlinear equations of motion technologies, and especially high-quality welding, in space heed for flexible manipulator arms consisting of rotary joints connecting developing. Author

60 09 PROPULSION

09 A84-21484 TRANSPORTATION - OPTIONS AND HIGH PAYOFF CHOICES PROPULSION M. W. HUNTER, II (Lockheed Missiles and Space Co., Inc., Palo Alto, CA) (United Nations, Symposium on Solar Energy from Space, Vienna, Austria, Aug. 9-21, 1982) Space Solar .Power Includes propulsion concepts and designs utilizing solar sailing, Review (ISSN 0191-9067), vol. 4, no. 1-2, 1983, p. 99-117. refs solar electric, ion, and low thrust chemical concepts. In recent years, nonrocket ideas have proliferated. Various electromagnetic acceleration schemes, energy transfer by laser from power stations to accelerating vehicles, and momentum A84-13397# transfer devices consisting of structures of vast proportions have A PARAMETRIC STUDY OF SPACE TRANSFER-PROPULSION been suggested. It is a complex array of possibilities, many of STAGES which potentially apply from low earth orbit to interstellar propulsion. V. R. LARSON, P. E. COFFMAN (Rockwell International Corp., This paper relies on the simple relations between energy and Rocketdyne Div., Canoga Park, CA), A. FABRIZI, and G. BAIOCCHI momentum which are fundamental to the various possible space (BPD Difesa-Spazio, Colleferro, Italy) International Astronautical propulsion systems. Energy transmission by new techniques, such Federation, International Astronautical Congress, 34th, Budapest, as a laser power station, and the various limitations on its Hungary, Oct. 10-15, 1983. 44 p. Research supported by the conversion to momentum are covered. Momentum storage and European Space Agency, Rockwell International Corp., and direct momentum transfer are also treated. Author Universitadi Roma. (IAF PAPER 83-401) Surveys of commercial spacecraft activities and future geosynchronous earth orbit (GEO) satellite requirements suggest A84-21485 that a spacecraft propulsion system that provides the perigee burn AN ELECTRIC PROPULSION TRANSPORTATION SYSTEM for a broad range of future commercial satellites would have an FROM LOW-EARTH ORBIT TO GEOSTATIONARY ORBIT excellent market potential. The efforts in this direction reported UTILIZING BEAMED MICROWAVE POWER here followed two approaches. The first concentrated on the W. C. BROWN (Raytheon Co., Microwave Power Transmission feasibility and the payload capabilities that could be provided by Dept., Waltham, MA) and P. E. GLASER (Arthur D. Little, Inc., an upper propulsion system assembled essentially from Cambridge, MA) (United Nations, Symposium on Solar Energy off-the-shelf components and subsystems. The second approach from Space, Vienna, Austria, Aug. 9-21, 1982) Space Solar Power considers the benefits that could be achieved by using major Review (ISSN 0191-9067), vol. 4, no. 1-2, 1983, p. 119-129. subsystems specifically tailored for the application. The results refs obtained thus far indicate that attractive UPS configurations can An electric propulsion transportation system from low-earth orbit be defined with either approach. C.R. to geostationary orbit that is based upon microwave power transmission technology derived from studies of the Solar Power Satellite is described. The ion engines in the transportation vehicle A84-16116 are supplied with d.c. electrical power that is obtained from a A FUTURE SOLAR ORBITAL TRANSFER VEHICLE CONCEPT microwave rectenna on the vehicle that collects and rectifies power C. F. GARTRELL (General Research Corp., McLean, VA) IEEE from a microwave beam originating from a transmitter located on Transactions on Aerospace and Electronic Systems (ISSN the earth near its equator. As the transportation vehicle passes 0018-9251), vol. AES-19, Sept. 1983, p. 704-710. refs over the transmitter on each revolution, it receives power first at The limiting payload performance of any transfer vehicle is low duty cycle and then rapidly at longer duty cycle as it gains in determined by the exhaust velocity of the propellant and the mass altitude. The paper contains estimates of transit times from characteristics of the transfer vehicle. The theoretical specific low-earth orbit to geostationary orbit and estimates of transportation impulse limit of liquid oxygen/liquid hydrogen systems is about costs for a typical scenario. These estimates indicate acceptable 560 s, while specific impulses obtained in practice are about 460 transit times to geostationary orbit and costs that are much less s. However, a much greater value for the specific impulse can be than existing chemical propulsion methods. Author produced by making use of the direct heating of low atomic number gases. It is pointed out that in the innerplanet environment the sun offers a convenient source of thermal energy. The present A84-22980* Spire Corp., Bedford, Mass. investigation is concerned with a solar orbital transfer vehicle LARGE AREA SPACE SOLAR CELL ASSEMBLIES (SOTV) which utilizes a 100 m diameter concentrator system to M. J. NOWLAN and M. B: SPITZER (Spire Corp., Bedford, MA) provide the approximately 10 MW of thermal power needed to IN: Photovoltaic Specialists Conference, 16th, San Diego, CA, obtain a nominal thrust level of 2780 N. G.R. September 27-30, 1982, Conference Record . New York, Institute of Electrical and Electronics Engineers, 1982, p. 150-155. refs A84-18141*# National Aeronautics and Space Administration. (Contract NAS3-22236) Langley Research Center, Hampton, Va. Results of the development of a 34.3 sq cm space solar cell VERTICAL ASCENT FROM EARTH TO GEOSYNCHRONOUS and integral glass cover are presented. Average AM(0) cell ORBIT efficiency is 14 percent. The cell design includes a high J. A. MARTIN (NASA, Langley Research Center, Space Systems performance back surface reflector yielding a thermal alpha of Div., Hampton, VA) American Institute of Aeronautics and approximately 0.66. A novel process is described which integrates Astronautics, Aerospace Sciences Meeting, 22nd, Reno, NV, Jan. cell fabrication and encapsulation thereby achieving a reduction 9-12, 1984. 11 p. refs of encapsulation cost. Test results indicate the potential of this (AIAA PAPER 84-0509) new technology. • • Author The concept of ascending vertically from the equator on earth to the point in geosynchronous orbit directly above was investigated. The gravity losses were found to be so great that A84-24980# vertical ascent is not practical with only chemical-rocket propulsion. HIGHLY EFFICIENT, VERY LOW-THRUST TRANSFER TO With laser propulsion, propellant requirements with vertical ascent GEOSYNCHRONOUS ORBIT - EXACT AND APPROXIMATE are reduced and might allow the use of single-stage vehicles from SOLUTIONS earth to geosynchronous orbit. Combined or composite chemical D. C. REDDING Journal of Guidance, Control, and Dynamics and laser propulsion is shown to be useful. A gravity ladder (ISSN 0731-5090), vol. 7, Mar-Apr. 1984, p. 141-147. suspended from geosynchronous orbit part of the distance to earth Previously cited in issue 19, p. 2988, Accession no. is shown to reduce the vehicle propulsion requirements. Author A83-39400

61 09 PROPULSION

A84-24981# A84-25294# OPTIMAL LOW-THRUST TRANSFERS TO SYNCHRONOUS WHY DON'T WE USE ION PROPULSION? ORBIT R. SPERBER (GTE Satellite Corp., Stamford, CT) IN: J. V. BREAKWELL (Stanford University, Stanford, CA) and D. C. Communication Satellite Systems Conference, 10th, Orlando, FL, REDOING Journal of Guidance, Control, and Dynamics (ISSN March 19-22, 1984, Technical Papers . New York, American 0731-5090), vol. 7, Mar.-Apr. 1984, p. 148-155. refs Institute of Aeronautics and Astronautics, 1984, p. 365-375. refs The general problem of circle-to-circle transfer is examined for (AIAA PAPER 84-0730) chemical rocket spacecraft, following Lawden's 'primer vector' Ion propulsion systems are compared with conventional catalytic theory. Impulsive and near-impulsive transfers are analyzed to and electrically augmented hydrazine systems and the potential predict initial conditions for low-thrust transfers. A computer solution for incorporation of ion propulsion into today's Delta spacecraft is of the low-thrust problem is described. Results 'are presented for discussed. Battery-powered ion propulsion systems tend to be more the low earth orbit to geosynchronous orbit case, showing behavior massive than electrically augmented hydrazine systems because of the optimal thrust direction, and developing transfer efficiency of the large fixed masses of additional batteries required. Solar figures for a range of acceleration limits. Both fixed-thrust and array power appears to be preferable for ion-propelled spacecraft. fixed-acceleration propulsion systems are considered. The effect For commercial use, ion propulsion will have to satisfy technical of multiple burns is discussed. Robbins's approximation for gravity problems with respect to life, contamination, RF noise, and loss is shown to be good for a large class of maneuvers. Author integration of the system into real spacecraft. Technical and political approaches to these problems are suggested. C.D.

A84-25344 INTERSTELLAR SOLAR SAILING - CONSIDERATION OF REAL A84-25292# AND PROJECTED SAIL MATERIALS A STANDARDIZED PROPULSION MODULE FOR FUTURE G. L. MATLOFF (Pratt Institute, Brooklyn, NY) British Interplanetary COMMUNICATIONS SATELLITES IN THE 2000 TO 3000 KG Society, Journal (Interstellar Studies) (ISSN 0007-084X), vol. 37, CLASS March 1984, p. 135-141. refs H. KELLERMEIER, D. E. KOELLE (Messerschmitt-Boelkow-Blohm The relevant theory of real partially transmitting films is GmbH, Ottobrunn, West Germany), and R. BARBERA (ESA, developed. Interstellar missions using 'real' beryllium and aluminium European Space Research and Technology Centre, Noordwijk, solar sails 5-30 nm thick are investigated, as is a mission using a Netherlands) IN: Communication Satellite Systems Conference, projected 10 nm composite sail. Analysis indicates that optimized 10th, Orlando, FL, March 19-22, 1984, Technical Papers . New performance projections for these sails do not vary appreciably York, American Institute of Aeronautics and Astronautics, 1984, p. from previous calculations for an idealized 90 percent reflective 345-353. sail with an area/mass thickness of 6 x 0.00001 kg/m sq and an (AIAA PAPER 84-0727) emissivity of 0.5. Substantial performance improvement is possible Applications of a propulsion module in the 2500 kg range are if a perforated sail is used in place of a hyper-thin, flat, metallic examined. Propulsion module technology in Europe is reviewed or composite sheet. The theory of two types of optical filters that and the goals of the Orbital Propulsion Module Study conducted might be relevant in the consideration of perforated solar sails, for ESA in 1983 are outlined. Propulsion systems investigated by although not entirely adequate in the visual spectral region, is the study for three types of missions are compared: (1) the GEO reviewed and discussed. Author insertion of an AR 44 L payload, (2) the GTO-GEO transfer of a Shuttle-launched spacecraft of three tons maximum, and (3) the LEO raising of a three-to-five ton spacecraft from the 300 km A84-27443# Shuttle orbit to some 1000 km with a moderate plane change. ROUNDTRIP INTERSTELLAR TRAVEL USING LASER-PUSHED Four major propulsion system alternatives are compared to each LIGHTSAILS other in terms of GEO payload and mission cost: a R. L. FORWARD (Hughes Research Laboratories, Malibu, CA) Journal of Spacecraft and Rockets (ISSN 0022-4560), vol. 21, satellite-integrated unified system, an attached unified propulsion module, a separable propulsion module, and an autonomous Mar.-Apr. 1984, p. 187-195. refs propulsion vehicle/stage. A conceptual definition of two different Design concepts for large lightsail spacecraft powered by propulsion modules resulting from the study is presented and solar-pumped lasers and capable of high-speed interstellar travel discussed. C.D. are proposed. Major components of the systems include circular thin-AI-film sails (optimum thickness about 16 nm for 650-nm radiation), powerful solar-driven CW-laser arrays with a 1000-km diameter in earth or solar orbit, and 1000-km-diameter Fresnel zone lenses to focus the laser beam. A fly-by mission to Alpha A84-25293# Centauri (with a 65-GW laser system, a 3.6-km-diameter sail, a UTILIZATION OF ELECTRIC PROPULSION FOR maximum speed of 0.11 c, and a travel time of about 40 yr), a COMMUNICATION SATELLITES /one-way rendezvous mission to Alpha Cen (7.2 TW, 100 km, 0.21 PH. SAINT-AUBERT (Matra SA, Toulouse, France), D. VALENTIAN c, 36 yr; deceleration phase 26 TW, 30 km, 5 yr), and a manned (SocieteEuropeenne de Propulsion, Vernon, Eure, France), and return mission to Epsilon Eridani (43 PW, 1000 km, 0.5 c, 51 yr W. BERRY (ESA, European Space Research and Technology earth time or 46 yr crew-aging time, including 5 yr for exploration) Centre, Noordwijk, Netherlands) IN: Communication Satellite are described and illustrated with drawings. T.K. Systems Conference, 10th, Orlando, FL, March 19-22, 1984, Technical Papers . New York, American Institute of Aeronautics A84-29869 and Astronautics, 1984, p. 354-364. refs MAKING THE HIGH FRONTIER HIGHLY VISIBLE WITH A (AIAA PAPER 84-0729) SOLAR SAIL RACE TO THE MOON The advantages and drawbacks of utilizing an electric propulsion G. PIGNOLET (Centre National d'Etudes Spatiales; Union pour la system for the station-keeping of future telecommunication Promotion de la Propulsion Photonique, Toulouse, France) IN: satellites are reviewed and analyzed. Two propulsion systems Space manufacturing 1983; Proceedings of the Sixth Conference, presently under development in Europe are used as reference Princeton, NJ, May 9-12, 1983 . San Diego, CA, Univelt, Inc., systems: The FEEP concept, where liquid caesium is ionized under 1983, p. 249-257. refs the field emission principle, and the RIT 10 concept, where the (AAS PAPER 83-226) ionization depends on radio frequency excitation of a gas. A mission It is felt that for too many people space and the possibilities it analysis is presented, and the optimization of the propulsion system offers remain too remote. It is difficult for the public to distinguish parameters using a solar array alone or combining an array with between science fiction and potential reality. What makes the on-board batteries, is discussed. C.D. difference is experience, sensory experience, and this is related

62 10 GENERAL directly to the structure of the human brain. It is thought that a N84-19474# Air Force Inst of Tech., Wright-Patterson AFB, race to the moon between several small solar sails could attract Ohio. School of Engineering. the attention to the reality of space. The sails would remain visible DISCONTINUOUS LOW THRUST ORBIT TRANSFER M.S. from the surface of the earth and could provide sustained interest Thesis for the world-wide public. The costs of such a race are also J. R. CASS, JR. Dec. 1983 64 p discussed. C.R. (AD-A136908; AFIT/GA/AA/83D-1) Avail: NTIS HC A04/MF A01 CSCL 21C This paper examines the use of discontinuous low thrust for N84-11206*# National Aeronautics and Space Administration. orbital transfers between two non-coplanar, circular orbits. The Lewis Research Center, Cleveland, Ohio. vehicle is assumed to be a solar-powered, ion rocket that cannot RESISTOJET PROPULSION FOR LARGE SPACECRAFT operate when it is within the Earth's shadow. Two timescales are SYSTEMS used to derive a minimum fuel trajectory. The fast timescale solution M. J. MIRTICH 1982 32 p refs Presented at the 16th maximizes a change in inclination when given a change in Intern. Elec. Propulsion Conf., New Orleans, 17-19 Nov. 1982; semi-major axis for a single orbit. The slow timescale solution sponsored by AIAA, the Japan Soc. for Aeron. and Space Sci., combines fast timescale results to obtain the minimum fuel and Deutsche Gesselschaft fur Luft-und Raumfarhrt trajectory. Results are presented for three specific transfers (NASA-TM-83489; E-1813; NAS 1.15:83489) Avail: NTIS HC requiring varying amounts of shadow penetration. It is shown that A03/MF A01 CSCL21H the fuel penalty caused by discontinuous thrust is small. However, Resistojet propulsion systems have characteristics that are there can be a moderate increase in total trip time if the time ideally suited for the on-orbit and primary propulsion requirements within the shadow is large. Author (GRA) of large spacecraft systems. These characteristics which offer advantages over other forms of propulsion are reviewed and presented. The feasibility of resistojets were demonstrated in space whereas only a limited number of ground life tests were performed. 10 The major technology issues associated with these ground tests are evaluated. .The past performance of resistojets is summarized GENERAL and, looks into the present day technology status is reviewed. The material criteria, along with possible concepts, needed to attain Includes either state-of-the-art or advanced technology which may high performance resistojets are presented. S.L. apply to Large Space Systems and does not fit within the previous categories. Publications of conferences, seminars, and workshops N84-12226*# Boeing Aerospace Co., Seattle, Wash. are covered in this area. STUDY OF AUXILIARY PROPULSION REQUIREMENTS FOR LARGE SPACE SYSTEMS. VOLUME 1: EXECUTIVE SUMMARY A84-10024*# National Aeronautics and Space Administration, W. W. SMITH and G. W. MACHLES Sep. 1983 22 p Washington, D. C. (Contract NAS3-23248) SPACE STATION AUTONOMY REQUIREMENTS (NASA-CR-168193-VOL-1; NAS 1.26:168193-VOL-1; J. L. ANDERSON (NASA, Washington, DC) IN: Computers in D180-27728-1) Avail: NTIS HC A02/MF A01 CSCL 21H Aerospace Conference, 4th, Hartford, CT, October 24-26, 1983, An insight into auxiliary propulsion systems (APS) requirements Collection of Technical Papers . New York, American Institute of for large space systems (LSS) launchable by a single shuttle is Aeronautics and Astronautics, 1983, p. 164-170. presented. In an effort to scope the APS requirements for LSS, a (AIAA PAPER 83-2352) set of generic LSSs were defined. For each generic LSS class a Several concepts of autonomy have emerged from space station specific structural configuration, representative of that most likely technology and mission studies. Unifying these concepts is to serve the needs of the 1980's and 1990's was defined. The important to enabling the needs for and requirements of environmental disturbance forces and torques which would be autonomous systems for a space station to be explored. One acting on each specific structural configuration in LEO and GEO purpose of autonomy related to a space station is to offload routine, orbits were then determined. Auxiliary propulsion requirements were demonstrated, precisely specifiable tasks and functions from determined as a function of: generic class specific configuration, humans to machines in order to increase habitability, increase size and openness of structure, orbit, angle of orientation, correction human-machine system productivity, or to decrease operational frequency, duty cycle, number and location of thrusters and costs. Defining incremental roles, functions, and technical direction of thrusters and APS/LSS interactions. The results of capabilities for autonomy leads to identification of computing this analysis were used to define the APS characteristics of: (1) systems technologies needed to enable various degrees of number and distribution of thrusters, (2) thruster modulation, (3) autonomy.. Author thrust level, (4) mission energy requirements, (5) total APS mass component breakdown, and (6) state of the art A84-10066*# National Aeronautics and Space Administration. adequacy/deficiency. S.L Goddard Space Flight Center, Greenbelt, Md. DATA SYSTEM ARCHITECTURE CONSIDERATIONS FOR A SPACE STATION N84-13218*# Boeing Aerospace Co., Seattle, Wash. E. B. CONNELL (NASA, Goddard Space Flight Center, Data STUDY OF AUXILIARY PROPULSION REQUIREMENTS FOR Systems Technology Office, Greenbelt, MD) IN: Computers in LARGE SPACE SYSTEMS, VOLUME 2 Final Report Aerospace Conference, 4th, Hartford, CT, October 24-26, 1983, W. W. SMITH and G. W. MACHLES Sep. 1983 305 p refs Collection of Technical Papers . New York, American Institute of (Contract NAS3-23248) Aeronautics and Astronautics, 1983, p. 472-477. (NASA-CR-168193-VOL-2; NAS 1.26:168193-VOL-2; (AIAA PAPER 83-2346) D180-27728-2) Avail: NTIS HC A14/MF A01 CSCL 21H The functions that a space station could serve are outlined A range of single shuttle launched large space systems were and details of the data systems requirements are discussed. The identified and characterized including a NASTRAN and loading data system design will be guided by an overall space systems dynamics analysis. The disturbance environment, characterization plan, and will feature distributed, layered architecture, user of thrust level and APS mass requirements, and a study of APS/LSS friendliness, hierarchical control, technology transparency, standard interactions were analyzed. State-of-the-art capabilities for chemical interfaces, and automated engineering tools. The station would and ion propulsion were compared with the generated propulsion begin with a limited core capability and evolve to serve functions requirements to assess the state-of-the-art limitations and benefits defined thereafter. The automation of the engineering tools will of enhancing current technology. Author be necessary to permit an optimized, minimized crew to control

63 10 GENERAL all functions of the space station, while at the same time freeing must be available in storage from the beginning, a project such the crew from being actively involved in maintaining the nominal as a space station. M.S.K. life support functions of the equipment. One major criterion is that the software must be error free, while another is adaptibility to A84-11722# changing space station configurations and demands. M.S.K. ESA SPACE STATION ACTIVITIES J. COLLET and G. PETERS (ESA, Directorate of Space A84-10883 Transportation Systems, Paris, France) International Astronautical SPACE APPLICATIONS AT THE CROSSROADS; PROCEEDINGS Federation, International Astronautical Congress, 34th, Budapest, OF THE TWENTY-FIRST GODDARD MEMORIAL SYMPOSIUM, Hungary, Oct. 10-15, 1983. 9 p. refs GREENBELT, MD, MARCH 24, 25, 1983 (IAF PAPER 83-30) J. H. MCELROY, ED. and E. L HEACOCK, ED. (NOAA, Washington, Current ESA space-station planning is surveyed, focusing on DC) Symposium sponsored by AAS, AIAA, American Society for the studies comprising the Long-Term Space-Transportation Aerospace Education, et al. San Diego, CA, Univelt, Inc. (Science Preparatory Programme. The present Spacelab, Ariane-2, 3, and and Technology Series. Volume 55), 1983, 308 p. 4, and European Retrievable Carrier (Eureca) projects are reviewed, NASA's accomplishments in space exploration in the quarter and the need for a European launch capability beyond Ariane-4, century since NASA was formed are reviewed and the directions a European space infrastructure, and continued cooperation with that could be taken in the near future are examined. The increases NASA is defined. User needs in the life sciences, material sciences, in spacefaring capabilities that were gained in the interval covering space science, remote sensing, communications, and industry are the Mercury program to near-operational status for the STS are described. Proposed ESA contributions to space-station design discussed, as are the historical, current, and future NASA include Spacelab-based habitation, logistics, and laboratory aeronautical research programs. Comparisons are made between modules; Eureca-based solar arrays and heat-pipe radiators; and the data available from the multispectral scanner and the thematic new designs for an orbital maneuvering vehicle (modular and mapper on board Landsat-4, particularly for land cover/use integrated versions are illustrated). The prospects for ESA/NASA applications. Attention is given to promising avenues for new cooperation in the space-station project are considered in terms classification schemes for the enhanced spectral range of the of political, economic, and technological factors. D.G. thematic mapper. D.H.K. A84-11723# A84-10965*# National Aeronautics and Space Administration. OVERVIEW OF SPACE STATION OPERATIONS Marshall Space Flight Center, Huntsville, Ala. W. C. SCHNEIDER (Computer Sciences Corp., Falls Church, VA) LAUNCH PROCESSING FOR SPACELAB 1 and J. H. DISHER International Astronautical Federation, R. O. MCBRAYER (NASA, Marshall Space Flight Center, Huntsville, International Astronautical Congress, 34th, Budapest, Hungary, Oct. AL) IN: Shuttle Environment and Operations Meeting, Washington, 10-15, 1983. 7 p. DC, October 31-November 2,1983, Collection of Technical Papers (IAF PAPER 83-38) . New York, American Institute of Aeronautics and Astronautics, Current planning and development for space-station operations 1983, p. 228-233. in the 1990's are summarized. The system elements (habitat, (AIAA PAPER 83-2622) power/utility module, multiple-docking/berthing module, logistics The final integration of Spacelab payloads with the Shuttle is module, discipline-oriented modules, teleoperator maneuvering described. Attention is given to launch processing planning, system, remote manipulation system, and ground support) and schedules, quality control, and problem reports and configuration capabilities (experiments, satellite service, upper-stage basing and maintenance. Also covered are the integration and checkout of servicing, structural fabrication or assembly, and operation of individual and combined experiments, mounting the end cones, tethered satellites) are characterized. It is shown that a station in attachment of the transfer tunnel, and inclusion of an extra a 450-km, 28.5-deg-inclined circular orbit with crew exchange and experiments pallet. The entire Spacelab module was subjected to resupply every 90-120 days could fulfill these requirements with a full systems simulation before deliverance to the Orbiter bay. an initial crew of 6-8 and mature-phase crew of 20-24. Launch Modular parts that were transferred from building-to-building were and support by the Space Shuttle are assumed. Consideration is placed in sealed containers filled with a purged atmosphere during given to data-management, mission-control, and operational safety transport. M.S.K. factors. The findings are illustrated with tables and graphs. D.G.

A84-11719# A84-11727# SPACE LOGISTICS EUROPEAN UTILISATION ASPECTS FOR A SPACE STATION D. S. EDGECOMBE, C. O. COOGAN, and R. R. TESTER (Battelle W. LEY and H. SAX (Deutsche Forschungs- und Versuchsanstalt Columbus Laboratories, Columbus, OH) International Astronautical fuer Luft- und Raumfahrt, Cologne, West Germany) International Federation, International Astronautical Congress, 34th, Budapest, Astronautical Federation, International Astronautical Congress, Hungary, Oct. 10-15, 1983. 9 p. 34th, Budapest, Hungary, Oct. 10-15, 1983. 8 p. Research (IAF PAPER 83-24) supported by the European Space Agency. Features of logistics for space missions are discussed with an (IAF PAPER 83-54) eye to existing trends and possible improvements. The thrust of The results of an ESA study on the payloads and benefits of space programs is shifting from exploration to exploitation of European participation in a NASA space station are reported. near-earth space, either through expansion of existing satellite Analyses and questionnaires were prepared of mission candidates capabilities or construction of a series of space stations. Payload in material sciences and processes, life sciences, space science dimensions and operating equipment are moving toward applications and technology, and new space utilization fields. standardization, in proven electronic components and in size to fit European hardware contributions to a space station were projected the Shuttle bay. Space stations and on-orbit servicing by the Orbiter as logistics, hangar, and experiments modules, as well as would extend the lifetimes of satellites while also encouraging retrievable free-flying platforms that would cany material' sciences, greater standardization of parts. A need then arises to stockpile biology, space sciences, and earth observation instrumentation. parts which may be subject to obsolescence because the assemby The usefulness of a manned presence for the space-based lines will have closed. The defense systems practice of front-end materials, life sciences, and space technologies is concluded valid, logistics analysis assimilates factors which impinge on the desired especially with regard to operations on a space station. The space degree of readiness and the ability to sustain operations over a station would be, in fact, a complement to present unmanned long time period. All components are analyzed for their criticality European space missions, and the human presence is essential and reliability to identify the logistics areas which are feasible to for constructing and maintaining larger, more complex apparatus alter, particularly for characterizing the parts and materials which in space. M.S.K.

64 10 GENERAL

A84-11728# The 2.2 m spacecraft will weigh about 3.5 tons, feature a 400 N SPACE STATION - A CANADIAN PERSPECTIVE thruster and propellant sufficient for a 400 m/sec velocity change, K. H. DOETSCH (National Aeronautical Establishment, Ottawa, and interface with the Orbiter RMS arm. The missions will support Canada) International Astronautical Federation, International biology, exobiology, and materials processing experiments. The Astronautical Congress, 34th, Budapest, Hungary, Oct. 10-15,1983. first mission will carry a protein crystallization experiment to provide 16 p. protein crystals for X ray diffraction studies, botany experiments (IAF PAPER 83-55) to determine the effect of gravity on plant growth, an experiment Canada's potential role in the development and operation of a to determine the long-term effect of space radiation on biological space-station infra-structure is discussed, reporting the results of materials, and the protection afforded biological materials by a survey of industrial, university, and government users and/or shielding equipment. The EURECA platform will maintain orbit for suppliers conducted in 1982-1983, in response to a NASA request. six months before lowering orbit for a passive capture by the Interest is found in applications from the fields of remote sensing, Orbiter. M.S.K. communications, materials processing, science, technology, medicine, and biology; while Canadian industry could contribute to A84-11773# such aspects as space construction and maintenance, THE FAIRCHILD LEASECRAFT SYSTEM - A large-solar-array design, flexible-structure design and control, and COMMERCIALLY-OPERATED PLATFORM FOR SCIENCE AND sensor-system development. It is suggested that most Canadian BUSINESS IN SPACE needs can be served by a combination of polar-orbit platforms for B. RAAB (Fairchild Space Co., Germantown, MD) International remote sensing, a low-inclination, low-earth-orbit, permanently or Astronautical Federation, International Astronautical Congress, intermittently manned research and development laboratory, and 34th, Budapest, Hungary, Oct. 10-15, 1983. 10 p. a local-orbit maneuvering vehicle to assemble and service them. (IAF PAPER 83-232) A block diagram of space infrastructures and graphs of the survey Design features and mission profiles for the Leasecraft responses are provided. T.K. free-flying platforms are described. The Leasecraft would use multimission modular spacecraft (MMS) configured for launch by A84-11737# the Shuttle, transfer to 28.5 deg polar sunsynchronous inclination AN OVERVIEW OF THE INSTITUTIONAL AND REGULATORY orbits, and return for later retrieval with the RMS arm, changeout ASPECTS AND THEIR IMPACT ON SYSTEM DESIGN and replacement of the payload, and return to the sunsynchronous F. M. GALANTE (Eutelsat, Paris, France) International orbit. The Leasecraft would have two optional solar power panels, Astronautical Federation, International Astronautical Congress, an attitude control subsystem, a special function module, and a 34th, Budapest, Hungary, Oct. 10-15, 1983. 11 p. TDRSS antenna, as well as a propulsion subsystem that would (IAF PAPER 83-82) also be refueled during Orbiter rendezvous. Payloads would be Attention is given to international regulations that are applicable categorized as primary or secondary, with the former claiming to geostationary orbit use by fixed satellite service systems, with priority on the spacecraft attitude, mission modes, and revisit a view to the means currently available for the reduction of potential intervals. An example of a primary mission would be the Advanced interference to acceptable levels through a system-coordination X-ray Astrophysics Facility, while secondary paylods could include process. This coordination process may result in either a reduction materials processing experiments and search and rescue of the capacity of the planned system, or in a reduction of service transponders. Primary services are expected to cost $2-4 quality. It is noted that if the interference environment is taken million/month, while secondary services run $0.5-1 million/month. into consideration at the time of a given system's planning, rather M.S.K. than at the coordination stage, it may be possible to achieve a system optimization that will reduce the negative economic impact A84-11779# of coordination. O.C. NATURAL SELECTION OF STELLAR CIVILIZATIONS BY THE LIMITS OF GROWTH A84-11739# M. D. PAPAGIANNIS (Boston University, Boston, MA) International COMMERCIAL COMMUNICATIONS SATELLITE MARKET AND Astronautical Federation, International Astronautical Congress, TECHNOLOGY IN THE 90'S 34th, Budapest, Hungary, Oct. 10-15, 1983. 9 p. refs R. T. FILEP (Communications 21 Corp., Redondo Beach, CA) (IAF PAPER 83-272) International Astronautical Federation, International Astronautical Evolution occurs in any system that possesses degrees of Congress, 34th, Budapest, Hungary, Oct. 10-15, 1983. 6 p. refs freedom to allow the appearance of new entities and constraints (IAF PAPER 83-86) to select a few of them to become part of the system which in A description is presented of a user requirement study which this manner continues to evolve. The limits of growth in a finite was conducted during the fall of 1982 to determine possible system, which will be imposed on all stellar civilizations by the commercial communications missions for a low-earth orbit space colossal distances that separate the stars, will become the station under consideration for the 1990s. The study included a constraint that will affect the natural selection of these civilizations. review of the literature on large space structures for Those that will manage to overcome their innate tendencies toward communications. The survey returns were grouped into four continuous material growth and replace them with non-material categories, taking into account missions relating to testing, space goals will be the only ones to survive this crisis. As a result the communications technology, scientific research priorities and entire galaxy in a cosmically short period will become populated suggestions for cost savings in space, and communications traffic by stable, highly ethical and spiritual civilizations. Author growth. In discussions regarding the space station, of considerable interest to many of the participants was the concept of the space A84-11787# station as a 'service station-in-the-sky'. Some interest was ANALYTICAL MODEL OF THE EVOLUTION OF ORBIT expressed in a low-earth orbit communications satellite. G.R. PARAMETERS OF A QUASI GEOSTATIONARY SATELLITE P. LEGENDRE (Centre National d'Etudes Spatiales, Toulouse, A84-11753# France) International Astronautical Federation, International UTILISATION OF THE EUROPEAN RETRIEVAL CARRIER Astronautical Congress, 34th, Budapest, Hungary, Oct. 10-15,1983. EURECA FOR LIFE SCIENCE RESEARCH 9 p. refs G. SEIBERT (ESA, Paris, France) International Astronautical (IAF PAPER 83-316) Federation, International Astronautical Congress, 34th, Budapest, The MASQ analytical model describing the evolution of the Hungary, Oct. 10-15. 1983, IAF Paper 83-169. 9 p. orbit parameters of a geostationary satellite maintained within a The design features, mission profiles, and functions of the narrow window (0.1 deg) in longitude and latitude is examined. EURECA free flying platform, to be launched from the Orbiter into The method used in developing the model involves expanding the a 500 km orbit, then return for retrieval at a later date, are described. perturbation functions in adapted orbit parameters and incorporating

65 10 GENERAL them in the Lagrange equations. The model is a secular evolution a MOD between NASA and ESRO in 1972, and was followed by model with sums of periodical terms; the periods are extensively configuration studies in both Europe and the U.S. It was decided variable and come under four different categories. The model is in 1973 that ESA would build the hardware and turn it over to shown to be sufficiently accurate to maintain geostationary satellites NASA, which would fly Spacelab on the Shuttle and buy a second in station and requires less computational effort than numerical Spacelab manned module. Once delivered, all responsibility for methods. V.L. Spacelab would be transferred to NASA. A total of 10 European countries participated in the design, construction, and testing, A84-11938* Jet Propulsion Lab., California Inst. of Tech., performed by a project team of 100 engineers and 40 industrial Pasadena. companies. Design reviews were performed until 1981, in concert SIMULATION OF THE GALILEO SPACECRAFT AXIAL - with hardware development of both Spacelab and pallets. The DELTA-V ALGORITHM Eureca free-flying platform is being developed as a follow-on J. M. LONGUSKI (California Institute of Technology, Jet Propulsion project, and studies are being conducted for activities in the future, Laboratory, Guidance and Control Section, Pasadena, CA) IN: such as participation in a space station. M.S.K. World Congress on System Simulation and Scientific Computation, 10th, Montreal, Canada, August 8-13, 1982, Proceedings. Volume 3 . Montreal, International Association for Mathematics and Computers in Simulation, 1983, p. 236-238. refs (Contract NAS7-100) Preliminary results are presented from the analysis of the Galileo A84-14586* Jet Propulsion Lab., California Inst. of Tech., spacecraft axial delta-V algorithm. The Galileo spacecraft is a dual Pasadena. spin interplanetary spacecraft which will study the four Galilean LARGE DEPLOYABLE REFLECTOR (LDR) - A CONCEPT FOR moons of Jupiter as well as the Jovian environment and AN ORBITING SUBMILLIMETER-INFRARED TELESCOPE FOR atmosphere. In order to achieve orbit about Jupiter and accurately THE 1990S deliver the probe to the planet's upper atmosphere, the Galileo P. N. SWANSON, S. GULKIS, T. B. H. KULPER (California Institute spacecraft must be capable of performing many trajectory of Technology, Jet Propulsion Laboratory, Pasadena, CA), and M. corrections or delta-V maneuvers. Twelve 10 Newton thrusters KIYA (NASA, Ames Research Center, Moffett Field, CA) Optical and one 400 Newton engine are utilized for this purpose. There Engineering (ISSN 0091-3286), vol. 22, Nov.-Dec. 1983, p. 725-731. are. many maneuver modes and control algorithms available to NASA-supported research, refs the spacecraft. In this paper only the analysis of the axial delta-V The history and background of the Large Deployable Reflector algorithm will be discussed. The analysis consists of two parts: (LDR) are reviewed. The results of the June 1982 Asilomar (CA) an analytic study and a simulation study. The analytic results are workshop are incorporated into the LDR science objectives and based on rigid body dynamics, while the simulation includes the telescope concept. The areas where the LDR may have the first order effect of the flexible magnetometer boom and nutation greatest scientific impact are in the study of star formation and damper. The simulation utilizes a program developed at JPL which planetary systems in the own and nearby galaxies and in allows flexible body effects to be simulated by modeling a collection cosmological studies of the structure and evolution of the early of rigid bodies attached together by hinges, springs and dampers. universe. The observational requirements for these and other In this preliminary study of the Galileo only two rigid bodies were scientific studies give rise to a set of telescope functional used in the simulation, but many more can and will be used in requirements. These, in turn, are satisfied by an LDR configuration the final tests. In this analysis, the algorithm appears to be working which is a Cassegrain design with a 20 m diameter, actively correctly and the analytic and simulation results agree very well. controlled, segmented, primary reflector, diffraction limited at a Author wavelength of 30 to 50 microns. Technical challenges in the LDR development include construction of high tolerance mirror segments, surface figure measurement, figure control, vibration A84-13376# control, pointing, cryogenics, and coherent detectors. Project status THE SPACELAB TEST PROGRAM and future plans for the LDR are discussed. Author J. K. VON DER LIPPE (Messerschmitt-Boelkow-Blohm GmbH; Raumfahrttechnik GmbH, Bremen, West Germany) AIAA, AHS, IES, SETP, SFTE, and DGLR, Flight Testing Conference, 2nd, Las Vegas, NV, Nov. 16-18, 1983. 12 p. (AIAA PAPER 83-2685) The design features, program organization, and tests of the A84-14764 Spacelab are described. Spacelab provides a shirtsleeve SPACEFLIGHT TO 2000 - INTERAVIA LOOKS FORWARD FROM environment for LEO missions lasting up to 30 days. The design THE PRESENT is modular and can accommodate up to three pallets as well as C. BULLOCH Interavia (ISSN 0020-5168), vol. 38, Nov. 1983, p. the pressurized vessel, with all components staying mounted in 1185-1192. the Orbiter bay. ESA provides design, development, and NASA and ESA space missions and technologies to the year manufacturing, as well as. the instrument pointing system, the first 2000 are discussed, together with economic and political factors flight payload package, and post-delivery support until after the impinging on the space activities. International cooperation is second flight. NASA will purchase a second Spacelab, supply essential for projects costing upwards of $10 billion, with one verification instrumentation for the hardware during the first two driving force being that nations must participate in space programs flights, and will construct the Spacelab tunnel. The final product or lose any technological competitiveness they could generate was constructed after complete testing of subsystem component, internally due to the cutting edge qualities of space technologies. and no environmental testing was performed on a complete system. Telecommunications will continually expand, with the STS Actual full system tests covered the initial power-up, interfaces, remaining the largest booster vehicle. ESA may develop a launcher EM compatibility, noise, off-gassing, leaks, mass properties, and for LEO applications, and use a lifting body first stage. Improved software. M.S.K. durability is planned for the Shuttle main engines, as are thrust augmentation and ceramic-lined chambers. Over 100 missions have A84-13901# been identified for a space station, and a range of orbit transfer SPACELAB'S DEVELOPMENT vehicles is being developed for a variety of applications. One M. BIGNIER (ESA, Paris, France) ESA Bulletin (ISSN 0376-4265), spin-off from space programs will be advances in computer no. 36, Nov. 1983, p. 6-11. technology because of current data rates from remote sensing Significant events in the international cooperation between ESA satellites, the need for a high level of artificial intelligence on a members and NASA in the development of Spacelab are outlined. space station, and remotely controlled devices such as free-flying The agreement to develop Spacelab in Europe was formalized in repair platforms. D.H.K.

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A84-15092 A84-15321 MISSION TO MARS - THE CASE FOR A SETTLEMENT FINANCING LARGE SPACE PROJECTS [LE FINANCEMENT DES C. STOKER (Colorado, University, Boulder, CO) and C. P. GRANDS PROJETS SPATIAUX] MCKAY Technology Review (ISSN 0040-1692), vol. 86, Nov.-Dec. M. E. LEVY (Paris, Banque Nationale, Paris, France) IN: 1983, p. 27-30, 35-37. Management of large space projects; Course on Space Technology, Scenarios and motivations for exploration, settlement, and Toulouse, France, May 3-14, 1982, Proceedings . Toulouse, exploitation of Mars are explored. Mars has an atmosphere that Cepadues-EditJons, 1983, p. 609-623. In French. contains enough oxygen to extract breathing gases, and the soil The arrangement possible for financing large space projects is mineralogically rich in elements suitable for the manufacture of are explored, together with various projects which can be construction materials, fuels, and soil for growing plants. The undertaken. The scale of financing is noted to be on the order location of Mars also serves as a gateway to the asteroids, which already experienced with petroleum, nuclear, natural gas production may be mined for raw materials. The Martian moons, Oeimos and and utilization facilities, the Airbus program, and international gas Phobos, are candidates for the development of asteroid mining pipelines. The projects depend on volume, time to operatinal status, techniques. The water supply on Mars consists of a 0.3 percent the novelty, international aspect, and the risks. Participants in the atmospheric concentration, the polar caps, and the potential for a venture comprise the promoter, the financiers, the public authorities, deeply penetrating permafrost that extends to the lower latitudes. and the clients. Financing plans include normal credit channels, NASA has a design for a Mars mapper satellite that could locate taking into account the associated risks and necessary advances the ground-frost areas of the entire planet. Ion-drive and solar-sail for capitalization, loans, credit-leasing arrangements, and through propulsive systems could provide power for the trip to Mars after concessions. Proposed and operational projects for which the the spacecraft have been assembled in earth orbit. The round-trip financing is necessary include the Ariane, the SPOT satellite, journey, plus landing, experimentation, and exploration, would last Spacelab, DBS satellites, and astronomical satellites. M.S.K. more than 2.5 yr. A larger data base is still needed to predict the health effects of the long journey in microgravity, isolation, and in exposure to occasional solar flare radiation. M.S.K.

A84-15161 MAN IN SPACE - AN OVERVIEW A84-15381 O. G. GAZENKO (Ministerstvo Zdravookhraneniia SSSR, Institut DEVELOPING THE SPACE FRONTIER; PROCEEDINGS OF THE Mediko-Biologicheskikh Problem, Moscow, USSR) Aviation, TWENTY-NINTH ANNUAL CONFERENCE, HOUSTON, TX, Space, and Environmental Medicine (ISSN 0095-0562), vol. 54, OCTOBER 25-27, 1982 Section II, Dec. 1983, p. S3-S5. A. NAUMANN, ED. and G. ALEXANDER, ED. (Lockheed The effects of the space environment on humans are reviewed Engineering and Management Services Co., Inc., Houston, TX) in the light of 22 years of experience, and the implications for Conference sponsored by the American Astronautical Society and future space-colonized projects are considered. The primary factors American Institute of Aeronautics and Astronautics. San Diego, discussed are cosmic radiation and weightlessness. While CA, Univelt, Inc. , 1983, 434 p. operations near the earth are shown to expose crew members to Projects which are planned, under development, in design, or only minimal amounts of radiation, interplanetary voyages will are being earned out as parts of the U.S. space program are involve exposure to relativistic androns which could affect vital discussed. Factors influencing the articulation of a U.S. space brain centers. Weightlessness brings numerous complications policy are examined from political, military, scientific, NASA, and related to changes in the afferent nervous system, the civilian viewpoints. Private sector participation in space activities cardiovascular system, and the loading of the musculoskeletal is explored in terms of remote sensing, the development of low-cost system which could well induce evolutionary changes in space spacecraft, and cooperative agreements among companies to fund colonists ('El Greco-type' humans in solar-system colonies or new space ventures. The implementation of government space species of the Homo genus in Galactic colonies). The risk factors development programs by government agencies is described, for current spacecraft crew members are shown to be comparable together with financial and business participation in space. Areas to those encountered by test pilots or professional boxers. T.K. requiring technological advance to commence space construction are delineated, covering propulsion, power sources, commercial needs, and data management systems. Economic, political, and A84-15189# social impediments and supports for space activities are assessed, GLOBAL IMPLICATIONS OF SPACE ACTIVITIES: AN as is progress in utilization and expansion of the capabilities of AIAA/ASPEN INSTITUTE ASSESSMENT the STS. Finally, the suitability of the Shuttle as a base for New York, American Institute of Aeronautics and Astronautics, development of the space frontier is examined. No individual items 1983, 7 p. are abstracted in this volume M.S.K. The impact of space technology on six areas of global impact was assessed by the AIAA and representatives of government, industry, and educational organizations in June 1983. Attention was given to percussions that would be felt in science, third world participation in space applications, space station policy, military activities, remote sensing, and technology transfer. Recommendations were developed that included continuance of A84-17026 the NASA Advanced Communications Technology program, COLLOQUIUM ON THE LAW OF OUTER SPACE, 25TH, PARIS, facilitating an open-door policy for remote-sensing data, FRANCE, SEPTEMBER 27-OCTOBER 2, 1982, PROCEEDINGS governmental sponsorship of meetings between representatives Colloquium sponsored by the International Astronautical Federation. of space-faring nations, encouragement of international New York, American Institute of Aeronautics and Astronautics, participation by scientists in the planning stages of a space station, 1983, 352 p. and efforts by the U.S. to benefit from the technologies of other International law aspects of outer space are addressed. The countries in planning future space stations. Continued open topics considered include: legal aspects of protection of the earth dissemination of nonclassified technological literature in the U.S. and outer space environment, legal aspects of the peaceful use is also advised, as are increased efforts to negotiate weapons of outer space in the light of Article IV of the 1967 Outer Space bans for space, separation of military and civilian space activities, Treaty, determination of applicable law to living and working in and persevering attention to the needs of developing countries in outer space, and legal aspects of direct broadcast satellites. space policy. M.S.K. C.D.

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A84-17054# solved in connection with such a project are related to JURISPRUDENTIAL PHILOSOPHIES OF THE ART OF LIVING environmental, societal, political, and institutional aspects. The IN SPACE THE TRANSNATIONAL IMPERATIVE present investigation is concerned with the initiation of a gradual, P. M. STERNS and L I. TENNEN IN: Colloquium on the Law of phased approach toward a Solar Power Satellite (SPS). Phase I Outer Space, 25th, Paris, France, September 27-October 2, 1982, of such an approach would involve the set-up of an organization Proceedings . New York, American Institute of Aeronautics and and the allocation of studies. The building of photovoltaic farms Astronautics, 1983, p. 187-202. refs and of an SPS pilot project would occur during the second phase, (IAF PAPER 82-IISL-38) while development and deployment of a full SPSS would take The parameters to be considered in determining the law place during the third phase. The developments are to be financed applicable to living and working in space are examined. In addition, under foreign aid. G.R. traditional jurisprudential philosophies are analyzed in terms of their rationale and policy considerations in the context of a space A84-17075# settlement. It is demonstrated that a jurisprudential philosophy ENERGY FROM SPACE - LEGAL IMPLICATIONS OF THE USE which transcends national legal structures will be necessary for OF THE GEOSTATIONARY ORBIT the continued existence of a space settlement. Such a philosophy S. GOROVE IN: Colloquium of the Law of Outer Space, 25th, will promote the interests and policies of all the participants in a Paris, France, September 27-October 2, 1982, Proceedings . New space settlement, in times of dispute as well as in times of peaceful York, American Institute of Aeronautics and Astronautics, 1983, p. coexistence. V.L 347-349. The provisions of international and treaty law governing the A84-17057# use of geostationary orbits (GEO) and the communications DETERMINATION OF APPLICABLE LAW TO LIVING AND spectrum associated with them are reviewed. The questions raised WORKING IN OUTER SPACE are considered especially important in the light of plans for L. FEKETE IN: Colloquium on the Law of Outer Space, 25th, solar-power satellites in GEO. The claims of national sovereignty Paris, France, September 27-October 2, 1982, Proceedings . New over portions of the GEO by equatorial nations in the Bogota York, American Institute of Aeronautics and Astronautics, 1983, p. Declaration of 1976 have been rejected, and the Outer Space 221, 222. refs Treaty of 1967 provides for free exploration and use of space. (IAF PAPER 82-IISL-44) The frequency-assignment resolutions of the successive WARC The international space law as it applies to national and meetings (1971, 1973, 1977, and 1979) on space international space crews is discussed. The subjects of space law telecommunications have also concerned themselves with GEO, are always states and never physical persons. States are obliged and call for 'equitable access' to GEO 'in practice'. Such provisions to see to it that their nationals conduct space activities in are interpreted to mean that nations can demand access to GEO accordance with international law. Space stations are under the slots or communications channels only when they possess the jurisdiction of the state on whose registry the station is launched technical capability to use them; no 'sharing in the benefits' (as into outer space. The law of the jurisdictional state applies to the stipulated in the Moon Agreement) is required. The need for more crew. Where the crew is an international one, the various states carefully defined criteria and the establishment of priorities for participating in the undertaking may agree between themselves future GEO use is stressed. T.K. as to the applicable law. C.D. A84-17076# A84-17058# CONSEQUENCES OF TRANSMISSION OF SOLAR ENERGY DETERMINATION OF APPLICABLE LAW TO LIVING AND FROM OUTER SPACE WORKING IN SPACE A. A. COCCA IN: Colloquium on the Law of Outer Space, 25th, H. DESAUSSURE (Akron, University, Akron, OH) and P. Paris, France, September 27-October 2, 1982, Proceedings . New HAANAPPEL (McGill University, Montreal, Canada) IN: Colloquium York, American Institute of Aeronautics and Astronautics, 1983, p. on the Law of Outer Space, 25th, Paris, France, September 351-353. 27-October 2, 1982, Proceedings . New York, American Institute The possible physical effects of MW, laser, or mirror-type SPS of Aeronautics and Astronautics, 1983, p. 223-228. refs transmissions and their legal implications are considered. The (IAF PAPER 82-IISL-45) bioeffects of the transmitted radiation and the atmospheric effects The existing body of international space law does not contain of transmission and of launcher-effluent injection (heating and a comprehensive set of rules dealing with living and working in ionospheric depletion) are examined, and the political aspects of outer space. In developing such a set of rules the international receiver siting (near the equator for GEO solar systems) are legal community can either follow a substantive law approach or indicated. The occupation of large portions of the MW band for a conflicts approach. This paper will deal with two recent SPS transmission and more generalized detrimental effects of SPS developments in U.S. domestic law which are relevant to the subject on space and terrestrial communications systems are explored, of living and working in space; first, a U.S. District Court decision and the provisions of the Space Treaty, the Liability Convention, on property and privacy law as affected by remote sensing from and (proposed) WARC Radio Regulations are discussed. Since the airspace; secondly, U.S. legislation giving U.S. courts criminal no specific regulations on the use of solar energy have been jurisdiction over launched spacecraft and personnel on board. Both adopted, a set of twelve basic tenets is proposed. The definition developments will be discussed and put into an international of solar energy and the GEO as nonappropriable parts of the context. Author 'common heritage of mankind' and the establishment of international organs (including a compulsory tribunal) to enforce A84-17074# the liability of SPS operators for ensuing damages and the fair THE SOLAR POWER SATELLITE - A PROGRAMME FOR sharing of soar resources are urged. T.K. DEVELOPMENT AID R. C. MEINER IN: Colloquium on the Law of Outer Space, 25th, A84-17077# Paris, France, September 27-October 2, 1982, Proceedings . New LEGAL ASPECTS OF SOLAR POWER SATELLITES IMPACT York, American Institute of Aeronautics and Astronautics, 1983, p. ON THE ENVIRONMENT 343-346. I. H. PH. DIEDERIKS-VERSCHOOR IN: Colloquium on the Law It is pointed out that there are essentially four types of foreign of Outer Space, 25th, Paris, France, September 27-October 2, aid. These types include the transfer of knowledge, the transfer 1982, Proceedings . New York, American Institute of Aeronautics of materials, the transfer of funds, and the provision of preferential and Astronautics, 1983, p. 355-363. refs agreements. A great number of studies have been conducted to There are three sources of the impact. The first has to do assess the pros and cons of a Solar Power Satellite System (SPSS). with the terrestrial operations connected with the construction of According to many, the most difficult problems which have to be the launching site, the space vehicles, the satellites themselves.

68 10 GENERAL and the receiving installations. The second concerns the transport It is believed that if the goals and benefits of the station are operations of the space vehicles carrying the satellites, and the specified too precisely, there may be insufficient interest and third the transmission of the solar energy back to earth. The overall support. The project should be approached as a long-term impact will comprise the biological effects of electromagnetic investment one that will enable the U.S. to continue making radiation, the atmospheric effects of radiation and launch effluents, progress in space. It is also believed that the efforts that the and the environmental effects of land requirements and the siting Soviet Union is making in this area should serve as an impetus to of launch facilities and ground-based energy receivers. The rules U.S. efforts. C.R. of space law that form the legal framework for this situation are set forth. A rudimentary foundation for protection of the environment does exist, thanks mainly to the Space treaty of 1967. The absence in current space law of any rule making it mandatory for states to A84-21344 act in such a way as to preclude any possibility of contaminating PROJECT SPACE STATION - PLANS FOR A PERMANENT the environment is decried. C.R. MANNED SPACE CENTER B. OLEARY (Science Applications, Inc., Pasadena, CA) Harrisburg, A84-17762 PA, Stackpole Books, 1983. 174 p. refs THE GERMAN SPACELAB MISSION D1 [DIE DEUTSCHE Plans and possibilities for a U.S. space station are discussed, SPACELAB-MISSION D1] and some visions of the human role in space at the turn of the N. KIEHNE and H. STEIMLE (Deutsche Forschungs- und century are presented. The Soviet role in space, the militarization Versuchsanstalt fuer Luft- und Raumfahrt, Cologne, West of space, the building of a space station from tinkermodules, and Germany) DFVLR-Nachrichten (ISSN 0011-4901), vol. 40, Nov. the use of space stations for industry, communications, and space 1983, p. 2-4. In German. travel are addressed. The possibility of mining precious metals in The goals, planning, and organization of the 7-day German asteroids is considered. Space station architecture, the construction Spacelab mission (D1) planned (in cooperation with NASA and of factories and hotels in space, commerce and homesteading in ESA) for mid-1985 are reviewed, with a focus on the roles played space, and space careers are discussed. C.D. by the DFVLR. The scientific payload components are listed in a table, and the biomedical, materials-science and processing, communications, and navigation experiments are characterized. DFVLR is responsible for choosing the experiments to be performed, developing and building the apparatus, integration of AB4-21476 the payload in the FRG, operational control of the mission, and ENERGY FROM SPACE; PROCEEDINGS OF THE SYMPOSIUM management of the program. Preparations are underway for the ON SOLAR ENERGY FROM SPACE, VIENNA, AUSTRIA, training of the ground personnel and the mission and payload AUGUST 9-21, 1982 specialists with a Spacelab simulator, and for staging operations J. W. FREEMAN, ED. (Rice University, Houston, TX) Symposium in cooperation with NASA to facilitate the integration of the D1 sponsored by the United Nations. Space Solar Power Review (ISSN payload into the STS. DFVLR project management is under the 0191-9067), vol. 4, no. 1-2, 1983, 192 p. supervision of a joint committee comprising both DFVLR and the Aspects of solar power generation in space are considered. FRG Science and Technology Ministry. A block diagram of the The subjects discussed include: a vision of future energy from organizational structure is provided. T.K. space; solar power satellite concept for utilization of energy from space; the institutional challenge of solar power satellites; system A84-17763 study of the solar power satellite concept; market potential and OPERATIONAL PLANNING, SIMULATION, AND PERFORMANCE possible limitations for satellite solar power stations; financing a OF THE GERMAN SPACELAB MISSION D1 [OPERATIONELLE solar power satellite project; and European questions related to PLANUNG, SIMULATION UND AUSFUEHRUNG DER satellite power systems. Also addressed are: options and high DEUTSCHEN SPACELAB-MISSION D1] payoff choices for transportation; an electric propulsion H. J. PANITZ (Deutsche Forschungs- und Versuchsanstalt fuer transportation system from low-earth orbit to geostationary orbit Luft- und Raumfahrt, Cologne, West Germany) utilizing beamed microwave power; the Canadarm robot arm of DFVLR-Nachrichten (ISSN 0011-4901), vol. 40, Nov. 1983, p. 5-10. the Shuttle Remote Manipulator System; an early experimental In German. solar power satellite; power economical considerations for the The current status of DFVLR preparations and planning for integration of terrestrial and extraterrestrial solar generators into the 7-day German Spacelab mission (D1) planned for June, 1985, existing power generation. stations; and space solar power in is reviewed, emphasizing operational rather than hardware aspects. perspective. C.D. The development of crew activity plans and operating procedures for the 100 scientific experiments, the selection and training of the two mission specialists and two payload specialists (using the Spacelab simulator being completed at Cologne), and the A84-21477 organization of the ground-support and communications systems ENERGY FROM SPACE - A VISION OF THE FUTURE are discussed. Drawings, block diagrams, and a sample activity P. JANKOWITSCH (Austrian National Assembly Parliament, Vienna, plan are included. T.K. Austria) (United Nations, Symposium on Solar Energy from Space, Vienna, Austria, Aug. 9-21,1982) Space Solar Power Review (ISSN A84-19850 0191-9067), vol. 4, no. 1-2, 1983, p. 3-10. SPACE STATIONS - A KEY TO SOCIO-ECONOMIC BENEFITS The SPS is one of the most promising nonprinting power FROM SPACE? generation options which could contribute to meeting global energy J. M. LOGSDON Earth-Oriented Applications of Space Technology demands in the 21st century. With proper organization and (ISSN 0277-4488), vol. 3, no. 3-4, 1983, p. 219-225. refs foresight, the nations of the world may one day collaborate in The way that the idea for a space station has evolved is traced. establishing a satellite solar power system to resolve their energy It was first proposed as a means for preparing for manned planetary needs. Intelsat and Inmarsat have emerged to provide exciting exploration. By 1966, however, it was concluded that such a station examples of the feasibility of such international efforts. The would be used instead for broadbased research and development implications of SPS deployment are international in scope. An programs in science and technology. In the latter part of the 1970s SPS would use outer space and radio frequency spectrum there was again a change, with the station now seen as an resources that are within the international domain. SPS would be operations center for constructing and maintaining space systems. subject to the present legal regime governing activities in outer Research was no longer to be the primary goal. At the present space which encompasses two international organizations and time, however, research is again being put forward as the rationale. three treaties. Author

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A84-21478 A84-21481 EVOLUTION OF THE SOLAR POWER SATELLITE CONCEPT - MARKET POTENTIAL AND POSSIBLE LIMITATIONS FOR THE UTILIZATION OF ENERGY FROM SPACE SATELLITE SOLAR POWER STATIONS P. E. GLASER (Arthur D. Little, Inc., Cambridge, MA) (United M. J. CLAVERIE and A. P. DUPAS (CNRS, Paris, France) (United Nations, Symposium on Solar Energy from Space, Vienna, Austria, Nations, Symposium on Solar Energy from Space, Vienna, Austria, Aug. 9-21, 1982) Space Solar Power Review (ISSN 0191-9067), Aug. 9-21, 1982) Space Solar Power Review (ISSN 0191-9067), vol. 4, no. 1-2, 1983, p. 11-21. refs vol. 4, no. 1-2, 1983, p. 49-59. refs The utilization of the inexhaustible resources available in space is discussed with emphasis on solar energy conversion in orbit for use on earth. The rationale for the solar power satellite (SPS) A84-21482 as a potential global energy supply option is presented, and the FINANCING A SOLAR POWER SATELLITE PROJECT evolution of this concept since 1968 is traced. Alternative concepts C. A. S. FAWCETT (Morgan Grenfell and Co., Ltd., London, for obtaining energy from space are also reviewed. The factors England) (United Nations, Symposium on Solar Energy from favoring the development of the SPS are highlighted, including Space, Vienna, Austria, Aug. 9-21, 1982) Space Solar Power projected dramatic increases in global electrical generating Review (ISSN 0191-9067), vol. 4, no. 1-2, 1983, p. 71-77. capacity. Environmental impacts and societal effects with emphasis It is pointed out that the solar power satellite project constitutes on international participation in an SPS program are considered a unique financial challenge because is represents the first attempt and the SPS is compared with alternative energy conversion to exploit extraterrestrial sources commercially. This project is to methods. The international implications of the SPS are underlined make electricity available to all nations from sources which are and the common interests of both developed and developing outside the claim of any nation. This transnational character of nations in the development of the SPS as a 21st century option the project and, in addition, the magnitude of the project costs, are recognized. The steps towards implementation of the SPS point to the desirability and the need for international funding. A option are outlined in the context of achieving the inevitable technique known as 'project financing' has been developed in the transition to renewable sources of energy. Author world's financial community specifically for the purpose of funding such very large ventures. Attention is given to details of project financing, the completion risk, the completion agreement, the economic risk (technological risk), aspects of equity, questions A84-21479 regarding the debt, and the United Nations revolving fund for natural SOLAR POWER SATELLITES - THE INSTITUTIONAL resources exploration. G.R. CHALLENGE J. M. LOGSDON (George Washington University, Washington, DC) (United Nations, Symposium on Solar Energy from Space, Vienna, Austria, Aug. 9-21,1982) Space Solar Power Review (ISSN A84-21483 EUROPEAN QUESTIONS RELATED TO SATELITE POWER 0191-9067), vol. 4, no. 1-2, 1983, p. 23-29. The tasks of designing, financing, developing, and operating a SYSTEMS solar power satellite (SPS) system would be as much organizational D. KASSING (ESA, European Space Research and Technology Centre, Noordwijk, Netherlands) (United Nations, Symposium on and institutional in character as they are technical and economic. The institutional character of a proposed SPS would be an issue Solar Energy from Space, Vienna, Austria, Aug. 9-21, 1982) Space Solar Power Review (ISSN 0191-9067), vol. 4, no. 1-2, 1983, p. of interest to almost all countries of the world, because the supply of large quantities of baseload of electricity by the SPS would 87-97. refs have global political and economic impact. This investigation has A number of problems which have been identified in recent the objective to provide some information regarding questions of European studies related to satellite power systems are addressed. organization and management of such a SPS, giving attention to Based on energy demand and supply projections for Europe, the point that similar (although far from identical) institutional developed by the International Institute for Applied Systems challenges have been solved. Thus, the International Analysis, the potential of power satellites in a future energy mix is Telecommunications Satellite Organization (Intelsat) is discussed discussed. A few major constraints are presented which may restrict power transmission to European receiving sites, e.g., orbital as an example. The reasons for the success of Intelsat are considered along with the limits to the Intelsat model, and the limitations, siting problems of the ground station, and economic global context for SPS development. G.R. and institutional issues. Conceptual designs for the structure of ground receiving stations located offshore near the European coastlines are described. Author

A84-21480* National Aeronautics and Space Administration. Lyndon B. Johnson Space Center, Houston, Tex. A84-21487 A SYSTEM STUDY OF THE SOLAR POWER SATELLITE SPACE STATION - AN EARLY EXPERIMENTAL SOLAR POWER CONCEPT SATELLITE R. O. PILAND (NASA, Johnson Space Center, Houston, TX) M. NAGATOMO (Tokyo University, Tokyo, Japan) (United Nations, (United Nations, Symposium on Solar Energy from Space, Vienna, Symposium on Solar Energy from Space, Vienna, Austria, Aug. Austria, Aug. 9-21, 1982) Space Solar Power Review (ISSN 9-21, 1982) Space Solar Power Review (ISSN 0191-9067), vol. 4, 0191-9067), vol. 4, no. 1-2, 1983, p. 35-47. no. 1-2, 1983, p. 143-154. refs The paper summarizes a system study of the solar power The Solar Power Satellite (SPS) is a typical macroengineering satellite (SPS) concept which was conducted in the 1977-1980 problem encompassing technical, social, and economic problems time period. The system study was sponsored by .the U.S. with many potential solutions, among which choices must be made. Department of Energy and the National Aeronautics and Space The 'macrophasing' project management concept presently Administration as part of an SPS Concept Development and introduced features a central facility for each of the several phases Evaluation Program. A reference system, developed during the which will serve as an experimental facility, demonstrating milestone study is described. The reference system was subsequently used achievements for each of the major SPS development problems. as a basis for environmental, economic, and societal assessments. The first phase will feature an orbital space station that is to be The reference system was recognized as probably not being an built within one decade. This dedicated space station may, after optimized approach. A number of alternate approaches which were furnishing valuable construction and operational experience, be studied in less depth are also described. The paper concludes used in turn as the construction platform for the larger (subscale) with a number of observations regarding the SPS concept, and models of the prospective SPS which constitute the second phase. the pertinence of ongoing space technology, development, and The third and last phase will emphasize economic evaluation of flight programs to various aspects of the concept. Author the system. O.C.

70 10 GENERAL

A84-21488 A84-21720 POWER-ECONOMICAL CONSIDERATIONS FOR THE SPACE 1991 INTEGRATION OF TERRESTRIAL AND EXTRATERRESTRIAL D. VELUPILLAI Flight International (ISSN 0015-3710), vol. 125, SOLAR GENERATORS INTO EXISTING POWER GENERATION Jan. 21, 1984, p. 163-165. SYSTEMS NASA's plans for a space station by 1991 are discussed. The I. B. STOY (Rheinisch-Westfaelisches Elektrizttaetswerk AG, Essen, space station, with a 500-km-high circular orbit inclined at 28.5 West Germany) (United Nations, Symposium on Solar Energy deg, is to be continuously manned, a staging post to higher orbits, from Space, Vienna, Austria, Aug. 9-21, 1982) Space Solar Power a satellite service center, and a platform for science and industry. Review (ISSN 0191-9067), vol. 4, no. 1-2, 1983, p. 155-167. It will comprise several repairable and evolvable modules and unmanned independent platforms, will have a 60 kW power capability, and will possess an open-loop life-support system for its rotating crew of six to eight people. An eventual self-sufficient A84-21489 colony is intended. Differences from the Space Shuttle will be the SPACE SOLAR POWER IN PERSPECTIVE station's electronic pilotage and distributed computer architecture G. R. WOODCOCK (Boeing Aerospace Co., Seattle, WA) (United with microprocessors controlling each task. Initial cost is estimated Nations, Symposium on Solar Energy from Space, Vienna, Austria, at $8,000 million spread over five years. Industry contracts are to Aug. 9-21, 1982) Space Solar Power Review (ISSN 0191-9067), be awarded for preliminary design of major elements, and vol. 4, no. 1-2, 1983, p. 169-181. refs international cooperation is indicated. C.M. When the solar power satellite (SPS) concept was introduced in 1968, it quickly became regarded as a fanciful idea which would not work. The claims made by early critics were mainly related to the assumed inefficiency of microwave power transmission, the problems concerning the construction and control of the required large space structures, the astronomical cost of space A84-22327 transportation, and the energy needed for delivery of the SPS to MANUFACTURING IN SPACE; PROCEEDINGS OF THE WINTER orbit. However, a number of studies and developments occurring ANNUAL MEETING, BOSTON, MA, NOVEMBER 13-18, 1983 at the time the criticisms were being leveled and afterwards showed L. KOPS, ED. (McGill University, Montreal, Canada) Meeting that many of the claims made by the critics were not true. The sponsored by the American Society of Mechanical Engineers. New present investigation synopsizes current knowledge of the SPS York, American Society of Mechanical Engineers (Production concept and reviews new circumstances not considered in Engineering Symposia Series. PED Volume 11), 1983, 223 p. evaluations conducted in 1980 and 1981. The technical challenges Processes, facilities, and issues related to manufacturing in are examined along with environmental issues, the 'reference outer space are addressed. The subjects discussed include: NASA, system1 created by DOE-NASA studies, cost issues, new European, and Japanese projects on materials processing in space; developments, and needs for further research. G.R. gravitational effects in dendritic growth; space research impact on semiconductor crystal growth technology; simulation prior to space manufacturing; hardware for materials processing in space; containerless science and technologies; a low orbit satellite A84-21497 manufacturing facility; remote manipulators in space; automation, MANNED PLANETARY MISSIONS? robotics, and machine intelligence systems in space manufacturing. R. C. PARKINSON (British Aerospace PLC, Dynamics Group, Also considered are: manufacturing space systems in space; Stevenage, Herts., England) Spaceflight (ISSN 0038-6340), vol. electrophoresis operations in space; rationale for commercial 26, Feb. 1984, p. 50-52. activities in space; Space Shuttle, private enterprise, and intellectual Manned planetary missions, mistakenly criticized as glamour properties in space manufacturing; manufacturers' liability for space projects, are shown to be more effective, more attractive and products; economics and profitability of space manufacturing; and less costly than unmanned missions; NASA is shown to outspend international cooperation and competition in materials processing ESA in both project types. The complexity of a manned mission in space. C.D. increases its information capturing ability and eliminates the need for multiple unmanned missions. Manned space activities will reduce costs with the proposed manned Space Station, which would serve as a transportation node to geosynchronous flight. The reusable Orbit Transfer Vehicle with large payload capability would move spacecraft to high orbit while decreasing the overall A84-22338# launching cost to approximately $11 million per ton. In conclusion MANUFACTURING SPACE SYSTEMS IN SPACE manned missions (e.g., to Mars and Jupiter) in coordination with G. R. WOODCOCK (Boeing, Kent Space Center, Kent, WA) IN: robots to maximize data collection are suggested. C.M. Manufacturing in space; Proceedings of the Winter Annual Meeting, Boston, MA, November 13-18, 1983 . New York, American Society of Mechanical Engineers, 1983, p. 127-137. It is pointed out that the strongest motivator for developing A84-21499 the initial steps in space manufacturing technology is the MANKIND'S INTERSTELLAR FUTURE opportunity afforded by the Space Shuttle to repair or maintain A. R. MARTIN Spaceflight (ISSN 0038-6340), vol. 26, Feb. 1984, spacecraft in low earth orbit. The steps that will be followed in p. 76-79. the repair of the Solar Max spacecraft are outlined. Even though Results of a questionnaire, based on the Delphi method, and this is a repair rather than a manufacturing mission, the steps to dealing with space predictions are presented. The results project be carried out are similar to those that could be used for mankind as a stellar civilization by the end of the 21st century. manufacturing in space. The use of EVA astronauts to simplify The questionnaires, answered by 15 individuals connected with deployment mechanism design is then discussed, noting that the space aspects, provide median dates and interquartile ranges for astronauts can readily remove launch retention fixtures, unfold a 11 space missions including the first manned mission to the Jupiter deployable device, and install braces or pip-pins, to place and system (2029), the use of solar system natural resources (2040), lock an appendage into its mission-operational position. This can and the mission colonization of an extrasolar planet (2260). A eliminate complex electromechanical drives and sequencers and, scenario forecast depicts humans as having landed on Phobos in many instances, provide a much stiffer structure in the process. and Deimos by 2005 and the establishment of L-5 colonies by A description is then given of the manufacturing processes foreseen 2075. C.M. for the space station. C.R.

71 10 GENERAL

A84-22341*# National Aeronautics and Space Administration, A84-24626* Washington, D. C. SPACE STATION: POLICY, PLANNING AND UTILIZATION; SPACE SHUTTLE, PRIVATE ENTERPRISE AND INTELLECTUAL PROCEEDINGS OF THE SYMPOSIUM, ARLINGTON, VA, JULY PROPERTIES IN THE CONTEXT OF SPACE MANUFACTURING 18-20, 1983 S. N. HOSENBALL and R. F. KEMPF (NASA, Washington, DC) M. GERARD, ED. and P. W. EDWARDS, ED. (American Institute IN: Manufacturing in space; Proceedings of the Winter Annual of Aeronautics and Astronautics, New York, NY) Symposium Meeting, Boston, MA, November 13-18,1983 . New York, American sponsored by the American Institute of Aeronautics and Society of Mechanical Engineers, 1983, p. 149-160. Astronautics and NASA. New York, American Institute of It is a national policy to make the capabilities of the Space Aeronautics and Astronautics , 1983, 221 p. Transportat ion System available to a wide range of potential The design, technology, and applications of the proposed Space users. This includes its availability as a space manufacturing facility Station (SS) are examined in contributions and discussions from for commercial activities, which may be carried out on a the AIAA/NASA Symposium on the Space Station held on July reimbursable basis or as a joint endeavor with NASA, but with 18-20, 1983. The role of man in space, the history of SS concepts, substantial private investment. In any high risk, long lead-time and the requirements of scientists, engineers, and commercial users research and development activity directed towards are reviewed. Discussion is included on military space activities; commercialization, the protection afforded the results of the the Solar Maximum Repair Mission; the role of the SS in earth research and development under the laws relating to intellectual sciences, life sciences, astronomy and astrophysics, and solar property rights may provide an important incentive for private physics; pharmaceutical manufacturing on the SS, satellite and investment. The paper reviews NASA's policies and practices for platform maintenance and repair from the SS; international the protection of privately-established intellectual property rights utilization of the SS; SS architectures and user concerns; the SS involved in STS use, with particular emphasis on reimbursable as an element of the total space-system architecture; productivity launch agreements and joint endeavor agreements. Author on an evolutionary SS, SS information and communications systems; and environmental-control and life-support systems for the SS. T.K. A84-22862# A CYLINDRICAL NEAR-FIELD TEST FACILITY FOR LARGE A84-24627*# National Aeronautics and Space Administration. SATELLITE ANTENNAS Lyndon B. Johnson Space Center, Houston, Tex. C.-P. FISCHER (Messerschmitt-Boelkow-Blohm GmbH, Munich, THE ROLE OF MAN IN SPACE West Germany) European Microwave Conference, 13th, J. R. LOUSMA (NASA, Johnson Space Center, Houston, TX) IN: Nuernberg, West Germany, Sept. 5-9, 1983, Paper. 6 p. refs Space station: Policy, planning and utilization; Proceedings of the (MBB-UR-628-83-OE) Symposium, Arlington, VA, July 18-20, 1983 . New York, American Recent developments in satellite antenna technology have the Institute of Aeronautics and Astronautics, 1983, p. 7-13. objective to achieve a more economical frequency spectrum The roles played by astronauts in space missions are discussed utilization for improved communication capacity. The approach using illustrations from the Spacelab and STS experience, and utilized in the implementation of this objective involves the the implications for the proposed space station are considered. employment of a narrow antenna beamwidth and frequency reuse. Man's ability to perform successfully for relatively long periods in Large reflectors will be needed along with high frequencies (up to space is demonstrated, and capabilities in manipulation, EVA, 40 GHz presently), low side lobe levels, excellent polarization purity, equipment repair and compensation for equipment failure, earth and high beam pointing accuracy. Spacecraft antennas will be observation, astronomy of sun and stars, and laboratory implemented as deployable reflector antennas with multifeed experimentation are characterized and illustrated with photographs. systems and antenna fine pointing mechanism built with Space station activities planned include repairs (like that of the carbon-fiber-reinforced plastic structures. Suitable approaches for Solar .Maximum Satellite), maintenance (of the Space Telescope), testing the antennas are discussed. It is found that near-field testing and construction and involve the use of a manned maneuvering provides major advantages over far-field testing in the considered unit, a teleoperator maneuvering system, and/or a manned or case. Attention is given to the principles of cylindrical near-field unmanned OTV. T.K. testing, the required instrumentation and the software, and test results. G.R. A84-24629# USE OF SPACE STATION FOR SCIENCE T. M. DONAHUE (National Academy of-Sciences, Washington, A84-23440* Chicago Univ., III. DC) IN: Space station: Policy, planning and utilization; Proceedings PYROELECTRIC MATERIALS AS ELECTRONIC PULSE of the Symposium, Arlington, VA, July 18-20, 1983 . New York, DETECTORS OF ULTRAHEAVY NUCLEI American Institute of Aeronautics and Astronautics, 1983, p. J. A. SIMPSON and A. J. TUZZOLINO (Chicago, University, 33-35. Chicago, IL) Physical Review Letters (ISSN 0031-9007), vol. 52, Scientific goals for the next 15 years in astronomy and Feb. 20, 1984, p. 601-604. refs astrophysics, earth sciences, planetary exploration, and solar and (Contract NGL-14-001-006; NGL-14-001-258) space physics are surveyed; the requirements of space missions The design and testing of ultraheavy-nucleus pulse detectors to attain them are listed; and the ability of the proposed space based on pyroelectric materials are reported, extending the station to fulfill the requirements is analyzed. The need for GEO, preliminary findings of Tuzzolino (1983) and Simpson and Tuzzolino deep-space, high-inclination-orbit, and free-flyer capabilities in (1983). Uranium-ion beams of about 240 MeV/u are detected by addition to a manned station in LEO at 28.5-deg inclination is a 39.5-micron-thick Si detector, degraded to about 175 MeV/u by identified: the manned station would serve primarily to service, Al absorbers, and then strike 700-micron-thick polyvinylidene launch, or even construct unmanned science vehicles which could fluoride or 1000-micron-thick LfTaO3 pyroelectric samples. Both serve the scientific needs better than experiments forcefully detector systems are connected to a coincidence circuit via adapted to the station itself. T.K. charge-sensitive preamplifiers, shaping amplifiers with 30-microsec effective time constants, and electronic discriminators. Sample A84-24631# spectra are shown, and the pulse heights measured are found to THE ROLE OF SPACE STATION IN EARTH SCIENCES agree with theoretical calculations to within a factor of about 2. L R. GREENWOOD (Fairchild Space Co., Germantown, MD) IN: The response of the pyroelectric materials is found to be unaffected Space station: Policy, planning and utilization; Proceedings of the by exposure to about 10 Mrad of 2-7-MeV/u heavy ion radiation. Symposium, Arlington, VA, July 18-20, 1983 . New York, American With further study and improvement of the detection sensitivity, Institute of Aeronautics and Astronautics, 1983, p. 66-72. refs devices of this type could be applied to large-area space Space-station or space-platform characteristics and measurements of low ultraheavy-ion fluxes. T.K. technologies required or desirable for future research in

72 10 GENERAL upper-atmosphere studies, global atmospheric chemistry, and communications to and from other spacecraft (TDRS) and meteorology, and climatology are examined, summarizing the free-flying vehicles for experiments (SPAS-01). These basic findings of a summer (1982) study by the Earth's Environment communication requirements will expand to the point where the Panel of the National Research Council Space Applications Board. man-computer alliance in the space station will transform the station Capabilities discussed include deployment of large numbers of into a space communications and computer center capable of sensors, high-inclination-orbit options, frequent recalibration and providing data processing and storage in association with intercalibration with satellites, introduction of new or larger lidar ground-based distributed processing along the growing terrestrial and microwave observatories, and repair and maintenance of ISDN global digital highway. The space station will also provide instruments and cooled detectors. Earth-science missions are found unique means to obtain data and information from one part of the to require only intermittent manned presence for maintenance and earth or space and transport them to another point on earth. calibration or for construction of large platforms for transfer to Author GEO, T.K. A84-24637# A84-24632# ENVIRONMENTAL CONTROL AND LIFE SUPPORT (ECLS) ROLE OF A SPACE STATION IN PHARMACEUTICAL DESIGN OPTIMIZATION APPROACH MANUFACTURING H. F. BROSE (United Technologies Corp., Hamilton Standard Div., J. T. ROSE (McDonnell Douglas Astronautics Co., St. Louis, MO) Windsor Locks, CT) IN: Space station: Policy, planning and IN: Space station: Policy, planning and utilization; Proceedings of utilization; Proceedings of the Symposium, Arlington, VA, July 18-20, the Symposium, Arlington, VA, July 18-20, 1983 . New York, 1983 . New York, American Institute of Aeronautics and American Institute of Aeronautics and Astronautics, 1983, p. Astronautics, 1983, p. 189-194. 79-84. The design of environmental-control and life-support (ECLS) The impact of the proposed space station on the commercial systems for the proposed space station is discussed. Design manufacture of Pharmaceuticals is discussed, with a focus on the constraints imposed by the overall station concept include crew prototype program (using electrophoresis) being developed by size and tour of duty, evolutionary vs. integral development, power McDonnell Douglas in cooperation with the Ortho Pharmaceutical concept, orbit-keeping and ACS concept, and EVA requirements. Corporation and NASA. The commercial organization of the The design process involves selecting the station scenario or range program is outlined, and the successful production tests carried of scenarios to be realized, setting the ECLS standards, reviewing out with the STS are briefly described and illustrated with concepts capable of meeting these standards, performing payback photographs and drawings. First test flight of a production-scale analysis, and selecting the technologies using specific criteria. prototype is planned for 1985, to be followed by an Basic, intermediate, and growth versions of a station ECLS system unmanned-free-flyer program and/or manned production on the are presented in block diagrams and characterized. A flexible space station. The economic advantages of the manned mode design approach applicable to different scenarios is are seen in ease of maintenance, lower transportation costs (raw recommended. T.K. materials and products only rather than whole vehicles or modules), and more rapid development of new products. T.K. A84-25251 COMMUNICATION SATELLITE SYSTEMS CONFERENCE, 10TH, A84-24635# ORLANDO, FL, MARCH 19-22, 1984, TECHNICAL PAPERS NATIONAL SECURITY IMPLICATIONS OF A U.S. SPACE Conference sponsored by the American Institute of Aeronautics STATION and Astronautics. New York, American Institute of Aeronautics C. W. COOK (USAF, Washington, DC) IN: Space Station: Policy, and Astronautics, 1984, 753 p. planning and utilization; Proceedings of the Symposium, Arlington, Topics are discussed which are related to satellite VA, July 18-20, 1983 . New York, American Institute of Aeronautics communications in Latin America, the efficient use of the and Astronautics, 1983, p. 145-157. geostationary orbit, spacecraft antennas, direct broadcast systems, The use of the proposed space station for military missions is communication networks, earth stations, Ka-band systems and discussed. The current military role in space is characterized hardware, mobile systems, launch system developments, and (unmanned communications and surveillance satellites), the DOD satellite evaluation and test. Other subjects considered are manned programs of the past are reviewed, and current projects concerned with Direct Broadcast Satellite (DBS) home terminals, in cooperation with NASA (manned-spaceflight-engineer program, regional and international systems, geostationary platforms and space test program, and space biotechnology program) are clusters, signal processing systems and technology, domestic examined. While DOD interest in further research on man's roles systems, propagation effects, advanced spacecraft bus technology, and capabilities in space remains high, and while the potential of military systems, systems availability and cost, and transponder a space station (e.g., for repairing or maintaining unmanned components, taking into account low power devices and power satellites on orbit) will continue to receive close attention, no military amplifiers. Attention is given to a low cost communications satellite missions requiring a manned space station or justifying DOD for developing countries, approaches for optimizing communications financing have been identified. A more evolutionary approach using satellite reliability, and digital technologies and systems for an extended STS and perhaps a space-based TMS is favored. geostationary orbit satellites. G.R. T.K. A84-25253# A84-24636# REDUCED DOMESTIC SATELLITE ORBIT SPACING SPACE STATION COMMUNICATIONS G. L SHARP (Federal Communications Commission, Washington, C. L. CUCCIA (Ford Aerospace and Communications Corp., Palo DC) IN: Communication Satellite Systems Conference, 10th, Alto, CA) IN: Space station: Policy, planning and utilization; Orlando, FL, March 19-22, 1984, Technical Papers . New York, Proceedings of the Symposium, Arlington, VA, July 18-20, 1983 . American Institute of Aeronautics and Astronautics, 1984, p. 7-17. New York, American Institute of Aeronautics and Astronautics, refs •> 1983, p. 182-188. (AIAA PAPER 84-0652) A concise history of the various types of communications that The demand for services provided by communications satellites have been used in low-earth-orbit vehicles and form the basis of in geostationary orbit is growing, and problems arise with respect the various types of communications and communication to the required increase in capacity. One approach for providing requirements that can be realized in space-station developments such an increase involves the employment of more satellites over the next decade is presented. The Space Shuttle can be operating at smaller orbital spacings. The present investigation is assumed to be a prototype space station in the tradition of Apollo concerned with the results of technical studies conducted by the and Spacelab. Shuttle operations require earth-to-ground support Federal Communications Commission (FCC) to determine the communications, EVA communications, internal communications, feasibility of reducing orbital spacings between U.S. 'domestic fixed

73 10 GENERAL satellites' (domsats). Attention is given to details regarding the integrated circuits, including speed, power consumption and usable orbital arc, an adjacent satellite interference model, antenna reliability are analyzed. Author sidelobe patterns, a single entry analysis, a 4/6 GHz aggregate analysis, results for the 4/6 GHz bands, results for the 12/14 GHz bands, data services, voice services, video reception, and high power spot beams. G.R. A84-25309# A84-25254# THE SPACE VAN AND ITS POTENTIAL IMPACT ON THE TIME PHASED INTRODUCTION OF ADVANCED DESIGN OF COMMUNICATIONS SATELLITES TECHNOLOGIES - ITS IMPACT ON ORBIT/SPECTRUM L. CORMIER (TranSpace, Inc., Washington, DC) IN: CONSERVATION Communication Satellite Systems Conference, 10th, Orlando, FL, D. TONG (Hughes Aircraft Co., El Segundo, CA) IN: March 19-22, 1984, Technical Papers . New York, American Communication Satellite Systems Conference, 10th, Orlando, FL, Institute of Aeronautics and Astronautics, 1984, p. 476-481. March 19-22, 1984, Technical Papers . New York, American (AIAA 84-0758) Institute of Aeronautics and Astronautics, 1984, p. 18-26. refs This paper outlines the impact that much lower transportation (AIM PAPER 84-0653) costs might have on the design of communications satellites. The It is pointed out that technical factors influence both the number first portion of the paper describes a launch vehicle, the 'Space of spacecraft which can occupy the geostationary orbit with Van,' which is fully reusable and promises to reduce transportation acceptable interference, and the amount of traffic which each . costs to synchronous orbit by a factor of between two and ten or spacecraft can carry. These factors are not static, but in a state more, depending upon the total tonnage transported. Such a of continuous evolution. It is suggested that the most practical reduction in transportation costs should be a powerful stimulus to procedure would involve the introduction of new technical standards new approaches to the design of communications satellites. The in stages over an extended period of time. The present investigation paper concludes with an outline of some concepts for these new has the objective to examine some of the foreseen improvements design approaches. Author in spacecraft and transmission technologies. Orbit conservation technologies are considered, taking into account spacecraft antenna improvements, earth station antenna improvements, and transponder technologies. Attention is given to telephony and record traffic-analog, telephony and record traffic-digital, analog television, and digital television. It is found that a number of A84-25318# techniques exist which can significantly increase the capacity of COMPUTER TOOLS FOR OPTIMIZING ORBIT USE the geostationary orbit. G.R. T. MIZUNO, Y. ITO, and T. MURATANI (Kokusai Denshin Denwa Co., Ltd., Research and Development Laboratories, Tokyo, A84-25281# Japan) IN: Communication Satellite Systems Conference, 10th, GEO SPACE PLATFORM ECONOMICS - IMPACT OF CONCEPT, Orlando, FL, March 19-22, 1984, Technical Papers . New York, SIZE, LAUNCH MODE AND LIFETIME American Institute of Aeronautics and Astronautics, 1984, p. D. E. KOELLE (Messerschmitt-Boelkow-Blohm GmbH; ERNO 549-557. Raumfahrttechnik GmbH, Ottobrunn, West Germany) IN: (AIAA PAPER 84-0651) Communication Satellite Systems Conference, 10th, Orlando, FL, The ORBIT-II orbit-spacing-optimization program for GEO March 19-22, 1984, Technical Papers . New York, American communications satellites is characterized and demonstrated. The Institute of Aeronautics and Astronautics, 1984, p. 241-248. refs problems inherent in current orbit-management (OM) techniques (AIM PAPER 84-0704) are discussed; the methods proposed to improve OM are surveyed The design of GEO communications platforms is examined from (earth and satellite antenna characteristics, positioning flexibility, an economic perspective. The historical and projected growth of transmission efficiency, and interference criteria); and the possible satellite services and spacecraft mass and capability is traced, administrative (WARC) approaches to OM are reviewed. The and the concepts proposed for large conventional satellites, ORBIT-II program represents a tool capable of optimizing both platforms with integrated transfer propulsion, modular platform positions and beam patterns, with world-map visualization of the assemblies, and large man-tended stations with service and repair results. Sample problems involving both a priori planning and the are reviewed. Spacecraft and launch costs are evaluated, taking phased introduction of orbit-conservation measures and including the impact of design lifetime into account. A decrease in as many as 94 satellites are calculated, and maps and tables of per-channel space-segment costs is predicted for larger satellites service-arc constraints are shown. D.G. and platforms. Graphs and tables of the numerical results and drawings of proposed systems are included. T.K.

A84-25304# DIGITAL TECHNOLOGIES AND SYSTEMS FOR A84-25319*# National Aeronautics and Space Administration, GEOSTATIONARY ORBIT SATELLITES Washington, D. C. R. PETERS (International Telecommunications Satellite LESSONS LEARNED DURING THE FIRST YEAR OF THE Organization, Washington, DC), R. RIEGER, and A. STANLEY TDRSS (Messerschmitt-Boelkow-Blohm GmbH, Munich, West Germany) R. O. ALLER and L. M. ROBINSON (NASA, Washington, DC) IN: Communication Satellite Systems Conference, 10th, Orlando, IN: Communication Satellite Systems Conference, 10th, Orlando, FL, March 19-22, 1984, Technical Papers . New York, American FL, March 19-22, 1984, Technical Papers . New York, American Institute of Aeronautics and Astronautics, 1984, p. 432-439. refs Institute of Aeronautics and Astronautics, 1984, p. 558-564. (AIM PAPER 84-0749) (AIM PAPER 84-0687) Power consumption, speed, and radiation resistance of bipolar The Tracking and Data Relay Satellite System (TDRSS) is the and CMOS technologies are reviewed for their suitability for use National Aeronautics and Space Administration's (NASA) newest in geosynchronous orbit satellites. Results of Intelsat sponsored capability for tracking and communicating with NASA's low-earth radiation tests on five complete microprocessor systems, plus orbiting scientific and operational satellites. This support will RAMs and PROMs, representing several different bipolar and eventually be provided through three identical satellites in CMOS techniques, are discussed with other recent test data. geosynchronous orbit. They will relay data through a single ground Radiation hardened CMOS devices proved quite radiation resistant, station located in New Mexico. This paper discusses both the had low power consumption and very low soft error rates, making overall TDRSS concept and NASA's experience to date with the' them well suited for satellite applications. Finally, future trends of first of the three relay satellites on station. Author 10 GENERAL

A84-253270 with the operational, almost routinewise, utilization of the cosmic DEVELOPMENT TRENDS IN EUROPE ON SATELLITE environment for humanity. The key to this development is the CLUSTERS AND GEOSTATIONARY PLATFORMS lowering of transportation costs by making use of a space U. RENNER (ESA, Communication Satellites Dept., Noordwijk, transportation system which is more economical than the one-way Netherlands) and J. NAUCK (ERNO Raumfahrttechnik GmbH, launch vehicles of the past Space industrialization can provide Bremen, West Germany) IN: Communication Satellite Systems access to the new world of space and utilize it for the common Conference, 10th, Orlando, FL, March 19-22, 1984, Technical good of mankind. Attention is given to details regarding the Space Papers . New York, American Institute of Aeronautics and Transportation System and plans for its utilization, the usable Astronautics, 1984, p. 622-628. refs characteristics of outer space, the aims of space industrialization, (AIAA PAPER 84-0703) products 'Made in Space', solar energy made available for terrestrial ESA development programs for advanced GEO communications applications with the aid of geostationary satellites, and the satellites or platforms are surveyed. The ongoing concentration of 'humanization' of space. G.R. space-communications traffic in the European region is evaluated, and a gradual transition from the current Eutalsat deployment (one 9-channel satellite in each of three orbital positions) to a configuration combining string-of-pearls clusters of medium-size A84-29063* Case Western Reserve Univ., Cleveland, Ohio. (18-channel) national satellites and large international platforms is GRAVITATIONAL BIOLOGY ON THE SPACE STATION predicted. The technology of clustering and platform assembly in J. R. KEEFE (Case Western Reserve University, Cleveland, OH) space, including TV observation of neighbor satellites, rendezvous, and A. D. KRIKORIAN (New York, State University, Stony Brook, and mechanical docking in LEO and/or GEO, is discussed. Various NY) AIAA, SAE, ASME, AlChE, and ASMA, Intersociety proposed vehicles and configurations are illustrated with drawings, Conference on Environmental Systems, 13th, San Francisco, CA, and the ESA efforts currently underway or planned (e.g., in-orbit July 11-13, 1983. 25 p. NASA-supported research, refs experiments using EURECA) are characterized. D.G. (SAE PAPER 831133) The current status of gravitational biology is summarized, future A84-28576 areas of required basic research in earth-based and spaceflight SYSTEMS CONSIDERATIONS IN MOSAIC FOCAL PLANES projects are presented, and potential applications of gravitational K. P. WHITE, III (Aerospace Corp., Los Angeles, CA) IN: Advanced biology on a space station are demonstrated. Topics covered remote sensing; Proceedings of the Meeting, San Diego, CA, August include vertebrate reproduction, prenatal/postnatal development, 26, 27, 1982 . Bellingham, WA, SPIE - The International Society a review of plant space experiments, the facilities needed for for Optical Engineering, 1983, p. 68-74. refs growing plants, gravimorphogenesis, thigmomorphogenesis, Two key reasons for pursuing the development of mosaic focal centrifuges, maintaining a vivarium, tissue culture, and artificial planes are reviewed and it is shown that rapid frame repetition human organ generation. It is proposed that space stations carrying rate is the only requirement that can be solved no other way than out these types of long-term research be called the National Space through mosaic focal planes. With the view that spaceborne mosaic Research Facility. C.M. focal plane sensors are necessarily 'smart sensors' requiring a lot of onboard processing just to function, it is pointed out that various artificial intelligence techniques may be the most appropriate to incorporate in the data processing. Finally, a novel mosaic focal plane design is proposed, termed a virtual mosaic focal plane, in A84-29126 response to other system constraints. Author U.S. NATIONAL CONGRESS OF APPLIED MECHANICS, 9TH, CORNELL UNIVERSITY, ITHACA, NY, JUNE 21-25, 1982, A84-28579 PROCEEDINGS COORDINATE TRANSFORMATION ASSEMBLY Congress supported by NSF, U.S. Navy, U.S. Army, et al. New C.-C. HUANG and J. BARNEY (Lockheed Missiles and Space York, American Society of Mechanical Engineers, 1982, 526 p. Co., Inc., Space Systems Div., Sunnyvale, CA) IN: Advanced Various topics in applied mathematics are addressed. The remote sensing; Proceedings of the Meeting, San Diego, CA, August subjects discussed include: two-phase flow, nonlinear fracture 26, 27, 1982 . Bellingham, WA, SPIE - The International Society mechanics, tribology, interfacial fluid mechanics, mechanical for Optical Engineering, 1983, p. 88-97. behavior of composite materials, large motions of systems The coordinate transformation assembly (CTA) is a noncontact containing flexible bodies, geophysical fluid dynamics, structural electrooptical device conceived to link the angular coordinates reliability and damage- assessment, electromagnetoelastic between two remote platforms to a high degree of accuracy. The interactions, flows in materials processing, qualitative theory of CTA is, therefore, highly desirable in cases in which the coordinates dynamical systems, and mechanics of energy technology. C.D. of one point have to be relayed around corners or over a number of obstacles to another point. It has been demonstrated that the CTA can be employed to measure slight angular shifts in the position of structures such as those inherent in the cargo of large A84-29656# spacecraft. The theoretical basis of CTA operation is discussed, THE RESIDUAL GRAVITATIONAL FIELD OF ORBITAL SPACE taking into account the roll coordinate, and pitch and yaw STATIONS [UEBER DAS RESTSCHWEREFELD IN ORBITALEN coordinates. Attention is given to the transmitter and receiver used RAUMSTATIONEN] in a laboratory setup. G.R. W. KNABE (ERNO Raumfahrttechnik GmbH, Bremen, West Germany) Deutsche Gesellschaft fuer Luft- und Raumfahrt, A84-28975# Jahrestagung, Munich, West Germany, Oct. 17-19, 1983. 16 p. In WITH THE SPACE SHUTTLE TOWARDS SPACE German, refs INDUSTRIALIZATION [MIT DER RAUMFAEHRE 'SPACE (DGLR PAPER 83-089) SHUTTLE' ZUR WELTRAUM-INDUSTRIALISIERUNG] The gravitational field within an orbiting space station and its J. VON PUTTKAMER IN: Annual report of the Frankfurt Physics influence on freely moving bodies in the station are investigated Union during the period Jan. 1, 1980 to Dec. 31, 1980, the 155th analytically. The field is shown to have a tensorial character, and year of the Union (Jahresbericht des physikalischen Vereins zu this finding is extended by analogy from Newtonian to modem Frankfurt am Main fuer die Zeit vom 1.1.1980 bis zum 31.12.1980, gravitational theory. The station is thus characterized as a freely 155. Vereinsjahr). Frankfurt am Main, Physikalischer Verein, 1982, falling inertial laboratory. Current gradiometric techniques for p. 47-67. In German. measuring the residual field are reviewed, and an alternative The -space transportation vehicle, 'Space Shuttle', introduces method theoretically applicable at near-zero gravity is proposed. an entirely new era for astronautics. The new era is concerned T.K.

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A84-29657# A84-29854 MICROGRAVITY CONDITIONS ON ORBITAL PLATFORMS PROBABLE MISSIONS AND TRANSPORTATION SCENARIOS [MIKROGRAVITATIONS-BEDINGUNGEN ORBITALER TO USE REGENERATIVE LIFE SUPPORT SYSTEMS PLATTFORMEN] T. VINOPAL, E. GUSTAN, and R. OLSON (Boeing Aerospace D. EILERS (ERNO Raumfahrttechnik GmbH, Bremen, West Corp., Seattle, WA) IN: Space manufacturing 1983; Proceedings Germany) Deutsche Gesellschaft fuer Luft- und Raumfahrt, of the Sixth Conference, Princeton, NJ, May 9-12, 1983 . San Jahrestagung, Munich, West Germany, Oct. 17-19, 1983. 20 p. In Diego, CA, Univelt, Inc., 1983, p. 27-43. refs German. ESA-sponsored research, refs (AAS PAPER 83-201) (DGLR PAPER 83-90) Six missions that could benefit from a controlled ecological life The design of orbital platforms to provide undisturbed support system type system are described along with their microgravity environments for experiments and manufacturing transportation and cost analyses: the Leo Low Inclination, the processes is discussed, with a focus on the European Retrievable Leo High Inclination, the 6 X GEO, the Lunar Base, the Asteroid Carrier (Eureca), a platform carrying a wide variety of payloads Base, and the Mars Surface Exploration. Each transportation for a 6-month mission in a 500-km orbit (with release and retrieval analysis consists of a trajectory analysis to determine the travel by the STS at 300 km). The microgravity requirements of the route, and a vehicle analysis to determine the most efficient rocket Eureca experiments are analyzed, and limits of 0.00001 g in the or group of rockets for the mission. Life support systems discussed 0.01-1-Hz frequency range, from 0.00001 to 0.001 g in the 1-100-Hz involve three materials supply methods: (1) storing materials on range, and about 0.001 Hz at higher frequencies are proposed. board at launch time for the entire mission, (2) periodically The verification methods currently employed in the Eureca design resupplying materials via a transportation vehicle, and (3) supplying process are characterized and illustrated. The natural phenomena all essential materials through waste recycling. Finally, cost affecting the microgravity environment (primarily residual estimates are provided for each mission on a per kilogram basis. atmosphere and gravitational gradients) and the effects of the C.M. platform systems (AOCS, thermal circulation, power supply, and data processing) and payloads are evaluated, and the allowable A84-29855 contributions of the subsystems to the microgravity 'budget' are SPACE STATIONS - THE NEXT STEP IN SPACE? presented in a table. T.K. J. M. LOGSDON IN: Space manufacturing 1983; Proceedings of the Sixth Conference, Princeton, NJ, May 9-12, 1983 . San Diego, A84-29658# CA, Univelt, Inc., 1983, p. 45-57. refs THE ATTITUDE AND ORBIT CONTROL SYSTEM FOR EURECA (AAS PAPER 83-202) [DAS BAHN- UND LAGEREGELUNGSSYSTEM FUER EURECA] This paper explores the question of whether a space station is G. LIPPNER and H. BAUER (Dornier System GmbH, the appropriate next major step in the U.S. space program. It Friedrichshafen, West Germany) Deutsche Gesellschaft fuer Luft- briefly traces past space station proposals, then reviews the kind und Raumfahrt, Jahrestagung, Munich, West Germany, Oct. 17-19, of forces affecting a possible decision within the next few years 1983. 6 p. In German. to proceed with a space station. The station is viewed as an (DGLR PAPER 83-091) investment opportunity which makes best sense if the United States The development of an AOCS for the European Retrievable is likely to pursue an active space program in coming decades. Carrier (Eureca) is reported.. The AOCS is designed to perform Author the transfer maneuver to a 500-km orbit after Eureca is released from the cargo bay of the STS, maintain attitude and orbit during A84-29856 the operational phase (about 6 months for the first flight), and UNDERSTANDING SPACE SETTLEMENTS AS HUMAN return Eureca to the STS orbit for retrieval. Major components SYSTEMS include sun and earth sensors; accelerometer; gyros; magnetic, F. WHITE (Human Systems, Inc., Newton, MA) IN: Space N2, and hydrazine positioning systems (the latter for orbit transfer); manufacturing 1983; Proceedings of the Sixth Conference, and control electronics. The AOCS design is modular, using the Princeton, NJ, May 9-12, 1983 . San Diego, CA, Univelt, Inc., modular attitude control system (MACS) bus to insure flexibility 1983, p. 59-84. refs for future Eureca modifications. The development of the AOCS (AAS PAPER 83-204) enters the C/D phase in June, 1984, with delivery of the first A unified approach to the development of space settlements flight unit for system integration planned for April, ,1986. Drawings, is discussed using as a framework Human Systems Theory. Human flow charts, block diagrams, and tables of hardware parameters systems as general systems are examined, and it is illustrated are provided. T.K. that the human mind, interacting with its environment, conceives of physical technologies to serve a need within the human system. A84-29852* Jet Propulsion Lab., California Inst. of Tech., The importance of human technologies interface and the Pasadena. development of a vision or purpose are demonstrated by three SPACE MANUFACTURING 1983; PROCEEDINGS OF THE SIXTH examples of companies that became successful human systems. CONFERENCE, PRINCETON UNIVERSITY, PRINCETON, NJ, In addition, pitfalls of North American colonies at Jamestown, MAY 9-12, 1983 Plymouth, and Massachusetts Bay are examined to alert space J. D. BURKE, ED: (California Institute of Technology, Jet Propulsion settlement planners. It is maintained that a successful human Laboratory, Pasadena, CA) and A. S. WHITT, ED. (Space Studies system requires a vision that supports the dynamic balance of Institute, Princeton, NJ) Conference sponsored by Princeton the physical, conceptual, and spiritual technologies of that system. University, American Astronautical Society, and Space Studies Finally, a proposal for a research program designed to generate Institute. San Diego, CA, Univelt, Inc. , 1983, 495 p. more knowledge about human systems for space applications is General topics are biomedical and social sciences, space proposed. C.M. stations and habitats, space manufacturing, international and legal considerations, materials resources and processing, accelerators A84-29857 and asteroids, and space economics. Among the papers presented, A PROGRAM TO DEVELOP EFFICIENT MANNED OPERATIONS consideration is given to the evolution of man as an explorer; IN SPACE whether people, robots, or hybrids should operate a space station; R. KLINE (Grumman Aerospace Corp., Bethpage, NY) IN: Space electrophoresis experiments in space; the emerging government manufacturing 1983; Proceedings of the Sixth Conference, regulation of American space entrepeneurs; the extraction and Princeton, NJ, May 9-12, 1983 . San Diego, CA, Univelt, Inc., purification of iron-group and precious metals from asteroidal 1983, p. 107-118. feedstocks; the construction, testing, and design comparison to (AAS PAPER 83-207) computer simulation fo the Mass-Driver III; and the international The evolutionary development of man's activities in space is competition in commercial aerospace markets. C.M. reviewed, and a program which combines man and machine for

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expanding on-orbit operations is discussed. The space station and and United States law. It is shown that both existing United States its general mission areas are covered: a National Space Test law and current regulation theory mandate a minimum exercise of Facility, a Transportation Harbor, Satellite Servicing, and an state supervision and authorization for a defined class of space Observatory. It is noted that as space missions change, the industrialiation activities and that they specify supervisory and •astronaut's tasks will expand to include tests set-up, data reduction, control responsibilities. This class of activity, together with the stage assembly, fueling operations, service, and repair. The supervisory and control responsibilities, is outlined. Statutory man-machine interface will change simultaneously with language is suggested pursuant to which firms will receive legal developments in robotics, artificial intelligence, and telepresence. charters to engage in a broad class of space development activity. Also examined are future manned and unmanned space stations On the basis of existing space law treaties and other fundamental in geosynchronous and hi-energy orbits. It is recommended that principles of international law, it is shown that state exercise of to use man efficiently in space, Shuttle Orbiter flights be used to supervision and authorization may range from state operation of develop space operational equipment, as well as demonstrate the all space activity to state responsibility for all space activity. equipment's applications to commercial, scientific, and defense C.R. communities. C.M.

A84-29865 A84-29883 MAJOR CONCERNS OF PRIVATE ENTERPRISE REGARDING INTERNATIONAL COMPETITION IN COMMERCIAL RECENT DEVELOPMENTS IN SPACE LAW AEROSPACE MARKETS S. GOROVE (Mississippi, University, University, MS) IN: Space A. M. DEERING (Johnson and Higgins, New York, NY) and W. A. manufacturing 1983; Proceedings of the Sixth Conference, GOOD (Earth Space Transport Systems Corp., New York, NY) Princeton, NJ, May 9-12, 1983 . San Diego, CA, Univelt, Inc., IN: Space manufacturing 1983; Proceedings of the Sixth 1983, p. 199-208. refs Conference, Princeton, NJ, May 9-12, 1983 . San Diego, CA, (AAS PAPER 83-221) Univelt, Inc., 1983, p. 421-430. refs This presentation starts out by recalling one of the early (AAS PAPER 83-244) concerns of private enterprise regarding the legitimacy of its The U.S. has not approached the subject of space commerce activities in outer space. The discussion moves on to a in a way which takes the best advantage of its competitive free consideration of some of the major concerns that have arisen in enterprise system. Many lessons can be learned by closely view of recent developments in space law. Among them are: (1) examining the relationship between government and entrepreneurs unresolved issues pertaining to the use. of the geostationary orbit; in the early days of air commerce. A review of recent international (2) similar issues regarding the exploitation of the moon and other trends in commercial space technology shows that the U.S. is not celestial bodies; (3) concerns about the international implications maintaining the technological leadership to which it is committed of direct television broadcasting by satellites; (4) misgivings about due to a suboptimal government/industry relationship vis a vis the adequacy of legal protection against damage, harm or other industrialized nations. Author interference which may occur in outer space; and, finally, (5) concerns about the state of governmental regulatory procedures. Author N84-10174*# Martin Marietta Corp., Denver, Colo. MOLECULAR CONTAMINATION MATH MODEL SUPPORT Final A84-29866* National Aeronautics and Space Administration, Report Washington, D. C. R. WELLS 30 Sep. 1983 97 p refs INTERNATIONAL ASPECTS OF COMMERCIAL SPACE (Contract NAS8-34945) ACTIVITIES (NASA-CR-170899; NAS 1.26:170899; MCR-83-640) Avail: K. S. PEDERSEN (NASA, International Affairs Div., Washington, NTIS HC A05/MF A01 CSCL 22B DC) IN: Space manufacturing 1983; Proceedings of the Sixth The operation and features of a preprocessor for the Conference, Princeton, NJ, May 9-12, 1983 . San Diego, CA, Shuttle/Payload Contamination Evaluation Program Version 2) are Univelt, Inc., 1983, p. 209-217. described. A preliminary preprocessor for SPACE 2 is developed. (AAS PAPER 83-222) Further refinements and enhancements of the preprocessor to Attention is given to problems in international cooperation that insure complete user friendly operation, are recommended. N.W. will arise if NASA proceeds with a Space Station. The rise in space budgets in many countries is cited as an indication of the growing importance being placed on space activities. It is also N84-10179# Applied Physics Lab., Johns Hopkins Univ., Laurel, pointed out that these nations are emphasizing areas which hold Md. promise for eventual commercial payoff. Developing countries are LARGE SPACE INSTRUMENTATION TO MEASURE THE also paying greater attention to space. As part of the European INTERACTION BETWEEN SPACE STRUCTURES AND THE Space Agency's development program, it is underwriting the ENVIRONMENT Final Report, 1 Oct. 1981 - 30 Sep. 1982 development of up to six multiuser facilities dedicated to C. I. MENG Dec. 1982 21 p microgravity research; these include furnaces and thermostats for (Contract MIPR-FY7121-82-00007; AF PROJ. 7661) processing metallurgical samples and for crystal growth and (AD-A129990; AFGL-TR-83-0059) Avail: NTIS HC A02/MF A01 botanical investigations. Competition from Europe is seen as a CSCL 14B spur to efficiency. Attention is also given to the question whether The major effort at the Applied Physics Laboratory of the Johns international cooperation will interfere with research carried out by Hopkins University while participating in the Air Force Geophysics the US for military purposes. C.R. Laboratory's planning of the polar orbiting space shuttle payload definition is to provide necessary information on the polar region A84-29868 space environment and suggestions on the various measurements A LEGAL CHARTER FOR NON-GOVERNMENTAL SPACE of the interaction between the space structure and the environment. INDUSTRIALIZATION During the first phase, the effort was concentrated on the polar M. A. ROTHBLATT (Schnader, Harrison, Segal and Lewis, region space environment, and results of the investigation were Washington, DC) IN: Space manufacturing 1983; Proceedings of presented to the first meeting of the IMPS Definition Phase at the Sixth Conference. Princeton, NJ, May 9-12, 1983 . San Diego, JPL. During the second phase of the program, the major effort CA, Univelt, Inc., 1983, p. 229-247. refs was on the investigation of possible instrumentation to perform (AAS PAPER 83-225) measurements of the interaction between space structures and Maximum and minimum legal bounds for the exercise of state the environment. Four measurements and their instrumentation supervision and authorization of nongovernmental activity in outer were conceived and suggested to the IMPS Definition Team. These space 'are specified. Legal limits are given in both international are summarized here. Author (GRA)

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N84-12228*# National Aeronautics and Space Administration. N84-16420*# National Aeronautics and Space Administration, Langley Research Center, Hampton, Va. Washington, D. C. INTEGRATED FLYWHEEL TECHNOLOGY, 1983 THE US SPACE STATION: POTENTIAL BASE FOR A C. R. KECKLER, ed., G. E. RODRIGUEZ, ed. (NASA. Goddard SPACEBORNE MICROWAVE FACILITY Space Flight Center), and N. J. GROOM, ed. Washington Dec. D. MCCONNELL In JPL Spaceborne Imaging Radar Symp. p 1983 205 p refs Workshop held in Greenbelt, Md., 2-3 Aug. 144-156 1 Jul. 1983 1983 Avail: NTIS HC A08/MF A01 CSCL 22B (NASA-CP-2290; L-15707; NAS 1.55:2290) Avail: NTIS HC Concepts for a U.S. space station were studied to achieve the A10/MFA01 CSCL 10C full potential of the Space Shuttle and to provide a more permanent Topics of discussion included: technology assessment of the presence in space. The space station study is summarized in the integrated flywheel systems, potential of system concepts, following questions: Given a space station in orbit in the 1990's, identification of critical areas needing development and, to scope how should it best be used to achieve science and applications and define an appropriate program for coordinated activity. objectives important at that time? To achieve those objectives, of what elements should the station be comprised and how should the elements be configured and equipped. These questions are addressed. E.A.K. N84-14752# CAP Sogeti Logiciel, Toulouse (France). Space Branch. N84-16677# Technische Univ., Darmstadt (West Germany). Inst. SOFTWARE PRODUCTION IN A LARGE SPACE PROJECT: THE of Physical Geodesy. SPOT MISSION CENTER GEODETIC ASPECTS OF ESA PROJECTS, STUDIES AND V. T. KHANG In ESA Software Eng. p 185-190 Aug. 1983 INVESTIGATIONS refs E. GROTEN In Technische Univ. Geodesy and Global Geodyn. Avail: NTIS HC A13/MF A01 p 429-438 1982 refs The MULTIPRO software workbench used to manage the Avail: NTIS HC A02/MF A01 software production of a team of up to 20 engineers on the SPOT Some of the various ESA projects which are of basic interest (French satellite) is described. The software runs on CDC Cybers to the advancement of modern geodesy are considered. Besides or the SEMS Solaris 16. Software tools were developed for the projects also studies and investigations sponsored by ESA or firmware of the terminals, a librarian and a document generator. carried out in ESA-offices and at ESA-facilities are mentioned. A detailed analysis language, not part of the workbench, is used References are given where more detailed information can be on the Cyber as required by quality assurance. Author (ESA) found. Author

N84-16991*# Iowa Univ., Iowa City. Dept. of Physics and N84-16075*# National Aeronautics and Space Administration. Astronomy. Marshall Space Flight Center, Huntsville, Ala. INTERPRETATION OF STS-3/PLASMA DIAGNOSTICS SIGNIFICANT SCIENTIFIC AND TECHNICAL RESULTS AT PACKAGE RESULTS IN TERMS OF LARGE SPACE STRUCTURE MARSHAL SPACE FLIGHT CENTER Annual Report for 1983 PLASMA INTERACTIONS Semiannual Technical Progress Nov. 1983 83 p refs Report, 10 Jul. 1983 - 25 Jan. 1984 (NASA-TM-82562; NAS 1.15:82562) Avail: NTIS HC A05/MF W. S. KURTH 27 Jan. 1984 19 p A01 CSCL 05B (Contract NAG3-449) Research programs in atmospheric science, materials (NASA-CR-173266; NAS 1.26:173266) Avail: NTIS HC A02/MF processing in space, and space sciences as well as technology A01 CSCL 20! programs in space power, materials processes, and space The Plasma Diagnostics Package, which was flown aboard structures are discussed. Author STS-3 recorded various chemical releases from the Orbiter. Changes in the plasma environment were observed to occur during Flash Evaporator System (FES) releases, water dumps and maneuvering thruster operations. During flash evaporator N84-16097*# Essex Corp., Huntsville, Ala. operations, broadband Orbiter-generated electro-static noise is SPACE TELESCOPE Final Report enhanced and plasma density irregularity (delta n/N) is observed E. C. PRUETT, K. B. ROBERTSON, C. N. VANVALKENBURG, to increase by as much as 4 times and is strongly peaked below and W. REED 13 Sep. 1983 34 p 6 Hz. In the case of water dumps, background electrostatic noise (Contract NAS8-33272) is enhanced or suppressed depending on frequency and Delta (NASA-CR-170948; NAS 1.26:170948; H-83-06) Avail: NTIS HC N/N is also seen to increase by as much as 4 times. Various A03/MF A01 CSCL 03A changes in the plasma environment are effected by primary and Space telescope drawings, mockup drawings, space support vernier thruster operations. In addition, thruster activity stimulates equipment, and Spacelab experiment hardware are discussed. electrostatic noise with a spectrum which is most intense at N.W. frequencies below 10 kHz. Author

N84-17050# La Jolla Inst., Calif. IDENTIFICATION OF NEW POTENTIAL SCIENTIFIC AND N84-16242*# National Aeronautics and Space Administration. TECHNOLOGY AREAS FOR DOD APPLICATION. SUMMARY John F. Kennedy Space Center, Cocoa Beach, Fla. OF ACTIVITIES Final Technical Report, 2 Aug. 1982 - 2 Aug. STS-9: ORBITAL WORKSHOP SPACELAB TO FLY ON NINTH 1983 SHUTTLE MISSION 2 Aug. 1983 301 p Oct. 1983 8 p (Contract MDA903-82-C-0376; ARPA ORDER 3710) (NASA-TM-85497; KSC-231-83; NAS 1.15:85497) Avail: NTIS (AD-A134372; UI-U-83-252) Avail: NTIS HC A14/MF A01 HCA02/MFA01 CSCL 22A CSCL 05A The first non-astronants are discussed. Spacelab is described. Document reports on highlights of this year's program, including Spacelab objectives, Spacelab 1 investigations, atmospheric laser propagation in the atmosphere, laser beam clean-up in Raman physics and Earth observations, space plasma physics, solar amplifiers, X-ray laser research, utilization of the external tanks of physics and astronomy, material sciences and technology the Space Shuttle, and the Status of Solid State materials suitable development, and life sciences are discussed. N.W. for high power lasers. GRA

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N84-17223'# Department of Communications, Ottawa (Ontario). N84-20605*# Engineering and Economics Research, Inc., Vienna, Space Technology and Applications Branch. Va. CANADIAN ATTITUDE SENSING EXPERIMENTAL PACKAGE AN ATTACHED PAYLOAD OPERATIONS CENTER (APOC) AT (CASEP) THE GODDARD SPACE FLIGHT CENTER (GSFC), VOLUME 1 A. H. REYNAUD In NASA. Langley Research Center STEP Final Report Expt. Requirements p 165-176 Jan. 1984 refs 7 Dec. 1983 101 p 2 Vol. Avail: NTISHC A15/MFA01 CSCL 22B (Contract NAS5-26962) The Canadian Attitude Sensing Experiment Package (CASEP) (NASA-CR-175160; NAS 1.26:175160) Avail: NTIS HC A06/MF was designed to demonstrate and verify the operation of an attitude A01 CSCL 14B sensing subsystem prior to committing its use on an operational A management overview of the Attached Payload Operations mission. Data telemetry/recording requirements, power and Center (APOC) functional requirements and design are presented. physical requirements, and mission requirements of the experiment The rationale for developing the APOC concept and the package are defined. M.G. assumptions utilized are presented. A summary of the concept complete with major functional areas and associated data flows is provided. The attributes of this concept are formalized and the necessary resources needed for its development and operation presented. S.L. N84-18315# European Space Agency, Paris (France). SPACELAB DATA BOOK N. LONGDON. comp. and J. HUNT, ed. Sep. 1983 127 p Original contains color illustrations N84-20613# Committee on Commerce, Science, and (ESA-BR-14; ISSN-0250-1589) Avail: NTIS HC A02/MF A01 Transportation (U. S. Senate). The Spacelab program is outlined. Crew training, functions, CIVIL SPACE STATION and accommodation are described. Safety factors; accommodation Washington GPO 1984 91 p refs Hearing before the for experiments; structural design; the Igloo; command and data Subcomm. on Sci., Technol. and Space of the Comm. on Com., management subsystem; electrical power distribution; environment Sci. and Transportation, 98th Congr., 1st Sess., 15 Nov. 1983 control; and the transfer tunnel are described. Ground operations; (S-REPT-98-523; GPO-29-426) Avail: Subcommittee on ground support; mission operations; and possible developments Science, Technology and Space are outlined. Author (ESA) How present uses of space can be extended and how other capabilities can be developed that have a unique applicability to a permanent presence in space are issues explored. Existing alternatives for accomplishing the nation's objectives in space are examined and the advantages and disadvantages of each are N84-19371*# Stanford Telecommunications, Inc., McLean, Va. considered. Private sector involvement, the possibility of STUDY OF A TRACKING AND DATA ACQUISITION SYSTEM international cooperation, and the functions and concepts for a FOR THE 1990'S. VOLUME 3: TDAS COMMUNICATION mixture of manned and unmanned elements are discussed. MISSION MODEL Draft Final Report A.R.H. T. MCCREARY 31 May 1983 122 p refs Prepared in cooperation with Space Communications Co., Gaithersburg, Md. (Contract NAS5-26546) N84-20617*# Lockheed Aircraft Corp., Burbank, Calif. (NASA-CR-175195; NAS 1.26:175195; STI/E-TR-25066-VOL-3) ON-ORBIT SPACECRAFT/STAGE SERVICING DURING STS Avail: NTIS HC A06/MF A01 CSCL 22A LIFE CYCLE Final Report A parametric description of the communication channels 27 Jan. 1984 140 p refs required between the user spacecraft to be supported and the (Contract NAS9-15800) user ground data systems is developed. Scenarios of mission (NASA-CR-171775; NAS 1.26:171775; LMSC-D931673) Avail: models, which reflect a range of free flyers vs space platform NTIS HC A07/MF A01 CSCL 22B usage as well as levels of NASA activity and potential support for A comprehensive and repesentative set of shuttle payloads military missions, and potential channel requirements which identify: was identified for shuttle and space station servicing missions. (1) bounds on TDAS forward and return link data communication The classes of servicing functions were determined and the general demand, and (2) the additional demand for providing servicing support required for the set of referenced spacecraft navigation/tracking support are covered. Author was allocated. A candidtate strawman space station was depicted from a synthesis of space station concepts derived from NASA space station architecture studies done by eight contractors. The shuttle servicing hardware and kits were identified and their N84-19429# Dornier-Werke G.m.b.H., Friedrichshafen (West applicability in transitioning servicing capability to the space station Germany). was evaluated. A.R.H. THE COMPLEMENTARY ROLES OF EXISTING AND ADVANCED ENVIRONMENTAL, THERMAL CONTROL AND LIFE SUPPORT TECHNOLOGY FOR SPACE STATIONS N84-21145# Massachusetts Inst. of Tech., Cambridge. A. I. SKOOG and H. F. BROSE (Hamilton Standard, Windsor Locks, IMPLEMENTATION OF MACLISP ON A LARGE ADDRESS Conn.) In ESA Environ, and Thermal Control Systems for Space SPACE COMPUTER Final Report Vehicles p 281-288 Dec. 1983 refs J. MOSES 21 Dec. 1983 4 p Avail: NTIS HC A25/MF A01 (Contract DE-AC02-79ER-10357) The role of existing technology, especially Shuttle and Spacelab (DE84-005042; DOE/ER-10357/1) Avail: NTIS HC A02/MF equipment, and the evolution to incorporation of advanced A01 hardware in a closed loop environmental thermal control and life This is a belated final report on the implementation of NIL - support (ETCLS) system are discussed. Analyses of regenerative the New Implementation of LISP. Work on this project began in and closed loop systems performed during Space Operations 1978 and is still continuing. The original timetable for the project - Center, Manned Space Platform, Space Station and Spacelab two years - slipped badly. Over four years were used to get a programs are reviewed. Cabin atmosphere, hygiene, water working version ready for distribution. At this point over 130 copies management, and galley requirements are considered. It is of the NIL System were distributed and many of the users find it concluded that a considerable amount of existing ETCLS equipment superior to all available alternatives on the DEC VAX. In that can be used for space stations. Author (ESA) sense the project was quite successful. DOE

79 10 GENERAL

N84-21437*# Terra-Mar, Mountain View, Calif. N84-21442# Committee on Science and Technology (U. S. ALTERNATIVE STRATEGIES FOR SPACE STATION House). FINANCING REVIEW OF THE NATIONAL AERONAUTICS AND SPACE ACT D. C. WALKLET and A. T. HEENAN 1 Sep. 1983 33 p refs OF 1958 (Contract NASW-3750) Washington GPO 1984 41 Op Hearings before the Subcomm. (NASA-CR-175412; NAS 1.26:175412) Avail: NTIS HC A03/MF on Space Sci. and Appl. of the Comm. on Sci. and Technol., 98th A01 CSCL 05C Congr., 1st Sess., 18, 19, 25. 26 Oct. 1983 The attributes of the proposed space station program are (GPO-28-915) Avail: Subcommittee on Space Science and oriented toward research activities and technologies which generate Applications long term benefits for mankind. Unless such technologies are Whether the policy objectives contained in the National deemed of national interest and thus are government funded, they Aeronautics and Space Act of 1958 adequately reflect the direction must stand on their own in the market place. Therefore, the and scope of NASA's future is explored including whether NASA's objectives of a United States space station should be based on ability to keep pace with changes in the space program is in any commercial criteria; otherwise, such a project attracts no long way limited by the agency's charter. Major trends which are term funding. There is encouraging evidence that some potential significantly changing the nature of the civilian space program space station activities should generate revenues from shuttle discussed include space commercialization, increased emphasis related projects within the decade. Materials processing concepts on national security, and international cooperation and as well as remote sensing indicate substantial potential. competition. A.R.H. Futhermore, the economics and thus the commercial feasibility of such projects will be improved by the operating efficiencies available with an ongoing space station program. B.G. N84-21443# Committee on Commerce, Science, and Transportation (U. S. Senate). NATIONAL AERONAUTICS AND SPACE ADMINISTRATION AUTHORIZATION ACT, 1985 Washington GPO 1984 21 p H.R. 5154 enacted into law by the 92nd Congr., 2d Sess., 28 Mar. 1984 N84-21440# Committee on Appropriations (U. S. Senate). Avail: US Capitol, House Document Room DEPARTMENT OF HOUSING AND URBAN Appropriations to the National Aeronautics and Space DEVELOPMENT-INDEPENDENT AGENCIES APPROPRIATIONS Administration for research and development, space flight, control FOR 1984: NATIONAL AERONAUTICS AND SPACE and data communications, construction of facilities, and research ADMINISTRATION and program management, and for other purposes are authorized. In its Dept. of Housing and Urban Develop., and Certain The provisions of the bill are presented. S.L. Independent Agencies Appropriations, 1984, Pt. 2 p 1133-1387 1984 N84-21444# Committee on Science and Technology (U. S. Avail: Comm. on Appropriations House). Research and development activities in the areas of space NATIONAL AERONAUTICS AND SPACE ADMINISTRATION transportation systems, space stations, space scence, technology AUTHORIZATION ACT, 1985 utilization, aeronautical research and technology, space research, Washington GPO 1984 22 p A bill, H.R. 5154, referred to energy technology, space tracking and data systems and the Comm. on Sci. and Technol., 98th Congr., 2d Sess., 15 Mar. construction of facilities are summarized. Achievements of the past 1984 year were also summarized. B.G. (H-REPT-98-629) Avail: US Capitol, House Document Room Appropriations are authorized to the National Aeronautics and Space Administratin for research and development, space flight, control and data communications, construction of facilities, and research and program management, and for other purposes. The N84-21441# Committee on Science and Technology (U. S. provisions of the bill are presented. S.L. House). AUTHORIZING APPROPRIATIONS TO THE NATIONAL N84-21590# European Space Agency, Paris (France). AERONAUTICS AND SPACE ADMINISTRATION FOR FISCAL INTRODUCTION TO GEOSTATIONARY ORBITS YEAR 1985 E. M. SOOP (ESOC, Darmstadt, West Germany) and W. R. BURKE, Washington GPO 1984 222 p Presented in accompaniment ed. Nov. 1983 148 p refs to H.R. 5154 to the Comm. on Sci. and Technol., 98th Congr., 2d (ESA-SP-1053; ISSN-0379-6566) Avail: NTIS HC A07/MF A01 Sess., 21 Mar. 1984 The laws governing spacecraft motion in geostationary orbit, (H-REPT-98-629; GPO-31-451) Avail: US Capitol, House and the orders of magnitude of perturbing effects on the orbit are Document Room discussed. Orbital maneuvers, perturbed orbits, in orbit control, The Committee on Science and Technology recommends eclipse effects, stationkeeping, and orbit determination are passage of the funding appropriations bill to NASA for research introduced. Author (ESA) and development, space flight, control and data communications, construction of facilities, and program management. Principal areas of activity in space transportation capability, relate to Spacelab, N84-21592*# Rockwell International Corp., Downey, Calif. Space high altitude satellite orbit placement, payload operations, and Operations Center. advanced programs study and evaluation. The completion of the SHUTTLE INTERACTION STUDY Quarterly Review fleet of shuttle orbiters along with mission preparation and control 3 Sep. 1980 86 p contribute to the fulfillment of the Space Transportation System. (Contract NAS9-16153) The advanced systems program performs studies and aids (NASA-CR-173400; NAS 1.26:173400; PD80-55; QR-1) Avail: development of improved capabilities in tracking and data systems NTIS HC A05/MF A01 CSCL 14B for new missions and to improve cost effectiveness and reliability The role of the Space Operations Center (SOC) as it effects for overall support of the spaceflight missions. The research and the missions of the space shuttle was analyzed. Graphic program management appropriation funds the performance and representation of space shuttle docking procedures with attention management of research, technology, and test activities at NASA to the docking module was presented. Other topics included installations along with the planning, and support of contractor extravehicular activity options, space station evaluation, space research and development in aeronautical and space research. logistics of the SOC, equipment interfacing, and SOC buildup MAC. scenarios. MAC.

80 10 GENERAL

N84-21593*# Rockwell International Corp., Downey, Calif. Space Operations Center. SHUTTER INTERACTION STUDY EXTENSION Monthly Progress Report, 6 Oct - 6 Nov. 1981 Oct. 1981 14 p (Contract NAS9-16153) (NASA-CR-173401; NAS 1.26:173401; MPR-3) Avail: NTIS HC A02/MFA01 CSCL 14B Plans for space shuttle missions as they effect the Space Operation Center (SOC) were examined. Shuttle fleet utilization, traffic analysis, SOC assembly operations, SOC propellant storage, and flight support facilities were studied with cost estimates, and completion schedules included. MAC.

N84-21594*# Rockwell International Corp., Downey, Calif. Space Operations Center. SHUTTLE INTERACTION STUDY EXTENSION Final Review Feb. 1982 257 p (Contract NAS9-16153) (NASA-CR-173398; NAS 1.26:173398; PD82-1 A) Avail: NTIS HCA12/MFA01 CSCL 14B The following areas of Space Shuttle technology were discussed: variable altitude strategy, spacecraft servicing, propellant storage, orbiter plume impingement, space based design, mating (docking and berthing), shuttle fleet utilization, and mission/traffic model, B.G.

N84-21595*# Rockwell International Corp., Downey, Calif. Space Operations Center. SHUTTER INTERACTION STUDY Monthly Progress Report, 19 Sep. - 24 Oct 1980 Oct. 1980 68 p (Contract NAS9-16153) (NASA-CR-173402; NAS 1.26:173402; MPR-3) Avail: NTIS HC A04/MFA01 CSCL 14B The deployment, transport, and exchange procedures for the SOC logistics module and for logistics modules/cradles envisioned to support both the flight support facilities operation and the space construction operation were developed. The use of a holding and positioning aid device was determined to be the most desirable arrangement for the parking/holding of the modules during this exchange operation. The capability/feasibility of transporting eight crew members in the orbiter to and from the SOC was analyzed. Two arrangements were defined for this operation: (1) with the airlock in the orbiter cabin, and (2) with no airlock in the cabin. Author

N84-21596*# Rockwell International Corp., Downey, Calif. Space Operations/Integration and Satellite Systems Div. SHUTTLE INTERACTION STUDY EXTENSION Midterm Review 15 Oct. 1981 160 p (Contract NAS9-16153) (NASA-CR-173403; NAS 1.26:173403; PD81-20A) Avail: NTIS HC A08/MF A01 CSCL 14B The implications of using the Shuttle with the SOC were analyzed, including constraints that the Shuttle places upon the SOC design. All the considerations involved in the use of the shuttle as a part of the SOC concept were identified. Author

81 SUBJECT INDEX

TECHNOLOGY FOR LARGE SPACE SYSTEMS / A Bibliography (Supplement 11) JANUARY 1985

Typical Subject Index Listing

ADAPTIVE CONTROL AEROSPACE SCIENCES SUBJECT HEADING The spatial order reduction problem and its effect on Developing the space frontier; Proceedings of the adaptive control of distributed parameter systems Twenty-ninth Annual Conference, Houston, TX, October p33 A84-19056 25-27, 1982 p 67 A84-15381 Multivariable direct adaptive control for a general class STEP Experiment Requirements of time-varying commands p 33 A84-19118 [NASA-CP-2294] p7 N84-17211 Some applications of direct adaptive control to large Space Technology Experiments Platform (STEP) ALIGNMENT structural systems p 34 A84-25496 overview p8 N84-17212 —Surface accuracy measurement sensor test on a Direct multivariable model reference adaptive control AEROSPACE SYSTEMS 50-meter antenna surface model with applications to large structural systems NTC '82; National Telesystems Conference, Galveston, [NASA-TM-85689] p 17 N84-16427 p38 N84-15840 TX, November 7-10, 1982, Conference Record ADAPTIVE FILTERS p44 A84-15623 Characteristics of the microprocessor implementation T Project space station - Plans for a permanent manned of algorithms for the processing of radio signals and noise space center - Book p69 A84-21344 in large antenna arrays p 48 A84-28067 AEROSPACE TECHNOLOGY TRANSFER i ADHESION TESTS NASA Space applications at the crossroads; Proceedings of REPORT PAGE Electrically conductive black optical paint TITLE ACCESSION p 55 A84-28553 the Twenty-first Goddard Memorial Symposium, Greenbelt, NUMBER NUMBER MD, March 24, 25, 1983 p 64 A84-10883 NUMBER AERODYNAMIC CONFIGURATIONS STEP mechanical systems p8 N84-17213 NASA priority technologies [IAF PAPER 83-345] p1 A84-11793 AERODYNAMIC HEATING Global implications of space activities: An AIAA/ ASPEN The subject heading is a key to the subject content Thermal control of tethered satellite in a very low altitude aerodynamic mission p 27 N84-19444 Institute Assessment — Book p 67 A84-15189 STEP Experiment Requirements of the document. The title is used to provide a AERODYNAMIC LOADS [NASA-CP-2294] p7 N84-17211 description of the subject matter. When the title is Simplified models and computational schemes of the STEP experiment integration p8 N84-17215 insufficiently descriptive of the document content, aerodynamic load — large space structures p28 N84-21614 Deployable beam flight experiment (MAST) p8 N84-17218 the title extension is added, separated from the title AERODYNAMIC STABILITY AIRBORNE/SPACEBORNE COMPUTERS by three hyphens. The (NASA or AIAA) accession Research on boundary feedback and control theories, Space station data management - A system evolving 1978-1983 number and the page number are included in each from changing requirements and a dynamic technology [AD-A136531] p 41 N84-18987 entry to assist the user in locating the abstract in base AERODYNAMICS [AIAA PAPER 83-2338) p 43 A84-10016 the abstract section. If applicable, a report number STEP mechanical systems p8 N84-17213 is also included as an aid in identifying the AEROELASTICITY Space station autonomy requirements Aggregate models for distributed parameter systems [AIAA PAPER 83-2352] p 63 A84-10024 document. Under any one subject heading, the A voice interactive system for aiding and documentation accession numbers are arranged in sequence with with applications to flexible air and spacecraft p31 A84-11945 of space-based tasks [AIAA PAPER 83-2355] p 43 A84-10025 the AIAA accession numbers appearing first. Aeroelastic stability and response of flexible tactical Space station communications p 73 A84-24636 weapons AIRCRAFT CONSTRUCTION MATERIALS [AIAA PAPER 84-0392] p 32 A84-18060 Research and technology, 1983 AERONAUTICAL ENGINEERING [NASA-TM-85702] p7 N84-12026 Research and technology, 1983 Composite structural materials [NASA-TM-85702] p7 N84-12026 [NASA-CR-173259] p 56 N84-17293 AEROSPACE ENGINEERING AIRCRAFT CONTROL ACCURACY Vibration characteristics of self-expanding stayed Aggregate models for distributed parameter systems Surface accuracy measurement sensor test on a columns for use in space p34 A84-21237 Higher temperature composite joints survive elimination with applications to flexible air and spacecraft 50-meter antenna surface model p31 A84-11945 [NASA-TM-85689] p 17 N84-16427 tests pSS A84-29565 ALGORITHMS ACTIVE CONTROL Graphite/polyimkJe joints extend temperature limits pSS A84-29572 Algorithms and computational aspects pertaining to Active control of large flexible space structures block diagonal dominance methods for design of Research and technology, 1983 p37 N84-14235 decentralized feedback compensation [NASA-TM-85702] p 7 N84-12026 Experimental study of active vibration control p 15 A84-19108 [AD-A133818] p 38 N84-14546 AEROSPACE ENVIRONMENTS Canadarm and the Space Shuttle p 57 A83-44602 Direct multivariable model reference adaptive control ACOSS Fourteen (Active Control of Space Structures) with applications to large structural systems [AD-A133411] p38 N84-15181 Man in space - An overview p67 A84-15161 p38 N84-15840 Space Technology Experiments Platform (STEP) ACOSS eleven (Active Control Of Space Structures), Spline-based estimation techniques for parameters in volume 1 overview p8 N84-17212 elliptic distributed systems [AD-A135675] p 40 N84-18311 The effects of the space environment on damping [NASA-TM-85439] p9 N84-17947 materials and damping designs on flexible structures ACOSS eleven (Active Control Of Space Structures), Time domain analysts and synthesis of robust controllers volume 2 p56 N84-17217 for large scale LOG (Linear Quadratic Gaussian) [AD-A135676] p 41 N84-18312 Environmental effects on the dynamics and control of regulators ACTUATORS an orbiting large flexible antenna system [AD-A137760] p 43 N84-21172 [NASA-CR-175448] p 42 N84-20627 ALIGNMENT On the number and placement of actuators for Surface accuracy measurement sensor test on a independent modal space control — (or large flexible AEROSPACE INDUSTRY spacecraft p 34 A84-24990 Management of large space projects; Course on Space 50-meter antenna surface model Technology. Toulouse. France. May 3-14. 1982. [NASA-TM-85689] p 17 NS4-16427 The dynamics and control of large flexible space ALUMINUM ALLOYS structures. 6 Proceedings p2 A84-15301 SiC-rernforced-aluminum alloys for aerospace [NASA-CR-174450] p 36 N84-10173 Human organization — and space project management p2 A84-15303 applications p54 A84-28242 Actuator placement considerations for the control of ALUMINUM OXIDES large space structures p20 N84-11199 The contract — management for space projects p2 A84-15304 Assessment of reliability of ceramic materials IPACS guidance navigation and control system p54 A84-24508 considerations and test activities p 37 N84-12245 The progression of projects — in space industry ANISOTROPIC PLATES Experimental study of active vibration control p2 A84-1S305 Buckling and vibration of any prismatic assembly of shear [AD-A133818] p 38 N84-14546 Management of large space projects - Quality assurance and compression loaded anisotropic plates with an Synchronously deployable truss structure or'product assurance' p3 A84-15310 arbitrary supporting structure p 23 A84-14050 [NASA-CASE-LAR-13117-1] p 59 N84-16250 International competition in commercial aerospace ANTENNA ARRAYS Selection of noisy sensors and actuators for regulation markets Radiation characteristics of array antennas with of linear systems — large space structures [AAS PAPER 83-244] p 77 A84-29883 disturbed aperture coverage p 48 A84-26516 [AD-A135442) p 51 N84-17931 Space Station needs, attributes and architectural Characteristics of the microprocessor implementation Precise control of flexible manipulators options, volume 2, book 2, part 4: International reports of algorithms for the processing of radio signals and noise [NASA-CR-175389] p 60 N84-20175 [NASA-CR-173319] p 14 N84-18303 in large antenna arrays p 48 A84-28067

A-1 ANTENNA DESIGN SUBJECT INDEX

ANTENNA DESIGN ARCHITECTURE (COMPUTERS) On the number and placement of actuators for Technology requirements for large flexible space Space station data management - A system evolving independent modal space control — for large flexible structures from changing requirements and a dynamic technology spacecraft p34 A84-24990 [IAF PAPER 83-404] p2 A84-11811 base The attitude and orbit control system for Eureca A hardware demonstration of control for a flexible [AIAA PAPER 83-2338] p 43 A84-10016 [DGLR PAPER 83-091] p 76 A84-29658 offset-feed antenna P 31 A84-13321 Space station autonomy requirements Control of flexible spacecraft by optimal model An advanced generation land mobile satellite system [AIAA PAPER 83-2352] p 63 A84-10024 following p 36 N84-12222 and its critical technologies p3 A84-15634 Data system architecture considerations for a space Integrated Flywheel Technology. 1983 Dynamics and control of a large space antenna station [NASA-CP-2290] p78 N84-12228 p32 A84-17361 [AIAA PAPER 83-2346] p 63 A84-10066 Space station control requirements and flywheel system Narrow multibeam satellite ground station antenna Attitude, control and stabilization p 40 N84-18281 weights for combined momentum and energy storage employing a linear array with a geosynchronous arc Data management p 12 N84-18287 p37 N84-12236 coverage of 60 deg. II - Antenna design ARRAYS IPACS attitude control technology considerations p46 A84-17743 Potential of minicomputer-array processor system for p37 N84-12238 A deployable 30/20 GHz multibeam offset antenna nonlinear finite-element analysis p 46 A84-20583 Advanced Control and Power System (ACAPS) [AIAA PAPER 84-0658] P 20 A84-25258 ARTIFICIAL INTELLIGENCE technology program p 37 N84-12243 Unfuriable offset antenna design for multipurpose A system for intelligent teleoperation research IPACS guidance navigation and control system applications [AIAA PAPER 83-2376] p 57 A84-10070 considerations and test activities p 37 N84-12245 [AIAA PAPER 84-0659] P 16 A84-25259 Knowledge based systems for intelligent robotics Exhibit D modular design attitude control system study Land-mobile communications satellite system design p57 A84-15667 [NASA-CR-170993] p 42 N84-20625 [AIAA PAPER 84-0753] p5 A84-25308 Automation, Robotics, and Machine Intelligence ATTITUDE GYROS Use of electromagnetic models in the optimal control Systems (ARAMIS) in space manufacturing Canadian Attitude Sensing Experimental Package of large space antennas P 35 A84-25552 p58 A84-22337 (CASEP) p 79 N84-17223 Study on large, ultralight long-life structures in space, Study of artificial intelligence techniques - Realization AUTOMATIC CONTROL phase 2C of a highly autonomous experimental robot system — Deployable beam flight experiment (MAST) [TM-EKR3] P17 N84-17284 French thesis p 58 A84-25828 p8 N84-17218 Construction concept for erecting an offset-fed ARTIFICIAL SATELLITES ' AUTOMATIC FLIGHT CONTROL antenna Servicing vehicle for satellites and platforms in low earth The attitude and orbit control system for Eureca [NASA-TM-85774] P 60 N84-20626 orbits [DGLR PAPER 83-091] p 76 A84-29658 Geometric modeling of large space antenna [DGLR PAPER 83-102] p6 A84-29666 AUTOMATION deployment p22 N84-22225 ASCENT PROPULSION SYSTEMS Automation, Robotics, and Machine Intelligence Systems (ARAMIS) in space manufacturing ANTENNA FEEDS A parametric study of space transfer-propulsion p58 A84-22337 Improved orbit utilization using auxiliary feeds in existing AUTONOMY earth terminals p46 A84-20647 [IAF PAPER 83-401 ] p 61 A84-13397 Vertical ascent from earth to geosynchronous orbit Space station autonomy requirements ANTENNA RADIATION PATTERNS [AIAA PAPER 83-2352] p 63 A84-10024 Narrow multibeam satellite ground station antenna [AIAA PAPER 84-0509] p 61 A84-18141 ASSEMBLING AUXILIARY POWER SOURCES employing a linear array with a geosynchronous arc Feasibility of remotely manipulated welding in space. Orbiting wire as a dynamo: Auxiliary power possibilities coverage of 60 deg. II - Antenna design for space platforms p46 A84-17743 A step in the development of novel joining technologies [NASA-CR-175437] p 60 N84-20857 [IFSI-83-3] p49 N84-12653 A cylindrical near-field test facility for large satellite ASTEROIDS AUXILIARY PROPULSION antennas The Tiros-based asteroid mission p2 A84-14762 Study of auxiliary propulsion requirements for large [MBB-UR-628-83-OE] P 72 A84-22862 ASTRODYNAMICS space systems, volume 2 Radiation characteristics of array antennas with A methodology to include static and kinetic friction [NASA-CR-168193-VOL-2] p 63 N84-13218 disturbed aperture coverage p48 A84-26516 effects in Space Shuttle payload transient loads analysis AVIONICS Airborne antenna pattern calculations [AIAA PAPER 83-2654] p 30 A84-10956 NTC '82; National Telesystems Conference, Gatveston, [NASA-CR-173284] p 51 N84-17436 Analytical model of the evolution of orbit parameters TX. November 7-10, 1982, Conference Record ANTENNAS of a quasi geostationary satellite p44 A84-15623 The dynamics and control of large flexible space [IAF PAPER 83-316] p 65 A84-11787 A definition of STS accommodations for attached structures, 6 Dynamics and control of a deformable gyrostat, utilizing payloads [NASA-CR-174450] P 36 N84-10173 continuum vehicle modes p31 A84-12488 [NASA-CR-172223] p 17 N84-10114 APERTURES On the dynamics of a subsatellite system supported by The effects of aperture antennas after signal propagation two tethers through anisotropic ionized media [AIAA PAPER 84-0062] p 32 A84-17854 B [AD-A138286] P 52 N84-21781 Attitude stability for the yaw-wheel class of orbiting APPROPRIATIONS gyrostats p33 A84-19675 BALL BEARINGS Authorizing appropriations to the National Aeronautics Transient dynamics during the orbiter based deployment Thermal conductance and torque of thin section and Space Administration for fiscal year 1985 of flexible members four-point contact ball bearings in vacuum [H-REPT-98-629] P 80 N84-21441 [AIAA PAPER 84-0061 ] p 34 A84-21285 [ESA-ESTL-54] p 25 N84-15562 National Aeronautics and Space Administration A simulator to study dynamic interaction of the Space BANDWIDTH Shuttle on-ortait flight control system with deployed flexible Authorization Act, 1985 P 80 N84-21443 IPACS attitude control technology considerations payloads p35 A84-26717 National Aeronautics and Space Administration p 37 N84-12238 ASTRONAUT MANEUVERING EQUIPMENT Authorization Act, 1985 BARRIER LAYERS Construction concept for erecting an offset-fed The role of potential barrier formation in spacecraft [H-REPT-98-629] P 80 N84-21444 antenna charging p 50 N84-17269 APPROXIMATION [NASA-TM-85774] p 60 N84-20626 Approximations method for space frame synthesis ASTRONAUT PERFORMANCE BEAM LEADS p 19 A84-10141 A definition of STS accommodations for attached Deployable beam flight experiment (MAST) The spatial order reduction problem and its effect on payloads p8 N84-17218 adaptive control of distributed parameter systems [NASA-CR-172223] p 17 N84-10114 Erectable beam experiment p 60 N84-17219 p33 A84-19056 ASTRONAUT TRAINING BEAMS (RADIATION) Parameter identification in continuum models Operational planning, simulation, and performance of Application of beam power technology to a space p 16 A84-25525 the German Spacelab mission 01 p 69 A84-17763 station p 45 A84-15642 ARC DISCHARGES ASTRONAUTS BEAMS (SUPPORTS) A review of SCATHA satellite results: Charging and The role of man in space p 72 AB4-24627 Control structure interactions in large space structures discharging p 50 N84-17254 ASTRONOMICAL TELESCOPES Analysis using energy approach—for constant and pulsed ARCHITECTURE Coherent arrays of separate optical telescopes in space thrusters p 35 A84-27934 Architectural options and development issues project Trio p3 A84-15363 The development of a composite beam building machine p4 A84-24633 ATMOSPHERIC CHEMISTRY for on-site construction of large space structures Space station needs, attributes and architectural options The role of space station in earth sciences [AAS PAPER 83-217] p 20 A84-29862 study. Volume 3: Requirements p72 A84-24631 Erectable beam experiment p60 N84-17219 Significant scientific and technical results at Marshal [NASA-CR-173332] P 10 N84-18267 Space Right Center The STEP/STACBEAM experiment technology Space station needs, attributes and architectural options development for very large solar array deployers [NASA-TM-82562] p 78 N84-16075 p8 N84-17220 study. Volume 4: Architectural options, subsystems, ATMOSPHERIC PHYSICS technology and programmatics The role of space station in earth sciences Component mode synthesis and large deflection [NASA-CR-173331] P 10 N84-18268 p72 A84-24631 vibrations of complex structures — beams and trusses Space station needs, attributes and architectural options Significant scientific and technical results at Marshal [NASA-CR-173338] p 21 N84-18680 study. Final executive review Space Right Center BEHAVIOR [NASA-CR-173335] P 10 N84-18269 [NASA-TM-82562] p 78 N84-16075 The flexural behavior of PACSAT (passive Space station needs, attributes and architectural options ATOMIC COLLISIONS communication satellite) in orbit study. Final review executive summary briefing Reactions of high velocity atomic oxygen with carbon [AD-A131406] p36 N84-11195 [NASA-CR-173674) p 10 N84-18272 [AIAA PAPER 84-0549] p 53 A84-18159 BENDING Space station needs, attributes and architectural ATTITUDE CONTROL The flexural behavior of PACSAT (passive options. Volume 1: - Executive summary NASA Science platform and attitude subsystem in-flight communication satellite) in orbit [NASA-CR-172792] p 12 N84-18292 calibration for the Galileo spacecraft p32 A84-17355 [AD-A131406] p36 N84-11195

A-2 SUBJECTINDEX COMPOSITE MATERIALS

BINARY CODES CASSEGRAIN OPTICS COMMUNICATION SATELLITES Sodium heat transfer system modeling Study of multi-kilowatt solar arrays for Earth orbit Application of a common reflector configuration to a [OE84-002051 ] p25 N84-16509 applications muttimission satellite of the 90's BINARY SYSTEMS (MATERIALS) [NASA-CO-170939] p 49 N84-12634 [IAF PAPER 83-60] p1 A84-11731 Recent and planned developments at the Goddard CELESTIAL MECHANICS Commercial communications satellite market and Space Flight Center in thermal control technology Introduction to geostationary orbits technology in the 90's p26 N84-19402 [ESA-SP-1053] p80 N84-21590 [IAF PAPER 83-86] p 65 A84-11739 BIOASTRONAUTICS CENTER OF MASS NTC '82; National Telesystems Conference, GaJveston, Man in space - An overview p67 A84-15161 Motion of a symmetric satellite about the center of mass TX. November 7-10.1S82. Conference Record in circular orbit in the presence of flexible viscoelastic Integrated water management system - Description and p44 A84-15623 rods p35 A84-26977 test results — for Space Station waste water processing An advanced generation land mobile satellite system CENTRAL ELECTRONIC MANAGEMENT SYSTEM [SAE PAPER 831111] p6 A84-29046 and its critical technologies p 3 A84-15634 Space station communications p 73 A84-24636 Advanced composite antenna reflectors for Gravitational biology on the space station CERAMICS communications satellites p 53 A84-17151 [SAE PAPER 831133] p 75 A84-29063 Fracture mechanics of ceramics. Volume 5 - Surface Improved orbit utilization using auxiliary feeds in existing BIOCHEMISTRY flaws, statistics, and microcracking p 54 A84-24501 earth terminals p 46 A84-20647 The Alpha-Helix Concept Innovative utilization of the Assessment of reliability of ceramic materials Communication Satellite Systems Conference, 10th, Space Station Program. A report to the National p54 A84-24508 Orlando, FL, March 19-22.1984, Technical Papers Aeronautical and Space Administration requesting CHARGED PARTICLES p73 A84-25251 establishment of a Sensory Physiology Laboratory on the Spacecraft/plasma interactions and their influence on Reduced domestic satellite orbit spacing Space Station field and particle measurements — conferences [AIAA PAPER 84-0652] p 73 A84-25253 [NASA-CR-175436] p 14 NB4-20610 [ESA-SP-198] p56 N84-17253 Time phased introduction of advanced technologies - BIOLOGICAL EFFECTS CIRCULAR ORBITS Its impact on orbit/spectrum conservation Gravitational biology on the space station Periodic oscillations of a gyrostat satellite with respect [AIAA PAPER 844)653] p 74 A84-25254 [SAE PAPER 831133] p 75 AB4-29063 to the centers of mass in a circular orbit A deployable 30/20 GHz multibeam offset antenna BODY KINEMATICS p33 A84-19728 [AIAA PAPER 84-0658] p 20 A84-25258 Manipulator interactive design with interconnected Optimal low-thrust transfers to synchronous orbit Unfuriable offset antenna design for multipurpose flexible elements p58 A84-25484 p62 A84-24981 applications BOOMS (EQUIPMENT) Motion of a symmetric satellite about the center of mass [AIAA PAPER 84-0659] p 16 A84-25259 Large space instrumentation to measure the interaction in circular orbit in the presence of flexible viscoelastic GEO space platform economics - Impact of concept, between space structures and the environment rods p35 A84-26977 size, launch mode and lifetime [AD-A129990] p 77 N84-10179 CLIMATOLOGY [AIAA PAPER 84-0704] p 74 A84-25281 BOUNDARY LAYERS The role of space station in earth sciences Tele-X - The first step in a satellite communications Research on boundary feedback and control theories, p72 A84-24631 system for the Nordic countries 1978-1983 CLOSED ECOLOGICAL SYSTEMS [AIAA PAPER 84-0713] p4 A84-25287 [AD-A136531] p 41 N84-18987 Systems engineering aspects of a preliminary A standardized propulsion module for future BROADCASTING conceptual design of the space station environmental communications satellites in the 2000 to 3000 kg class control and life support system The Franco-German DBS program TV-SAT/TDF-1' [AIAA PAPER 84-0727] p 62 A84-25292 [AIAA PAPER 84-0661 ] p4 A84-25260 [SAE PAPER 831109] p5 A84-29044 Utilization of electric propulsion for communication Electrochemical and steam-desorbed amine CO2 BUCKLING satellites concentration Subsystem comparison — for oxygen [AIAA PAPER 84-0729] p 62 A84-25293 Buckling and vibration of any prismatic assembly of shear recovery on Space Station Why don't we use ion propulsion? and compression loaded anisotropic plates with an [SAE PAPER 831120] p6 A84-29054 [AIAA PAPER 84-0730] p 62 A84-25294 arbitrary supporting structure p 23 A84-140SO Phase change water recovery techniques - Vapor The space van and its potential impact on the design Stability, vibration and passive damping of partially compression distillation and thermoelectric/membrane of communications satellites restrained imperfect columns concepts — from waste water as part of Space Station [AIAA 84-0758] p 74 A84-25309 [NASA-TM-85697] p 37 N84-13608 life support system Computer tools for optimizing orbit use BUS CONDUCTORS [SAE PAPER 831122] p6 A84-29056 [AIAA PAPER 84-0651 ] p 74 A84-25318 Evaluation of bus impedance on the SPOT muttimission The complementary roles of existing and advanced NASA's geostationary communications platform platform p 44 A84-13521 environmental, thermal control and life support technology program BYPASSES for space stations p79 N84-19429 [AIAA PAPER 84-0702] p 5 A84-25326 Evaluation of bus impedance on the SPOT multimission CMOS Development trends in Europe on satellite clusters and platform p 44 A84-13521 Digital technologies and systems for geostationary orbit geostationary platforms satellites [AIAA PAPER 84-0703] p 75 A84-25327 [AIAA PAPER 34-0749] p 74 A84-25304 The flexural behavior of PACSAT (passive COATINGS communication satellite) in orbit Simulated space radiation effects on dielectrics and [AD-A131406] p36 N84-11195 CALIBRATING coatings p 54 A84-20682 Space Station needs, attributes and architectural Science platform and attitude subsystem in-flight CODING options. Volume 2. book 1, part 3: Manned Space Station calibration for the Galileo spacecraft p 32 A84-17355 Implementation of MACLISP on a large address space relevance to commercial telecommunications satellites CANADIAN SPACE PROGRAMS computer [NASA-CR-173314] p 13 N84-18298 Space station - A Canadian perspective [DE84-005042] p 79 N84-21145 Design and development of an advanced solar array [IAF PAPER 83-55] p 65 A84-11728 COLUMNS (SUPPORTS) drive mechanism p 17 N84-18457 MSAT mobile communication demonstration satellite Vibration characteristics of self-expanding stayed BAe reaction wheels for Olympus — Olympus system and bus tradeoff considerations columns for use in space p 34 A84-21237 telecommunication satellite p 17 N84-18475 [AIAA PAPER 84-0751 ] p 48 A84-25306 Stability, vibration and passive damping of partially •Assessment of satellite power flux-density limits in the CARBON restrained imperfect columns 2025-2300 MHz frequency range, part 1 Reactions of high velocity atomic oxygen with carbon [NASA-TM-85697] p 37 N84-13608 [PBB4-129402] p51 N84-18S32 [AIAA PAPER 84-0549] p 53 A84-18159 COMBINED STRESS Heat pipes for the L-SAT communications module CARBON DIOXIDE CONCENTRATION Instability analysis of space trusses radiators p26 N84-19405 Electrochemical and steam-desorbed amine CO2 p 32 . A84-16885 A Variable Conductance Heat Pipe (VCHP) radiator concentration Subsystem comparison — for oxygen COMMERCIAL SPACECRAFT system for communications payloads p 27 N84-19406 recovery on Space Station Leasecraft - An innovative space vehicle The thermal design of L-SAT large telecommunication [SAE PAPER 831120] P6 A84-29054 p5 A84-27945 satellite p 27 N84-19414 CARBON DIOXIDE LASERS Reusable commercial space processing platforms COMPENSATORS Application of laser interferometry to robotics [AAS PAPER 83-208] p7 A84-29858 Algorithms and computational aspects pertaining to p58 A84-28541 Space Station needs, attributes and architectural block diagonal dominance methods for design of CARBON FIBER REINFORCED PLASTICS options. Volume 2, book 1, part 3: Manned Space Station decentralized feedback compensation Thermo-mechanical behaviour of CFRP tubes for space relevance to commercial telecommunications satellites p 15 A84-19108 structures [NASA-CR-173314] p 13 N84-18298 COMPILERS [IAF PAPER 83-417] p 22 A84-11814 Implementation of MACLISP on a large address space COMMONALITY Materials and construction techniques for large computer Space Station needs, attributes and architectural spacecraft structures p53 A84-17768 [DE84-005042] p79 N84-21145 options. Volume 2, book 2, parti: Mission implementation Integrity control of carbon fiber reinforced plastics concepts COMPLEX SYSTEMS structural elements, phase 1 report — space Muttivariable direct adaptive control for a general class [NASA-CR-173316] p 13 N84-18300 applications of time-varying commands p 33 A84-19118 [TB-TS-11-01/82-A] pS6 N84-18416 COMMUNICATION EQUIPMENT COMPONENT RELIABILITY Review report of the third year's activities on the study A communications system conceptual design for a low Reliability issues in active control of large flexible space earth orbiting Manned Space Station p45 A84-15643 survey of advanced materials — for spacecraft and launch structures vehicles COMMUNICATION NETWORKS [NASA-CR-175341] p 39 N84-16248 [R878] p56 N84-21675 Space station communications and tracking equipment COMPOSITE MATERIALS CARBON FIBERS management/control system p 45 AB4-15639 Tests and prediction of composite material viscoelastic New fabric structures of carbon fiber Space station communications p 73 A84-24636 behaviour for large space structure p 52 A84-17108 Telecommunication systems for large-scale space [IAF PAPER 83-418] p 30 A84-11815 Composite structural materials manufacturing activity Effect of temperature, moisture and radiation exposures [NASA-CR-173259] p 56 N84-17293 [AAS PAPER 83-216] p 48 A84-29861 on composite mechanical properties p 55 A84-28900

A-3 COMPOSITE STRUCTURES SUBJECT INDEX

Composite structural materials Simplified models and computational schemes of the CONSTRAINTS [NASA-CR-173259] p 56 NB4-17293 aerodynamic load — large space structures Stability, vibration and passive damping of partially COMPOSITE STRUCTURES p28 N84-21614 restrained imperfect columns . Thermal control of tubular composite structures in space COMPUTER TECHNIQUES [NASA-TM-85697] p 37 N84-13608 environment p 22 A84-10440 Data system architecture considerations for a space Systems/operations technology p 11 N84-18278 Advanced composite antenna reflectors for station CONSTRUCTION communications satellites p 53 A84-17151 [AIAA PAPER 83-2346] p 63 A84-10066 Authorizing appropriations to the National Aeronautics The development of a composite beam building machine Optimal low-thrust transfers to synchronous orbit and Space Administration for fiscal year 1985 for on-site construction of large space structures p62 A84-24981 [H-REPT-98-629] p 80 N84-21441 [AAS PAPER 83-217] p 20 A84-29862 Sodium heat transfer system modeling Operational modules for space station construction COMPUTATION [DE84-002051 ] p25 N84-16509 [NASA-TM-85772] p 21 N84-21608 Mathematical syntrtesization of complex structures Space Station needs, attributes and architectural CONTINUUM MECHANICS p 19 N84-22224 options: Summary briefing Parameter identification in continuum models COMPUTATIONAL FLUID DYNAMICS [NASA-CR-173328] p 10 N84-18271 p 16 A84-25525 Modular design attitude control system COMPUTERIZED SIMULATION CONTRACT MANAGEMENT [NASA-CR-170996] p 41 N84-19392 Some aspects of simulation studies in spacecraft The contract — management for space projects COMPUTER AIDED DESIGN dynamics p 15 A84-11930 p2 A84-15304 Buckling and vibration of any prismatic assembly of shear Dielectric charging in space - Ground test data and model CONTRACT NEGOTIATION and compression loaded anisotropic plates with an verification p 47 A84-20709 The contract — management for space projects arbitrary supporting structure p 23 A84-14050 ACOSS eleven (Active Control Of Space Structures), p2 A84-15304 Spacecraft thermal design using interactive graphics volume 2 CONTRACTS [AIAA PAPER 84-0143] p 23 A84-17910 [AO-A135676] p 41 N84-18312 The contract — management for space projects Algorithms and computational aspects pertaining to CONDUCTIVE HEAT TRANSFER p2 A84-15304 block diagonal dominance methods for design of Radiation-conduction interaction in large space CONTROL decentralized feedback compensation structures The effects of the space environment on damping p 15 A84-19108 [AIAA PAPER 84-0144] p 23 A84-17911 materials and damping designs on flexible structures Matrix(X) - Application to large space structure control A Variable Conductance Heat Pipe (VCHP) radiator p 56 N84-17217 design problems p 16 A84-19129 system for communications payloads p27 N84-19406 Scale model testing for control system parameters of Potential of minicomputer-array processor system for CONFERENCES large structures nonlinear finite-element analysis p 46 A84-20S83 Space applications at the crossroads; Proceedings of [AD-A135652] p 41 N84-18313 Computer tools for optimizing orbit use the Twenty-first Goddard Memorial Symposium. Greenbelt, CONTROL CONFIGURED VEHICLES [AIAA PAPER 84-0651] p 74 A84-25318 MD, March 24, 25, 1983 p 64 A84-10883 The Toysat structural control experiment — for large Manipulator interactive design with interconnected Management of large space projects; Course on Space flexible space structure p31 A84-13320 flexible elements p 58 A84-25484 Technology, Toulouse, France, May 3-14, 1982, Sampled data control of large space structures using Thermal analysis research applicable to space station Proceedings p2 A84-15301 constant gain velocity feedback - A negative view technology needs Developing the space frontier; Proceedings of the p46 A84-19169 [NASA-TM-84658] p 25 N84-15426 Twenty-ninth Annual Conference, Houston, TX, October Some applications of direct adaptive control to large Computer aided synthesis of a satellite antenna structure 25-27,1982 p 67 A84-15381 structural systems p 34 A84-25496 with probabilistic constraints p21 N84-19899 NTC '82; National Telesystems Conference, Gaiveston, Control structure interactions in large space structures Computer-Aided Geometry Modeling TX, November 7-10,1982. Conference Record Analysis using energy approach — for constant and pulsed [NASA-CP-2272] p 18 N84-22179 p44 A84-15623 thrusters p 35 A84-27934 Mathematical synthesization of complex structures Colloquium on the Law of Outer Space, 25th, Paris, CONTROL EQUIPMENT p 19 N84-22224 France, September 27-October 2,1982, Proceedings Digital control system for space structural dampers Geometric modeling of large space antenna p67 A84-17026 [NASA-CR-175355] p 39 N84-16246 deployment p22 N84-22225 Manufacturing in space; Proceedings of the Winter A deployable structure and solar array controls COMPUTER AIDED MANUFACTURING Annual Meeting, Boston, MA, November 13-18, 1983 experiment tor STEP p 39 N84-17227 Study of artificial intelligence techniques - Realization p 71 A84-22327 CONTROL SIMULATION of a highly autonomous experimental robot system — Space station: Policy, planning and utilization; Hardware simulation of spacecraft dynamics and French thesis p 58 A84-25828 Proceedings of the Symposium, Arlington, VA, July 18-20, control p30 A84-11932 COMPUTER GRAPHICS 1983 p72 A84-24626 A flexible structure controller design method using mode Spacecraft thermal design using interactive graphics Communication Satellite Systems Conference, 10th, residualization and output feedback — for Large Flexible [AIAA PAPER 84-0143] p 23 A84-17910 Orlando, FL, March 19-22, 1984, Technical Papers Space System p32 A84-17369 Computer-Aided Geometry Modeling p73 A84-25251 CONTROL STABILITY [NASA-CP-2272] p 18 N84-22179 U.S. National Congress of Applied Mechanics. 9th, Time domain analysis and synthesis of robust controllers Mathematical synthesization of complex structures Cornell University, Ithaca, NY, June 21-25, 1982, for large scale LOG (Linear Quadratic Gaussian) p 19 N84-22224 Proceedings p75 A84-29126 regulators Geometric modeling of large space antenna Space manufacturing 1983; Proceedings of the Sixth [AD-A137760] p43 N84-21172 deployment p22 N84-22225 Conference, Princeton University, Princeton, NJ, May 9-12, CONTROL SURFACES Research on boundary feedback and control theories, COMPUTER PROGRAMS 1983 p76 A84-29852 A comparison of linear and geometrically nonlinear finite Integrated Flywheel Technology. 1983 1978 -1983 [AD-A136531] p41 N84-1B987 element analyses applied to large space structures [NASA-CP-2290] p 78 N84-12228 [AIAA PAPER 84-0069] p 16 A84-19887 STEP Experiment Requirements CONTROL THEORY Dynamics and control of a large space antenna Highly efficient, very low-thrust transfer to [NASA-CP-2294] p7 N84-17211 Spacecraft/plasma interactions and their influence on p32 A84-17361 geosynchronous orbit - Exact and approximate solutions Multjvariable direct adaptive control for a general class p 61 A84-24980 field and particle measurements — conferences [ESA-SP-198] p56 N84-17253 of time-varying commands p33 A84-19118 On modeling dilution jet flowfields Environmental and thermal control systems for space A large space structure benchmark problem - ACOSS [AIAA PAPER 84-1379] p 58 AS4-44183 vehicles — conferences Model No. 2 ' p 33 A84-19127 A definition of STS accommodations for attached [ESA-SP-200] p26 N84-19396 Number crunching on the ACOSS Model No. 2 payloads Sheath ionization model of beam emissions from large p33 A84-19128 [NASA-CH-172223] p 17 N84-10114 spacecrafts Matrix(X) - Application to large space structure control Control of flexible spacecraft by optimal model [AD-A137181] p52 N84-19463 design problems p16 A84-19129 following p 36 N84-12222 Computer-Aided Geometry Modeling Some applications of direct adaptive control to large Software quality assurance Spacelab experience and [NASA-CP-2272] p18 N84-22179 structural systems p 34 A84-25498 future trends p 17 N84-14759 CONGRESSIONAL REPORTS Controllability and observability criteria for muttjvariable Stability enhancement of a flexible robot manipulator NASA's space station activities linear second-order models p 35 A84-25516 [AD-A134185] p 59 N84-16B07 [GPO-27-393] p7 N84-14234 The dynamics and control of large flexible space Static and dynamic structural-sensitivity derivative National Aeronautics and Space Administration Act, structures, 6 [NASA-CR-174450] p 36 N84-10173 calculations in the finite-element-based Engineering 1985 p9 N84-18116 Analysis Language (EAL) system Civil space station Control of flexible spacecraft by optimal model [NASA-TM-85743] p 42 N84-20880 [S-REPT-98-523] p 79 N84-20613 following p36 N84-12222 IPACS attitude control technology considerations Interactive geometry modeling of space station Department of Housing and Urban p37 N84-12238 conceptual designs p 18 N84-22191 Development-independent agencies appropriations for 1984: National Aeronautics and Space Administration Study on synthesis and characterization of large space COMPUTER SYSTEMS DESIGN p80 N84-21440 systems, phase 2. Part 2: Proposals for additions, Space station autonomy requirements Authorizing appropriations to the National Aeronautics modifications and new analytical methods, volume 2 [AIAA PAPER 83-2352] p 63 A84-10024 and Space Administration for fiscal year 1985 [ESA-CR(P)-1779-VOL-4] p 29 N84-21616 COMPUTER SYSTEMS PROGRAMS [H-REPT-98-629] p 80 N84-21441 CONTROLLABILITY Software quality assurance Spacelab experience and Review of the National Aeronautics and Space Act of A degree of controllability definition - Fundamental . future trends p17 N84-14759 1958 concepts and application to modal systems IRSIM: A program for the calculation of infrared flux [GPO-28-915] p80 N84-21442 p 34 A84-24991 intensity incident on a spacecraft inside a test chamber National Aeronautics and Space Administration Controllability and observability criteria for multrvariable p26 N84-19400 Authorization Act, 1985 p 80 N84-21443 linear second-order models p35 A84-25516 Computing the radiation pressure forces by adapting National Aeronautics and Space Administration Environmental effects on the dynamics and control of thermal design verification softwares — large space Authorization Act, 1985 an orbiting large flexible antenna system structures p 28 N84-21613 [H-REPT-98-629] p 80 N84-21444 [NASA-CR-175448] p 42 N84-20627

A-4 SUBJECT INDEX DYNAMIC STABILITY

CONTROLLERS DIGITAL SYSTEMS Dynamics and control ol a large space antenna Digital technologies arid systems for geostationary orbit p32 A84-17361 DATA ACQUISITION satellites Selection of noisy sensors and actuators for regulation Study of a tracking and data acquisition system for the (AIAA PAPER 84-0749] p 74 A84-25304 of linear systems — large space structures 1990's. Volume 3: TDAS Communication Mission Digital control system for space structural dampers [AD-A135442] p 51 N84-17931 Model [NASA-CR-175355] p 39 N84-16246 Decentralized control of a large space structure using (NASA-CR-175195) p 79 N84-19371 DILUTION direct output feedback DATA BASE MANAGEMENT SYSTEMS On modeling dilution jet flowfields [AD-A136781] p 41 N84-19464 Space station data management - A system evolving [AIAA PAPER 84-1379] p 58 A84-44183 from changing requirements and a dynamic technology CONVECTION DISPLACEMENT base Second All-Union Seminar on Hydromechanics and New elements for analysis of space frames with tapered (AIAA PAPER 83-2338] p 43 A84-10016 Heat-Mass Transfer in Weightlessness. Abstracts of members p 20 N84-14561 DATA LINKS reports: Table of contents DISTILLATION EQUIPMENT Communications p 12 N84-18285 [NASA-TM-77534] p 26 N84-18576 Phase change water recovery techniques - Vapor Space Station needs, attributes and architectural COOLING SYSTEMS compression distillation and thermoelectric/membrane options. Volume 2, book 2, part 3: Communication Thermofluidynamics of heat pipes p 27 N64-19423 concepts — from waste water as part of Space Station system life support system Design and manufacturing of a heat rejection system [NASA-Cfl-173318] , p 14 N84-18302 [SAE PAPER 631122] p6 A84-29056 for advanced thermal control — spacecraft and or payload DATA PROCESSING cooling p 27 N84-19434 Spacelab Data Processing Facility DISTRIBUTED PARAMETER SYSTEMS COORDINATE TRANSFORMATIONS [NASA-TM-85556] p 51 N84-19382 Aggregate models for distributed parameter systems Coordinate transformation assembly — for space DATA REDUCTION with applications to flexible air and spacecraft platform angular coordinate linking p 75 A84-28579 Computational savings in view factor evaluation on mode p31 A84-11945 COORDINATES prescreening — large space structures Model error estimation for distributed systems described Computer-Aided Geometry Modeling p 29 N84-21618 by elliptic equations p 15 A84-11946 [NASA-CP-2272] p 18 N84-22179 DATA SAMPLING The spatial order reduction problem and its effect on COPPER Sampled data control of large space structures using adaptive control of distrirbuted parameter systems Cracked inner layer foil in high-density multilayer printed constant gain velocity feedback - A negative view p33 A84-19056 wiring boards p 53 A84-17200 p46 A84-19169 Time domain analysis and synthesis of robust controllers COSMIC RAYS DATA SYSTEMS for large scale LOG (Linear Quadratic Gaussian) Pyroelectric materials as electronic pulse detectors ol Data system architecture considerations for a space regulators ultraheavy nuclei p 72 A84-23440 station [AD-A137760] p43 N84-21172 [AIAA PAPER 83-2346] p 63 A84-10066 COSMOLOGY DISTRIBUTED PROCESSING Space Station needs, attributes and architectural Natural selection of stellar civilizations by the limits of Attitude, control and stabilization p 40 N84-18281 options. Volume 2, book 2, part 2, Task 2: Information growth Data management p 12 N84-18287 management system [IAF PAPER 83-272] p 65 A84-11779 DOCUMENTATION [NASA-CR-173317] p 13 N84-18301 COSMONAUTS A voice interactive system for aiding and documentation Spacelab Data Processing Facility For the first time — Russian book on construction of of space-based tasks [NASA-TM-85556] p 51 N84-19382 first Soviet earth satellites p 16 A84-21564 [AIAA PAPER 83-2355] p 43 A84-10025 DATA TRANSMISSION . Space vehicles — Russian book on development of Experiment data communications (48 Mbit/s) between DOMESTIC SATELLITE COMMUNICATIONS SYSTEMS Soviet spacecraft and planning of first manned flights Spacelab, the Space Shuttle and the ground Reduced domestic satellite orbit spacing p4 A84-21573 p 44 A84-10396 [AIAA PAPER 84-0652] p 73 A84-25253 COST ANALYSIS A communications system conceptual design for a low MSAT mobile communication demonstration satellite Determination of critical parameters in large flexible earth ortiting Manned Space Station p45 A84-15643 system and bus tradeoff considerations space structures with uncertain modal data Spacelab Data Processing Facility [AIAA PAPER 84-0751 ] ' p 48 A84-25306 p 33 A84-20047 [NASA-TM-85556] p 51 N84-19382 DOWNLINKING Power-economical considerations for the integration of DEGRADATION Experiment data communications (48 Mbit/s) between terrestrial and extraterrestrial solar generators into existing Evaluation of spacecraft materials and processes for Spacelab, the Space Shuttle and the ground power generation systems p 71 A84-21488 optical degradation potential p 54 A84-28458 p44 A84-10396 Space Station needs, attributes and architectural DEPLOYMENT DRUGS options, volume 2, book 3: Cost and programmatics Transient dynamics during the orbiter based deployment Role of a space station in pharmaceutical [NASA-CR-173320] p 14 N84-18304 of flexible members manufacturing p 73 A84-24632 COST EFFECTIVENESS [AIAA PAPER 84-0061] p 34 A84-21285 DUCTED FLOW Advanced Control and Power System (ACAPS) Finite element analysis of a deployable space On modeling dilution jet flowfields technology program p37 N84-12243 structure P 38 N84-16056 [AIAA PAPER 84-1379] p 58 A84-44183 Synchronously deployable truss structure Development of procedures for component mode DURABILITY [NASA-CASE-LAR-13117-1] p 59 N84-16250 synthesis Assessment of potential for batteries in space [DFVLR-IB-232-82-C-09] p 30 N84-21626 The STEP/STACBEAM experiment technology applications p48 N84-12246 development for very large solar array deployers COST ESTIMATES DUST p8 N84-17220 Feasibility study to conduct windblown sediment Authorizing appropriations to the National Aeronautics Low concentration ratio solar array structural experiments aboard a space station' and Space Administration for fiscal year 1985 configuration p17 N84-17225 [NASA-CR-175434] p 15 N84-21586 [H-REPT-98-629] p 80 N84-21441 Development of Test Article Building Block (TABB) for DYNAMIC CHARACTERISTICS COST REDUCTION deployable platform systems p21 N84-17226 Dynamics of nonrigid articulated robot linkages New component development for mutti-100 kW tow-cost Space telescope: Solar array primary development p58 A84-25531 solar array applications p 47 AB4-22963 mechanism p51 N84-18458 DYNAMIC CONTROL Large area, low cost space solar cells Geometric modeling of large space antenna Geodetic control of the reflectors of large antennas p47 A84-22979 deployment p22 N84-22225 p 31 A84-15785 The space van and its potential impact on the design DESIGN ANALYSIS Closed-form solutions for feedback control with terminal of communications satellites ACOSS Fourteen (Active Control of Space Structures) constraints p 36 A84-29471 (AIAA 84-0758] p 74 AB4-25309 [AD-A133411] p38 N84-15181 A deployable structure and solar array controls Systems/operations technology p11 N84-18278 Study on synthesis and characterization of large space experiment for STEP p39 N84-17227 Auxiliary propulsion p11 N84-18283 systems, phase 2. Part 2: Proposals for additions, DYNAMIC LOADS ' • COUPLING modifications and new analytical methods, volume 1 Static and dynamic structural-sensitivity derivative [ESA-CR(P)-1779-VOL-3] p43 N84-21611 Radiating dipole model of interference induced in calculations in the finite-element-based Engineering spacecraft circuitry by surface discharges Study on synthesis and characterization of large space Analysis Language (EAL) system [NASA-TP-2240) p 50 N84-16247 systems, phase 2. Part 1: Assessment of design [NASA-TM-85743] p 42 N84-20880 verification analytical methods. Volume 1: Mechanical CRACK PROPAGATION DYNAMIC RESPONSE design Finite element analysis of a deployable space Fracture mechanics of ceramics. Volume 5 - Surface [ESA-CR(P)-1779-VOL-1] p 18 N84-21624 structure p38' N84-16056 flaws, statistics, and microcracking p 54 AS4-24501 Study on synthesis and characterization of large space Self-shadowing of orbiting trusses Assessment of reliability of ceramic materials systems, phase 2. Part 1: Assessment of design [NASA-CR-173215] p 25 N84-16565 p 54 A84-24508 verification analytical methods. Volume 2: Thermal Photovoltaic concentrator pointing dynamics and plasma CRACKING (FRACTURING) design interaction study p 50 NB4-17224 Cracked inner layer foil in high-density multilayer printed [ESA-CR(P)-1779-VOL-2] p 18 N84-21625 Validation methods for mathematical models of flexible wiring boards p 53 A84-17200 Mathematical synttiesization of complex structures satellite dynamics CREW WORK STATIONS p19 N84-22224 [ESA-CR(P)-1794] p40 N84-17241 Environmental control and life support (ECLS) design DEVELOPING NATIONS Dynamic behaviour of a satellite antenna structure in optimization approach p 73 A84-24637 The solar power satellite - A programme for random vibration environment p 42 N84-19900 CRITICAL LOADING development aid p 68 A84-17074 Evaluation of modal testing techniques for spacecraft Optimization of shallow trusses against limit point DIELECTRICS structures p 28 N84-19906 instability p 20 A84-23366 Simulated space radiation effects on dielectrics and DYNAMIC STABILITY CRYOGENIC COOLING coatings p 54 A84-20682 ACOSS eleven (Active Control Of Space Structures), NASA needs and trends in cryogenic cooling Dielectric charging in space - Ground test data and model volume 1 p25 N84-15329 verification p 47 AB4-20709 [AD-A135675] p40 NB4-18311

A-5 DYNAMIC STRUCTURAL ANALYSIS SUBJECTINDEX

DYNAMIC STRUCTURAL ANALYSIS Geometrically nonlinear analysis of beam-in-space ELECTROSTATICS Dynamics and control of a large space antenna structures Static shape forming for an electrostatically controlled p32 A84-17361 [MITT-28] p22 N84-21914 membrane mirror p 16 A84-25551 The beam-like behavior of space trusses ELASTIC BENDING Adaptive microwave reflector p 50 N84-17235 p 19 AB4-21517 The beam-like behavior of space trusses ELLIPTIC DIFFERENTIAL EQUATIONS A variational theorem for the viscoelastodynamic p 19 A84-21517 Model error estimation for distributed systems described analysis of high-speed linkage machinery fabricated from ELASTIC PROPERTIES by elliptic equations p 15 A84-11946 composite materials Parameter identification in continuum models ELLIPTICAL ORBITS [ASME PAPER 83-DET-6] p 55 A84-29101 p16 A84-25S25 The flexural behavior of PACSAT (passive communication satellite) in orbit Multibody dynamics - Analysis of flexibility effects ELASTIC SHELLS [AD-A132533] p 36 A84-29145 Numerical solution of several classes of nonlinear [AD-A131406] p36 N84-11195 EMBEDDED COMPUTER SYSTEMS Study on damping representation related to spacecraft flexible shell theory problems p35 A84-25586 structural design A system for intelligent teleoperation research ELASTODYNAMICS [EMSB-18/83] p38 N84-15182 [AIAA PAPER 83-2376] p 57 A84-10070 A variational theorem for the viscoelastodynamic Finite element analysis of a deployable space ENERGY CONSUMPTION analysis of high-speed linkage machinery fabricated from structure p38 N84-16056 Market potential and possible limitations for satellite composite materials The STEP/STACBEAM experiment technology solar power stations p 70 A64-21481 [ASME PAPER 83-DET-6] p 55 A84-29101 development for very large solar array deployers ENERGY CONVERSION EFFICIENCY p8 N84-17220 ELECTRIC CONDUCTORS Space station energy sizing p48 N84-12233 General requirements for Shuttle flight experiments Electrically conductive black optical paint Power p12 N84-18288 p8 N84-17221 p55 A84-28553 ENERGY REQUIREMENTS Validation methods for mathematical models of flexible ELECTRIC DIPOLES Power p 12 N84-18288 satellite dynamics Radiating dipole model of interference induced in ENERGY SOURCES [ESA-CR(P)-1794] p40 N84-17241 spacecraft circuitry by surface discharges Energy from space - Legal implications of the use of Scale model testing for control system parameters of [NASA-TP-2240] p 50 N84-16247 the geostationary orbit p 68 A84-17075 large structures ELECTRIC FIELDS ( ENERGY STORAGE [AD-A135652] p 41 N84-18313 Radiating dipole model of interference induced in Space station control requirements and flywheel system Analysis of large space structures p 18 N84-20621 spacecraft circuitry by surface discharges weights for combined momentum and energy storage Environmental effects on the dynamics and control of [NASA-TP-2240] p 50 N84-16247 p37 N84-12236 an orbiting large flexible antenna system Spacecraft/plasma interactions and their influence on Advanced Control and Power System (ACAPS) [NASA-CR-17S448] p 42 N84-20627 field and particle measurements — conferences technology program p 37 N84-12243 Derivation and combination of impedance matrices for [ESA-SP-198] p56 N84-17253 Assessment of potential for batteries in space flexible satellites ELECTRIC POTENTIAL applications p48 N84-12246 [ESA-STR-209] p 43 N84-21604 Current collection from the space plasma through Integrated Power/Attitude Control System (IPACS) The solution of the dynamic problem of the periodic defects in high voltage solar array insulation technology experiment p 39 N84-17229 structures by cyclosymmetric technique — large space p49 N84-15970 ENERGY TECHNOLOGY structures p43 N84-21612 ELECTRIC POWER TRANSMISSION High capacity power systems for space Simplified models and computational schemes of the Application of beam power technology to a space [IAF PAPER 83-421] p 44 A84-11816 . aerodynamic load — large space structures station p45 A84-15642 Consequences of transmission of solar energy from p28 N84-21614 Power-economical considerations for the integration of outer space p68 A84-17076 Finite element formulations for tensioned members — terrestrial and extraterrestrial solar generators into existing Energy from space; Proceedings of the Symposium on large space structures p21 N84-21615 power generation systems p 71 A84-21488 Solar Energy from Space, Vienna, Austria, August 9-21, Assessment of the existing ground test technology and ELECTRIC PROPULSION 1982 p 69 A84-21476 confronting with the Large Space Structures (LSS) An electric propulsion transportation system from Evolution of the solar power satellite concept - The requirements. Experimental techniques in structural low-earth orbit to geostationary orbit utilizing beamed utilization of energy from space p70 A84-21478 analysis p 29 N84-21621 microwave power p 61 A84-21485 A system study of the solar power satellite concept Utilization of electric propulsion for communication p70 A84-21480 satellites European questions related to satelite power systems [AIAA PAPER 84-0729] p 62 A84-25293 p 70 A84-21483 ELECTRIC PULSES Space solar power in perspective p 71 A84-21489 EARTH OBSERVATIONS (FROM SPACE) Pyroelectric materials as electronic pulse detectors of Assessment of potential for batteries in space Space applications at the crossroads; Proceedings of ultraheavy nuclei p72 A84-23440 the Twenty-first Qoddard Memorial Symposium, Greertbelt, applications p48 N84-12246 ELECTRIC WIRE MD, March 24, 25, 1983 p 64 A84-10883 ENVIRONMENT EFFECTS Orbiting wire as a dynamo: Auxiliary power possibilities The US space station: Potential base for a spacebome Legal aspects of solar power satellites impact on the for space platforms environment p68 A84-17077 microwave facility p78 N84-16420 [IFSI-83-3] p49- N84-12653 Technology needs of advanced Earth observation Evaluation and prediction of long-term environmental ELECTRICAL IMPEDANCE spacecraft effects of nonmetallic materials, second phase Evaluation of bus impedance on the SPOT multimission [NASA-CR-3698] p9 N84-17248 [NASA-CR-170915] p56 N84-11595 platform p44 A84-13521 EARTH ORBITS ELECTRO-OPTICS ENVIRONMENTAL CONTROL Reactions of nigh velocity atomic oxygen with carbon Environmental control and life support (ECLS) design Coordinate transformation assembly — for space [AIAA PAPER 84-0549] p 53 A84-18159 optimization approach p 73 A84-24637 platform angular coordinate linking p 75 A84-28579 EARTH TERMINALS ELECTROCHEMICAL CELLS Environmental Control and Life Support for an Improved orbit utilization using auxiliary feeds in existing Electrochemical and steam-desorbed amine CO2 evolutionary Space Station earth terminals p 46 A84-20647 concentration Subsystem comparison — for oxygen [SAE PAPER 831108] p5 A84-29043 ECCENTRIC ORBITS recovery on Space Station Systems engineering aspects of a preliminary Semiautonomous stafjonkeeping of geosynchronous [SAE PAPER 831120] p6 A84-29054 conceptual design of the space station environmental satellites p32 A84-17359 ELECTROCHEMISTRY control and life, support system ECONOMIC ANALYSIS Assessment of potential for batteries in space [SAE PAPER 831109] p5 A84-29044 Commercial communications satellite market and applications p48 N84-12246 The thermal design of the European complement of technology in the 90's ELECTRODYNAMICS FSLP — First SpaceLab Mission {IAF PAPER 83-86] p 65 A84-11739 Investigation of electrodynamic stabilization and control [SAE PAPER 831144] p 24 A84-29071 Space stations - A key to socio-economic benefits from of long orbiting tethers Regenerate non-venting thermal control subsystem for space? p 69 A84-19850 [NASA-CR-170972] p 40 N84-17251 GEO space platform economics - Impact of concept, extravehicular activity Tethers in space: Birth and growth of a new avenue [SAE PAPER 831151] P 24 A84-29076 size, launch mode and lifetime to space utilization [AIAA PAPER 84-0704] p 74 A84-25281 ENVIRONMENTAL ENGINEERING [NASA-TM-82571] p 18 N84-21607 ECONOMIC DEVELOPMENT Environmental control and life support (ECLS) design ELECTROMAGNETIC COMPATIBILITY The solar power satellite - A programme for optimization approach p 73 A84-24637 Assessment of satellite power flux-density limits in the Systems engineering aspects of a preliminary development aid p68 A84-17074 2025-2300 MHz frequency range, part 1 ECONOMIC FACTORS conceptual design of the space station environmental [PB84-129402] p51 N84-18532 control and life support system Financing a solar power satellite project ELECTRON BEAMS p70 A84-21482 [SAE PAPER 831109] p5 A84-29044 Sheath ionization model of beam emissions from large ECONOMIC IMPACT ENVIRONMENTAL LABORATORIES The Large Space Simulator (LSS) at ESA/ESTEC (a The space van and its potential impact on the design [AD-A137181] p52 N84-19463 summary of the main characteristics) p 27 N84-19458 of communications satellites ELECTRON IRRADIATION [AIAA 84-0758] p 74 A84-25309 Dielectric charging in space - Ground test data and model ENVIRONMENTAL TESTS EIGENVALUES verification p47 A84-20709 The effect of pressure and temperature on Time domain analysis and synthesis of robust controllers ELECTRONS time-dependent changes in graphite/epoxy composites for large scale LOG (Linear Quadratic Gaussian) Interpretation of STS-3/plasma diagnostics package below the glass transition P 54 A84-21775 regulators results in terms of large space structure plasma Effect of temperature, moisture and radiation exposures [AD-A137760] p 43 N84-21172 interactions on composite mechanical properties p 55 A84-28900 ELASTIC BARS [NASA-CR-173266] p 78 N84-16991 EQUATIONS OF MOTION Motion of a symmetric satellite about the center of mass ELECTROSTATIC SHIELDING Validation methods for mathematical models of flexible in circular orbit in the presence of flexible viscoelastic Electrically conductive black optical paint satellite dynamics rods p35 A84-26977 p55 A84-28553 [ESA-CR(P)-1794] p40 N84-17241

A-6 SUBJECT INDEX FLEXIBLE BODIES

EROSION EXPANDABLE STRUCTURES FEEDBACK CONTROL Erosion of mylar and protection by thin metal films Vibration characteristics of self-expanding stayed A flexible structure controller design method using mode [AIAA PAPER 83-2636] P 52 A84-10949 columns for use in space p 34 A84-21237 residualization and output feedback — for Large Flexible ERROR ANALYSIS Synchronously deployable truss structure Space System p32 A84-17369 Model error estimation for distributed systems described [NASA-CASE-LAR-13117-1] p 59 N84-16250 Control of large space structures by elliptic equations P 15 A84-11946 EXPERIMENT DESIGN [AIAA PAPER 84-0081 ] p 32 A84-17866 Evolution of European telecommunication satellite STEP experiment integration p8 N84-17215 Algorithms and computational aspects pertaining to pointing performance EXPERT SYSTEMS block diagonal dominance methods for design of [AIAA PAPER 84-0725] P 34 A84-25291 Knowledge based systems for intelligent robotics decentralized feedback compensation ESA SATE LUTES p57 A84-15667 p15 A84-19108 Unfurtable offset antenna design for multipurpose EXPLORER SATELLITES Sampled data control of large space structures using applications Thermally induced spin rate ripple on spacecraft with constant gain velocity feedback - A negative view [AIAA PAPER 844659] p 16 A84-25259 long radial appendages p 46 A84-19169 Development and application of new technologies in the (NASA-TM-8S058] p 39 N84-16249 Closed-form solutions for feedback control with terminal ESA Olympus Programme EXTERNAL SURFACE CURRENTS constraints p 36 A84-29471 [AIAA PAPER 84-0706] p 4 A84-25282 Spacecraft/plasma interactions and their influence on Experimental study of active vibration control A standardized propulsion module for future field and particle measurements — conferences [AD-A133818] p 38 N84-14546 communications satellites in the 2000 to 3000 kg class [ESA-SP-198] p56 N84-17253 Direct muttjvariable model reference adaptive control [AIAA PAPER 84-0727] p 62 A84-25292 EXTERNAL TANKS with applications to large structural systems Development trends in Europe on satellite clusters and Low cost space science and astronomy platforms in p38 N84-15840 geostationary platforms orbit Selection of noisy sensors and actuators for regulation [AIAA PAPER 84-0703] p 75 A84-25327 (AIAA PAPER 84-0297] p 4 A84-18005 of linear systems — large space structures ESA SPACECRAFT Identification of new potential scientific and technology [AD-A135442] p 51 N84-17931 European utilisation aspects for a space station areas for DoD application. Summary of activities Decentralized control of a large space structure using [IAF PAPER 83-54] p 64 A84-11727 [AD-A134372] p 78 N84-17050 direct output feedback ESTIMATING A large-area gamma-ray imaging telescope system [AD-A136781] p 41 N84-19464 Spline-based estimation techniques for parameters in [NASA-CR-175435] p 14 N84-20604 Time domain analysis and synthesis of robust controllers elliptic distributed systems EXTRATERRESTRIAL INTELLIGENCE for large scale LOG (Linear Quadratic Gaussian) [NASA-TM-85439] p9 N84-17947 Natural selection of stellar civilizations by the limits of regulators EULER-LAGRANGE EQUATION growth [AD-A137760] p 43 N84-21172 Recursive lagrangian dynamics of flexible manipulator [IAF PAPER 83-272] p 65 A84-11779 FIBER COMPOSITES arms via transformation matrices EXTRATERRESTRIAL LIFE New fabric structures of carbon fiber [AD-A137345] p 60 N84-20316 Natural selection of stellar civilizations by the limits of p52 A84-17108 EURECA (ESA) growth Local stability of sandwich structures with thin fibre ESA space station activities [IAF PAPER 83-272] p 65 A84-11779 reinforced face skins for space application [MBB-UD-381-83-OE] p 19 A84-22859 [IAF PAPER 83-30] p 64 A84-11722 EXTRAVEHICULAR ACTIVITY Utilisation of the European retrieval carrier EURECA for Review report of the third year's activities on the study Regenerate non-venting thermal control subsystem for life science research p 65 A84-11753 extravehicular activity survey of advanced materials — for spacecraft and launch The attitude and orbit control system for Eureca vehicles [SAE PAPER 831151 ] p 24 A84-29076 [DGLH PAPER 83-091] p 76 A84-29658 [R878] p56 N84-21675 EUROPE Orbiter-based construction equipment study. The FIBER OPTICS European questions related to satelite power systems HPA/DTA technology advancement plan Communications p 12 N84-18285 p70 AB4-21483 [NASA-CR-174605] p 17 N84-14233 FIBER ORIENTATION EUROPEAN COMMUNICATIONS SATELLITE Crew and life support EVA p 11 N84-18279 Thermal control of tubular composite structures in space Development and application of new technologies in the Space station needs, attributes and architectural environment p22 A84-10440 ESA Olympus Programme options. Volume 2, attachment 2: Supporting data and FIBER REINFORCED COMPOSITES [AIAA PAPER 84-0706] p4 AB4-25282 analysis reports Surface analysis of graphite fiber reinforced polyimide Evolution of European telecommunication satellite [NASA-CR-173329] p 12 N84-18291 composites pointing performance Shuttle interaction study [NASA-TM-85700] p 55 N84-11220 [AIAA PAPER 84-0725] p 34 A84-25291 [NASA-CR-173400] p 80 N84-21592 FINANCIAL MANAGEMENT EUROPEAN SPACE AGENCY Financing large space projects p 67 A84-15321 ESA space station activities Financing a solar power satellite project [IAF PAPER 83-30] p 64 A84-11722 p?0 A84-21482 Spacelab's development p66 A84-13901 Alternative strategies for space station financing Spaceflight to 2000 - Interavia looks forward from the FABRICATION [NASA-CR-175412] p 80 N84-21437 present p66 A84-14764 Materials and construction techniques for large FINGERS Space Station needs, attributes and architectural spacecraft structures p 53 A84-17768 Self-locking telescoping manipulator arm options, volume 2, book 2, part 4: International reports Solar array Shuttle flight experiment - Hardware [NASA-CASE-MFS-25906-1] p 59 N84-11761 [NASA-CR-173319] p 14 N84-18303 development and testing p 47 AS4-22961 FINITE ELEMENT METHOD EUROPEAN SPACE PROGRAMS A comparison of linear and geometrically nonlinear finite Large area space solar cell assemblies ESA space station activities element analyses applied to large space structures p 61 A84-22980 [IAF PAPER 83-30] p 64 A84-11722 [AIAA PAPER 84-0069] p 16 A84-19887 Payload placing using an operational support platform FABRICS Potential of minicomputer-array processor system for [IAF PAPER 83-44] p1 A84-11724 New fabric structures of carbon fiber nonlinear finite-element analysis p 46 A84-20583 European utilisation aspects for a space station p52 A84-17108 The dynamics and control of large flexible space [IAF PAPER 83-54] p 64 A84-11727 FAILURE ANALYSIS structures, 6 The Spacelab test program Graphite/polyimide joints extend temperature limits [NASA-CR-174450] p 36 N84-10173 [AIAA PAPER 83-2685] p 66 AB4-13376 p 55 A84-29572 Finite element analysis of a deployable space The German Spacelab mission 01 p69 A84-17762 An evaluation of Techroll seal flexible joint material structure p 38 N84-16056 Operational planning, simulation, and performance of p 56 N84-16037 Scale model testing for control system parameters of the German Spacelab mission 01 p69 A84-17763 Reliability issues in active control of large flexible space large structures Technology components of solar arrays for space structures [AD-A135652] p 41 N84-18313 platforms p 47 A84-22959 [NASA-CR-175341] p 39 N84-16248 Static and dynamic structural-sensitivity derivative The Franco-German DBS program TV-SAT/TDF-1' FAILURE MODES calculations in the finite-element-based Engineering [AIAA PAPER 84-0661] p4 A84-25260 An evaluation of Techroll seal flexible joint material Analysis Language (EAL) system Tele-X - The first step in a satellite communications p56 N84-16037 [NASA-TM-65743] p 42 N84-20880 system for the Nordic countries FAST FOURIER TRANSFORMATIONS Finite element formulations for tensioned members — [AIAA PAPER 84-0713] p4 A84-25287 Validation methods for mathematical models of flexible large space structures p21 N84-21615 Geodetic aspects of ESA projects, studies and satellite dynamics Geometrically nonlinear analysis of beam-in-space investigations p 78 N84-16677 [ESA-CR(P)-1794] P40 N84-17241 structures The thermal design of L-SAT large telecommunication [MITT-28] p22 NB4-21914 FEASIBILITY ANALYSIS satellite p27 N84-19414 FLEXIBILITY Muttivariable direct adaptive control for a general class EVAPORATORS Multibody dynamics - Analysis of flexibility effects ol time-varying commands p 33 A84-19118 Phase change water recovery techniques - Vapor [AD-A132533] p 36 A84-29145 compression distillation and thermoelectric/membrane Space stations - A key to socio-economic benefits from The dynamics and control of large flexible space concepts — from waste water as part of Space Station space? p 69 A84-19850 structures, 6 life support system FEDERAL BUDGETS [NASA-CR-174450] p 36 NB4-10173 [SAE PAPER 831122] p6 A84-29056 National Aeronautics and Space Administration Act, Control of flexible spacecraft by optimal model EXCITATION 1985 p9 N84-18116 following p36 N84-12222 Dynamic behaviour of a satellite antenna structure in Department of Housing and Urban Flexible radiator system random vibration environment p42 N84-19900 Development-independent agencies appropriations for [NASA-CR-171765] p 28 N84-20623 EXOBIOLOGY 1984: National Aeronautics and Space Administration FLEXIBLE BODIES Utilisation of the European retrieval carrier EURECA for p80 N84-21440 Analysis and design of leaf-spring flexible joints lor life science research p 65 A84-11753 Authorizing appropriations to the National Aeronautics driving gyroscopic rotors p 19 A84-11922 Gravitational biology on the space station and Space Administration for fiscal year 1985 Model error estimation for distributed systems described [SAE PAPER 831133] p 75 A84-29063 [H-REPT-98-629] p 80 N84-21441 by elliptic equations p 15 A84-11946

A-7 FLEXIBLE SPACECRAFT SUBJECTINDEX

Control of large space structures Precise control of flexible manipulators FURLABLE ANTENNAS [AIAA PAPER 84-0081 ] p 32 A84-17866 [NASA-CR-175389] p 60 N84-20175 Unfurlable offset antenna design for multipurpose Aeroelastic stability and response of flexible tactical Exhibit D modular design attitude control system study applications weapons [NASA-CR-170993] p 42 N84-20625 [AIAA PAPER 84-0659] p 16 A84-25259 [AIAA PAPER 84-0392] p 32 AB4-18060 Environmental effects on the dynamics and control of Manipulator interactive design with interconnected an orbiting large flexible antenna system flexible elements p 58 A84-25484 [NASA-CR-175448] p 42 N84-20627 Numerical solution of several classes of nonlinear Derivation and combination of impedance matrices for flexible shell theory problems p35 A84-25S86 GALILEO SPACECRAFT flexible satellites A variational theorem for the viscoelastodynamic Simulation of the Galileo spacecraft axial - Delta-V [ESA-STR-209] p 43 N84-21604 analysis of high-speed linkage machinery fabricated from algorithm p66 A84-11938 FLIGHT CONTROL composite materials Science platform and attitude subsystem in-flight [ASME PAPER 83-DET-6] p 55 A84-29101 A simulator to study dynamic interaction of the Space calibration for the Galileo spacecraft p32 A84-17355 Multibody dynamics - Analysis of flexibility effects Shuttle on-orbit flight control system with deployed flexible GAMMA RAY TELESCOPES [AD-A132S33] p 36 A84-29145 payloads p35 A84-26717 A large-area gamma-ray imaging telescope system Stability enhancement of a flexible robot manipulator Attitude, control and stabilization p 40 N84-18281 (NASA-CR-175435] p 14 N84-20604 [AD-A134185] p 59 N84-16807 FLIGHT SIMULATORS GAS DYNAMICS Attitude, control and stabilization p 40 N84-18281 A simulator to study dynamic interaction of the Space Thermofluidynamics of heat pipes p 27 N84-19423 Capture of satellite stabilized by gravity gradient with a Shuttle on-orbit flight control system with deployed flexible GAS-SOLID INTERACTIONS flexible mast during and after deployment payloads p 35 A84-26717 Reactions of high velocity atomic oxygen with carbon [INPE-2749-PRE/325] p 41 N84-19383 FLIGHT TESTS [AIAA PAPER 84-0549] p 53 A84-18159 FLEXIBLE SPACECRAFT STEP flight experiments Large Deployable Reflector GEARS A methodology to include static and kinetic friction (LDR) telescope p8 N84-17231 Self-locking telescoping manipulator arm effects in Space Shuttle payload transient loads analysis Flight test of a synthetic aperture radar antenna using [NASA-CASE-MFS-25906-1] p 59 N84-11761 GEODESY [AIAA PAPER 83-2654] p 30 A84-10956 STEP p9 N84-17237 Geodetic aspects of ESA projects, studies and Technology requirements for large flexible space Study on synthesis and characterization of large space investigations p 78 N84-16677 structures systems, phase 2. Part 3: Experimental design verification GEODETIC COORDINATES [ IAF PAPER 83-404] p 2 A84-11811 techniques Geodetic control of the reflectors of large antennas Some aspects of simulation studies in spacecraft [ESA-CR(P)-1779-VOL-5] p 18 N84-21620 dynamics p 15 A84-11930 p31 A84-15785 Proposals for additions, modifications, and new Simulation of the motion of a Shuttle-attached flexible GEOMETRY experimental methods. Part 1: Ground tests. Part 2: manipulator arm p 57 A84-11935 Computer-Aided Geometry Modeling Flight tests — large space structures p 15 N84-21623 Simulation of the Galileo spacecraft axial - Delta-V [NASA-CP-2272] p 18 N84-22179 FLOW DISTRIBUTION algorithm p 66 AS4-11938 Interactive geometry modeling of space station Aggregate models for distributed parameter systems On modeling dilution jet flowfields conceptual designs p 18 N84-22191 with applications to flexible air and spacecraft [AIAA PAPER 84-1379] p 58 A84-44183 GEOSYNCHRONOUS ORBITS p31 A84-11945 FLUID DYNAMICS An overview of the institutional and regulatory aspects Dynamics and control of a deformable gyrostat, utilizing Space station attitude control system concept and and their impact on system design — of geostationary continuum vehicle modes p 31 A84-12488 requirements p 37 N84-12234 satellites The Toysat structural control experiment — for large FLUID FILTERS [IAF PAPER 83-82] p 65 A84-11737 flexible space structure p 31 A84-13320 Hyperfiltration wash water recovery subsystem - Design Analytical model of the evolution of orbit parameters A hardware demonstration of control for a flexible and test results — for extended mission spacecraft such of a quasi geostationary satellite offset-feed antenna p 31 A84-13321 as space stations [IAF PAPER 83-316] p 65 A84-11787 Dynamics and control of a large space antenna [SAE PAPER 831112] p6 A84-29047 Autonomous navigation of geosynchronous satellites p32 A84-17361 FLUX DENSITY using the Navstar Global Positioning System A flexible structure controller design method using mode Assessment of potential for batteries in space p45 A84-15671 resldualization and output feedback — for Large Flexible applications p48 NS4-12246 A future solar orbital transfer vehicle concept Space System p32 A84-17369 FLYING PLATFORMS p61 A84-16116 Comments on 'Dynamics of a spacecraft during Multibeam phased arrays - Application to Energy from space - Legal implications of the use of extension Of flexible appendages' p32 A84-17370 SOC/Free-Flyer communication system — Space the geostationary orbit p68 A84-17075 Structural parameter identification for flexible Operation Center p 45 A84-15641 Semiautonomous stationkeeping of geosynchronous spacecraft FLYWHEELS satellites p32 A84-17359 [AIAA PAPER 84-0060] p 23 A84-17853 Integrated Flywheel Technology, 1983 Vertical ascent from earth to geosynchronous orbit Determination of critical parameters in large flexible [NASA-CP-2290] p78 N84-12228 [AIAA PAPER 84-0509] p 61 A84-18141 space structures with uncertain modal data Space station energy sizing p 48 N84-12233 Improved orbit utilization using auxiliary feeds in existing p33 A84-20047 The Boeing flywheel study p 37 N84-12235 earth terminals p 46 A84-20647 Transient dynamics during the orbiter based deployment Space station control requirements and flywheel system Highly efficient, very low-thrust transfer to of flexible members weights for combined momentum and energy storage geosynchronous orbit - Exact and approximate solutions p 61 A84-24980 [AIAA PAPER 84-0061] p 34 A84-21285 p 37 N84-12236 On the number and placement of actuators for IPACS attitude control technology considerations Optimal tow-thrust transfers to synchronous orbit independent modal space control — for large flexible p37 N84-12238 p62 A84-24981 spacecraft p34 A84-24990 Advanced Control and Power System (ACAPS) Reduced domestic satellite orbit spacing Identification of large flexible structures mass/stiffness technology program p 37 N84-12243 [AIAA PAPER 84-0652] p 73 A84-25253 and damping from on-orbit experiments FOILS (MATERIALS) Time phased introduction of advanced technologies - p34 A84-24995 Cracked inner layer foil in high-density multilayer printed Its impact on orbit/spectrum conservation [AIAA PAPER 84-0653] p 74 A84-25254 Static shape forming for an electrostatically controlled wiring boards p 53 A84-17200 membrane mirror p 16 A84-25551 FOLDING STRUCTURES Digital technologies and systems for geostationary orbit A simulator to study dynamic interaction of the Space Self-locking telescoping manipulator arm satellites Shuttle on-orbit flight control system with deployed flexible [NASA-CASE-MFS-25906-1] p 59 N84-11761 [AIAA PAPER 84-0749] p 74 A84-25304 payloads p35 A84-26717 Synchronously deployable truss structure Computer tools for optimizing orbit use Stability of large flexible clamped spacecraft modeled [NASA-CASE-LAR-13117-1] p 59 N84-16250 [AIAA PAPER 84-0651 ] p 74 A84-25318 as elastic continua p 35 A84-26845 Low concentration ratio solar array structural Lessons learned during the first year of the TDRSS Motion of a symmetric satellite about the center of mass configuration p 17 N84-17225 [AIAA PAPER 84-0687] p 74 A84-25319 in circular orbit in the presence of flexible viscoelastic FRACTURE MECHANICS NASA's geostationary communications platform rods p35 A84-26977 Fracture mechanics of ceramics. Volume 5 - Surface program On transient dynamics and stability of large space flaws, statistics, and microcracking p 54 A84-24501 [AIAA PAPER 84-0702] p5 A84-25326 structures p 36 A84-29143 Assessment of reliability of ceramic materials Development trends in Europe on satellite clusters and geostationary platforms Closed-form solutions for feedback control with terminal p54 A84-24508 FRAMES [AIAA PAPER 84-0703] p 75 A84-25327 constraints p 36 A84-29471 Capture-ejector satellites Approximations method for space frame synthesis The effects of the space environment on damping [NASA-TM-85686] p7 N84-15179 materials and damping designs on flexible structures p 19 A84-10141 New elements for analysis of space frames with tapered The role of potential barrier formation in spacecraft p56 N84-17217 charging pSO N84-17269 The 55-meter-structure flight experiment members p 20 N84-14561 FREE VIBRATION Introduction to geostationary orbits p 8 N84-17233 [ESA-SP-1053] p80 N84-21590 Vibration characteristics of self-expanding stayed Validation methods for mathematical models of flexible columns for use in space p 34 A84-21237 GLOBAL POSITIONING SYSTEM satellite dynamics FREQUENCY ASSIGNMENT Autonomous navigation of geosynchronous satellites [ESA-CR(P)-1794] p 40 N84-17241 Land-mobile communications satellite system design using the Navstar Global Positioning System Control of large flexible spacecraft by the independent [AIAA PAPER 84-0753] p 5 A84-25308 p45 A84-15671 modal-space control method FRICTION FACTOR GOVERNMENT/INDUSTRY RELATIONS [NASA-CR-3760] p 40 N84-18262 A methodology to include static and kinetic friction A legal charter for non-governmental space Modular design attitude control system effects in Space Shuttle payload transient loads analysis industrialization [NASA-CR-170996] p 41 N84-19392 (AIAA PAPER 83-2654] p 30 A84-10956 [AAS PAPER 83-225] p 77 A84-29868 Maintenance and operational enhancement of the FUNCTIONAL DESIGN SPECIFICATIONS International competition in commercial aerospace flexible spacecraft dynamics program Space station attitude control system concept and markets [NASA-CR-175211] p 41 N84-19394 requirements p 37 N84-12234 [AAS PAPER 83-244] p 77 A84-29883

A-8 SUBJECT INDEX INTERNATIONAL COOPERATION

GRAPHITE HARDWARE I Thermal-mechanical behavior of graphite/magnesium Hardware simulation of spacecraft dynamics and composites P 24 A84-28237 control p30 A84-11932 IMPACT. GRAPHITE-CPOXY COMPOSITES The flexural behavior of PACSAT (passive Reid repair of graphite epoxy skin panels on the [NASA-CR-170948] p 78 N84-16097 communication satellite) in orbit spaceship Columbia p 52 A84-17120 HEAT EXCHANGERS [AD-A131406] p36 N84-11195 The effect of pressure and temperature on Multi-megawatt space power thermal management IN-FLIGHT MONITORING time-dependent changes in graphite/epoxy composites system requirements Science platform and attitude subsystem in-flight below the glass transition p 54 A84-21775 [AIAA PAPER 84-0056] p 23 A84-21284 calibration for the Galileo spacecraft p 32 A84-17355 Design and development of the INTELSAT V Thermal management system technology development INERTIAL UPPER STAGE graphite-epoxy central thrust tube p 19 A84-22I53 for space station applications An evaluation of Techroll seal flexible joint material p56 N84-16037 GRAPHITE-POLYIMIDE COMPOSITES [SAE PAPER 831097] p 24 A84-29032 INFLATABLE SPACECRAFT Higher temperature composite joints survive elimination Thermal control p 25 N84-18289 Study on large, ultralight long-life structures in space, tests p55 A84-29565 HEAT FLUX phase 2C Graphite/polyimide joints extend temperature limits Thermal analysis research applicable to space station [TM-EKR3] p17 N84-17284 pSS A84-29572 technology needs INFLATABLE STRUCTURES Surface analysis of graphite fiber reinforced potyimide [NASA-TM-84658] p 25 N84-15426 Large inflated-antenna system p9 N84-17234 composites HEAT PIPES INFORMATION DISSEMINATION [NASA-TM-85700] p 55 N84-11220 Thermal management system technology development Crew and life support EVA p11 N84-18279 GRAPHS (CHARTS) for space station applications INFORMATION MANAGEMENT Space station energy sizing p 48 N84-12233 [SAE PAPER 831097] p 24 A84-29032 Space Station needs, attributes and architectural GRAVITATIONAL EFFECTS Heat pipes for the L-SAT communications module options. Volume 2, book 2, part 2, Task 2: Information Periodic oscillations of a gyrostat satellite with respect radiators p 26 N84-19405 management system to the centers of mass in a circular orbit A Variable Conductance Heat Pipe (VCHP) radiator [NASA-CR-173317] p 13 N84-18301 p33 A84-19728 system for communications payloads p 27 N84-19406 INFRARED ASTRONOMY Gravitational biology on the space station Thermofluidynamics of heat pipes p 27 N84-19423 Large Deployable Reflector (LOR) - A concept for an [SAE PAPER 831133] p 75 A84-29063 HEAT RADIATORS orbiting submillimeter-infrared telescope for the 1990s Micrograviry conditions on orbital platforms Thermal management system technology development p 66 A84-14586 [DGLR PAPER 83-90] p 76 A84-29657 for space station applications INFRARED RADIATION Tethers in space: Birth and growth of a new avenue [SAE PAPER 831097] p 24 A84-29032 Development of a spacecraft infrared test technique as an alternative to solar simulation: First steps on L-SAT to space utilization Space Station Technology, 1983 [NASA-TM-82571] p 18 N84-21607 [NASA-CP-2293] p 11 N84-18277 thermal model p26 N84-19398 Spacecraft thermal balance testing using infrared lamps GRAVITATIONAL FIELDS Thermal control p 25 N84-18289 The residual gravitational field of orbital space stations on a dummy spacecraft p26 N84-19399 Flexible radiator thermal vacuum test report IRSIM: A program for the calculation of infrared flux [DGLR PAPER 83-089] p 75 A84-29656 [NASA-CR-171764] p 28 N84-20622 GRAVITY GRADIENT SATELLITES intensity incident on a spacecraft inside a test chamber Capture of satellite stabilized by gravity gradient with a Flexible radiator system: Executive summary p26 N84-19400 [NASA-CR-171766] p 28 N84-20624 flexible mast during and after deployment INFRARED TELESCOPES [INPE-2749-PRE/325] p 41 N84-19383 HEAT SHIELDING Large Deployable Reflector (LDR) - A concept for an GROUND STATIONS Spacecraft thermal control, design, and operation orbiting submillimeter-infrared telescope for the 1990s Narrow multibeam satellite ground station antenna p22 A84-10224 p66 A84-14586 employing a linear array with a geosynchronous arc HEAT STORAGE STEP flight experiments Large Deployable Reflector coverage of 60 deg. II - Antenna design Sodium heat transfer system modeling (LDR) telescope p8 N84-17231 p46 A84-17743 [DE84-002051 ] p 25 N84-16509 INSTRUMENT ORIENTATION Lessons learned during the first year of the TDRSS HEAT TRANSFER Geometric modeling of large space antenna [AIAA PAPER 84-0687] p 74 A84-25319 Sodium heat transfer system modeling deployment p 22 N84-22225 GROUND SUPPORT EQUIPMENT [DE84-002051] p 25 N84-16509 INTEGRATED ENERGY SYSTEMS Spacelab data book IPACS attitude control technology considerations Thermal energy management process experiment p 37 N84-12238 [ESA-BR-14] p79 N84-18315 p25 N84-17222 GROUND SUPPORT SYSTEMS IPACS guidance navigation and control system Startab Ground System guidelines document HEAVY NUCLEI considerations and test activities p 37 N84-12245 [NASA-CR-175192] p 14 N84-20435 Pyroelectric materials as electronic pulse detectors of INTEGRITY ultraheavy nuclei p 72 A84-23440 GROUND TESTS Integrity control of carbon fiber reinforced plastics Solar array Shuttle flight experiment - Hardware HELIUM-NEON LASERS structural elements, phase 1 report — space development and testing p 47 A84-22961 Application of laser interferometry to robotics applications Study on synthesis and characterization of large space p58 A84-28541 [TB-TS-11-01/82-A] p 56 N84-18416 INTELSAT SATELLITES systems, phase 2. Part 3: Experimental design verification HEURISTIC METHODS Solar power satellites - The institutional challenge techniques A heuristic method for the design of minimum weight p70 A84-21479 [ESA-CR(P)-1779-VOL-5] p 18 N84-21620 trusses using discrete member sizes p 15 A84-16841 Assessment of the existing ground test technology and Design and development of the INTELSAT V HIGH POWER LASERS confronting with the Large Space Structures (LSS) graphite-epoxy central thrust tube p 19 A84-22153 Identification of new potential scientific and technology Technical aspects of the Intelsat V solar array requirements. Experimental techniques in structural areas for DoD application. Summary of activities analysis p29 N84-21621 p47 A84-22962 [AD-A134372] p 78 N84-17050 Assessment of the existing ground test technology and INTERACTIVE CONTROL confronting with the Large Space Structures (LSS) HIGH VOLTAGES A voice interactive system for aiding and documentation requirements. Thermal test techniques Radiating dipole model of interference induced in of space-based tasks p29 N84-21622 spacecraft circuitry by surface discharges [AIAA PAPER 83-2355] p 43 AB4-10025 Proposals for additions, modifications, and new [NASA-TP-2240] p 50 N84-16247 Algorithms and computational aspects pertaining to experimental methods. Part 1: Ground tests. Part 2: HUBBLE SPACE TELESCOPE block diagonal dominance methods for design of Right tests — large space structures p 15 N84-21623 Space telescope decentralized feedback compensation GUIDANCE SENSORS [NASA-CR-170948] p 78 N84-16097 p15 A84-19108 Manipulator interactive design with interconnected IPACS guidance navigation and control system HUMAN FACTORS ENGINEERING considerations and test activities p37 N84-12245 flexible elements p58 AB4-25484 Habitability design elements for a space station Interactive structural-thermal-control analytical GUY WIRES [AAS PAPER 83-200] p7 A84-29853 Vibration characteristics of self-expanding stayed formulations — large space structures columns for use in space p 34 A84-21237 Space Applications of Automation, Robotics and p29 N84-21619 GYROSCOPIC STABILITY Machine Intelligence Systems (ARAMIS), phase2. Volume INTERNATIONAL COOPERATION Dynamics and control of a deformable gyrostat, utilizing 1: Telepresence technology base development European utilisation aspects for a space station [NASA-CR-3734] p 59 N84-10S83 continuum vehicle modes p31 A84-12488 [IAF PAPER 83-54] p 64 A84-11727 Attitude stability for the yaw-wheel class of orbiting Space Applications of Automation, Robotics and An overview of the institutional and regulatory aspects gyrostats p33 A84-19675 Machine Intelligence Systems (ARAMIS), phase 2. Volume and their impact on system design — of geostationary Periodic oscillations of a gyrostat satellite with respect 2: Telepresence project applications satellites to the centers of mass in a circular orbit [NASA-CR-3735] p 59 N84-10584 [IAF PAPER 83-82] p 65 A84-11737 Spacelab's development p 66 A84-13901 p 33 A84-19728 HYBRID PROPULSION Spaceflight to 2000 - Interavia looks forward from the Vertical ascent from earth to geosynchronous orbit present p 66 A84-14764 [AIAA PAPER 84-0509] p 61 A84-18141 H Determination of applicable law to living and working HYDRAZINE ENGINES in space HABIT ABILITY Why don't we use ion propulsion? [IAF PAPER 82-IISL-45] p 68 A84-17058 Habitability design elements for a space station [AIAA PAPER 84-0730] p 62 A84-25294 The solar power satellite - A programme for [AAS PAPER 83-200] p7 A84-29853 HYDRODYNAMICS development aid p 68 A84-17074 HANGARS Second Ail-Union Seminar on Hydromechanics and Energy from space - A vision of the future Development of deployable structures for large space Heat-Mass Transfer in Weightlessness. Abstracts of p69 A84-21477 platforms. Volume 2: Design development reports: Table of contents Solar power satellites - The institutional challenge [NASA-CR-170914] p 20 N84-10176 [NASA-TM-77534] p 26 N84-18576 p70 A84-21479

A-9 INTERNATIONAL LAW SUBJECT INDEX

Financing a solar power satellite project The thermal design of L-SAT large telecommunication The development of a composite beam building machine p70 A84-21482 satellite p 27 N84-19414 for on-site construction of large space structures Integrated requirements for a space station LAGUERRE FUNCTIONS [AAS PAPER 83-217] p 20 A84-29862 p4 A84-24628 Validation methods for mathematical models of flexible The dynamics and control of large flexible space Tele-X - The first step in a satellite communications satellite dynamics structures, 6 system for the Nordic countries [ESA-CR(P)-1794] p40 N84-17241 [NASA-CR-174450] p 36 N84-10173 [AIAA PAPER 84-0713] p4 A84-25287 LAMINATES Development of deployable structures for large space International aspects of commercial space activities Cracked inner layer foil in high-density multilayer printed platform systems. Volume 1: Executive summary [AAS PAPER 83-222] p 77 A84-29866 wiring boards p 53 A84-17200 [NASA-CR-170913] p 20 N84-10175 Space Station needs, attributes and architectural Development of deployable structures for large space A variational theorem for the viscoelastodynamic options, volume 2, book 2, part 4: International reports analysis of high-speed linkage machinery fabricated from platforms. Volume 2: Design development [NASA-CR-173319] p 14 N84-18303 [NASA-CR-170914] p 20 N84-10176 composite materials INTERNATIONAL LAW [ASME PAPER 83-DET-6] p 55 A84-29101 Large space instrumentation to measure the interaction Determination of applicable law to living and working between space structures and the environment LAND MOBILE SATELLITE SERVICE in outer space [AD-A129990] p 77 N84-10179 An advanced generation land mobile satellite system [IAF PAPER 82-IISL-44] p 68 A84-17057 Actuator placement considerations for the control of and its critical technologies p3 A84-15634 Energy from space - Legal implications of the use of large space structures p 20 N84-11199 the geostationary orbit p68 A84-17075 MSAT mobile communication demonstration satellite Resistojet propulsion for large spacecraft systems Legal aspects of solar power satellites impact on the system and bus tradeoff considerations [NASA-TM-83489] p 63 N84-11206 environment p68 A84-17077 [AIAA PAPER 84-0751] p 48 A84-25306 Control of flexible spacecraft by optimal model INTERSTELLAR TRAVEL Land-mobile communications satellite system design following p 36 N84-12222 Mankind's interstellar future p 71 A84-21499 [AIAA PAPER 844753] p5 A84-25308 Study of auxiliary propulsion requirements for large Interstellar solar sailing - Consideration of real and LARGE SPACE STRUCTURES space systems. Volume 1: Executive summary projected sail materials p 62 A84-25344 Technology requirements for large flexible space [NASA-CR-168193-VOL-1] p 63 N84-12226 Roundtrip interstellar travel using laser-pushed structures Analysis of large space structures assembly: lightsails p62 A84-27443 [IAF PAPER 83-404] . p2 A84-11811 Man/machine assembly analysis ION BEAMS Tests and prediction of composite material viscoelastic [NASA-CR-3751] p 59 N84-13208 Sheath tonization model of beam emissions from large behaviour for large space structure Study of auxiliary propulsion requirements for large spacecrafts [IAF PAPER 83-418] p 30 A84-11815 space systems, volume 2 [AD-A137181] pS2 N84-19463 Torque from solar radiation pressure gradient during [NASA-CR-168193-VOL-2] p 63 N84-13218 ION ENGINES eclipse — for very large spacecraft p 31 A84-12489 Active control of large flexible space structures Control structure interactions in large space structures p37 N84-14235 The Toysat structural control experiment — for large Analysis using energy approach — for constant and pulsed New elements for analysis of space frames with tapered flexible space structure p 31 A84-13320 thrusters p 35 A84-27934 members p 20 N84-14561 A hardware demonstration of control for a flexible ION IMPLANTATION ACOSS Fourteen (Active Control of Space Structures) offset-feed antenna p31 A84-13321 [AD-A133411] p38 N84-15181 p 61 A84-22980 Coherent arrays of separate optical telescopes in space Direct multivariable model reference adaptive control ION PROPULSION project Trio p3 A84-15363 with applications to large structural systems Why don't we use ion propulsion? Dynamics and control of a large space antenna p38 N84-15840 [AIAA PAPER 84-0730] p 62 A84-2S294 p32 A84-17361 Finite element analysis of a deployable space Discontinuous low thrust orbit transfer A flexible structure controller design method using mode structure p38 N84-16056 [AD-A136908] p 63 N84-19474 residualization and output feedback — for Large Flexible Digital control system for space structural dampers IONIZATION Space System p32 A84-17369 [NASA-CR-175355] p 39 N84-16246 Sheath ionization model of beam emissions from large Materials and construction techniques for large Reliability issues in active control of large flexible space spacecrafts spacecraft structures p53 A84-17768 structures [AD-A137181] p52 N84-19463 Structural parameter identification for flexible [NASA-CR-175341] p 39 N84-16248 IONOSPHERIC PROPAGATION spacecraft Surface accuracy measurement sensor test on a The effects of aperture antennas after signal propagation [AIAA PAPER 84-0060] p 23 A84-17853 50-meter antenna surface model through anisotropic ionized media Control of large space structures [NASA-TM-85689] p 17 N84-16427 [AD-A138286] p 52 N84-21781 [AIAA PAPER 84-0081 ] p 32 A84-17866 Self-shadowing of orbiting trusses IONS Radiation-conduction interaction in large space [NASA-CR-173215] p 25 N84-16565 Interpretation of STS-3/plasma diagnostics package structures Interpretation of STS-3/plasma diagnostics package results in terms of large space structure plasma [AIAA PAPER 84-0144] p 23 A84-17911 results in terms of large space structure plasma interactions The spatial order reduction problem and its effect on interactions [NASA-CR-173266] p 78 N84-16991 adaptive control of distributed parameter systems [NASA-CR-173266] p 78 N84-16991 IRRADIATION p33 A84-19056 STEP Experiment Requirements Surface analysis of graphite fiber reinforced polyimide A large space structure benchmark problem - ACOSS [NASA-CP-2294] p7 N84-17211 composites Model No. 2 p 33 A84-19127 Deployable beam flight experiment (MAST) [NASA-TM-85700] p 55 N84-11220 Number crunching on the ACOSS Model No. 2 p8 N84-17218 p33 A84-19128 The STEP/STACBEAM experiment technology Matrix(X) - Application to large space structure control development for very large solar array deployers design problems p 16 A84-19129 p8 N84-17220 Sampled data control of large space structures using General requirements for Shuttle flight experiments JET FLOW constant gain velocity feedback - A negative view p8 N84-17221 On modeling dilution jet flowfields p46 A84-19169 Photovoltaic concentrator pointing dynamics and plasma p58 A84-44183 [AIAA PAPER 84-1379] A comparison of linear and geometrically nonlinear finite interaction study p50 N84-17224 JOINTS (JUNCTIONS) element analyses applied to large space structures Low concentration ratio solar array structural Analysis and design of leaf-spring flexible joints for [AIAA PAPER 84-0069] p 16 A84-19887 configuration ' p 17 N84-17225 driving gyroscopic rotors p 19 A84-11922 Determination of critical parameters in large flexible Development of Test Article Building Block (TABB) for Welded solar cell interconnection p 19 A84-22965 space structures with uncertain modal data deployable platform systems p21 N84-17226 Higher temperature composite joints survive elimination . p33 A84-20047 A deployable structure and solar array controls tests p55 A84-29565 Potential of minicomputer-array processor system for experiment for STEP p 39 N84-17227 Graphite/polyimide joints extend temperature limits nonlinear finite-element analysis p 46 A84-20583 vibration isolation technology experiment p55 A84-29572 Solar array Shuttle flight experiment - Hardware p39 N84-17228 development and testing p 47 A84-22961 Integrated Power/Attitude Control System (IPACS) K New component development for murb-100 kW low-cost technology experiment p39 N84-17229 solar array applications p 47 A84-22963 Investigation of articulated panel dynamics On the number and placement of actuators for p40 N84-17230 KEVLAR (TRADEMARK) independent modal space control — for large flexible Large deployable antenna flight experiment for the Review report of the third year's activities on the study spacecraft p 34 A84-24990 survey of advanced materials — for spacecraft and launch Space Technology Experiments Platform (STEP) Identification of large flexible structures mass/stiffness p8 N84-17232 vehicles and damping from on-orbit experiments [R878] p56 NS4-21675 The 55-meter-structure flight experiment p34 A84-24995 p8 NS4-17233 KINEMATICS Some applications of direct adaptive control to large Dynamics of nonrigid articulated robot linkages structural systems p 34 A84-25496 Study on large, ultralight long-life structures in space, phase 2C p58 A84-25531 Use of electromagnetic models in the optimal control [TM-EKR3] p 17 N84-17284 of large space antennas p 35 A84-25552 Stability of large flexible damped spacecraft modeled Selection of noisy sensors and actuators for regulation as elastic continue p 35 A84-26845 of linear systems — large space structures Control structure interactions in large space structures [AD-A135442] p 51 N84-17931 L-SAT Analysis using energy approach—for constant and pulsed Control of large flexible spacecraft by the independent Development of a spacecraft infrared test technique as thrusters p 35 A84-27934 modal-space control method an alternative to solar simulation: First steps on L-SAT Thermal-mechanical behavior of graphite/magnesium [NASA-CR-3760] p 40 N84-18262 thermal model p26 N84-19398 composites p 24 A84-28237 ACOSS eleven (Active Control Of Space Structures), Heat pipes for the L-SAT communications module On transient dynamics and stability of large space volume 1 radiators p 26 N84-19405 structures p36 A84-29143 [AD-A135675] p 40 N84-18311

A-10 SUBJECTINDEX MANNED SPACECRAFT

ACOSS eleven (Active Control Of Space Structures), UBRAT1ONAL MOTION M volume 2 Transient dynamics during the orbiter based deployment (AD-A135676) p 41 NB4-18312 of flexible members MAGNESIUM The thermal design of L-SAT large telecommunication [AIAA PAPER 84-0061] p 34 A84-21285 Thermal-mechanical behavior of graphite/magnesium satellite p27 N84-19414 UFE SUPPORT SYSTEMS composites p 24 A84-28237 Decentralized control of a large space structure using Environmental control and life support (ECLS) design MAINTENANCE direct output feedback optimization approach p 73 A84-24637 Field repair of graphite epoxy skin panels on the [AD-A136781] P 41 N84-19484 Environmental Control and Life Support for an spaceship Columbia p52 A84-17120 evolutionary Space Station The effect of mass and stiffness changes on the damping MAN MACHINE SYSTEMS [SAE PAPER 831108] p5 A84-29043 factor in a large space structure as represented by the Space station autonomy requirements Probable missions and transportation scenarios to use CSDL 2 model [AIAA PAPER 83-2352] p 63 A84-10024 regenerative life support systems [AO-A136984] P 42 N84-19465 Automation, Robotics, and Machine Intelligence [AAS PAPER 83-201] p 76 A84-29854 Systems (ARAMIS) in space manufacturing Analysis of large space structures p 18 NS4-20621 Space Station Technology, 1983 p58 A84-22337 Construction concept for erecting an offset-fed [NASA-CP-2293] p11 N84-18277 Habitability design elements for a space station antenna Crew and life support ECLSS p 11 N84-18280 [AAS PAPER 83-200] p 7 A84-Z9853 [NASA-TM-85774] p 60 N84-20626 LINE OF SIGHT COMMUNICATION A program to develop efficient manned operations in Environmental effects on the dynamics and control of Space operations center communications path an orbiting large flexible antenna system obscuration p3 A84-1S695 [AAS PAPER 83-207] p 76 A84-29857 [NASA-CR-175448] p 42 N84-20627 Assessment of satellite power flux-density limits in the Space applications of Automation, Robotics And Feasibility of remotely manipulated welding in space. 2025-2300 MHz frequency range, part 1 Machine Intelligence Systems (ARAMIS). Volume 3. phase A step in the development of novel joining technologies [PB84-129402] p 51 N84-18532 2: Executive summary [NASA-CR-175437J P 60 N84-20857 LINEAR ARRAYS [NASA-CR-3736] p 59 N84-10582 Study on synthesis and characterization of large space Narrow multibeam satellite ground station antenna Space Applications of Automation, Robotics and systems, phase 2- Part 2: Proposals for additions, employing a linear array with a geosynchronous arc MachinelntelligenceSystems(ARAMIS),phase2. Volume modifications and new analytical methods, volume 1 coverage of 60 deg. II - Antenna design 1: Telepresence technology base development [ESA-CR(PH779-VOL-3] p 43 N84-21611 p46 A84-17743 [NASA-CR-3734] p 59 N84-10583 The solution of the dynamic problem of the periodic LINEAR SYSTEMS Space Applications of Automation, Robotics and structures by cyclosymmetric technique — large space A comparison of linear and geometrically nonlinear finite Machine Intelligence Systems (ARAMIS), phase 2. Volume structures p43 N84-21612 element analyses applied to large space structures 2: Telepresence project applications [AIAA PAPER 84-0069] p 16 A84-19887 Computing the radiation pressure forces by adapting [NASA-CR-3735] p 59 N84-10584 A degree of controllability definition - Fundamental thermal design verification softwares — large space Analysis of large space structures assembly: concepts and application to modal systems structures p28 N84-21613 Man/machine assembly analysis p 34 A84-24991 [NASA-CR-3751] p 59 N84-13208 Simplified models and computational schemes of the Controllability and observability criteria for multivariable Space Station Technology, 1983 aerodynamic load — large space structures linear second-order models p 35 A84-25516 p28 N84-21614 [NASA-CP-2293] p 11 N84-18277 Selection of noisy sensors and actuators for regulation Human capabilities p11 N84-18282 Finite element formulations for tensioned members — of linear systems — large space structures A manned-machine space station construction large space structures p21 N84-2161S [AD-A135442] p 51 N84-17931 concept Study on synthesis and characterization of large space Time domain analysis and synthesis of robust controllers [NASA-TM-85762] p 21 N84-19395 systems, phase 2. Part 2: Proposals for additions, for large scale LOG (Linear Quadratic Gaussian) MANAGEMENT METHODS modifications and new analytical methods, volume 2 regulators Management of large space projects; Course on Space [ESA-CR(P)-1779-VOL-4] p 29 NB4-21616 [AD-A137760] . p43 N84-21172 Technology, Toulouse, France. May 3-14, 1982, Thermal design verification of the large open truss LINKAGES Proceedings p 2 A84-15301 structures. The local approach and the shadow problem Dynamics of nonrigid articulated robot linkages Human organization — and space project — large space structures p29 N84-21617 p58 A84-25531 management p2 A84-15303 Computational savings in view factor evaluation on mode A variations! theorem for the viscoelastodynamic The progression of projects — in space industry prescreening — large space structures analysis of high-speed linkage machinery fabricated from p2 A84-15305 p29 N84-21618 composite materials MANAGEMENT PLANNING Interactive structural-thermal-control analytical [ASME PAPER 83-DET-6] p 55 A84-29101 Shuttle interaction study extension formulations — large space structures LISP (PROGRAMMING LANGUAGE) [NASA-CR-173403] p 81 N84-21596 p29 N84-21619 Implementation of MACLISP on a large address space MANIPULATORS Study on synthesis and characterization of large space computer Remote manipulators in space p 57 A84-22336 systems, phase 2. Part 3: Experimental design verification [DE84-005042] p 79 N84-21145 Manipulator interactive design with interconnected techniques LOADS (FORCES) flexible elements p 58 A84-25484 [ESA-CR(P)-1779-VOL-5] p 18 N84-21620 The flexural behavior of PACSAT (passive Dynamics of nonrigid articulated robot linkages Assessment of the existing ground test technology and communication satellite) in orbit p58 AB4-25531 confronting with the Large Space Structures (LSS) [AD-A131406] p36 N84-11195 Self-locking telescoping manipulator arm requirements. Experimental techniques in structural LOCKING [NASA-CASE-MFS-25906-1] p 59 N84-11761 analysis p29 N84-21621 Self-locking telescoping manipulator arm Stability enhancement of a flexible robot manipulator Assessment of the existing ground test technology and [NASA-CASE-MFS-25906-1] p 59 N84-11761 [AD-A134185] p59 N84-16807 confronting with the Large Space Structures (LSS) LONG DURATION SPACE FLIGHT Recursive lagrangian dynamics of flexible manipulator requirements. Thermal test techniques Roundtrip interstellar travel using laser-pushed arms via transformation matrices p29 N84-21622 lightsails p62 A84-27443 [AD-A137345] p 60 N84-20316 Proposals for additions, modifications, and new LONG TERM EFFECTS MANNED ORBITAL LABORATORIES experimental methods. Part 1: Ground tests. Part 2: Evaluation and prediction of long-term environmental • Jurisprudentel philosophies of the art of living in space Flight tests — large space structures p 15 N84-21623 effects of nonmetalllc materials, second phase The transnational imperative Study on synthesis and characterization of large space [NASA-CR-170915] p 56 N84-11595 [IAF PAPER 82-IISL-38] p 68 A84-17054 systems, phase 2. Part 1: Assessment of design Auxiliary propulsion p11 NB4-18283 Space stations - A key to socio-economic benefits from verification analytical methods. Volume 1: Mechanical LOW ALTITUDE space? p69 A84-19850 design Thermal control of tethered satellite in a very low altitude The role of man in space p 72 A84-24627 (ESA-CR(P)-1779-VOL-1) p18 N84-21624 aerodynamic mission p27 N84-1S444 Integrated requirements for a space station Study on synthesis and characterization of large space LOW COST p4 A84-24628 systems, phase 2. Part 1: Assessment of design Mechanical wraparound contacted cell for low cost Use of space station for science p 72 A84-24629 verification analytical methods. Volume 2: Thermal space arrays p 48 A84-22982 MANNED SPACE FLIGHT design LOW GRAVITY MANUFACTURING Overview of space station operations [ESA-CR(P)-1779-VOL-2J p 18 N84-21625 Manufacturing In space; Proceedings of the Winter [IAF PAPER 83-38] p 64 A84-11723 LASER GUIDANCE Annual Meeting, Boston, MA, November 13-18.1983 The German Spacelab mission D1 p69 A84-17762 Application of laser interferometry to robotics p 71 AB4-22327 Manned planetary missions? p 71 AB4-21497 pS8 AB4-28541 LOW PRESSURE Mankind's interstellar future p71 A84-21499 LASER INTERFEROMETRY The effect of pressure and temperature on For the first time — Russian book on construction of Application of laser interferometry to robotics time-dependent changes in graphite/epoxy composites first Soviet earth satellites p 16 A84-21564 pS8 A84-28S41 below the glass transition p 54 A84-21775 Space vehicles — Russian book on development of LASER PROPULSION LOW THRUST PROPULSION Soviet spacecraft and planning of first manned flights Vertical ascent from earth to geosynchronous orbit Highly efficient, very low-thrust transfer to p4 A84-21573 (AIAA PAPER 84-0509] p 61 A84-18141 geosynchronous orbit - Exact and approximate solutions Hyperfiltrabon wash water recovery subsystem - Design Transportation - Options and high payoff choices — for p 61 A84-24980 and test results — for extended mission spacecraft such spacecraft propulsion p 61 AB4-21484 Optimal low-thrust transfers to synchronous orbit Roundtrip interstellar travel using laser-pushed p62 A84-24981 (SAE PAPER 831112] p6 A84-29047 lightsails p 62 A84-27443 LOW WEIGHT An alternate concept for expanding man's presence In LAWS Approximations method for space frame synthesis IPACS attitude control technology considerations p 19 A84-10141 [NASA-TM-84617] p7 N84-15172 p37 N84-12238 LUNAR FLIGHT MANNED SPACECRAFT LEAD ACID BATTERIES Management of the radiolink of the solar sail spacecraft Overview of NASA space station activities Assessment of potential for batteries in space by radio-amateurs [IAF PAPER 83-48] pt A84-11726 applications p48 NS4-12246 [IAF PAPER 83-447] p 44 A84-11823 The role of man in space p 72 A84-24627

A-11 MARKET RESEARCH SUBJECT INDEX

MARKET RESEARCH MECHANICS (PHYSICS) Use of space station for science p 72 A84-24629 Market potential and possible limitations for satellite U.S. National Congress of Applied Mechanics, 9th, The role of space station in earth sciences solar power stations p 70 A84-21481 Cornell University, Ithaca, NY, June 21-25, 1982, p72 A84-24631 MSAT mobile communication demonstration satellite Proceedings p75 A84-29126 Probable missions and transportation scenarios to use system and bus tradeoff considerations MEMBRANE STRUCTURES regenerative life support systems [AIAA PAPER 84-0751] p 48 A84-25306 Static shape forming for an electrostatically controlled [AAS PAPER 83-201 ] p 76 A84-29854 MARKETING membrane mirror p 16 A84-25551 Payload missions integration Commercial communications satellite market and METAL FILMS [NASA-CR-170949] p7 N84-15171 technology in the 90's Erosion of mylar and protection by thin metal films An alternate concept for expanding man's presence in [IAF PAPER 83-86] p 65 A84-11739 [AIAA PAPER 83-2636] p 52 A84-10949 space MARS (PLANET) METAL MATRIX COMPOSITES [NASA-TM-84617] p7 N84-15172 Mission to Mars - The case for a settlement Thermal-mechanical behavior of graphite/magnesium STS-9: Orbital workshop spacelab to fly on ninth Shuttle p67 A84-15092 composites p 24 A84-28237 mission MARS ENVIRONMENT SiC-reinforced-aluminum alloys for aerospace [NASA-TM-85497] p 78 N84-16242 Mission to Mars - The case for a settlement applications p 54 A84-28242 Space station needs, attributes and architectural options p67 A84-15092 MICROCRACKS study. Volume 1: Executive study MATERIALS HANDLING Thermo-mechanical behaviour of CFRP tubes for space [NASA-CR-173334] p 9 N84-18265 Shutter Interaction Study structures Space station needs, attributes and architectural options [NASA-CR-173402] p 81 N84-21595 [IAF PAPER 83-417] p 22 A84-11814 study. Volume 2: Mission analysis MATERIALS SCIENCE Fracture mechanics of ceramics. Volume 5 - Surface [NASA-CR-173333] p9 N84-18266 Manufacturing in space; Proceedings of the Winter flaws, statistics, and microcracking p 54 A84-24501 Space station needs, attributes and architectural options Annual Meeting, Boston, MA, November 13-18, 1983 MICROMETEOROIDS study. Final executive review p 71 A84-22327 Flexible radiator thermal vacuum test report [NASA-CR-173335] p 10 N84-18269 MATERIALS TESTS [NASA-CR-171764] p 28 N84-20622 Space station needs, attributes and architectural Tests and prediction of composite material viscoelastic MICROPROCESSORS options. Part 1: Summary behaviour for large space structure Characteristics of the microprocessor implementation [NASA-CR-175382] p 10 N84-18270 [IAF PAPER 83-418] p 30 A84-11815 of algorithms for the processing of radio signals and noise Space Station needs, attributes and architectural Using the outgassing test to screen materials for in large antenna arrays p 48 A84-28067 options: Summary briefing contamination potential p 53 A84-17174 MICROWAVE ANTENNAS [NASA-CR-173328] p 10 N84-18271 Simulated space radiation effects on dielectrics and The small transmitter receiver stations in the Sirio Space station needs, attributes and architectural options coatings p 54 A84-20682 experiment — microwave transmission study. Briefing material: Final review and executive Electrically conductive black optical paint [FUB-50-1982] p49 N84-15386 summary p 55 A84-28553 Adaptive microwave reflector p 50 N84-17235 [NASA-CR-173321] p 10 N84-18273 MATHEMATICAL MODELS Microwave reflector characterization using simple Space Station needs, attributes, and architectural Model error estimation for distributed systems described instruments in EVA p 50 N84-17236 options study by elliptic equations p 15 A84-11946 MICROWAVE EQUIPMENT [NASA-CR-173327] p11 N84-18274 Thermal design verification of the large open truss The US space station: Potential base for a spacebome Space station needs, attributes and architectural structures. The local approach and the shadow problem microwave facility p 78 N84-16420 options. Summary of major study activities and results. — large space structures p29 N84-21617 MICROWAVE RADIOMETERS Space station program observations Development of procedures for component mode Technology needs of advanced Earth observation [NASA-CR-173345] p11 N84-18275 synthesis spacecraft Space station needs, attributes and architectural [DFVLR-IB-232-82-C-09] p 30 N84-21626 [NASA-CR-3698] p9 N84-17248 options. Volume 4, attachment 1: Task 2 and 3 mission Computer-Aided Geometry Modeling MICROWAVE TRANSMISSION implementation and cost [NASA-CP-2272] p 18 NB4-22179 Application of beam power technology to a space [NASA-CR-173330] p 12 N84-18290 Interactive geometry modeling of space station Station p45 A84-15642 Space station needs, attributes and architectural conceptual designs p 18 N84-22191 An electric propulsion transportation system from options. Volume 1, attachment 1: Executive summary Mathematical synthesization of complex structures low-earth orbit to geostationary orbit utilizing beamed NASA p19 N84-22224 microwave power p61 A84-21485 [NASA-CR-173337] p 12 N84-18293 MATRICES (MATHEMATICS) Radiation characteristics of array antennas with Space station needs, attributes and architectural Recursive lagrangian dynamics of flexible manipulator disturbed aperture coverage p 48 A84-26516 options. Volume 1, attachment 2: Supporting data and arms via transformation matrices The small transmitter receiver stations in the Sirio analysis reports [AD-A137345] p 60 N84-20316 experiment — microwave transmission [NASA-CR-173336] p 13 N84-18294 MATRIX METHODS [FUB-50-1982] p49 N84-15386 Study on damping representation related to spacecraft Space Station needs, attributes and architectural MILITARY OPERATIONS options. Volume 2, book 1, part 1: Mission structural design Potential military applications of space platforms and [EMSB-18/83] p38 N84-15182 requirements space stations p2 A84-13330 [NASA-CR-173312] p 13 N84-18296 Derivation and combination of impedance matrices for MILITARY SPACECRAFT Space Station needs, attributes and architectural flexible satellites Systems considerations in mosaic focal planes — for [ESA-STR-209] p 43 N84-21604 military spacebome surveillance p 75 A84-28576 options. Volume 2, book 1, part 2, task 1: Mission The solution of the dynamic problem of the periodic MILITARY TECHNOLOGY requirements structures by cyctosymmetric technique — large space National security implications of a U.S. space station [NASA-CR-173313] p 13 N84-18297 structures p 43 N84-21612 p 73 A84-24635 Space Station needs, attributes and architectural Rnite element formulations for tensioned members — Identification of new potential scientific and technology options. Volume 2, book 1, part 3: Manned Space Station large space structures p 21 N84-21615 areas for DoD application. Summary of activities relevance to commercial telecommunications satellites MAYPOLE ANTENNAS [AD-A134372] p 78 N84-17050 [NASA-CR-173314] p 13 N84-18298 Spline-based estimation techniques for parameters in MINICOMPUTERS Space Station needs, attributes and architectural elliptic distributed systems Potential of minicomputer-array processor system for options. Volume 2, book 1, part 4: Payload element [NASA-TM-85439] p9 N84-17947 nonlinear finite-element analysis p 46 A84-20583 mission data sheets MEASURING INSTRUMENTS MIRRORS [NASA-CR-173315] p 13 N84-18299 Space Station needs, attributes and architectural Spacecraft thermal control selection for seven years of Space Station needs, attributes and architectural options. Volume 2, book 1. part 4: Payload element lifetime in synchronous orbit options. Volume 2, book 2, part 2, Task 2: Information mission data sheets [MBB-UR-584-82-OE] p 25 N84-11200 management system [NASA-CR-173315] p 13 N84-18299 Optical coating in space [NASA-CR-173317] p 13 N84-18301 MECHANICAL DRIVES [NASA-CR-175441] p 56 N84-21290 Space Station needs, attributes and architectural Design and development of an advanced solar array MISSION PLANNING options. Volume 2, book 2, part 3: Communication drive mechanism p 17 N84-18457 Space logistics — preparing for future space missions system Space telescope: Solar array primary development [IAF PAPER 83-24] p 64 A84-11719 [NASA-CR-173318] p 14 N84-18302 mechanism p51 N84-18458 Overview of NASA space station activities Space Station needs, attributes and architectural MECHANICAL ENGINEERING [IAF PAPER 83-48] p1 A84-11726 options, volume 2, book 3: Cost and programmatics U.S. National Congress of Applied Mechanics. 9th, European utilisation aspects for a space station [NASA-CR-173320] p 14 N84-18304 [IAF PAPER 83-54] p 64 A84-11727 Cornell University, Ithaca, NY, June 21-25. 1982, Spacelab data book Space station - A Canadian perspective Proceedings p75 A84-29126 [ESA-BR-14] p79 N84-18315 [IAF PAPER 83-55] p 65 A84-11728 MECHANICAL IMPEDANCE Definition of technology development missions for early Management of the radiolink of the solar sail spacecraft Derivation and combination of impedance matrices for space stations orbit transfer vehicle serving. Phase 2, flexible satellites by radio-amateurs [IAF PAPER 83-447] p 44 A84-11823 task 1: Space station support of operational OTV [ESA-STR-209] p43 N84-21604 servicing The German Spacelab mission D1 p69 A84-17762 [NASA-CR-170984] p 14 N84-19377 MECHANICAL PROPERTIES Operational planning, simulation, and performance of Thermal-mechanical behavior of graphite/magnesium the German Spacelab mission D1 p 69 A84-17763 Civil space station composites p24 A84-28237 Manned planetary missions? p 71 A84-21497 [S-REPT-98-523] p 79 N84-20613 SiC-reinforced-aluminum alloys for aerospace Mankind's interstellar future p 71 A84-21499 MODAL RESPONSE applications p 54 A84-28242 Space station: Policy, planning and utilization; Experimental study of active vibration control Effect of temperature, moisture and radiation exposures Proceedings of the Symposium, Arlington. VA, July 18-20, [AD-A133818] p 38 N84-14546 on composite mechanical properties p 55 A84-28900 1983 p72 A84-24626 Component mode synthesis and large deflection Composite structural materials Integrated requirements for a space station vibrations of complex structures — beams and trusses [NASA-CR-173259] p 56 N84-17293 p 4 A84-24628 [NASA-CR-173338] p 21 N84-18680

A-12 SUBJECT INDEX ORBITAL SPACE STATIONS

Development of procedures for component mode NASTRAN ORBIT SPECTRUM UTILIZATION synthesis Component mode synthesis and large deflection Improved orbit utilization using auxiliary feeds in existing [DFVLR-IB-232-82-C-09] p 30 N84-21626 vibrations of complex structures — beams and trusses earth terminals p 46 A84-2O647 MOISTURE CONTENT (NASA-CR-173338] p 21 N84-18680 Reduced domestic satellite orbit spacing Effect of temperature, moisture and radiation exposures Decentralized control of a large space structure using [AIAA PAPER 64-0652) p 73 AB4-25253 on composite mechanical properties p 55 A84-28900 direct output feedback Time phased introduction of advanced technologies - MOMENTUM TRANSFER [AD-A136781] p 41 N84-19464 Its impact on orbit/spectrum conservation Space station control requirements and flywheel system The effect of mass and stiffness changes on the damping [AIAA PAPER 64-0653) p 74 A84-25254 weights for combined momentum and energy storage factor in a large space structure as represented by the Computer tools for optimizing orbit use p37 N84-12236 CSDL 2 model • [AIAA PAPER 84-0651] p 74 A84-25318 [AD-A136984] p 42 N84-19465 MSAT ORBIT TRANSFER VEHICLES MSAT mobile communication demonstration satellite NAVSTAH SATELLITES Servicing vehicle for satellites and platforms in low earth system and bus tradeoff considerations Autonomous navigation of geosynchronous satellites orbits [AIAA PAPER 84-0751 ] p 48 A84-25306 using the Navstar Global Positioning System [DGLR PAPER 83-102] p 6 A84-29666 p 45 A84-15671 Development of deployable structures for large space MULTIBEAM ANTENNAS NEAR FIELDS Multibeam phased arrays - Application to platforms. Volume 2: Design development A cylindrical near-field test facility for large satellite SOC/Free-Flyer communication system — Space [NASA-CR-170914] p 20 N84-10176 antennas Fluid management p11 N84-18284 Operation Center p 45 A84-15641 [MBB-UR-628-83-OE] p 72 A84-22862 Definition of technology development missions for early Narrow muttibeam satellite ground station antenna NETWORK CONTROL space stations orbit transfer vehicle serving. Phase 2, employing a linear array with a geosynchronous arc Space station communications and tracking equipment task 1: Space station support of operational OTV coverage of 60 deg. II - Antenna design management/control system p 45 A84-15639 servicing p46 A84-17743 NONEOUIUBRIUM THERMODYNAMICS [NASA-CR-170984] p 14 N84-19377 A deployable 30/20 GHz multibeam offset antenna Thermofluidynamics of heat pipes p 27 N84-19423 ORBITAL ASSEMBLY [AIAA PAPER 84-0658] p 20 A84-25258 NONLINEAR EQUATIONS A voice interactive system for aiding and documentation Land-mobile communications satellite system design Numerical solution of several classes of nonlinear of space-based tasks [AIAA PAPER 84-0753] p 5 A84-25308 flexible shell theory problems p 35 A84-25586 [AIAA PAPER 83-2355] p 43 A84-10025 MULT1MISSION MODULAR SPACECRAFT NONLINEAR SYSTEMS A manned-machine space station construction Application of a common reflector configuration to a A comparison of linear and geometrically nonlinear finite concept multimission satellite of the 90's element analyses applied to large space structures [NASA-TM-85762] p 21 N84-19395 [IAF PAPER 83-60] p 1 A84-11731 [AIAA PAPER 84-0069] p 16 A84-19887 Construction concept for erecting an offset-fed MYLAR (TRADEMARK) NUMERICAL CONTROL antenna Erosion of mylar and protection by thin metal films Digital control system for space structural dampers [NASA-TM-85774] p 60 N84-20626 [AIAA PAPER 83-2636] p 52 A84-10949 [NASA-CR-175355] p 39 N84-16246 Shutter interaction study extension [NASA-CR-173401] p 81 N84-21593 ORBITAL MANEUVERS N Payload placing using an operational support platform [IAF PAPER 83-44] p1 A84-11724 OBSERVABILITY (SYSTEMS) ORBITAL MECHANICS NASA PROGRAMS Controllability and observability criteria for multivariable Space applications at the crossroads: Proceedings of Investigation of electrodynamic stabilization and control linear second-order models p 35 A84-25516 of long orbiting tethers the Twenty-first Goddard Memorial Symposium. Greenbelt, OCCULTATION MD, March 24, 25, 1983 p 64 A84-10883 [NASA-CR-170972] p 40 N84-17251 Space operations center communications path Introduction to geostationary orbits Overview of NASA space station activities obscuration p 3 A84-15695 [ESA-SP-1053] p80 N84-21590 [IAF PAPER 83-48] p1 A84-11726 ONBOARD DATA PROCESSING ORBITAL POSITION ESTIMATION European utilisation aspects for a space station Modem software development tools in space projects Semiautonomous stationkeeping of geosynchronous [IAF PAPER 83-54] p 64 A84-11727 on the example of a Spacelab experiment satellites p32 A84-17359 NASA priority technologies p49 N84-14761 ORBITAL SERVICING [IAF PAPER 83-345] p 1 A84-11793 OPERATORS (MATHEMATICS) A voice interactive system for aiding and documentation Spacelab's development p 66 A84-13901 Active control of large flexible space structures of space-based tasks Spaceflight to 2000 - Interavia looks forward from the p37 N84-14235 [AIAA PAPER 83-2355] p 43 A84-10025 OPTICAL EQUIPMENT present p66 A84-14764 Manufacturing space systems in space Coherent arrays of separate optical telescopes in space Mission to Mars - The case for a settlement p 71 A84-22338 project Trio p3 A84-15363 p67 A84-15092 NASA research in teleoperation and robotics OPTICAL MEASUREMENT Developing the space frontier; Proceedings of the p 58 A84-28523 Systems considerations in mosaic focal planes — for Servicing vehicle for satellites and platforms in low earth Twenty-ninth Annual Conference, Houston, TX, October military spacebome surveillance p 75 A84-2B576 25-27,1982 p 67 A84-15381 orbits OPTICAL MEASURING INSTRUMENTS [DGLR PAPER 83-102] p6 A84-29666 Space stations - A key to socio-economic benefits from Coordinate transformation assembly — for space space? p69 A84-19850 An alternate concept for expanding man's presence in platform angular coordinate linking p 75 A84-28579 space Space 1991 p 71 A84-21720 OPTICAL PATHS [NASA-TM-84617] p7 N84-15172 NASA's geostationary communications platform Space operations center communications path On-orbit spacecraft/stage servicing during STS life obscuration p 3 A84-15695 program cycle [AIAA PAPER 84-0702] pS A84-25326 OPTICAL PROPERTIES [NASA-CR-171775] p 79 N84-20617 NASA research in teleoperation and robotics Evaluation of spacecraft materials and processes for ORBITAL SHOTS p58 AB4-28523 optical degradation potential p 54 A84-28458 Capture-ejector satellites Space stations - The next step in space? Effects of combined ultraviolet and oxygen plasma [NASA-TM-85686] p7 N84-15179 [AAS PAPER 83-202] p 76 A84-29855 environment on spacecraft thermal control materials — ORBITAL SPACE STATIONS International .aspects of commercial space activities space shuttle payloads p 27 N84-19449 Space station autonomy requirements [AAS PAPER 83-222] p 77 A84-29866 OPTIMAL CONTROL [AIAA PAPER 83-2352] p 63 A84-10024 International competition in commercial aerospace A hardware demonstration of control for a flexible Overview of space station operations markets offset-feed antenna p31 A84-13321 [IAF PAPER 83-38] p 64 A84-11723 [AAS PAPER 83-244] p 77 A84-29883 Number crunching on the ACOSS Model No. 2 European utilisation aspects for a space station Research and technology, 1983 p33 A84-19128 [IAF PAPER 83-54] p 64 A84-11727 [NASA-TM-85702] p7 N84-12026 Use of electromagnetic models in the optimal control Photovoltaic solar arrays leading to a candidate space NASA's space station activities of large space antennas p 35 A84-25552 power system in the regime beyond 100 kW OPTIMIZATION [GPO-27-393] p7 N84-14234 [IAF PAPER 83-422] p 44 A84-11817 STEP Experiment Requirements Approximations method for space frame synthesis Communications, tracking, and docking on the Space [NASA-CP-2294] p7 N84-17211 p 19 A84-10141 Station p45 A84-15640 Civil space station Optimization of shallow trusses against limit point Application of beam power technology to a space instability p 20 A84-23366 [S-REPT-98-523] p 79 N84-20813 station p 45 A84-15642 Department of Housing and Urban Optimal low-thrust transfers to synchronous orbit A communications system conceptual design for a low Development-independent agencies appropriations for p 62 A84-24981 earth orbiting Manned Space Station p 45 A84-15643 1984: National Aeronautics and Space Administration Computer tools for optimizing orbit use Determination of applicable law to living and working p 80 N84-21440 [AIAA PAPER 84-0651 ] p 74 A84-25318 in space Authorizing appropriations to the National Aeronautics ORBIT MANEUVERING ENGINE (SPACE SHUTTLE) [IAF PAPER 82-IISL-45] p 68 A84-17058 and Space Administration for fiscal year 1985 An alternate concept for expanding man's presence in Project space station - Plans for a permanent manned [H-REPT-98-629] p 80 N84-21441 space center — Book p 69 A84-21344 Review of the National Aeronautics and Space Act of [NASA-TM-84617] p7 N84-15172 Space station - An early experimental solar power 1958 ORBIT PERTURBATION satellite p 70 A84-21487 [GPO-28-915] p80 N84-21442 Analytical model of the evolution of orbit parameters Space station: Policy, planning and utilization: National Aeronautics and Space Administration of a quasi geostationary satellite Proceedings of the Symposium, Arlington. VA, July 18-20, Authorization Act, 1985 p 60 N84-21443 [IAF PAPER 83-316] p 65 A84-11787 1983 p72 A84-24626 National Aeronautics and Space Administration Periodic oscillations of a gyrostat satellite with respect The role of man in space p 72 A84-24627 Authorization Act. 1985 to the centers of mass in a circular orbit Integrated requirements for a space station [H-REPT-98-629] p 80 N84-21444 p33 A84-19728 p4 A84-24628

A-13 ORBITAL VELOCITY SUBJECTINDEX

Use of space station for science p 72 A84-24629 PANELS PERFORMANCE TESTS The role of space station in earth sciences Field repair of graphite epoxy skin panels on the Experiment data communications (48 Mbit/s) between p 72 A84-24631 spaceship Columbia p 52 A84-17120 Spacelab, the Space Shuttle and the ground Role of a space station in pharmaceutical Investigation of articulated panel dynamics P44 A84-10396 manufacturing p 73 A84-24632 p40 N84-17230 The Spacelab test program Architectural options and development issues Flexible radiator thermal vacuum test report [AIM PAPER 83-2685] p 66 A84-13376 p 4 A84-24633 [NASA-CR-171764] p 28 N84-20622 Design and development of the INTELSAT V Space station architectural issues as viewed by the user Flexible radiator system: Executive summary graphite-epoxy central thrust tube p19 AB4-22153 community - Applications p 4 AB4-24634 [NASA-CR-171766] p 28 N84-20624 A cylindrical near-field test facility for large satellite National security implications of a U.S. space station antennas PARABOLIC ANTENNAS p73 A84-24635 [MBB-UR-628-83-OE] p 72 A84-22862 Large inflated-antenna system p9 N84-17234 Space station communications p 73 A84-24636 Hyperfiltration wash water recovery subsystem - Design Environmental control and life support (ECLS) design PARABOLIC REFLECTORS and test results — for extended mission spacecraft such optimization approach p 73 A84-24637 Study on large, ultralight long-life structures in space, as space stations Thermal management system technology development phase 2C [SAE PAPER 831112] p6 A84-29047 for space station applications [TM-EKR3] p 17 N84-17284 PHASE CHANGE MATERIALS [SAE PAPER 831097] p 24 A84-29032 PARAMETER IDENTIFICATION Weight characteristics of future spacecraft thermal The residual gravitational field of orbital space stations Structural parameter identification for flexible management systems [DGLR PAPER 83-089] p 75 A84-29656 spacecraft [AIAA PAPER 84-0054] p 23 A84-17850 Microgravity conditions on orbital platforms [AIAA PAPER 84-0060] p 23 A84-17853 PHASED ARRAYS [DGLR PAPER 83-90] p 76 A84-29657 Determination of critical parameters in large flexible Multibeam phased arrays - Application to Probable missions and transportation scenarios to use space structures with uncertain modal data SOC/Free-Flyer communication system — Space regenerative life support systems p33 A84-20047 Operation Center p45 A84-15641 [AAS PAPER 83-201 ] p 76 A84-29854 Identification of large flexible structures mass/stiffness Radiation characteristics of array antennas with Study of multi-kilowatt solar arrays for Earth orbit and damping from on-orbit experiments disturbed aperture coverage p 48 A84-26516 applications p34 A84-24995 PHOTONIC PROPULSION [NASA-CR-170939] p 49 N84-12634 Parameter identification in continuum models Management of the radiolink of the solar sail spacecraft An alternate concept for expanding man's presence in p16 A84-25525 by radio-amateurs space PARTICLE INTERACTIONS [IAF PAPER 83-447] p 44 A84-11823 [NASA-TM-84617] p7 N84-15172 Feasibility study to conduct windblown sediment Roundtrip interstellar travel using laser-pushed Capture-ejector satellites experiments aboard a space station lightsails p62 A84-27443 [NASA-TM-85686) p7 N84-15179 [NASA-CR-175434] p 15 N84-21586 PHOTOVOLTAIC CELLS Feasibility study to conduct windblown sediment PARTICLE MOTION Photovoltaic solar arrays leading to a candidate space experiments aboard a space station Feasibility study to conduct windblown sediment power system in the regime beyond 100 kW [NASA-CR-175434] p 15 N84-21586 experiments aboard a space station [IAF PAPER 83-422] p 44 A84-11817 Shuttle interaction study [NASA-CR-175434] p 15 N84-21586 PHOTOVOLTAIC CONVERSION [NASA-CR-173400] p 80 N84-21S92 PARTICLE TRAJECTORIES Mechanical wraparound contacted cell for low cost Shutter interaction study extension Feasibility study to conduct windblown sediment space arrays p 48 A84-22982 [NASA-CR-173401] p81 N84-21593 experiments aboard a space station PHYSIOLOGICAL EFFECTS ORBITAL VELOCITY [NASA-CR-175434] p 15 N84-21586 Man in space - An overview p 67 A84-15161 Capture-ejector satellites PARTITIONS (MATHEMATICS) PHYSIOLOGY [NASA-TM-85686] p7 N84-15179 Algorithms and computational aspects pertaining to The Alpha-Helix Concept Innovative utilization of the ORBITS block diagonal dominance methods for design of Space Station Program. A report to the National Space Station needs, attributes and architectural decentralized feedback compensation Aeronautical and Space Administration requesting options. Volume 2, book t, part 1: Mission p15 A&4-19108 establishment of a Sensory Physiology Laboratory on the requirements PAYLOAD CONTROL Space Station [NASA-CR-173312] p 13 N84-18296 A methodology to include static and kinetic friction [NASA-CR-175436] p 14 N84-20610 ORGANIZATIONS effects in Space Shuttle payload transient loads analysis PIPES (TUBES) Human organization — and space project [AIM PAPER 83-2654] p 30 A84-10956 Thermal control of tubular composite structures in space management p2 A84-15303 A design strategy for multiple payload pointing from a environment p 22 A84-10440 OSCILLATIONS three axis stabilized spacecraft Thermo-mechanical behaviour of CFRP tubes for space Periodic oscillations of a gyrostat satellite with respect [AIAA PAPER 84-0566] p 33 A84-18168 structures to the centers of mass in a circular orbit Space platform accommodations — for multiple [IAF PAPER 83-417] p 22 A64-11814 p33 A84-19728 interchangeable payloads p 16 A84-22131 PIVOTS OUTER SPACE TREATY Geometric modeling of large space antenna Self-locking telescoping manipulator arm Determination of applicable law to living and working deployment p 22 N84-22225 [NASA-CASE-MFS-25906-1] p 59 N84-11761 PAYLOAD DELIVERY (STS) PLASMA DENSITY [IAF PAPER 82-IISL-44] p 68 A84-17057 Space platform accommodations — for multiple Interpretation of STS-3/plasma diagnostics package OUTGASSING interchangeable payloads p 16 A84-22131 results in terms of large space structure plasma Using the oulgassing test to screen materials for Space station needs, attributes and architectural interactions contamination potential p53 A84-17174 options. Part 1: Summary [NASA-CR-173266] p 78 N84-16991 Evaluation of spacecraft materials and processes for [NASA-CR-175382] p 10 N84-18270 PLASMA DIAGNOSTICS optical degradation potential p54 A84-28458 Space station needs, attributes and architectural options Interpretation of STS-3/plasma diagnostics package OXIDATION study. Briefing material: Final review and executive results in terms of large space structure plasma Low earth orbit atomic oxygen effects on surfaces — summary interactions of Space Shuttle Orbiters [NASA-CR-173321] p 10 N84-18273 [NASA-CR-173266] p 78 N84-16991 [AIAA PAPER 84-0548] p 53 A84-19912 PAYLOAD INTEGRATION PLAN PLASMA INTERACTIONS OXIDATION RESISTANCE Launch processing for Spacelab 1 Plasma sheath structure surrounding a large powered Erosion of mylar and protection by thin metal films [AIM PAPER 83-2622] p 64 A84-10965 spacecraft [AIAA PAPER 83-2636] p 52 A84-10949 Space platform accommodations — for multiple [AIM PAPER 84-0329] p 46 AB4-18025 OXYGEN ATOMS interchangeable payloads p 16 A84-22131 Interpretation of STS-3/plasma diagnostics package Reactions of high velocity atomic oxygen with carbon Payload missions integration results in terms of large space structure plasma [AIAA PAPER 84-0549] p 53 A84-18159 [NASA-CR-170949] p7 N84-15171 interactions Low earth orbit atomic oxygen effects on surfaces — PAYLOAD RETRIEVAL (STS) [NASA-CR-173266] p 78 N84-16991 of Space Shuttle Orbiters On modeling and simulation of the dynamics of tether Photovoltaic concentrator pointing dynamics and plasma [AIAA PAPER 84-0548] p 53 A84-19912 connected satellite systems p30 A84-11933 interaction study p50 N84-17224 PAYLOAD TRANSFER OXYGEN PLASMA Spacecraft/plasma interactions and their influence on Payload placing using an operational support platform Effects of combined ultraviolet and oxygen plasma field and particle measurements — conferences • [IAF PAPER 83-44] pi A84-11724 environment on spacecraft thermal control materials — [ESA-SP-198] p56 N84-17253 PAYLOADS space shuttle payloads p27 N84-19449 PLASMA POTENTIALS Space Station needs, attributes and architectural Spacecraft/plasma interactions and their influence on OXYGEN PRODUCTION options. Volume 2. book 1, part 2, task 1: Mission Electrochemical and steam-desorbed amine CO2 field and particle measurements — conferences requirements [ESA-SP-198] p56 N84-17253 concentration Subsystem comparison — for oxygen [NASA-CR-173313] p 13 N84-18297 The role of potential barrier formation in spacecraft recovery on Space Station Space Station needs, attributes and architectural charging p 50 N84-17269 [SAE PAPER 831120] p6 A84-29054 options. Volume 2, book 1, part 4: Payload element mission data sheets PLASMA SHEATHS [NASA-CR-173315] p 13 N84-18299 Plasma sheath structure surrounding a large powered Space Station needs, attributes and architectural spacecraft options, volume 2, book 2, part 4: International reports [AIM PAPER 844329] p 46 A84-18025 PAINTS [NASA-CR-173319] p 14 N84-18303 Sheath iortzation model of beam emissions from large Electrically conductive black optical paint A Variable Conductance Heat Pipe (VCHP) radiator spacecrafts p55 A84-28553 system for communications payloads p27 N84-19406 [AD-A137181] p52 N84-19463 PANEL FLUTTER PERFORMANCE PREDICTION PLATFORMS Investigation of articulated panel dynamics Prediction of solar cell performance in space STEP Experiment Requirements p40 N84-17230 p48 A84-22997 [NASA-CP-2294] p7 N84-17211

A-14 SUBJECTINDEX REDUCED GRAVITY

Space Technology Experiments Platform (STEP) Software production in a large space project The SPOT RADIATION COUNTERS overview ' pS N84-17212 mission center p 78 N84-14752 Pyroelectric materials as electronic pulse detectors of STEP mechanical systems p8 N84-17213 Space Station needs, attributes and architectural ultraheavy nuclei p 72 A84-23440 STEP experiment integration pS NS4-1721S options, volume 2. book 3: Cost and programmatics RADIATION DAMAGE [NASA-CR-173320] p 14 N84-18304 POINTING CONTROL SYSTEMS Effect of temperature, moisture and radiation exposures Simulation of the Galileo spacecraft axial - Oelta-V An Attached Payload Operations Center (APOC) at the on composite mechanical properties p 55 A84-28900 Goddard Space Flight Center (GSFQ, volume 1 algorithm P 66 A84-11938 RADIATION EFFECTS [NASA-CR-175160] p 79 N84-20605 A design strategy for multiple paytoad pointing from a Simulated space radiation effects on dielectrics and PROJECT PLANNING three axis stabilized spacecraft coatings p 54 A84-20682 Spacelab's development p66 A84-13901 Effects of combined ultraviolet and oxygen plasma [AIAA PAPER 84-0566J P 33 A84-18168 Management of large space projects; Course on Space Evolution of European telecommunication satellite environment on spacecraft thermal control materials — Technology, Toulouse, France, May 3-14. 1982, space shuttle payloads p27 N84-19449 pointing performance Proceedings p2 A84-15301 RADIATION PRESSURE tAIAA PAPER 840725] p 34 AB4-25291 The progression of projects — in space industry Torque from solar radiation pressure gradient during Photovoltaic concentrator pointing dynamics and plasma p2 A84-15305 eclipse — for very large spacecraft p31 A84-12489 interaction study pSO NB4-17224 Tethers in space: Birth and growth of a new avenue Space Station needs, attributes and architectural to space utilization Computing the radiation pressure forces by adapting options, volume 2, book 2, part 4: International reports (NASA-TM-82571 ] p 18 N84-21607 thermal design verification softwares — large space [NASA-CR-173319] P 14 N84-18303 PROPELLANT STORAGE structures p 28 N84-21613 Precise control of flexible manipulators Shuttle interaction study extension RADIATION SHIELDING [NASA-CH-175389] P 60 N84-20175 [NASA-CR-173398] p 81 N84-21594 Digital technologies and systems for geostationary orbit POLAR REGIONS PROPULSION SYSTEM PERFORMANCE satellites Large space instrumentation to measure the interaction Utilization of electric propulsion for communication [AIAA PAPER 84-0749] p 74 A84-25304 between space structures and the environment satellites RADIATIVE HEAT TRANSFER [AO-A129990] P 77 N84-10179 [AIAA PAPER 84-0729] p 62 A84-25293 Thermal analysis research applicable to space station POLICIES Why don't we use ion propulsion? technology needs Global implications of space activities: An AIAA/ASPEN [AIAA PAPER 84-0730] p 62 A84-25294 [NASA-TM-84658] p 25 N84-15426 Institute Assessment — Book p 67 A84-15189 PROTECTIVE COATINGS RADIO ANTENNAS Space station: Policy, planning and utilization: Erosion of mylar and protection by thin metal films Geodetic control of the reflectors of large antennas Proceedings of the Symposium, Arlington, VA, July 18-20. [AIAA PAPER 83-2636] p 52 A84-10949 p31 A84-15785 1983 p72 A84-24626 Optical coating in space Characteristics of the microprocessor implementation Review of the National Aeronautics and Space Act of [ NASA-CR. 175441] p 56 N84-21290 of algorithms for the processing of radio signals and noise 1958 PROTOTYPES in large antenna arrays p 48 A84-28067 [GPO-28-915] p80 N84-21442 Feasibility study to conduct windblown sediment RADIO COMMUNICATION POSITIONING experiments aboard a space station A communications system conceptual design for a low Geometric modeling of large space antenna [NASA-CR-175434] p 15 N84-21586 earth orbiting Manned Space Station p 45 A84-15643 deployment p 22 N84-22225 PUBLIC RELATIONS Telecommunication systems for large-scale space POWER CONDITIONING Making the high frontier highly visible with a solar sail manufacturing activity A programmable power processor for high power space race to the moon [AAS PAPER 83-216] p 48 A84-29861 applications p46 A84-18394 [AAS PAPER 83-226] p 62 A84-29869 Space Station needs, attributes and architectural Power-economical considerations for the integration of PYROELECTRICITY options. Volume 2, book 2, part 3: Communication terrestrial and extraterrestrial solar generators into existing Pyroelectric materials as electronic pulse detectors of system power generation systems p71 A84-21488 ultraheavy nuclei p 72 A84-23440 [NASA-CR-173318] p 14 N84-18302 IPACS attitude control technology considerations RADIO FREQUENCIES p37 N84-12238 Use of electromagnetic models in the optimal control Advanced Control and Power System (ACAPS) of large space antennas p 35 A84-25552 technology program p 37 N84-12243 RF systems in space. Volume 2: Space-based radar IPACS guidance navigation and control system QUALITY CONTROL analyses considerations and test activities P 37 N84-12245 Management of large space projects - Quality assurance [AD-A133735] p 49 N84-14394 POWER EFFICIENCY or'product assurance' p3 A84-15310 RF systems in space. Volume 1: Space antennas A programmable power processor for high power space frequency (SARF) simulation Using the outgassing test to screen materials for applications p46 A84-18394 [AD-A133734] p 49 N84-14395 contamination potential p 53 A84-17174 POWER SUPPLIES RADIO RELAY SYSTEMS Current collection from the space plasma through Software quality assurance Spacelab experience and A communications system conceptual design for a low defects in high voltage solar array insulation future trends p 17 N84-14759 earth orbiting Manned Space Station p 45 A84-15643 p49 N84-15970 Integrity control of carbon fiber reinforced plastics RADIO TELEMETRY PREDICTION ANALYSIS TECHNIQUES structural elements, phase 1 report — space Management of the radiolink of the solar sail spacecraft Development of procedures for component mode applications by radio-amateurs synthesis [TB-TS-11-01/82-A] p56 N84-18416 [IAF PAPER 83-447] p 44 A84-11823 [DFVLR-IB-232-62-C-09] p 30 N84-21626 QUARTZ LAMPS RANDOM VIBRATION PRODUCT DEVELOPMENT Spacecraft thermal balance testing using infrared lamps Dynamic behaviour of a satellite antenna structure in Space station data management - A system evolving on a dummy spacecraft p26 N84-19399 random vibration environment p 42 N84-19900 from changing requirements and a dynamic technology QUENCHING (COOLING) REACTION KINETICS base The effect of pressure and temperature on Second Ail-Union Seminar on Hydromechanics and [AIAA PAPER 83-2338] p 43 A84-10016 time-dependent changes in graphite/epoxy composites Heat-Mass Transfer in Weightlessness. Abstracts of Role of a space station in pharmaceutical below the glass transition p54 A84-21775 reports: Table of contents manufacturing p 73 A84-24632 [NASA-TM-77534] p 26 N84-18576 Software production in a large space project: The SPOT REACTION WHEELS mission center p 78 N84-14752 BAe reaction wheels for Olympus — Olympus Modem software development tools in space projects telecommunication satellite p 17 N84-18475 on the example of a Spacelab experiment RADAR ANTENNAS RECONNAISSANCE SPACECRAFT p49 N84-14761 RF systems in space. Volume 2: Space-based radar Systems considerations in mosaic focal planes — for Design and development of an advanced solar array analyses military spacebome surveillance p 75 A84-28576 drive mechanism p 17 N84-18457 [AD-A133735] p 49 N84-14394 RECTANGULAR PLATES PRODUCTION ENGINEERING RF systems in space. Volume 1: Space antennas Control structure interactions in large space structures Study of artificial intelligence techniques - Realization frequency (SARF) simulation Analysis using energy approach—for constant and pulsed of a highly autonomous experimental robot system — [AD-A133734] p 49 N84-14395 thrusters p 35 A84-27934 French thesis p 58 A84-25828 The effects of aperture antennas after signal propagation RECURSIVE FUNCTIONS PROJECT MANAGEMENT through anisotropic ionized media Recursive lagrangian dynamics of flexible manipulator Management of large space projects; Course on Space arms via transformation matrices [AD-A138286] p 52 N84-21781 Technology. Toulouse. France. May 3-14, 1982, [AD-A137345] p 60 N84-20316 RADIAL DISTRIBUTION Proceedings p2 A84-15301 REDUCED GRAVITY Human organization — and space project Thermally induced spin rate ripple on spacecraft with Utilisation of the European retrieval carrier EURECA for management p 2 A84-15303 long radial appendages life science research p65 A84-11753 [NASA-TM-85058] p 39 N84-16249 The progression of projects — in space industry Mfcrogravity conditions on orbital platforms p2 A84-15305 RADIANT FLUX DENSITY [DGLR PAPER 83-90] p 76 A84-29657 Management of large space projects • Quality assurance Assessment of satellite power flux-density limits in the Second All-Union Seminar on Hydromechanics and or'product assurance' p3 A84-15310 2025-2300 MHz frequency range, part 1 Heat-Mass Transfer in Weightlessness. Abstracts of Financing large space projects P 67 AB4-15321 [PB84-129402] p51 N84-18532 reports: Table of contents The Spacelab program - The management of the IRSIM: A program for the calculation of infrared flux [NASA-TM-77534] p 26 N84-18576 program, problems encountered and the solutions intensity incident on a spacecraft inside a test chamber The Alpha-Helix Concept Innovative utilization of the adopted P 3 A84-15325 p26 N84-19400 Space Station Program. A report to the National Solar power satellites - The institutional challenge RADIANT HEATING Aeronautical and Space Administration requesting p70 A84-21479 Radiation-conduction interaction in large space establishment of a Sensory Physiology Laboratory on the Space station - An early experimental solar power structures Space Station p70 A84-21487 [AIAA PAPER 84-0144] p 23 A84-17911 [MASA-CR-175436) p 14 N84-20610

A-15 REFLECTING TELESCOPES SUBJECT INDEX

REFLECTING TELESCOPES Department of Housing and Urban A cylindrical near-field test facility for large satellite STEP flight experiments Large Deployable Reflector Development-independent agencies appropriations for antennas (LDR) telescope P8 N84-17231 1984: National Aeronautics and Space Administration [MBB-UR-628-83-OE] p 72 A84-22862 REFLECTORS p80 N84-21440 A deployable 30/20 GHz multibeam offset antenna Application of a common reflector configuration to a Authorizing appropriations to the National Aeronautics [AIAA PAPER 84-0658] p 20 A84-25258 multimission satellite of the 90's and Space Administration for fiscal year 1985 Unturiable offset antenna design for multipurpose [IAF PAPER 83-60] P1 A84-11731 [H-REPT-98-629] p 80 N84-21441 applications Geodetic control of the reflectors of large antennas National Aeronautics and Space Administration [AIAA PAPER 84-0659] p 16 A84-25259 p31 A84-15785 Authorization Act, 1985 p 80 N84-21443 Evolution of European telecommunication satellite pointing performance Advanced composite antenna reflectors for National Aeronautics and Space Administration [AIAA PAPER 84-0725] p 34 A84-25291 communications satellites P 53 A84-17151 Authorization Act, 1985 RF systems in space. Volume 2: Space-based radar Static shape forming tor an electrostatically controlled [H-REPT-98-629] p 80 N84-21444 membrane mirror P 16 A84-25551 analyses RESEARCH MANAGEMENT REGENERATION (ENGINEERING) [AD-A133735] p 49 N84-14394 National Aeronautics and Space Administration Crew and life support: ECLSS p11 N84-18280 Computer aided synthesis of a satellite antenna structure Authorization Act, 1985 p 80 N84-21443 REGENERATIVE FUEL CELLS with probabilistic constraints p 21 N84-19899 The Boeing flywheel study P 37 NB4^12235 National Aeronautics and Space Administration Dynamic behaviour of a satellite antenna structure in Authorization Act, 1985 REGENERATORS random vibration environment p 42 N84-19900 Regenerate non-venting thermal control subsystem for [H-REPT-98-629] p 80 N84-21444 Environmental effects on the dynamics and control of extravehicular activity RESISTOJET ENGINES an orbiting large flexible antenna system [SAE PAPER 831151] P 24 AS4-29076 Resistojet propulsion for large spacecraft systems [NASA-CR-175448] p 42 N84-20627 REGULATIONS [NASA-TM-83489] p 63 N84-11206 The effects of aperture antennas after signal propagation A legal charter for non-governmental space REUSABLE SPACECRAFT through anisotropic ionized media industrialization The space van and its potential impact on the design [AD-A138286] P 52 N84-21781 IAAS PAPER 83-225] P 77 AB4-29868 of communications satellites SATELLITE ATTITUDE CONTROL REINFORCED PLATES [AIAA 84-0758] p 74 A84-25309 Hardware simulation of spacecraft dynamics and Buckling and vibration of any prismatic assembly of shear Reusable commercial space processing platforms control P30 A84-11932 and compression loaded anise-tropic plates with an [AAS PAPER 83-208] p7 A84-29858 Attitude control and dynamics of the space operations arbitrary supporting structure P 23 A84-14050 RIGID STRUCTURES center p 31 A84-11934 RELIABILITY ANALYSIS Geometrically nonlinear analysis of beam-in-space Satellite attitude dynamics and control in the presence Assessment of reliability of ceramic materials structures of environmental torques - A brief survey p54 A84-24508 [MITT-28] p22 N84-21914 p31 A84-12483 A hardware demonstration of control for a flexible REMOTE CONTROL RIPPLES offset-feed antenna P 31 A84-13321 Space Applications of Automation, Robotics and Thermally induced spin rate ripple on spacecraft with Attitude stability for the yaw-wheel class of orbiting Machine Intelligence Systems (ARAMIS), phase 2. Volume long radial appendages gyrostats p33 A84-19675 1: Telepresence technology base development [NASA-TM-85058] p 39 N84-16249 Evolution of European telecommunication satellite [NASA-CR-3734] P 59 N84-10583 ROBOTICS Space Applications of Automation, Robotics and A system for intelligent teleoperation research pointing performance [AIAA PAPER 84-0725] p 34 A84-25291 Machine Intelligence Systems (ARAMIS), phase 2. Volume [AIAA PAPER 83-2376] p 57 A84-10070 The attitude and orbit control system for Eureca 2: Telepresence project applications Knowledge based systems for intelligent robotics [DGLR PAPER 83-091] P 76 A84-29658 CNASA-CR-3735] P 59 N84-10584 p57 A84-15667 Study of auxiliary propulsion requirements for large REMOTE MANIPULATOR SYSTEM The Shuttle remote manipulator system: CANADARM Canadarm and the Space Shuttle p 57 A83-44602 - A robot arm in space p 57 A84-21486 space systems, volume 2 [NASA-CR-168193-VOL-2] p 63 N84-13218 A system for intelligent teleoperation research Remote manipulators in space p 57 A84-22336 Sensitivity analysis of the influence of the flexibility of [AIAA PAPER 83-2376] P 57 A84-10070 Automation, Robotics, and Machine Intelligence solar panels on the attitude dynamics of artificial Simulation of the motion Of a Shuttle-attached flexible Systems (ARAMIS) in space manufacturing satellites manipulator arm P 57 A84-11935 p 58 A84-22337 [INPE-2763-PRE/337] p 39 N84-16232 The Shuttle remote manipulator system: CANADARM Study of artificial intelligence techniques - Realization Canadian Attitude Sensing Experimental Package - A robot arm in space P 57 A84-21486 of a highly autonomous experimental robot system — (CASEP) p79 N84-17223 Remote manipulators in space p 57 A84-22336 French thesis p 58 A84-25828 BAe reaction wheels for Olympus — Olympus Space applications Of Automation, Robotics And NASA research in teleoperation and robotics telecommunication satellite p 17 N84-18475 Machine Intelligence Systems (ARAMIS). Volume 3. phase p58 A84-28523 Modular design attitude control system 2: Executive summary Application of laser interferometry to robotics [NASA-CR-170996] P 41 N84-19392 [NASA-CR-3736] P 59 N84-10582 p58 A84-28541 SATELLITE CONFIGURATIONS Space Applications of Automation, Robotics and Human capabilities p11 N84-18282 For the first time — Russian book on construction of Machine Intelligence Systems (ARAMIS), phase 2. Volume ROBOTS 1: Telepresence technology base development first Soviet earth satellites p 16 A84-21564 Dynamics of nonrigid articulated robot linkages SATELLITE CONTROL [NASA-CR-3734] P 59 N84-10583 p58 A84-25531 On modeling and simulation of the dynamics of tether Space Applications of Automation, Robotics and Stability enhancement of a flexible robot manipulator connected satellite systems p 30 A84-11933 Machine Intelligence Systems (ARAMIS), phase 2. Volume [AD-A134185] p 59 N84-16607 On the dynamics of a subsatellite system supported by 2: Telepresence project applications ROCKET ENGINE DESIGN two tethers [NASA-CR-3735] P 59 N84-10584 A parametric study of space transfer-propulsion REMOTE SENSING [AIAA PAPER 84-0062] P 32 A84-17854 A degree of controllability definition - Fundamental Space station architectural issues as viewed by the user [IAF PAPER 83-401 ] p 61 A84-13397 concepts and application to modal systems community - Applications P4 A84-24634 Design and development of the INTELSAT V p 34 A84-24991 Technology needs of advanced Earth observation graphite-epoxy central thrust tube p 19 A84-22153 Reliability issues in active control of large flexible space spacecraft ROCKET NOZZLES structures [NASA-CR-3698] P9 N84-17248 Design and development of the INTELSAT V [NASA-CR-175341] p 39 N84-16248 REMOTE SENSORS graphite-epoxy central thrust tube p 19 A84-22153 Capture of satellite stabilized by gravity gradient with a Systems considerations in mosaic focal planes — for ROTARY GYROSCOPES flexible mast during and after deployment military spacebome surveillance p75 A84-28576 Analysis and design of leaf-spring flexible joints for [INPE-2749-PRE/325] p 41 N84-19383 REPORTS driving gyroscopic rotors p 19 A84-11922 SATELLITE DESIGN Second All-Union Seminar on Hydromechanics and ROTARY STABILITY An overview of the institutional and regulatory aspects Heat-Mass Transfer in Weightlessness. Abstracts of Motion of a symmetric satellite about the center of mass and their impact on system design — of geostationary reports: Table of contents in circular orbit in the presence of flexible viscoelastic satellites [NASA-TM-77534] P 26 N84-18576 rods p 35 A84-26977 REQUIREMENTS [IAF PAPER 83-82] p 65 A84-11737 Space station needs, attributes and architectural options An advanced generation land mobile satellite system study. Volumes: Requirements and its critical technologies p3 A84-15634 [NASA-CR-173332] P 10 N84-18267 Spacecraft thermal design using interactive graphics Space station needs, attributes and architectural SAILS [AIAA PAPER 84-0143] p 23 A84-17910 options. Part 1: Summary Roundtrip interstellar travel using laser-pushed Design and development of the INTELSAT V [NASA-CR-175382] P 10 N84-18270 lightsails p62 A84-27443 graphite-epoxy central thrust tube p 19 A84-22153 RESEARCH SANDWICH STRUCTURES New directions in solar array development Identification of new potential scientific and technology Local stability of sandwich structures with thin fibre p47 A84-22958 areas for DoD application. Summary of activities reinforced face skins for space application Technical aspects of the Intelsat V solar array [AD-A134372] P 78 N84-17050 [MBB-UD-381-83-OE] p 19 A84-22859 p47 A84-22962 RESEARCH AND DEVELOPMENT SATELLITE ANTENNAS GEO space platform economics - Impact of concept, A system for intelligent teleoperation research Application of a common reflector configuration to a size, launch mode and lifetime [AIAA PAPER 83-2376] P 57 A84-10070 multimission satellite of the 90's [AIAA PAPER 84-0704] p 74 A84-25281 NASA priority technologies [IAF PAPER 83-60] p1 A84-11731 Development and application ot new technologies in the [IAF PAPER 83-345] P1 A84-11793 Multibeam phased arrays - Application to ESA Olympus Programme Evolutionary concepts for a space station and the SOC/Free-Flyer communication system — Space [AIAA PAPER 84-0706] p4 A84-25282 relevant utilisation potential p5 A84-26926 Operation Center p 45 A84-15641 A standardized propulsion module for future National Aeronautics and Space Administration Act, Advanced composite antenna reflectors for communications satellites in the 2000 to 3000 kg class 1985 P9 N84-18116 communications satellites p 53 A84-17151 [AIAA PAPER 84-0727] P 62 A84-25292

A-16 SUBJECT INDEX SOLAR GENERATORS

Utilization of electric propulsion for communication SATELLITE TRANSMISSION SIRIO SATELLITE satellites Narrow multibeam satellite ground station antenna The small transmitter receiver stations in me Sirio (AIAA PAPER 84-0729) p 62 AS4-25293 employing a linear array with a geosynchronous arc experiment — microwave transmission MSAT mobile communication demonstration satellite coverage of 60 deg. II - Antenna design [FUB-50-1982] p 49 N84-15386 system and bus tradeoff considerations p46 A84-17743 SKIN (STRUCTURAL MEMBER) [AIAA PAPER 84-0751 ] p 48 A84-25306 SATELLITE-BORNE INSTRUMENTS Reid repair of graphite epoxy skin panels on the Land-mobile communications satellite system design NASA needs and trends in cryogenic cooling spaceship Columbia p 52 A84-17120 [AIAA PAPER 84-0753] p 5 AB4-25308 p25 N84-15329 SKYLAB PROGRAM The space van and its potential impact on the design SCALE MODELS The role of man in space p 72 A84-24627 Scale model testing for control system parameters of of communications satellites SOFTWARE ENGINEERING [AIAA 84-0758] p 74 A84-25309 large structures Space Station Technology. 1983 [AD-A135652] p 41 N84-18313 Thermal control of the Tethered Satellite Module [NASA-CP-2293] p11 N84-18277 [SAE PAPER 831138] p 24 A84-29067 Spacecraft thermal balance testing using infrared tamps Data management p 12 N84-18287 The thermal design of L-SAT large telecommunication on a dummy spacecraft p 26 N84-19399 satellite p27 N84-19414 SCATHA SATELLITE SOFTWARE TOOLS Derivation and combination of impedance matrices for A review of SCATHA satellite results: Charging and Software production in a large space project: The SPOT flexible satellites discharging p 50 N84-17254 mission center p 78 N84-14752 [ESA-STR-209] p 43 N84-21604 SCIENCE Modem software development tools in space projects SATELLITE INSTRUMENTS Use of space station for science p 72 A84-24629 on the example of a Spacelab experiment Attitude stability for the yaw-wheel class of orbiting SCIENTIFIC SATELLITES p 49 N84-14761 gyrostats p33 A84-19675 Use of space station for science p 72 A84-24629 SOLAR ARRAYS Canadian Attitude Sensing Experimental Package SEALS (STOPPERS) Photovoltaic solar arrays leading to a candidate space (CASEP) p79 N84-17223 An evaluation of Techroll seal flexible joint material power system in the regime beyond 100 kW SATELLITE NETWORKS p56 N84-16037 [IAF PAPER 83-422] p 44 A84-11817 An overview of the institutional and regulatory aspects SECURITY Evaluation of bus impedance on the SPOT muttimtssion and their impact on system design ~ of geostationary National security implications of a U.S. space station platform p44 A84-13521 satellites p73 A84-24635 New directions in solar array development [IAF PAPER 83-82] p 65 A84-11737 SELF EXCITATION p47 A84-22958 Commercial communications satellite market and Interactive structural-thermal-control analytical Technology components of solar arrays for space technology in the 90's formulations — large space structures platforms p 47 AB4-22959 [IAF PAPER 83-86] p 65 A84-11739 p29 N84-21619 Solar array Shuttle flight experiment - Hardware Tele-X - The first step in a satellite communications SENSITIVITY development and testing p 47 A84-22961 system for the Nordic countries Sensitivity analysis of the influence of the flexibility of Technical aspects of the Intelsat V solar array [AIAA PAPER 84-0713] p4 AB4-25287 solar panels on the attitude dynamics of artificial p47 A84-22962 Lessons learned during the first year of theTDRSS New component development for multi-100 kW low-cost satellites [AIAA PAPER 84-0687] p 74 A84-25319 [INPE-2763-PRE/337] p 39 N84-16232 solar array applications p47 AB4-22963 Development trends in Europe on satellite clusters and Study of multi-kilowatt solar arrays for Earth orbit SERVICE LIFE geostationary platforms applications Flexible radiator thermal vacuum test report [AIAA PAPER 84-0703] p 75 A84-25327 [NASA-CR-170939] p 49 N84-12634 [NASA-CR-171764] p 28 N84-20622 SATELLITE ORBITS Current collection from the space plasma through Analytical model of the evolution of orbit parameters SERVICE MODULES defects in high voltage solar array insulation of a quasi geostationary satellite Servicing vehicle for satellites and platforms In low earth p49 N84-15970 [IAF PAPER 83-316] p 65 A84-11787 orbits Finite element analysis of a deployable space Attitude stability for the yaw-wheel class of orbiting [DGLR PAPER 83-102] p6 A84-29666 structure p 38 N84-16056 gyrostats p 33 A84-19675 SHADOWS The STEP/STACBEAM experiment technology SATELLITE PERTURBATION Self-shadowing of orbiting trusses development for very large solar array deployers Periodic oscillations of a gyrostat satellite with respect [NASA-CR-173215] p 25 N84-16565 p8 N84-17220 to the centers of mass in a circular orbit SHAPE CONTROL Photovoltaic concentrator pointing dynamics and plasma p33 A84-19728 Model error estimation for distributed systems described interaction study p50 N84-17224 SATELLITE POWER TRANSMISSION (TO EARTH) by elliptic equations p 15 A84-11946 A deployable structure and solar array controls Consequences of transmission of solar energy from On the number and placement of actuators for experiment for STEP p 39 N84-17227 outer space p68 A84-17076 independent modal space control — for large flexible Integrated Power/Attitude Control System (IPACS) Legal aspects of solar power satellites impact on the spacecraft p 34 A84-24990 technology experiment p39 N84-17229 environment p 68 A84-17077 A degree of controllability definition - Fundamental Design and development of an advanced solar array Energy from space; Proceedings of the Symposium on concepts and application to modal systems drive mechanism p 17 N84-18457 Solar Energy from Space, Vienna, Austria, August 9-21, p34 A84-24991 Space telescope: Solar array primary development 1982 p69 A84-21476 Static shape forming for an electrostatically controlled mechanism p 51 N84-18458 Energy from space - A vision of the future membrane mirror p 16 A84-25551 Operational modules for space station construction p69 A84-21477 [NASA-TM-85772] p 21 N84-21608 The 55-meter-structure flight experiment Evolution of the solar power satellite concept - The SOLAR CELLS p8 N84-17233 utilization of energy from space p 70 A84-21478 Welded solar cell interconnection p 19 A84-22965 A system study of the solar power satellite concept SHAPES Large area, low cost space solar cells p70 A84-21480 Computer-Aided Geometry Modeling p 47 A84-22979 Market potential and possible limitations for satellite [NASA-CP-2272] p 18 N84-22179 Large area space solar cell assemblies solar power stations p 70 A84-21481 SHEAR STRESS p 61 AB4-22980 European questions related to satelite power systems Buckling and vibration of any prismatic assembly of shear Mechanical wraparound contacted cell for low cost p70 A84-21483 and compression loaded anisotropic plates with an space arrays p 48 A84-22982 Space station - An early experimental solar power arbitrary supporting structure p 23 A84-14050 Prediction of solar cell performance in space satellite p70 A84-21487 SHELL THEORY p 48 AB4-22997 Power-economical considerations for the integration of Numerical solution of several classes of nonlinear Current collection from the space plasma through terrestrial and extraterrestrial solar generators into existing flexible shell theory problems p 35 A84-25586 defects in high voltage solar array insulation power generation systems p 71 A84-21488 SHORT CIRCUIT CURRENTS p49 N84-15970 Radiation characteristics of array antennas with Orbiting wire as a dynamo: Auxiliary power possibilities Operational modules for space station construction disturbed aperture coverage p48 A84-26516 for space platforms [NASA-TM-85772] p 21 N84-21608 SATELLITE ROTATION [IFSI-83-3] p49 N84-12653 SOLAR COLLECTORS Capture-ejector satellites SHUTTERS Study of mufti-kilowatt solar arrays for Earth orbit [NASA-TM-85686] P7 N84-15179 A Maltese cross shaped mobile thermal control shutter applications SATELLITE SOLAR POWER STATIONS — for satellites p27 NB4-19454 [NASA-CR-170939] p 49 N84-12634 Application of beam power technology to a space Photovoltaic concentrator pointing dynamics and plasma SIDELOBE REDUCTION station p45 A84-15642 Improved orbit utilization using auxiliary feeds in existing interaction study p 50 NB4-17224 Space solar power in perspective p 71 A84-21489 earth terminals p 46 A84-20647 SOLAR ECUPSES SATELLITE SURFACES Torque from solar radiation pressure gradient during Large space instrumentation to measure the interaction SIGNAL PROCESSING eclipse — for very large spacecraft p 31 A84-12489 Characteristics of the microprocessor implementation between space structures and the environment SOLAR ELECTRIC PROPULSION [AD-A129990] p 77 N84-10179 of algorithms for the processing of radio signals and noise Discontinuous low thrust orbit transfer in large antenna arrays p 48 A84-28067 SATELLITE TELEVISION [AD-A136908] p 63 N84-19474 The Franco-German DBS program TV-SAT/TDF-V SIGNAL TO NOISE RATIOS SOLAR ENERGY CONVERSION [AIAA PAPER 84-0661 ] p4 A84-25260 Characteristics of the microprocessor implementation Consequences of transmission of solar energy from SATELLITE TEMPERATURE of algorithms for the processing of radio signals and noise outer space p 68 A84-17076 Spacecraft thermal design using interactive graphics in large antenna arrays p 48 A84-28067 Space station - An early experimental solar power [AIAA PAPER 84-0143] p 23 A84-17910 SILICON CARBIDES satellite p 70 A84-21487 Thermal control of the Tethered Satellite Module SiC-reinforced-aluminum alloys for aerospace Space solar power in perspective p 71 A84-21489 [SAE PAPER 831138] p 24 A84-29067 applications p 54 A84-28242 SOLAR GENERATORS SATELLITE TRACKING SILICON NITRIDES Power-economical considerations for the integration of Space station communications and tracking equipment Assessment of reliability of ceramic materials terrestrial and extraterrestrial solar generators into existing management/control system p 45 A84-15639 p 54 A84-24508 power generation systems p 71 A84-21488

A-17 SOLAR POWER SATELLITES SUBJECTINDEX

SOLAR POWER SATELLITES SPACE COMMERCIALIZATION National Aeronautics and Space Administration The solar power satellite - A programme for Space Shuttle, private enterprise and intellectual Authorization Act 1985 p80 N84-21443 development aid p68 AB4-17074 properties in the context of space manufacturing National Aeronautics and Space Administration Energy from space - Legal implications of the use of p72 A84-22341 Authorization Act. 1985 the geostationary orbit p68 A84-17075 Space station: Policy, planning and utilization; [H-REPT-98-629J p 80 N84-21444 Consequences of transmission of solar energy from Proceedings of the Symposium, Arlington, VA, July 18-20, SPACE INDUSTRIALIZATION outer space P 68 A84-17076 1983 p72 A84-24626 Determination of applicable law to living and working Legal aspects of solar power satellites impact on the Role of a space station in pharmaceutical in space environment P 68 A84-17077 manufacturing p 73 A84-24632 [IAF PAPER 82-IISL-45] p 68 A84-17058 Energy from space; Proceedings of the Symposium on Space station architectural issues as viewed by the user Leasecraft - An innovative space vehicle Solar Energy from Space. Vienna. Austria. August 9-21, community - Applications p 4 A84-24634 p 5 A84-27945 1982 p69 A84-21476 Leasecraft - An innovative space vehicle With the Space Shuttle towards space industrialization Energy from space - A vision of the future p 5 A84-27945 p75 A84-28975 p 69 A84-21477 Major concerns of private enterprise regarding recent A legal charter for non-governmental space Evolution of the solar power satellite concept - The developments in space law industrialization utilization of energy from space p 70 A84-21478 [AAS PAPER 83-221 ] p 77 A84-29865 [AAS PAPER 83-225] p 77 A84-29868 Solar power satellites - The institutional challenge International aspects of commercial space activities SPACE LABORATORIES p70 A84-21479 [AAS PAPER 83-222] p 77 A84-29866 The Alpha-Helix Concept Innovative utilization of the A system study of the solar power satellite concept A legal charter for non-governmental space Space Station Program. A report to the National p70 A84-21480 industrialization Aeronautical and Space Administration requesting Market potential and possible limitations for satellite [AAS PAPER 83-225] p 77 A84-29868 establishment of a Sensory Physiology Laboratory on the solar power stations P 70 A84-21481 International competition in commercial aerospace Space Station Financing a solar power satellite project markets [NASA-CR-175436] p 14 N84-20610 p70 AB4-21482 [AAS PAPER 83-244] p 77 A84-29883 SPACE LAW European questions related to satelite power systems Alternative strategies for space station financing An overview of the institutional and regulatory aspects p70 A84-21483 [NASA-CR-175412] p 80 N84-21437 and their impact on system design — of geostationary Space station - An early experimental solar power SPACE COMMUNICATION satellites satellite p70 A84-21487 NTC '82; National Telesystems Conference, Gatveston, [IAF PAPER 83-82] p 65 A84-11737 Power-economical considerations for the integration of TX, November 7-10, 1982, Conference Record Colloquium on the Law of Outer Space, 25th, Paris, terrestrial and extraterrestrial solar generators into existing P44 A84-15623 France. September 27-October 2.1982, Proceedings power generation systems p 71 A84-21488 Space station architectural issues as viewed by the user p67 A84-17026 Space solar power in perspective p 71 A84-21489 community - Applications p 4 A84-24634 Jurisprudential philosophies of the art of living in space Radiation characteristics of array antennas with Telecommunication systems for large-scale space The transnational imperative disturbed aperture coverage p48 A84-26516 manufacturing activity [IAF PAPER 82-IISU-38] p 68 A84-17054 Determination of applicable law to living and working Sensitivity analysis of the Influence of the flexibility of [AAS PAPER 83-216] p 48 A84-29861 in outer space solar panels on the attitude dynamics of artificial SPACE ENVIRONMENT SIMULATION [IAF PAPER 82-IISL-44] p 68 A84-17057 satellites Hardware simulation of spacecraft dynamics and Determination of applicable law to living and working [INPE-2763-PRE/337] P 39 N84-16232 control p30 A84-11932 Simulated space radiation effects on dielectrics and in space SOLAR RADIATION [IAF PAPER 82-IISL-45] p 68 A84-17058 Torque from solar radiation pressure gradient during coatings p 54 A84-20682 Evaluation and prediction of long-term environmental Major concerns of private enterprise regarding recent eclipse — for very large spacecraft p31 A84-12489 effects of nonmetallic materials, second phase developments in space law Development of a spacecraft infrared test technique as [NASA-CR-170915] p 56 N84-11595 [AAS PAPER 83-221 ] p 77 A84-29865 an alternative to solar simulation: First steps on L-SAT Development of a spacecraft infrared test technique as A legal charter for non-governmental space thermal model P 26 N84-19398 an alternative to solar simulation: First steps on L-SAT industrialization IRSIM: A program for the calculation of infrared flux thermal model p 26 N84-19398 [AAS PAPER 83-225] p 77 A84-29868 intensity incident on a spacecraft inside a test chamber Spacecraft thermal balance testing using infrared lamps SPACE LOGISTICS p26 N84-19400 on a dummy spacecraft p26 N84-19399 Space logistics — preparing for future space missions Computing the radiation pressure forces by adapting IRSIM: A program for the calculation of infrared flux [IAF PAPER 83-24] p 64 A84-11719 thermal design verification softwares — large space intensity incident on a spacecraft inside a test chamber Shutter interaction study extension structures P 28 N84-21613 p26 N84-19400 [NASA-CR-173401] p 81 N84-21593 SOLAR SAILS Thermal cycling tests in space environment simulation SPACE MAINTENANCE Management of the radiolink of the solar sail spacecraft chambers p26 N84-19401 Servicing vehicle for satellites and platforms in low earth by radio-amateurs The Large Space Simulator (LSS) at ESA/ESTEC (a orbits [IAF PAPER 83-447] p 44 A84-11823 summary of the main characteristics) p27 N84-19458 [DGLR PAPER 83-102] p 6 A84-29666 Interstellar solar sailing - Consideration of real and Assessment of the existing ground test technology and Shuttle interaction study extension projected sail materials p62 A84-25344 confronting with the Large Space Structures (LSS) [NASA-CR-173398] p 81 N84-21594 SPACE MANUFACTURING Making the high frontier highly visible with.a solar sail requirements. Thermal test techniques Knowledge based systems for intelligent robotics race to the moon p29 N84-21622 p57 A84-15667 [AAS PAPER 83-226] P 62 A84-29869 SPACE ERECTABLE STRUCTURES The development of a composite beam building machine The Shuttle remote manipulator system: CANADARM SOLAR SYSTEM - A robot ami in space p 57 A84-21486 Manned planetary missions? p 71 A84-21497 for on-site construction of large space structures [AAS PAPER 83-217] p 20 A84-29862 Remote manipulators in space p 57 A84-22336 SOLAR THERMAL PROPULSION Development of deployable structures for large space Automation, Robotics, and Machine Intelligence A future solar orbital transfer vehicle concept platform systems. Volume 1: Executive summary Systems (ARAMIS) in space manufacturing p61 A84-16116 [NASA-CR-170913] p 20 N84-10175 p58 A84-22337 SOLDERING Development of deployable structures for large space Manufacturing space systems in space Welded solar cell interconnection p 19 A84-2296S platforms. Volume 2: Design development p71 A84-22338 SOLID STATE LASERS [NASA-CR-170914] p20 N84-10176 Space Shuttle, private enterprise and intellectual Application of laser interferometry to robotics Orbiter-based construction equipment study. The properties in the context of space manufacturing p58 A84-28541 HPA/DTA technology advancement plan p72 A84-22341 SOVIET SPACECRAFT [NASA-CR-174605] p17 N84-14233 Role of a space station in pharmaceutical For the first time — Russian book on construction of Synchronously deployable truss structure manufacturing p 73 A84-24632 first Soviet earth satellites P 16 A84-21564 [NASA-CASE-LAR-13117-1] p 59 N84-16250 A contact conductance interface for a space Space vehicles — Russian book on development of Erectable beam experiment p60 N84-17219 constructable heat pipe radiator Soviet spacecraft and planning of first manned flights The STEP/STACBEAM experiment technology p4 A84-21573 development for very large solar array deployers [SAE PAPER 831101 ] p 24 A84-29036 Space manufacturing 1983; Proceedings of the Sixth SPACE BASED RADAR p8 N84-17220 Conference, Princeton University, Princeton, NJ, May 9-12. RF systems in space. Volume 2: Space-based radar Low concentration ratio solar array structural 1983 p76 A84-29852 analyses configuration p 17 N84-17225 [AD-A133735] P 49 N84-14394 Development of Test Article Building Block (TABS) for Telecommunication systems for large-scale space deployable platform systems p 21 N84-17226 manufacturing activity RF systems in space. Volume 1: Space antennas A deployable structure and solar array controls [AAS PAPER 83-216] p 48 A84-29861 frequency (SARF) simulation experiment for STEP p39 N84-17227 [AD-A133734] P 49 N84-14395 The development of a composite beam building machine Shutter interaction study extension for on-site construction of large space structures The effects of aperture antennas after signal propagation [NASA-CR-173401] p 81 NS4-21593 [AAS PAPER 83-217] p 20 A84-29862 through anisotropic ionized media SPACE EXPLORATION [AD-A138286] p 52 N84-21781 SPACE MISSIONS Developing the space frontier; Proceedings of the Space logistics — preparing for future space missions SPACE COLONIES Twenty-ninth Annual Conference. Houston. TX, October [IAF PAPER 83-24] p 64 A84-11719 Natural selection of stellar civilizations by the limits of 25-27,1982 p 67 A84-15381 The Tiros-based asteroid mission p 2 A84-14762 growth Manned planetary missions? p71 A84-21497 The German Spaoelab mission 01 p69 A84-17762 [IAF PAPER 83-272] p 65 A84-11779 Mankind's interstellar future p 71 A84-21499 Mission to Mars - The case for a settlement Space 1991 p 71 A84-21720 The role of man in space p 72 A84-24627 p67 A84-1S092 SPACE FLIGHT Integrated requirements for a space station Understanding space settlements as human systems Spacefltght to 2000 - Interavia looks forward from the p 4 A84-24628 [AAS PAPER 83-204] p 76 A84-29856 present p66 A84-14764 Use of space station for science p 72 A84-24629

A-18 SUBJECTINDEX SPACE STATIONS

Probable missions and transportation scenarios to use A deployable structure and solar array controls Space Shuttle, private enterprise and intellectual regenerative life support systems experiment (or STEP p 39 N84-17227 properties in the context of space manufacturing [AAS PAPER 83-201 ] p 76 A84-29854 STEP flight experiments Large Deployable Reflector p72 A84-22341 A program to develop efficient manned operations in (LOR) telescope p8 N84-17231 Solar array Shuttle flight experiment - Hardware Flight test of a synthetic aperture radar antenna using development and testing p 47 A84-2296I [AAS PAPER 83-207) p 76 A84-29857 STEP p9 N84-17237 A simulator to study dynamic interaction of the Space Space Station needs, attributes and architectural Space Station needs, attributes and architectural Shuttle on-orbit flight control system with deployed flexible options. Volume 2, book 1, part 1: Mission options: Summary briefing payloads p35 A84-26717 requirements [NASA-CR-173328] p 10 N84-18271 Thermal control of the Tethered Satellite Module [NASA-CR-173312] p 13 N84-18296 Space station needs, attributes and architectural options [SAE PAPER 831138] p 24 A84-29067 Space Station needs, attributes and architectural study. Briefing material: Final review and executive summary A definition of STS accommodations for attached options. Volume 2, book 1, part 2, task 1: Mission [NASA-CR-173321] p 10 N84-18273 payloads requirements [NASACR-172223] p 17 N84-10114 [NASA-CR-173313] p 13 N84-18297 Space Station needs, attributes and architectural options. Volume 2, book 2. part 1: Mission implementation Molecular contamination math model support Shutter interaction study extension concepts [NASA-CR-170899] p 77 N84-10174 [NASA-CR-173401] p 81 N84-21593 [NASA-CR-173316] p 13 N84-1B300 General requirements for Shuttle flight experiments SPACE NAVIGATION A large-area gamma-ray imaging telescope system p8 N84-17221 Autonomous navigation of geosynchronous satellites [NASA-CR-175435] p 14 N84-20604 Effects of combined ultraviolet and oxygen plasma using the Navstar Global Positioning System The Alpha-Helix Concept Innovative utilization of the environment on spacecraft thermal control materials — p 45 A84-15671 Space Station Program. A report to the National space shuttle payloads p27 N84-19449 SPACE OPERATIONS CENTER (NASA) Aeronautical and Space Administration requesting A large-area gamma-ray imaging telescope system Attitude control and dynamics of the space operations establishment of a Sensory Physiology Laboratory on the [NASA-CR-175435] p 14 N84-20604 center p31 A84-11934 Space Station On-orbit spacecraft/stage servicing during STS life MulSbeam phased arrays - Application to [NASA-CR-175436] p 14 N84-20610 cycle SOC/Free-Flyer communication system — Space Exhibit D modular design attitude control system study [NASA-CR-171775] p 79 N84-20617 Operation Center p45 A84-15641 [NASA-CR-170993] p 42 NS4-20625 Flexible radiator system Space operations center communications path SPACE PROCESSING [NASA-CR-171765] p 28 N84-20623 obscuration p3 A84-15695 Manufacturing in space; Proceedings of the Winter Feasibility of remotely manipulated welding in space. Shuttle interaction study Annual Meeting, Boston. MA, November 13-18,1983 A step in the development of novel joining technologies [NASA-CR-173400] p 80 N84-21592 p 71 A84-22327 [NASA-CR-175437] p 60 N84-20857 Shutter interaction study extension Space station architectural issues as viewed by the user Alternative strategies for space station financing [NASA-CR-173401] p 81 N84-21593 community - Applications p 4 A84-24634 [NASA-CR-175412] p 80 N84-21437 Shutter Interaction Study Reusable commercial space processing platforms Shuttle interaction study [NASA-CR-173402] p 81 N84-21595 [AAS PAPER 83-208] p7 A84-29858 [NASA-CR-173400] p 80 N84-21592 Shuttle interaction study extension Significant scientific and technical results at Marshal Shutter Interaction Study [NASA-CR-173403] p 81 N84-21596 Space Right Center [NASA-CR-173402] p 81 N84-21595 SPACE PLASMAS [NASA-TM-82562] p 78 N84-16075 Shuttle interaction study extension Radiating dipole model of interference induced in SPACE PROGRAMS [NASA-CR-173403] p 81 N84-21596 spacecraft circuitry by surface discharges Management of large space projects; Course on Space SPACE SHUTTLE UPPER STAGES [NASA-TP-2240] p 50 N84-16247 Technology, Toulouse, France, May 3-14, 1982, A parametric study of space transfer-propulsion SPACE PLATFORMS Proceedings p2 A84-15301 Payload placing using an operational support platform Human organization — and space project [IAF PAPER 83-401] p 61 A84-13397 [IAF PAPER 83-44] p1 A84-11724 management p 2 A84-15303 SPACE SHUTTLES The Fairchild Leasecraft system - A The contract — management for space projects High capacity power systems for space commercially-operated platform for science and business p2 A84-15304 [IAF PAPER 83-421] p 44 A84-11816 in space The progression of projects — in space industry With the Space Shuttle towards space industrialization [IAF PAPER 83-232] p 65 A84-11773 p2 A84-15305 p 75 A84-28975 Potential military applications of space platforms and Management of large space projects - Quality assurance Molecular contamination math model support space stations p2 A84-13330 or'product assurance' p3 A84-15310 [NASA-CR-170899] p 77 N84-10174 Science platform and attitude subsystem in-flight Financing large space projects p 67 A84-15321 Study of auxiliary propulsion requirements for large calibration for trie Galileo spacecraft p 32 A84-17355 A program to develop efficient manned operations in space systems. Volume 1: Executive summary Low cost space science and astronomy platforms in [NASA-CR-168193-VOL-1] p 63 N84-12226 orbit [AAS PAPER 83-207] p 76 A84-29857 STS-9: Orbital workshop spacelab to fly on ninth Shuttle [AIAA PAPER 84-0297] p4 A84-18005 International aspects of commercial space activities mission Space platform accommodations — for multiple [AAS PAPER 83-222] p 77 A84-29866 [NASA-TM-85497] p 78 N84-16242 interchangeable payloads p 16 A84-22131 Making the high frontier highly visible with a solar sail Identification of new potential scientific and technology Technology components of solar arrays for space race to the moon areas for DoD application. Summary of activities platforms p 47 A84-22959 [AAS PAPER 83-226] p 62 A84-29869 [AD-A134372] p 78 N84-17050 Architectural options and development issues Review of the National Aeronautics and Space Act of Stariab Ground System guidelines document p4 A84-24633 1958 [NASA-CR-175192] p 14 N84-20435 GEO space platform economics - Impact of concept, [GPO-28-915] p80 N84-21442 Shuttle interaction study size, launch mode and lifetime SPACE SHUTTLE ORBITERS [NASA-CR-173400] p 80 N84-21592 [AIAA PAPER 84-0704] p 74 A84-25281 Canadarm and the Space Shuttle p 57 A83-44602 Shutter interaction study extension NASA's geostationary communications platform Experiment data communications (48 Mbit/s) between [NASA-CR-173401] p81 N84-21593 program Spacelab, the Space Shuttle and the ground • Shuttle interaction study extension [AIAA PAPER 84-0702] p5 A84-25326 p44 AB4-10396 [NASA-CR-173398] p 81 N84-21594 Evolutionary concepts for a space station and the Low earth orbit atomic oxygen effects on surfaces — Operational modules for space station construction relevant utilisation potential p 5 A84-26926 of Space Shuttle Orbiters [NASA-TM-85772] p 21 N84-21608 Leasecraft - An innovative space vehicle [AIAA PAPER 84-0548] p 53 AB4-19912 SPACE STATIONS pS A84-27945 Regenerable non-venting thermal control subsystem for Space station data management - A system evolving Coordinate transformation assembly — for space extravehicular activity from changing requirements and a dynamic technology platform angular coordinate linking p 75 A84-28579 [SAE PAPER 831151] p 24 A84-29076 base MicroQrfivrty conditions on orbttsl plstforrns Ortaiter-based construction equipment study. The [AIAA PAPER 83-2338] p 43 A84-10016 [DGLR PAPER 83-90] p 76 A84-29657 HPA/DTA technology advancement plan Data system architecture considerations for a space The attitude and orbit control system for Eureca [NASA-CR-174605] p 17 N84-14233 station [DGLR PAPER 83-091] p 76 A84-29658 The complementary roles of existing and advanced (AIAA PAPER 83-2346] p 63 AB4-10066 Servicing vehicle for satellites and platforms in low earth environmental, thermal control and life support technology Space applications at the crossroads; Proceedings of orbits for space stations p79 N84-19429 the Twenty-first Goddard Memorial Symposium, Greenbelt, [DGLR PAPER 83-102] p6 A84-29666 MD, March 24, 25,1983 p 64 A84-10883 SPACE SHUTTLE PAYLOADS Reusable commercial space processing platforms ESA space station activities A methodology to include static and kinetic friction [AAS PAPER 83-208] p7 A84-29858 [IAF PAPER 83-30] p 64 A84-11722 effects In Space Shuttle payload transient loads analysis A definition of STS accommodations for attached [AIAA PAPER 83-2654] p 30 A84-10956 Overview of NASA space station activities payloads [IAF PAPER 83-48] p1 A84-11726 [NASA-CR-172223] p 17 N84-10114 Utilisation of the European retrieval carrier EURECA for Space station - A Canadian perspective Development of deployable structures for large space life science research p 65 A84-11753 [IAF PAPER 83-55] p 65 A84-11728 platform systems. Volume 1: Executive summary The Fairchild Leasecraft system - A Commercial communications satellite market and [NASA-CR-170913] p 20 N84-10175 commercially-operated platform for science and business technology in the 90's Development of deployable structures for large space in space [IAF PAPER 83-86] p 65 A84-11739 platforms. Volume 2: Design development [IAF PAPER 83-232] p 65 A84-11773 Potential military applications of space platforms and [NASA-CR-170914] p 20 N84-10176 Low cost space science and astronomy platforms in space stations p 2 A84-13330 Identification of new potential scientific and technology orbit Space station communications and tracking equipment areas for DoD application. Summary of activities [AIAA PAPER 844)297] p4 A84-18005 management/control system p 45 A84-15639 [AD-A134372] p 78 N84-17050 Automation, Robotics, and Machine Intelligence Juriscrudential philosophies of the art of living in space Development of Test Article Building Slock (TABS) for Systems (ARAMIS) in space manufacturing The transnational imperative deployable platform systems p 21 NS4-17226 p58 A84-22337 [IAF PAPER 82-MSL-38] p 68 A84-WOS4

A-19 SPACE SURVEILLANCE (SPACEBORNE) SUBJECTINDEX

Space stations - A key to socio-economic benefits from Space station needs, attributes and architectural options On-orbit spacecraft/stage servicing during STS life space? p69 A84-19850 study. Final review executive summary briefing cycle Project space station - Plans for a permanent manned [NASA-CR-173674] p 10 N84-18272 [NASA-CR-171775] p 79 N84-20617 space center — Book p 69 A84-21344 Space station needs, attributes and architectural options Alternative strategies for space station financing Space 1991 p 71 A84-21720 study. Briefing material: Final review and executive [NASA-CR-175412] p 80 N84-21437 Evolutionary concepts for a space station and the summary Interactive geometry modeling of space station relevant utilisation potential p 5 A84-26926 [NASA-CR-173321] p 10 N84-18273 conceptual designs p 18 N84-22191 Environmental Control and Life Support for an Space Station needs, attributes, and architectural SPACE SURVEILLANCE (SPACEBORNE) evolutionary Space Station options study National security implications of a U.S. space station [SAE PAPER 831108] p5 A84-29043 [NASA-CR-173327] p11 N84-18274 p73 A84-24635 Systems engineering aspects of a preliminary SPACE TRANSPORTATION Space station needs, attributes and architectural conceptual design of the space station environmental Transportation - Options and high payoff choices — for options. Summary of major study activities and results. control and life support system spacecraft propulsion p61 A84-21484 Space station program observations [SAE PAPER 831109] p5 A84-29044 An electric propulsion transportation system from [NASA-CR-173345] p 11 N84-18275 Integrated water management system - Description and low-earth orbit to geostationary orbit utilizing beamed Space Station Technology, 1983 test results — for Space Station waste water processing microwave power p 61 A84-21485 [SAE PAPER 831111] p6 A84-29046 [NASA-CP-2293] p11 N84-18277 The space van and its potential impact on the design Electrochemical and steam-desorbed amine CO2 Systems/operations technology p11 N84-18278 of communications satellites concentration Subsystem comparison — for oxygen Crew and life support EVA p 11 N84-18279 [AIAA 84-0758] p 74 A84-25309 recovery on Space Station Crew and life support: ECLSS p11 N84-18280 SPACE TRANSPORTATION SYSTEM [SAE PAPER 831120] p 6 A84-29054 Attitude, control and stabilization p 40 N84-18281 Overview of space station operations Phase change water recovery techniques - Vapor Human capabilities p11 N84-18282 [IAF PAPER 83-38] p 64 A84-11723 compression distillation and thermoelectric/membrane The Fairchild Leasecraft system - A Auxiliary propulsion p 11 N84-18283 concepts — from waste water as part of Space Station commercially-operated platform for science and business life support system Fluid management p 11 N84-18284 in space [SAE PAPER 831122] p6 A84-29056 Communications p 12 NS4-18285 [IAF PAPER 83-232] p 65 A84-11773 Gravitational biology on the space station Structures and mechanisms p21 NS4-18286 Low cost space science and astronomy platforms in [SAE PAPER 831133] p 75 A84-29063 Data management p 12 N84-18287 orbit Regenerable non-venting thermal control subsystem for Power p 12 N84-18288 [AIAA PAPER 84-0297] p4 A84-18005 extravehicular activity Thermal control p 25 N84-18289 Space Shuttle, private enterprise and intellectual [SAE PAPER 831151] P24 A84-29076 Space station needs, attributes and architectural properties in the context of space manufacturing Habitability design elements for a space station options. Volume 4, attachment 1: Task 2 and 3 mission p72 A84-22341 [AAS PAPER 83-200] p7 A84-29853 implementation and cost With the Space Shuttle towards space industrialization Space stations - The next step in space? [NASA-CR-173330] p 12 N84-18290 p75 A84-28975 [AAS PAPER 83-202] p 76 A84-29855 Space station needs, attributes and architectural Space Technology Experiments Platform (STEP) A program to develop efficient manned operations in options. Volume 2, attachment 2: Supporting data and overview p8 N84-17212 space analysis reports National Aeronautics and Space Administration Act, [AAS PAPER 83-207] p 76 A84-29857 [NASA-CR-173329] p 12 N84-18291 1985 p9 N84-18116 International aspects of commercial space activities Space station needs, attributes and architectural Spacelab data book [AAS PAPER 83-222] p 77 A84-29866 options. Volume 1: Executive summary NASA [ESA-BR-14] p79 NB4-18315 Integrated Flywheel Technology. 1983 [NASA-CR-172792] p 12 N84-18292 On-orbit spacecraft/stage servicing during STS life [NASA-CP-2290] p 78 N84-12228 Space station needs, attributes and architectural cycle Space station attitude control system concept and options. Volume 1, attachment 1: Executive summary [NASA-CR-171775] p 79 N84-20617 requirements p 37 N84-12234 NASA Authorizing appropriations to the National Aeronautics Space station control requirements and flywheel system [NASA-CR-173337] p 12 N84-18293 and Space Administration for fiscal year 1985 weights for combined momentum and energy storage Space station needs, attributes and architectural [H-REPT-98-629] p 80 N84-21441 p 37 N84-12236 options. Volume 1, attachment 2: Supporting data and SPACE TRANSPORTATION SYSTEM FLIGHTS Advanced Control and Power System (ACAPS) analysis reports Field repair of graphite epoxy skin panels on the technology Program P37 N84-12243 [NASA-CR-173336] p 13 N84-18294 spaceship Columbia p 52 A84-17120 NASA's space station activities Space Station needs, attributes and architectural Low earth orbit atomic oxygen effects on surfaces — [GPO-27-393] p 7 N84-14234 options. Volume 2, book 1, part 1: Mission of Space Shuttle Orbiters Thermal analysis research applicable to space station requirements [AIAA PAPER 84-0548] p 53 A84-19912 technology needs [NASA-CR-173312] p 13 N84-18296 Shutter interaction study extension [NASA-TM-84658] p 25 N84-15426 Space Station needs, attributes and architectural [NASA-CR-173401] p81 N84-21593 The US space station: Potential base for a spacebome options. Volume 2, book 1, part 2, task 1: Mission SPACE VEHICLE CHECKOUT PROGRAM microwave facility p78 N84-16420 requirements Launch processing for Spacelab 1 STEP Experiment Requirements [NASA-CR-173313] p 13 N84-18297 [AIAA PAPER 83-2622] p 64 A84-10965 [NASA-CP-2294] P7 N84-17211 Space Station needs, attributes and architectural SPACE WEAPONS Space Technology Experiments Platform (STEP) options. Volume 2, book 1, part 3: Manned Space Station National security implications of a U.S. space station overview p8 N84-17212 relevance to commercial telecommunications satellites p73 A84-24635 STEP mechanical systems p8 N84-17213 [NASA-CR-173314] p 13 N84-18298 SPACEBORNE ASTRONOMY STEP experiment integration p8 N84-17215 Space Station needs, attributes and architectural Space applications at the crossroads; Proceedings of the Twenty-first Goddard Memorial Symposium, Greenbelt, Deployable beam flight experiment (MAST) options. Volume 2, book 1, part 4: Payload element mission data sheets MD, March 24, 25, 1983 p64 A84-10883 p8 N84-17218 [NASA-CR-173315] p 13 N84-18299 The Tiros-based asteroid mission p2 A84-14762 Erectable beam experiment p60 N84-17219 Space Station needs, attributes and architectural SPACEBORNE EXPERIMENTS Integrated Power/Attitude Control System (IPACS) options. Volume 2, book 2. parti: Mission implementation Utilisation of the European retrieval carrier EURECA for technology experiment p39 N84-17229 concepts life science research p 65 A84-11753 User manual of the CATSS system (version 1.0) [NASA-CR-173316] p 13 N84-18300 Space platform accommodations — for multiple communication analysis tool for space station Space Station needs, attributes and architectural interchangeable payloads p16 A84-22131 [NASA-CR-171728] p 51 N84-17431 options. Volume 2, book 2, part 2, Task 2: Information The US space station: Potential base for a spacebome Airborne antenna pattern calculations management system microwave facility p78 N84-16420 [NASA-CR-173284] p 51 N84-17436 [NASA-CR-173317] p 13 N84-18301 STEP Experiment Requirements Space station needs, attributes and architectural options Space Station needs, attributes and architectural [NASA-CP-2294] p7 N84-17211 study. Volume 1: Executive study options. Volume 2, book 2, part 3: Communication The STEP/STACBEAM experiment technology [NASA-CR-173334] p9 N84-18265 system development for very large solar array deployers p8 N84-17220 Space station needs, attributes and architectural options [NASA-CR-173318] p 14 N84-18302 study. Volume 2: Mission analysis Space Station needs, attributes and architectural General requirements for Shuttle flight experiments [NASA-CR-173333] p9 N84-18266 options, volume 2, book 2, part 4: International reports p8 N84-17221 [NASA-CR-173319] p 14 N84-18303 Thermal energy management process experiment Space station needs, attributes and architectural options p25 N84-17222 study. Volumes: Requirements Space Station needs, attributes and architectural Canadian Attitude Sensing Experimental Package [NASA-CR-173332] p 10 N84-18267 options, volume 2, book 3: Cost and programmatjcs [NASA-CR-173320] p 14 N84-18304 (CASEP) p79 N84-17223 Space station needs, attributes and architectural options Definition of technology development missions for early Photovoltaic concentrator pointing dynamics and plasma study. Volume 4: Architectural options, subsystems, space stations orbit transfer vehicle serving. Phase 2, interaction study p50 N84-17224 technology and programmatics task 1: Space station support of operational OTV A deployable structure and solar array controls [NASA-CR-173331] p 10 N84-18268 servicing experiment for STEP p39 N84-17227 Space station needs, attributes and architectural options [NASA-CR-170984] p 14 N84-19377 Vibration isolation technology experiment study. Final executive review A manned-machine space station construction p39 N84-17228 [NASA-CR-173335] p 10 N84-18269 concept STEP flight experiments Large Deployable Reflector Space station needs, attributes and architectural [NASA-TM-85762] p 21 N84-19395 (LDR) telescope p8 N84-17231 options. Part 1: Summary The complementary roles of existing and advanced Large deployable antenna flight experiment for the [NASA-CR-175382] p 10 N84-18270 environmental, thermal control and life support technology Space Technology Experiments Platform (STEP) Space Station needs, attributes and architectural for space stations p 79 N84-19429 p8 N84-17232 options: Summary briefing Civil space station Large inflated-antenna system p9 N84-17234 [NASA-CR-173328] p 10 N84-18271 [S-REPT-98-523] p 79 N84-20613 Adaptive microwave reflector p 50 N84-17235

A-20 SUBJECTINDEX SPACECRAFT DESIGN

Microwave reflector characterization using simple Communications p 12 N84-18285 Aggregate models for distributed parameter systems instruments in EVA ' P 50 N84-17236 Study of a tracking and data acquisition system for the with applications to flexible air and spacecraft Flight test of a synthetic aperture radar antenna using 1990's. Volume 3: TDAS Communication Mission p31 A84-11945 STEP P9 N84-17237 Model Dynamics and control of a deformable gyrostat, utilizing Space station needs, attributes add architectural options [NASA-CR-175195] p 79 N84-19371 continuum vehicle modes p31 A84-12488 study. Volume 2: Mission analysis An Attached Paytoad Operations Center (APOQ at the The Toysat structural control experiment — for large [NASA-Cfl-173333] P9 N84-18266 Goddard Space Right Center (GSFC). volume 1 flexible space structure p 31 A84-13320 Space Station needs, attributes and architectural [NASA-CR-175160] p 79 N84-20605 Structural parameter identification for flexible options. Volume 2. book 1, pat 2. task 1: Mission Authorizing appropriations to the National Aeronautics spacecraft requirements and Space Administration for fiscal year 1985 [AIAA PAPER 84-0060] p 23 A84-17853 [NASA-CR-173313] P 13 N84-18297 (H-REPT-98-629] p 80 N84-21441 A design strategy for multiple paytoad pointing from a Space Station needs, attributes and architectural The effects of aperture antennas after signal propagation three axis stabilized spacecraft ' options. Volume 2, book 1, part 4: Paytoad element through anisotropic ionized media [AIAA PAPER 84-0566] p 33 A84-18168 mission data sheets [AD-A138286] p 52 N84-21781 The spatial order reduction problem and its effect on [NASA-CR-173315] P 13 N84-18299 SPACECRAFT COMPONENTS adaptive control of distrirbuted parameter systems Feasibility study to conduct windblown sediment Transient dynamics during the orbiter based deployment p33 A84-19056 experiments aboard a space station of flexible members Sampled data control of large space structures using [NASA-CR-175434] P 15 N84-21586 [AIAA PAPER 84-0061] p 34 A84-21285 constant gain velocity feedback - A negative view SPACEBORNE TELESCOPES Design and development of an advanced solar array p46 A84-19169 Large Deployable Reflector (LDR) - A concept for an drive mechanism p 17 N84-18457 On the number and placement of actuators for orbiting submillimeter-infrared telescope for the 1990s Design and manufacturing of a heat rejection system independent modal space control — for large flexible p66 A84-14586 for advanced thermal control — spacecraft and or paytoad spacecraft p34 A84-24990 Coherent arrays of separate optkal telescopes in space cooling p 27 N84-19434 Manipulator interactive design with interconnected project Trio P3 A84-15363 Flexible radiator system: Executive summary flexible elements p 58 A84-25484 STEP flight experiments Large Deployable Reflector [NASA-CR-171766] p 28 N84-20624 A simulator to study dynamic interaction of the Space (LDR) telescope P8 N84-17231 Development of procedures for component mode Shuttle on-orbit flight control system with deployed flexible The effect of mass and stiffness changes on the damping synthesis payloads p35 A84-26717 factor in a large space structure as represented by the [DFVLR-IB-232-82-C-09] p 30 N84-21626 Closed-form solutions for feedback control with terminal CSDL 2 model SPACECRAFT CONFIGURATIONS constraints p 36 A84-29471 [AD-A136984] ' P "2 N84-19465 Space station attitude control system concept and Actuator placement considerations for the control of Optical coating in space requirements p 37 N84-12234 large space structures p 20 N84-11199 [NASA-CR-175441] P 56 NB4-21290 Space station needs, attributes and architectural Integrated Power/Attitude Control System (IPACS) SPACECRAFT ANTENNAS options. Part 1: Summary technology experiment p 39 N84-17229 Technology requirements for large flexible space [NASA-CR-175382] p 10 N84-18270 Control of large flexible spacecraft by the independent structures Space Station needs, attributes and architectural modal-space control method [IAF PAPER 83-404] p2 A84-11811 options: Summary briefing [NASA-CR-3760] p 40 N84-18262 A hardware demonstration of control for a flexible [NASA-CR-173328] p 10 N84-18271 Authorizing appropriations to the National Aeronautics offset-feed antenna p31 A84-13321 Space station needs, attributes and architectural options and Space Administration for fiscal year 1985 Static shape forming for an elec*ostattcally controlled study. Briefing material: Final review and executive [H-REPT-98-629] p 80 N84-21441 membrane mirror P 16 A84-25551 summary SPACECRAFT DESIGN Large deployable antenna flight experiment for the [NASA-CR-173321] p 10 N84-18273 Spacecraft thermal control, design, and operation Space Technology Experiments Platform (STEP) Space Station needs, attributes and architectural p 22 A84-10224 p8 N84-17232 options. Volume 2, book 1, part 1: Mission Overview of NASA space station activities Large inflated-antenna system P9 N84-17234 requirements [IAF PAPER 83-48] p1 A84-11726 Study on large, ultralight long-life structures in space, [NASA-CR-173312] p 13 N84-18296 Utilisation of the European retrieval carrier EURECA for phase 2C Space Station needs, attributes and architectural life science research p 65 A84-11753 [TM-EKR3] P17 N84-17284 options. Volumes, books, part 1: Mission implementation Some aspects of simulation studies in spacecraft Airborne antenna pattern calculations concepts dynamics p 15 A84-11930 [NASA-CR-173284] P 51 N84-17436 [NASA-CR-173316] p 13 N84-18300 Spacelab's development p66 A84-13901 Spline-based estimation techniques for parameters in SPACECRAFT CONSTRUCTION MATERIALS Developing the space frontier: Proceedings of the elliptic distributed systems Erosion of mylar and protection by thin metal films Twenty-ninth Annual Conference, Houston, TX, October [NASA-TM-85439) P9 N84-17947 [AIAA PAPER 83-2638] p 52 A84-10949 25-27,1982 p 67 A84-15381 SPACECRAFT CHARGING Tests and prediction of composite material viscoelastic A future solar orbital transfer vehicle concept Dielectric charging in space - Groiind test data and model behaviour for large space structure p61 A84-16116 verification P 47 A84-20709 [IAF PAPER 83-418] p 30 A84-11815 Weight characteristics of future spacecraft thermal Radiating dipole model of interference induced in Using the outgassing test to screen materials for management systems spacecraft circuitry by surface discharges contamination potential p 53 A84-I7174 [AIAA PAPER 84-0054] p 23 A84-17850 [NASA-TP-2240] P 50 N84-16247 Cracked inner layer foil in high-density multilayer printed Plasma sheath structure surrounding a large powered Spacecraft/plasma interactions and their influence on wiring boards p53 A84-17200 spacecraft field and particle measurements — conferences Materials and construction techniques for large [AIAA PAPER 84-0329] p 46 A84-18025 [ESA-SP-198] P56 N84-17253 spacecraft structures p 53 A84-17768 Multi-megawatt space power thermal management A review of SCATHA satellite results: Charging and Simulated space radiation effects on dielectrics and system requirements discharging P 50 N84-17254 coatings p 54 A84-20682 [AIAA PAPER 84-0056] p 23 . A84-21284 The role of potential barrier formation in spacecraft The effect of pressure and temperature on Project space station - Plans for a permanent manned charging P 50 N84-17269 time-dependent changes in graphite/epoxy composites space center — Book p69 A84-21344 Sheath ionization model of bean' emissions from large below the glass transition p54 A84-21775 Space platform accommodations — for multiple spacecrafts Interstellar solar sailing - Consideration of real and interchangeable payloads p 16 A84-22131 [AD-A137181] P52 N84-19463 projected sail materials p62 A84-25344 Solar array Shuttle flight experiment - Hardware SPACECRAFT COMMUNICATION SiC-reinforced-aluminum alloys for aerospace development and testing p 47 A84-22961 Experiment data communications (48 Mbit/s) between applications p 54 A84-28242 Architectural options and development issues Spacelab, the Space Shuttle and tne ground Evaluation of spacecraft materials and processes for p4 A84-24633 p44 A84-10396 optical degradation potential p 54 A84-28458 Environmental control and life support (ECLS) design Management of the radtolink of me solar sail spacecraft Electrically conductive black optical paint optimization approach p 73 A84-24637 by radio-amateurs pSS A84-28553 Leasecraft - An innovative space vehicle [IAF PAPER 83-447] P 44 A84-11823 Research and technology, 1983 p5 A84-27945 Space station communications and tracking equipment [NASA-TM-85702] p7 N84-12026 The thermal design of the European complement of management/control system P 45 A84-15639 Composite structural materials FSLP — First SpaceLab Mission Communications, tracking, and docking on the Space [NASA-CR-173259] p 56 N84-17293 [SAE PAPER 831144] p 24 A84-29071 Station p45 A84-15640 Review report of the third year's activities on the study On transient dynamics and stability of large space Multibeam phased arrays - Application to survey of advanced materials — for spacecraft and launch structures p 36 A84-29143 SOC/Free-Flyer communication system — Space vehicles Space station attitude control system concept and Operation Center p45 A84-1S641 [R878] p56 N84-21675 requirements p 37 N84-12234 Space operations center communications path SPACECRAFT CONTAMINATION ACOSS Fourteen (Active Control of Space Structures) obscuration p3 A84-15695 Using the outgassing test to screen materials for [AD-A133411] p38 N84-1S181 Space station communications P 73 A84-24636 contamination potential p 53 A84-17174 Study on damping representation related to spacecraft Communication Satellite System* Conference, 10th, Evaluation of spacecraft materials and processes for structure) dssiQn Orlando, FL, March 19-22,1984. Technical Papers optical degradation potential p 54 A84-28458 [EMSB-18/83] p38 N84-15182 p 73 AB4-25251 Molecular contamination math model support Thermal analysis research applicable to space station Time phased introduction of advanced technologies - [NASA-CR-170899] p 77 N84-10174 technology needs Its impact on orbit/spectrum conservation SPACECRAFT CONTROL [NASA-TM-84658] . p 25 N84-15426 [AIAA PAPER 84-0653] P 74 A84-25254 Spacecraft thermal control, design, and operation Study on large, ultralight long-Ufa structures in space, User manual of the CATSS system (version 1.0) p22 A84-10224 phase 2C communication analysis tool for space station Simulation of the motion of a Shuttle-attached flexible [TM-EKR3] p 17 N84-17284 [NASA-CR-171728] P 51 N84-17431 manipulator arm p 57 A84-11935 Space station needs, attributes and architectural options Space Station Technology. 1S83 Simulation of the Galileo spacecraft axial - Delta-V study. Volume 1: Executive study [NASA-CP-2293] P11 N84-18277 algorithm p66 A84-11938 [NASA-CR-173334] p9 N84-18265

A-21 SPACECRAFT DOCKING SUBJECTINDEX

Space Station needs, attributes, and architectural Spacecraft thermal balance testing using infrared lamps Resistojet propulsion for large spacecraft systems options study on a dummy spacecraft p26 N84-19399 [NASA-TM-83489] p 63 N84-11206 [NASA-CR-173327) p11 N84-18274 Development of procedures for component mode Study of auxiliary propulsion requirements for large Space Station needs, attributes and architectural synthesis space systems. Volume 1: Executive summary options, volume 2, book 3: Cost and programmatics [DFVLR-IB-232-82-C-09] p 30 N84-21626 [NASA-CR-168193-VOL-1] p 63 N84-12226 [NASA-CR-173320] p 14 N84-18304 SPACECRAFT MODULES Auxiliary propulsion p11 N84-18283 Environmental and thermal control systems for space A standardized propulsion module for future SPACECRAFT RADIATORS vehicles — conferences communications satellites in the 2000 to 3000 kg class Spacecraft thermal control, design, and operation [ESA-SP-200] p26 N84-19396 [AIAA PAPER 84-0727] p 62 A84-25292 p22 A84-10224 Recent and planned developments at the Goddard Operational modules for space station construction Weight characteristics of future spacecraft thermal Space Flight Center in thermal control technology [NASA-TM-85772] p 21 N84-21608 management systems p26 N84-19402 SPACECRAFT MOTION [AIAA PAPER 84-0054] p 23 A84-17850 Study on synthesis and characterization of large space Some aspects of simulation studies in spacecraft Multi-megawatt space power thermal management systems, phase 2. Part 1: Assessment of design dynamics p 15 A84-11930 system requirements verification analytical methods. Volume 1: Mechanical On modeling and simulation of the dynamics of tether [AIAA PAPER 84-0056] p 23 A84-21284 design connected satellite systems p 30 A84-11933 Thermal management system technology development [ESA-CR(P)-1779-VOL-1] p 18 N84-21624 Attitude control and dynamics of the space operations for space station applications Study on synthesis and characterization of large space center p31 A84-11934 [SAE PAPER 831097] p 24 A84-29032 systems, phase 2. Part 1: Assessment of design Simulation of the motion of a Shuttle-attached flexible A contact conductance interface for a space verification analytical methods. Volume 2: Thermal manipulator arm p 57 A84-11935 constructable heat pipe radiator design Satellite attitude dynamics and control in the presence [SAE PAPER 831101 ] p 24 A84-29036 . [ESA-CR(P)-1779-VOL-2] p 18 N84-21625 of environmental torques - A brief survey Thermal energy management process experiment Development of procedures for component mode p 31 A84-12483 p25 N84-17222 synthesis Comments on 'Dynamics of a spacecraft during Heat pipes for the L-SAT communications module [DFVLR-IB-232-82-C-09] p 30 N84-21626 extension of flexible appendages' p32 A84-17370 radiators p 26 N84-19405 SPACECRAFT DOCKING On the dynamics of a subsatellite system supported by A Variable Conductance Heat Pipe (VCHP) radiator Communications, tracking, and docking on the Space two tethers system for communications payloads p 27 N84-19406 Station p45 A84-1S640 [AIAA PAPER 84-0062] p 32 A84-17854 Flexible radiator system Shuttle interaction study Stability of large flexible damped spacecraft modeled [NASA-CR-171765] p 28 N84-20623 [NASA-CR-173400] p 80 N84-21592 as elastic continue p 35 A84-26845 SPACECRAFT SHIELDING Shuttle interaction study extension Motion of a symmetric satellite about the center of mass Reactions of high velocity atomic oxygen with carbon [NASA-CR-173398] p 81 N84-21594 in circular orbit in the presence of flexible viscoelastic [AIAA PAPER 84-0549] p 53 A84-18159 SPACECRAFT DOCKING MODULES rods p 35 A84-26977 A Maltese cross shaped mobile thermal control shutter Shuttle interaction study SPACECRAFT PERFORMANCE — for satellites p27 N84-19454 [NASA-CR-173400] p 80 N84-21S92 Evolution of European telecommunication satellite SPACECRAFT STABILITY SPACECRAFT ENVIRONMENTS pointing performance On modeling and simulation of the dynamics of tether Thermal control of tubular composite structures in space [AIAA PAPER 84-0725] p 34 A84-25291 connected satellite systems p 30 A84-11933 environment p22 A84-10440 SPACECRAFT POWER SUPPLIES A design strategy for multiple payload pointing from a Satellite attitude dynamics and control in the presence High capacity power systems for space three axis stabilized spacecraft of environmental torques - A brief survey [IAF PAPER 83-421 ] p 44 A84-11816 [AIAA PAPER 84-0566] p 33 A84-18168 p31 A84-12483 Photovoltaic solar arrays leading to a candidate space The beam-like behavior of space trusses Plasma sheath structure surrounding a large powered power system in the regime beyond 100 kW p 19 A84-21517 spacecraft [IAF PAPER 83-422] p 44 A84-11817 Stability of large flexible damped spacecraft modeled [AIAA PAPER 84-0329] p 46 A84-18025 Application of beam power technology to a space as elastic continua p 35 A84-26845 Low earth orbit atomic oxygen effects on surfaces — station p45 A84-15642 On transient dynamics and stability of large space of Space Shuttle Orbiters Plasma sheath structure surrounding a large powered structures p36 A84-29143 [AIAA PAPER 84-0548] p 53 A84-19912 spacecraft Digital control system for space structural dampers Environmental Control and Life Support for an [AIAA PAPER 84-0329] p 46 A84-18025 [NASA-CR-175355] p 39 N84-16246 evolutionary Space Station A programmable power processor for high power space SPACECRAFT STRUCTURES [SAE PAPER 831108] p 5 A84-29043 applications p46 A84-18394 Thermal control of tubular composite structures in space Phase change water recovery techniques - Vapor Multi-megawatt space power thermal management environment p 22 A84-10440 compression distillation and thermoelectric/membrane system requirements Thermo-mechanical behaviour of CFRP tubes for space concepts — from waste water as part of Space Station [AIAA PAPER 84-0056] p 23 A84-21284 structures life support system New directions in solar array development [IAF PAPER 83-417] p 22 A84-11814 [SAE PAPER 831122] p6 A84-29056 p47 A84-22958 Field repair of graphite epoxy skin panels on the The residual gravitational field of orbital space stations Technology components of solar arrays for space spaceship Columbia p52 A84-17120 [DGLR PAPER 83-089] p 75 A84-29656 platforms p 47 A84-22959 Comments on 'Dynamics of a spacecraft during Microtjravity conditions on orbital platforms Technical aspects of the Intelsat V solar array extension of flexible appendages' p32 A84-17370 [DGLR PAPER 83-90] p 76 A84-29657 p 47 A84-22962 The beam-like behavior of space trusses Large space instrumentation to measure the interaction New component development for multM 00 kW low-cost p19 A84-21517 between space structures and the environment solar array applications p 47 A84-22963 Design and development of the INTELSAT V [AD-A129990] p 77 N84-10179 Large area, low cost space solar cells graphtte-epoxy central thrust tube p 19 A84-22153- SPACECRAFT INSTRUMENTS p 47 A84-22979 Local stability of sandwich structures with thin fibre Science platform and attitude subsystem in-flight Large area space solar cell assemblies calibration for the Galileo spacecraft p 32 A84-17355 reinforced face skins for space application p 61 A84-22980 [MBB-UD-381-83-OE] p 19 A84-22859 Coordinate transformation assembly — for space Mechanical wraparound contacted cell for low cost Higher temperature composite joints survive elimination platform angular coordinate linking p 75 A84-28579 space arrays p 48 A84-22982 tests . p 55 A84-29565 Large space instrumentation to measure the interaction Prediction of solar cell performance in space between space structures and the environment p 48 A84-22997 ACOSS Fourteen (Active Control of Space Structures) [AD-A129990] p 77 N84-10179 Space station energy sizing p 48 N84-12233 [AD-A133411] p38 N84-15181 SPACECRAFT LAUNCHING Study of multi-kilowatt solar arrays for Earth orbit Integrity control of carbon fiber reinforced plastics GEO space platform economics - Impact of concept, applications structural elements, phase 1 report — space size, launch mode and lifetime [NASA-CR-170939] p 49 N84-12634 applications [AIAA PAPER 84-0704] p 74 A84-25281 Orbiting wire as a dynamo: Auxiliary power possibilities [TB-TS-11-01/82-A] p 56 N84-18416 Study of auxiliary propulsion requirements for large for space platforms Development of a spacecraft infrared test technique as space systems. Volume 1: Executive summary [IFSI-83-3] p49 N84-12653 an alternative to solar simulation: First steps on L-SAT [NASA-CR-168193-VOL-1] p 63 N84-12226 Integrated Power/Attitude Control System (IPACS) thermal model P 26 N84-19398 SPACECRAFT MANEUVERS technology experiment p39 N84-17229 IRSIM: A program for the calculation of infrared flux Simulation of the Galileo spacecraft axial - Delta-V Power p 12 N84-18288 intensity incident on a spacecraft inside a test chamber algorithm p66 A84-11938 SPACECRAFT PROPULSION p26 N84-19400 Semiautonomous stationkeeping of geosynchronous A parametric study of space transfer-propulsion Computer aided synthesis of a satellite antenna structure satellites p32 A84-17359 with probabilistic constraints p 21 N84-19899 Closed-form solutions for feedback control with terminal [IAF PAPER 83-401] p 61 A84-13397 constraints p 36 A84-29471 Dynamic behaviour of a satellite antenna structure in Transportation - Options and high payoff choices — for random vibration environment p42 N84-19900 SPACECRAFT MODELS spacecraft propulsion p61 A84-21484 Evaluation of modal testing techniques for spacecraft On modeling and simulation of the dynamics of tether An electric propulsion transportation system from structures p 28 N84-19906 connected satellite systems p30 A84-11933 low-earth orbit to geostationary orbit utilizing beamed Simulation of the motion of a Shuttle-attached flexible microwave power p 61 A84-21485 Study on synthesis and characterization of large space manipulator arm p57 A84-11935 A standardized propulsion module for future systems, phase 2. Part 2: Proposals for additions, A large space structure benchmark problem - ACOSS communications satellites in the 2000 to 3000 kg class modifications and new analytical methods, volume 1 Model No. 2 p 33 A84-19127 [AIAA PAPER 84-0727] p 62 A84-25292 [ESA-CR(P)-1779-VOL-3] p 43 N84-21611 Number crunching on the ACOSS Model No. 2 Utilization of electric propulsion for communication Mathematical synthesization of complex structures p33 A84-19128 p 19 N84-22224 Development of a spacecraft infrared test technique as [AIAA PAPER 84-0729] p 62 A84-25293 SPACECRAFT TRACKING an alternative to solar simulation: First steps on L-SAT Why don't we use ion propulsion? Communications, tracking, and docking on the Space thermal model p 26 N84-19398 [AIAA PAPER 84-0730) p 62 A84-2S294 Station p45 A64-15640

A-22 SUBJECT INDEX SYNCHRONOUS SATELLITES

SPACECRAFT TRAJECTORIES STATIC TESTS Study on damping representation related to spacecraft Discontinuous low thrust orbit transfer Assessment of the existing ground test technology and structural design [AD-A136908] p 63 NB4-19474 confronting with the Large Space Structures (LSS) [EMSB-18/83] P38 N84-15182 SPACECREWS requirements. Experimental techniques in structural Surface accuracy measurement sensor test on a Determination of applicable law to living and working analysis p29 N84-21621 50-meter antenna surface model in outer space STATIONARY ORBITS [NASA-TM-85689] P 17 N84-16427 [IAF PAPER 82-IISL-44] p 68 A84-17057 Introduction to geostationary orbits Study on large, ultralight long-life structures in space, Spacelab data book [ESA-SP-1053] p80 N84-21590 phase 2C [ESA-BR-14] p79 N84-18315 STATIONKEEPING [TM-EKR3] p 17 N84-17284 SPACELAB Semiautonomous stationkeeping of geosynchronous Spacelab data book satellites p32 A84-17359 Experiment data communications (48 Mbit/s) between [ESA-BR-14] p79 N84-18315 Utilization of electric propulsion for communication Spacelab, the Space Shuttle and the ground Study on synthesis and characterization of large space p44 A84-10396 satellites systems, phase 2. Part 2: Proposals for additions, [AIAA PAPER 84-0729] p 62 A84-25293 modifications and new analytical methods, volume 1 Launch processing for Spacelab 1 STIFFNESS [ESA-CR(P)-1779-VOL-3] p 43 N84-21611 [AIAA PAPER 83-2622] p 64 A64-10965 Stability, vibration and passive damping of partially Mathematical synthesization of complex structures The Spacelab test program restrained imperfect columns p19 N84-22224 [AIAA PAPER 83-2685] p 66 A84-13376 [NASA-TM-85697] p 37 N84-13608 STRUCTURAL ENGINEERING Spacelab's development p 66 A84-13901 STIFFNESS MATRIX The Toysat structural control experiment — for large The Spacelab program - The management of the Identification of large flexible structures mass/stiffness flexible space structure p 31 A84-13320 program, problems encountered and the solutions and damping from on-orbit experiments STRUCTURAL STABILITY adopted - p3 A84-1S325 p34 A84-24995 Instability analysis of space trusses The German Spacelab mission O1 p69 A84-17762 New elements for analysis of space frames with tapered p32 A84-16885 Operational planning, simulation, and performance of members p 20 N84-14561 Dynamics and control of a large space antenna the German Spacelab mission D1 p69 A84-17763 Geometrically nonlinear analysis of beam-in-space P32 A84-17361 structures The thermal design of the European complement of Aeroelastic stability and response of flexible tactical [MITT-28] p22 N84-21914 FSLP — First SpaceLab Mission weapons [SAE PAPER 831144] p24 A84-29071 STOCHASTIC PROCESSES [AIAA PAPER 84-0392) p 32 AB4-18060 Active control of large flexible space structures Local stability of sandwich structures with thin fibre Software quality assurance Spacelab experience and p37 N84-14235 reinforced face skins for space application future trends p 17 N84-14759 STORAGE BATTERIES [MBB-UD-381-83-OE] p 19 A84-22859 Modern software development tools in space projects Assessment of potential for batteries in space Stability, vibration and passive damping of partially on the example of a Spacelab experiment applications p 48 N84-12246 restrained imperfect columns p49 N84-14761 STRESS ANALYSIS [NASA-TM-85697] p 37 N84-13608 Payload missions integration Instability analysis of space trusses STRUCTURAL VIBRATION [NASA-CR-170949] p7 N84-15171 p 32 A84-16885 Buckling and vibration of any prismatic assembly of shear Space telescope A comparison of linear and geometrically nonlinear finite and compression loaded anisotropic plates with an [NASA-CR-170948] p 78 N84-16097 element analyses applied to large space structures arbitrary supporting structure p 23 AB4-14050 STS-9: Orbital workshop spacelab to fly on ninth Shuttle [AIAA PAPER 84-0069] p 16 A84-19887 Control of large space structures mission STRUCTURAL ANALYSIS [AIAA PAPER 84-0081] p 32 A84-17866 [NASA-TM-85497] p 78 N84-16242 Parameter identification in continuum models Identification of large flexible structures mass/stiffness STEP mechanical systems p8 N84-17213 p 16 A84-25525 and damping from on-orbit experiments Spacelab data book Development of deployable structures for large space p 34 A84-24995 [ESA-BR-14] p79 N84-18315 platforms. Volume 2: Design development Stability of large flexible damped spacecraft modeled [NASA-CR-170914] p20 N84-10176 as elastic continua p 35 A84-26845 Spacelab Data Processing Facility Control of flexible spacecraft by optimal model Experimental study of active vibration control [NASA-TM-85556] p 51 N84-19382 following p 36 N84-12222 [AD-A133818] p 38 N84-14546 Operational modules for space station construction New elements for analysis of space frames with tapered Component mode synthesis and large deflection [NASA-TM-85772] p 21 N84-21608 members p 20 N84-14561 vibrations of complex structures — beams and trusses SPACELAB PAYLOADS ACOSS Fourteen (Active Control of Space Structures) [NASA-CR-173338] p 21 N84-18680 Spacelab data book [AD-A133411] p38 N84-15181 Evaluation of modal testing techniques for spacecraft [ESA-BR-14] p79 N84-18315 Thermal analysis research applicable to space station structures p 28 N84-19906 An Attached Payload Operations Center (APOC) at the technology needs Analysis of large space structures p 18 N84-20621 Goddard Space Right Center (GSFC), volume 1 [NASA-TM-84658] p 25 N84-15426 STRUCTURAL WEIGHT [NASA-CR-175160] p 79 N84-20605 Self-shadowing of orbiting trusses A heuristic method for the design of minimum weight SPACETENNAS [NASA-CR-173215] p 25 N84-16565 trusses using discrete member sizes p 15 A84-16841 Use of electromagnetic models in the optimal control Low concentration ratio solar array structural Optimization of shallow trusses against limit point of large space antennas p 35 A84-25552 configuration p 17 N84-17225 instability p20 A84-23366 SPIN DYNAMICS Structures and mechanisms p 21 N84-18286 SUBMILUMETER WAVES Satellite attitude dynamics and control in the presence Integrity control of carbon fiber reinforced plastics Large Deployable Reflector (LDR) - A concept for an of environmental torques - A brief survey structural elements, phase 1 report — space orbiting submillimeter-infrared telescope for the 1990s p 31 A84-12483 applications p 66 A84-14586 SPIN REDUCTION [TB-TS-11-01/82-A] p 56 N84-18416 SURFACE DEFECTS Maintenance and operational enhancement of the Component mode synthesis and large deflection Fracture mechanics of ceramics. Volume 5 - Surface flexible spacecraft dynamics program vibrations of complex structures — beams and trusses flaws, statistics, and microcracking p 54 A84-24501 [NASA-CR-175211] p 41 N84-19394 [NASA-CR-173338] p 21 N84-18680 SURFACE PROPERTIES SPIN-ORBIT INTERACTIONS The effect of mass and stiff ness changes on the damping Surface analysis of graphite fiber reinforced polyimide Thermally induced spin rate ripple on spacecraft with factor in a large space structure as represented by the composites long radial appendages CSDL 2 model [NASA-TM-85700] p 55 N84-11220 [NASA-TM-85058] p 39 N84-16249 [AD-A136984] p 42 N84-19465 SURFACES SPUNE FUNCTIONS Computer aided synthesis of a satellite antenna structure Computer-Aided Geometry Modeling Parameter identification in continuum models with probabilistic constraints p 21 N84-19899 [NASA-CP-2272] p 18 N84-22179 p16 A84-25525 Static and dynamic structural-sensitivity derivative SYMMETRY Spline-based estimation techniques for parameters in calculations in the finite-element-based Engineering The solution of the dynamic problem of the periodic elliptic distributed systems Analysis Language (EAL) system structures by cydosymmetric technique — large space [NASA-TM-85439] p9 N84-17947 [NASA-TM-85743] p 42 N84-20880 structures p43 N84-21612 SPOT (FRENCH SATELLITE) Mathematical synthesization of complex structures SYNCHRONOUS PLATFORMS Evaluation of bus impedance on the SPOT multimission P19 N84-22224 NASA's geostationary communications platform platform p 44 A84-13521 STRUCTURAL DESIGN program Software production in a large space project The SPOT Approximations method for space frame synthesis [AIAA PAPER 844702] p5 A84-25326 mission center p 78 N84-14752 p 19 A84-10141 Development trends in Europe on satellite clusters and STABILIZATION A heuristic method for the design of minimum weight geostationary platforms Investigation of electrodynamic stabilization and control trusses using discrete member sizes p 15 A84-16841 [AIAA PAPER 844703) p 75 A84-25327 of long orbiting tethers Radiation-conduction interaction in large space SYNCHRONOUS SATELLITES [NASA-CR-17097J] p 40 N84-172S1 structures Analytical model of the evolution of orbit parameters STAR TRACKERS [AIAA PAPER 84-0144] p 23 A84-17911 of a quasi geostationary satellite Canadian Attitude Sensing Experimental Package A large space structure benchmark problem - ACOSS (IAF PAPER 83-316] p 65 A84-11787 (CASEP) p79 N84-17223 Model No. 2 p33 A84-19127 Energy from space - Legal implications of the use of STARLAB MatrixpQ - Application to large space structure control the geostationary orbit p6B A84-17075 Starlab Ground System guidelines document design problems p 16 A84-19129 Semiautonomous stationkeeping of geosynchronous [NASA-CR-175192] p 14 N84-20435 Potential of minicomputer-array processor system for satellites p 32 A84-173S9 STATIC LOADS nonlinear finite-element analysis p 46 A84-20583 Digital technologies and systems for geostationary orbit Static and dynamic structural-sensitivity derivative Optimization of shallow trusses against limit point satellites calculations in the finite-element-based Engineering instability p20 AB4-23366 [AIAA PAPER 84-0749] p 74 A84-25304 Analysis Language (EAL) system Some applications of direct adaptive control to large Computer tools for optimizing orbit use [NASA-TM-85743] p 42 N84-20880 structural systems p 34 A84-25496 [AIAA PAPER 844651] p 74 A84-25318

A-23 SYNOPTIC METEOROLOGY SUBJECTINDEX

Spacecraft thermal control selection for seven years of SYSTEMS INTEGRATION Lessons learned during the first year of the TDRSS lifetime in synchronous orbit Integrated Flywheel Technology, 1983 [AIAA PAPER 84-0687] p 74 A84-25319 [MBB-UR-584-82-OE] p 25 N84-11200 [NASA-CP-2290] p 78 N84-12228 Systems/operations technology p11 N84-18278 SYNOPTIC METEOROLOGY The Boeing flywheel study p 37 N84-12235 Auxiliary propulsion p 11 N84-18283 The role of space station in earth sciences STEP experiment integration p8 N84-17215 Fluid management p11 N84-18284 p 72 A84-24631 TECHNOLOGY TRANSFER SYSTEMS SIMULATION SYNTAX Identification of new potential scientific and technology Simulation of the motion of a Shuttle-attached flexible Interactive geometry modeling of space station manipulator arm p 57 A84-11935 areas for DoD application. Summary of activities conceptual designs p 18 N84-22191 [AD-A134372] p 78 N84-17050 A flexible structure controller design method using mode SYNTHETIC APERTURE RADAR Structures and mechanisms p 21 NB4-18286 residualization and output feedback — for Large Flexible Flight test of a synthetic aperture radar antenna using TECHNOLOGY UTILIZATION Space System p 32 A84-17369 STEP p9 N84-17237 Evolution of the solar power satellite concept - The SYSTEMS Selection of noisy sensors and actuators for regulation utilization of energy from space p 70 A84-21478 Space station needs, attributes and architectural of linear systems — large space structures Space station: Policy, planning and utilization; options. Volume 1, attachment 2: Supporting data and [AD-A135442] p 51 N84-17931 Proceedings of the Symposium, Arlington, VA, July 18-20, analysis reports SYSTEMS STABILITY 1983 p72 A84-24626 [NASA-CR-173336] p 13 N84-18294 Controllability and observability criteria for multhrariable Space station architectural issues as viewed by the user Space Station needs, attributes and architectural linear second-order models p 35 A84-25516 community - Applications p 4 A84-24634 options. Volume 2, book 2, part 2, Task 2: Information Stability enhancement of a flexible robot manipulator Development and application of new technologies in the management system [AD-A134185] p 59 N84-16807 ESA Olympus Programme [NASA-Cfl-173317] ' p 13 NB4-18301 [AIAA PAPER 84-0706] p 4 A84-25282 SYSTEMS ANALYSIS With the Space Shuttle towards space industrialization A system study of the solar power satellite concept p 75 A84-28975 p 70 A84-21480 Understanding space settlements as human systems A degree of controllability definition - Fundamental TAPERING [AAS PAPER 83-204] p 76 A84-29856 concepts and application to modal systems New elements for analysis of space frames with tapered The complementary roles of existing and advanced p 34 A84-24991 members p 20 N84-14561 environmental, thermal control and life support technology STEP mechanical systems p8 N84-17213 TOR SATELLITES for space stations p79 N84-19429 Space station needs, attributes and architectural options Space operations center communications path TELECOMMUNICATION study. Volume 4: Architectural options, subsystems, obscuration p 3 A84-15695 NTC '82; National Telesystems Conference, Galveston, technology and programmatics Lessons learned during the first year of the TDRSS TX, November 7-10, 1982, Conference Record [NASA-CR-173331] p 10 N84-18268 [AIAA PAPER 84-0687] p 74 A84-25319 p44 A84-15623 Space station needs, attributes and architectural An evaluation of Techroll seal flexible joint material Tele-X - The first step in a satellite communications options. Part 1: Summary p56 N84-16037 system for the Nordic countries [NASA-CR-175382] p 10 N84-18270 TECHNOLOGICAL FORECASTING [AIAA PAPER 84-0713] p4 A84-25287 Space station needs, attributes and architectural options Overview of NASA space station activities Telecommunication systems for large-scale space study. Briefing material: Final review and executive [IAF PAPER 83-48] p1 A84-11726 manufacturing activity summary Commercial communications satellite market and [AAS PAPER 83-216] p 48 A84-29861 [NASA-Cfl-173321] p 10 N84-18273 technology in the 90's Space Station needs, attributes and architectural Space Station needs, attributes and architectural [IAF PAPER 83-86] p 65 A84-11739 options. Volume 2, book 1, part 3: Manned Space Station options. Volume 2, book 1, part 1: Mission High capacity power systems for space relevance to commercial telecommunications satellites requirements [IAF PAPER 83-421) p 44 A84-11816 [NASA-CR-173314] p 13 N84-18298 [NASA-CR-173312] p 13 N84-18296 Spaceflight to 2000 - Interavia looks forward from the TELEMETRY Space Station needs, attributes and architectural present p 66 A84-14764 Space Station needs, attributes and architectural options. Volume 2, book 2, part 3: Communication An advanced generation land mobile satellite system options. Volume 2, book 2, part 2. Task 2: Information system and its critical technologies p3 A84-15634 management system [NASA-CR-173318] p 14 N84-18302 Project space station - Plans for a permanent manned [NASA-CR-173317] p 13 N84-18301 SYSTEMS ENGINEERING space center — Book p 69 A84-21344 TELEOPERATORS Data system architecture considerations for a space Mankind's interstellar future p 71 A84-21499 A system for intelligent teleoperation research station Space 1991 p 71 A84-21720 [AIAA PAPER 83-2376] p 57 A84-10070 [AIAA PAPER 83-2346] p 63 A84-10066 National security implications of a U.S. space station Remote manipulators in space p 57 A84-22336 Photovoltaic solar arrays leading to a candidate space p73 A84-24635 NASA research in teleoperation and robotics power system in the regime beyond 100 kW Space station communications p 73 A84-24636 p58 A84-28523 [IAF PAPER 83-422] p 44 A84-11817 A standardized propulsion module for future Space applications of Automation, Robotics And Architectural options and development issues communications satellites in the 2000 to 3000.kg class Machine Intelligence Systems (ARAMIS). Volume 3, phase p 4 A84-24633 [AIAA PAPER 84-0727] p 62 A84-25292 2: Executive summary Study of artificial intelligence techniques - Realization Development trends in Europe on satellite clusters and [NASA-CR-3736] p 59 N84-10582 of a highly autonomous experimental robot system — geostationary platforms Analysis of large space structures assembly: % French thesis p 58 A84-25828 [AIAA PAPER 84-0703] p 75 A84-25327 Man/machine assembly analysis Thermal management system technology development Evolutionary concepts for a space station and the [NASA-CR-3751] p 59 N84-13208 for space station applications relevant utilisation potential p 5 A84-26926 Human capabilities p11 N84-18282 [SAE PAPER 831097] p 24 A84-29032 Space Station needs, attributes and architectural TELESCOPES Systems engineering aspects of a preliminary options. Volume 2, book 1, part 3: Manned Space Station Surface accuracy measurement sensor test on a conceptual design of the space station environmental relevance to commercial telecommunications satellites 50-meter antenna surface model control and life support system [NASA-CR-173314] p 13 N84-18298 [NASA-TM-85689] p 17 N84-16427 [SAE PAPER 831109] p5 A84-29044 TECHNOLOGY ASSESSMENT TELEVISION SYSTEMS Hyperfiltration wash water recovery subsystem - Design Space station data management - A system evolving The Franco-German DBS program TV-SAT/TDF-1' and test results — for extended mission spacecraft such from changing requirements and a dynamic technology [AIAA PAPER 84-0661] p4 A84-25260 as space stations base TEMPERATURE CONTROL [SAE PAPER 831112] p 6 A84-29047 [AIAA PAPER 83-2338] p 43 A84-10016 Spacecraft thermal control, design, and operation Research and technology, 1983 NASA priority technologies p22 A84-10224 [NASA-TM-85702] p7 N84-12026 [IAF PAPER 83-345] p1 A84-11793 Thermal control of tubular composite structures in space Space station needs, attributes and architectural Global implications of space activities: An AIAA/ASPEN environment p 22 A84-10440 options. Summary of major study activities and results. Institute Assessment — Book p 67 A84-15189 Weight characteristics of future spacecraft thermal Space station program observations Developing the space frontier; Proceedings of the management systems INASA-CR-173345] p11 N84-18275 Twenty-ninth Annual Conference, Houston, TX, October [AIAA PAPER 84-0054] p 23 A84-17850 Crew and life support ECLSS p11 N84-18280 25-27, 1982 p 67 A84-15381 Multi-megawatt space power thermal management Structures and mechanisms p21 N84-18286 Energy from space; Proceedings of the Symposium on system requirements Solar Energy from Space, Vienna, Austria, August 9-21, Space station needs, attributes and architectural [AIAA PAPER 84-0056] p 23 A84-21284 1982 p69 A84-21476 options. Volume 4, attachment 1: Task 2 and 3 mission Thermal management system technology development implementation and cost A system study of the solar power satellite concept for space station applications p70 A84-21480 [NASA-CR-173330] p 12 N84-18290 [SAE PAPER 831097] p 24 A84-29032 Market potential and possible limitations for satellite Space station needs, attributes and architectural Thermal control of the Tethered Satellite Module solar power stations p 70 A84-21481 options. Volume 2, attachment 2: Supporting data and [SAE PAPER 831138] p 24 A84-29067 European questions related to satelite power systems analysis reports The thermal design of the European complement of p70 A84-21483 [NASA-CR-173329] p 12 N84-18291 FSLP - First SpaceUb Mission New directions in solar array development [SAE PAPER 831144] p 24 A84-29071 Space station needs, attributes and architectural p47 A84-22958 options. Volume 1: Executive summary NASA Time phased introduction of advanced technologies - Regenerable non-venting thermal control subsystem for [NASA-CR-172792] p 12 N84-18292 Its impact on orbit/spectrum conservation extravehicular activity Space Station needs, attributes and architectural [AIAA PAPER 84-0653] p 74 A84-25254 [SAE PAPER 831151] p 24 A84-29076 options. Volume 2, book 2, parti: Mission implementation Why don't we use ion propulsion? Thermal energy management process experiment concepts [AIAA PAPER 84-0730] p 62 A84-25294 p25 N84-17222 [NASA-CR-173316] p 13 N84-18300 Digital technologies and systems for geostationary orbit Environmental and thermal control systems for space Flexible radiator system satellites vehicles — conferences [NASA-CR-171765] p 28 N84-20623 [AIAA PAPER 84-0749] p 74 A84-25304 [ESA-SP-200] p26 N84-19396

A-24 SUBJECT INDEX USER REQUIREMENTS

Spacecraft thermal balance testing using infrared lamps Assessment of the existing ground test technology and TRANSIENT HEATING on a dummy spacecraft p26 N84-19399 confronting with the Urge Space Structures (LSS) Weight characteristics of future spacecraft thermal Recent and planned developments at the Goddard requirements. Thermal test techniques management systems Space Flight Center in thermal control technology p29 NS4-21622 [AIAA PAPER 84-0054] p 23 AS4-17850 p26 N84-19402 THERMAL EXPANSION TRANSIENT LOADS The thermal design of L-SAT large telecommunication Thermo-mechanical behaviour of CFRP tubes for space A methodology to include static and kinetic friction satellite p27 N84-19414 structures effects in Space Shuttle payload transient loads analysis The complementary roles of existing and advanced [IAF PAPER 83-417] p 22 A84-11814 [AIAA PAPER 83-2654] p 30 A84-10956 environmental, thermal control and life support technology THERMAL RADIATION TRANSIENT RESPONSE for space stations p79 N84-19429 Computational savings in view factor evaluation on mode Transient dynamics during the orbiter based deployment Design and manufacturing of a heat rejection system prescreening — large space structures of flexible members for advanced thermal control — spacecraft and or payload p29 N84-21618 [AIAA PAPER 84-0061] p 34 A84-21285 cooling P27 N84-19434 THERMAL SIMULATION On transient dynamics and stability of large space Thermal control of tethered satellite in a very low altitude Spacecraft thermal design using interactive graphics structures p36 A84-29143 [AIAA PAPER 84-0143] p 23 A84-17910 aerodynamic mission p 27 N84-19444 TRANSITION TEMPERATURE A Maltese cross shaped mobile thermal control shutter THERMAL STRESSES Radiation-conduction interaction in large space The effect of pressure and temperature on ~ for satellites P 27 NS4-19454 time-dependent changes in graphite/epoxy composites structures Study on synthesis and characterization of large space below the glass transition p 54 A84-21775 systems, phase 2. Part 2: Proposals for additions, [AIAA PAPER 84-0144] p 23 A84-17911 TRANSMISSION EFFICIENCY modifications and new analytical methods, volume 2 THERMAL VACUUM TESTS User manual of the CATSS system (version 1.0) [ESA-CR(P)-1779-VOL-4] P 29 N84-21616 Thermal conductance and torque of thin section communication analysis tool for space station Interactive structural-thermal-control analytical four-point contact ball bearings in vacuum [NASA-CR-171728] p 51 N84-17431 formulations — large space structures [ESA-ESTL-54] p 25 N84-15562 P29 N84-21619 Spacecraft thermal balance testing using infrared lamps TRANSMITTER RECEIVERS TEMPERATURE EFFECTS on a dummy spacecraft p26 N84-19399 An advanced generation land mobile satellite system Effect of temperature, moisture and radiation exposures Thermal cycling tests in space environment simulation and its critical technologies p3 A84-15634 on composite mechanical properties p 55 A84-28900 chambers p26 N84-19401 The small transmitter receiver stations in the Sirio Study on synthesis and characterization of large space The Large Space Simulator (LSS) at ESA/ESTEC (a experiment — microwave transmission systems, phase 2. Part 2: Proposals for additions, summary of the main characteristics) p 27 N84-19458 [FUB-50-1982] p49 N84-15386 modifications and now analytical methods, volume 2 Assessment of the existing ground test technology and TRIBOLOGY [ESA-CR(P)-1779-VOL-4] p 29 N84-21616 confronting with the Large Space Structures (LSS) Thermal conductance and torque of thin section Thermal design verification of the large open truss requirements. Thermal test techniques four-point contact ball bearings in vacuum Structures. The local approach and the shadow problem p29 N84-21622 [ESA-ESTL-54] p 25 N84-15562 — large space structures p 29 N84-21617 THERMODYNAMIC PROPERTIES TRUSSES TERMINAL GUIDANCE Thermal-mechanical behavior of graphite/magnesium A heuristic method for the design of minimum weight Closed-form solutions for feedback control with terminal composites p 24 A84-28237 trusses using discrete member sizes p 15 A84-16841 constraints p 36 A84-29471 Thermally induced spin rate ripple on spacecraft with Instability analysis of space trusses TERRESTRIAL RADIATION long radial appendages p32 A84-16885 Computing the radiation pressure forces by adapting [NASA-TM-85058] p 39 N84-16249 The beam-like behavior of space trusses thermal design verification softwares — large space THIN PLATES p 19 A84-21517 Radiation-conduction interaction in large space structures p 28 N84-21613 Optimization of shallow trusses against limit point TEST FACILITIES structures instability p 20 A84-23366 [AIAA PAPER 84-0144] p 23 A84-17911 A cylindrical near-field test facility for large satellite Synchronously deployable truss structure antennas THREE AXIS STABILIZATION [NASA-CASE-LAR-13117-1] p 59 N84-16250 [MBB-UR-628-83-OE] p 72 A84-22862 A design strategy for multiple payload pointing from a Self-shadowing of orbiting trusses three axis stabilized spacecraft IPACS guidance navigation and control system [NASA-CR-173215] p 25 N84-16565 considerations and test activities p 37 N84-12245 [AIAA PAPER 84-0566] p 33 A84-18168 Development of Test Article Building Block (TABB) for TIME OPTIMAL CONTROL The Large Space Simulator (LSS) at ESA/ESTEC (a deployable platform systems p21 N84-17226 Highly efficient, very low-thrust transfer to summary of the main characteristics) p 27 N84-19458 Component mode synthesis and large deflection TETHERED SATELLITES geosynchronous orbit - Exact and approximate solutions vibrations of complex structures — beams and trusses On modeling and simulation of the dynamics of tether p 61 A84-24980 [NASA-CR.173338] p 21 N84-18680 connected satellite systems p30 A84-11933 TIROS SATELLITES TUBE HEAT EXCHANGERS On the dynamics of a sutasatellite system supported by The Tiros-based asteroid mission p 2 A84-14762 A contact conductance interface for a space two tethers TORQUE constructable heat pipe radiator Satellite attitude dynamics and control in the presence [AIAA PAPER 84-0062] p 32 A84-17854 [SAE PAPER 831101] p 24 A84-29036 Thermal control of the Tethered Satellite Module of environmental torques - A brief survey Flexible radiator system [SAE PAPER 831138] p 24 A84-29067 p 31 A84-12483 [NASA-CR-171765] p 28 N84-20623 Investigation of electrodynamic stabilization and control Torque from solar radiation pressure gradient during TWO PHASE FLOW of long orbiting tethers eclipse — for very large spacecraft p31 A84-12489 Thermal control p 25 N84-18289 [NASA-CR-170972] p 40 N84-17251 Thermal conductance and torque of thin section Thermal control of tethered satellite in a very low altitude four-point contact ball bearings in vacuum aerodynamic mission p 27 N84-19444 [ESA-ESTL-54] p 25 N84-15562 u Tethers in space: Birth and growth of a new avenue TRACKING NETWORKS to space utilization Space station communications and tracking equipment U.S.S.R. SPACE PROGRAM [NASA-TM-82571 ] p 18 N84-21607 management/control system p45 A84-15639 For the first time — Russian book on construction of THERMAL ANALYSIS Study of a tracking and data acquisition system for the first Soviet earth satellites p 16 A84-21564 Thermal control of the Tethered Satellite Module 1990's. Volume 3: TDAS Communication Mission ULTRAHIGH FREQUENCIES [SAE PAPER 831138] p 24 A84-29067 Model Assessment of satellite power flux-density limits in the The thermal design of the European complement of [NASA-CR-175195] p 79 N84-19371 2025-2300 MHz frequency range, part 1 FSLP — First SpaceLab Mission TRAJECTORY CONTROL [PB84-129402] p 51 N84-18532 [SAE PAPER 831144] p 24 A84-29071 Simulation of the Galileo spacecraft axial - Delta-V ULTRASONIC WELDING THERMAL CONDUCTIVITY algorithm p66 A84-11938 Welded solar cell interconnection p 19 A84-22965 Thermal conductance and torque of thin section TRANSFER FUNCTIONS ULTRAVIOLET RADIATION four-point contact ball bearings in vacuum Algorithms and computational aspects pertaining to Effects of combined ultraviolet and oxygen plasma [ESA-ESTL-54] p2S N84-15562 block diagonal dominance methods for design of environment on spacecraft thermal control materials — THERMAL CONDUCTORS decentralized feedback compensation space shuttle payloads p 27 N84-19449 A contact conductance interface for a space p15 A84-19108 Optical coating in space constructable heat pipe radiator TRANSFER ORBITS [NASA-CR-175441] p 56 N84-21290 [SAE PAPER 831101] p24 A84-29036 A future solar orbital transfer vehicle concept UNITED STATES THERMAL CONTROL COATINGS p61 A84-16116 Space stations - The next step in space? Spacecraft thermal control selection for seven years of An electric propulsion transportation system from [AAS PAPER 83-202] p 76 A84-29855 lifetime in synchronous orbit low-earth orbit to geostationary orbit utilizing beamed UPPER STAGE ROCKET ENGINES [MBB-UR-584-82-OE] p 25 NB4-11200 microwave power p61 A84-21485 A parametric study of space transfer-propulsion Effects of combined ultraviolet and oxygen plasma Highly efficient, very low-thrust transfer to environment on spacecraft thermal control materials — geosynchronous orbit - Exact and approximate solutions [IAF PAPER 83-401 ] p 61 A84-13397 space shuttle payloads p 27 N84-19449 p 61 A84-24980 USER MANUALS (COMPUTER PROGRAMS) THERMAL CYCLING TESTS Optimal low-thrust transfers to synchronous orbit User manual of the CATSS system (version 1.0) Thermo-mechanical behaviour of CFRP tubes for space p62 A84-24981 communication analysis tool for space station structures Capture-ejector satellites [NASA-CR-171728] . p 51 N84-17431 [IAF PAPER 83-417] p 22 A84-11814 [NASA-TM-85686] p7 N84-15179 USER REQUIREMENTS Higher temperature composite joints survive elimination Discontinuous low thrust orbit transfer Space station - A Canadian perspective tests p 55 A84-29565 [AD-A136908] p 63 N84-19474 [IAF PAPER 83-55] p 65 A84-11728 Thermal cycling tests in space environment simulation TRANSFORMATIONS (MATHEMATICS) The Boeing flywheel study p 37 N84-12235 chambers p 26 N84-19401 Recursive lagrangian dynamics of flexible manipulator Space station needs, attributes and architectural options The Large Space Simulator (LSS) at ESA/ESTEC (a arms via transformation matrices study. Final review executive summary briefing summary of the main characteristics) p27 N84-19458 [AD-A137345] pSO N84-20316 [NASA-CR-173674] p 10 N84-18272

A-25 VACUUM CHAMBERS SUBJECTINDEX

Space Station Technology, 1983 VIBRATION MODE Feasibility study to conduct windblown sediment [NASA-CP-2293] p11 N84-18277 Determination of critical parameters in large flexible experiments aboard a space station Systems/operations technology p11 N84-18278 space structures with uncertain modal data [NASA-Cfl-175434] p 15 N84-21586 Crew and life support EVA p11 N84-18279 p33 AB4-20047 WELDED STRUCTURES Human capabilities p11 N84-18282 Evaluation of modal testing techniques for spacecraft Feasibility of remotely manipulated welding in space. Thermal control p 25 N84-18289 structures p28 N84-19906 A step in the development of novel joining technologies Space station needs, attributes and architectural VIBRATION TESTS [NASA-CR-175437] p 60 N84-20857 options. Volume 1, attachment 1: Executive summary Vibration characteristics of self-expanding stayed WHITE NOISE NASA columns for use in space p34 A84-21237 Research on boundary feedback and control theories, 1978 -1983 [NASA-CR-173337] p 12 N84-18293 Evaluation of modal testing techniques for spacecraft [AD-A136531] p 41 N84-18987 Space Station needs, attributes and architectural structures p28 N84-19906 options. Volume 2, book 1, part 2, task 1: Mission WIND EFFECTS VIDEO EQUIPMENT requirements Feasibility study to conduct windblown sediment Communications p 12 N84-18285 [NASA-CR-173313] p 13 N84-18297 experiments aboard a space station Space Station needs, attributes and architectural VIEW EFFECTS [NASA-CR-175434] p 15 N84-21586 options. Volume 2, book 1, part 4: Payload element Study on synthesis and characterization of large space mission data sheets systems, phase 2. Part 2: Proposals for additions, [NASA-CR-173315] p 13 N84-18299 modifications and new analytical methods, volume 2 [ESA-CR(P)-1779-VOL-4] p29 N84-21616 VISCOELASTIC DAMPING YAW Study on damping representation related to spacecraft Attitude stability for the yaw-wheel class of orbiting structural design gyrostats p 33 A84-19675 VACUUM CHAMBERS [EMSB-18/83] p38 N84-15182 IRSIM: A program for the calculation of infrared flux viscoELASTicrrv intensity incident on a spacecraft inside a test chamber Tests and prediction of composite material viscoelastic p26 N84-19400 behaviour for large space structure Thermal cycling tests in space environment simulation [IAF PAPER 83-418] p 30 A84-11815 chambers p26 N84-19401 A variational theorem for the viscoelastodynamic VACUUM EFFECTS analysis of high-speed linkage machinery fabricated from Canadarm and the Space Shuttle p 57 A83-44602 composite materials VARIABILITY [ASME PAPER 83-DET-6] p 55 A84-29101 A Variable Conductance Heat Pipe (VCHP) radiator system for communications payloads p27 N84-19406 VOICE COMMUNICATION A communications system conceptual design for a low VARIABLE GEOMETRY STRUCTURES Approximations method for space frame synthesis earth orbiting Manned Space Station p45 A84-15643 p19 A84-10141 VOICE CONTROL VARIATIONAL PRINCIPLES A voice interactive system for aiding and documentation A variational theorem for the viscoelastodynamic of space-based tasks analysis of high-speed linkage machinery fabricated from [AIAA PAPER 83-2355] p 43 A84-10025 composite materials VOLTAGE REGULATORS [ASME PAPER B3-DET-6) p 55 A84-29101 Evaluation of bus impedance on the SPOT multimission VAX-11 SERIES COMPUTERS platform p 44 A84-13521 Implementation of MACLISP on a large address space computer [DE84-005042] p 79 N84-21145 w VERTICAL TAKEOFF Vertical ascent from earth to geosynchronous orbit WASTE TREATMENT [AIAA PAPER 84-0509] p 61 A84-18141 Hyperfiltration wash water recovery subsystem - Design VIBRATION and test results — for extended mission spacecraft such The flexural behavior of PACSAT (passive as space stations communication satellite) in orbit [SAE PAPER 831112] p6 A84-29047 [AD-A131406] p36 N84-11195 WASTE UTILIZATION VIBRATION DAMPING Phase change water recovery techniques - Vapor A flexible structure controller design method using mode compression distillation and thermoelectric/membrane residualization and output feedback — for Large Flexible concepts — from waste water as part of Space Station Space System p32 A84-17369 life support system Control of large space structures [SAE PAPER 831122] p6 A84-29056 [AIAA PAPER 84-0081 ] p 32 A84-17866 WASTE WATER Identification of large flexible structures mass/stiffness Integrated water management system - Description and and damping from on-orbit experiments test results — for Space Station waste water processing p34 A84-24995 [SAE PAPER 831111] p6 A84-29046 Control structure interactions in large space structures Hyperfiltration wash water recovery subsystem - Design Analysis using energy approach — for constant and pulsed, and test results — for extended mission spacecraft such thrusters p 35 A84-27934 as space stations Stability, vibration and passive damping of partially [SAE PAPER 831112] p6 A84-29047 restrained imperfect columns WATER MANAGEMENT [NASA-TM-85697] p 37 N84-13608 Integrated water management system - Description and Experimental study of active vibration control test results — for Space Station waste water processing [AO-A133818] p 38 N84-14546 [SAE PAPER 831111] p6 A84-29046 Study on damping representation related to spacecraft WATER RECLAMATION structural design Hyperfiltration wash water recovery subsystem - Design [EMSB-18/83] p38 N84-15182 and test results — for extended mission spacecraft such Digital control system for space structural dampers as space stations [NASA-CR-175355] p 39 N84-16246 [SAE PAPER 831112] p6 A84-29047 The effects of the space environment on damping Phase change water recovery techniques - Vapor materials and damping designs on flexible structures compression distillation and thermoelectric/membrane p56 N84-17217 concepts — from waste water as part of Space Station Vibration isolation technology experiment life support system p39 N84-17228 [SAE PAPER 831122] p6 A84-29056 Investigation of articulated panel dynamics WEAPONS p40 N84-17230 Aeroelastic stability and response of flexible tactical ACOSS eleven (Active Control Of Space Structures), weapons [AIAA PAPER 84-0392] p 32 A84-18060 volume 1 [AD-A135675] p 40 N84-18311 WEIGHT ANALYSIS Weight characteristics of future spacecraft thermal Maintenance and operational enhancement of the management systems flexible spacecraft dynamics program [AIAA PAPER 84-0054] p 23 A84-17850 tNASA-CR-1752111 p 41 N84-19394 WEIGHT REDUCTION The effect of mass and stiffness changes on the damping Multi-megawatt space power thermal management factor in a large space structure as represented by the system requirements CSDL 2 model [AIAA PAPER 84-0056] p 23 A84-21284 [AD-A136984] p 42 N84-19465 WEIGHTLESSNESS Analysis of large space structures p 18 N84-20621 Second All-Union Seminar on Hydromechanics and VIBRATION ISOLATORS Heat-Mass Transfer in Weightlessness. Abstracts of Vibration isolation technology experiment reports: Table of contents p39 N84-17228 [NASA-TM-77534] p 26 N84-18576

A-26 PERSONAL AUTHOR INDEX

TECHNOLOGY FOR LARGE SPACE SYSTEMS / A Bibliography (Supplement 11) JANUARY 1985

Typical Personal Author Index Listing

ALET.I. ARMSTRONG, E. S. PERSONAL AUTHOR I A Maltese cross shaped mobile thermal control Spline-based estimation techniques for parameters in shutter p 27 N84-19454 elliptic distributed systems ALEXANDER, a [NASA-TM-85439] p 9 N84-17947 AKIN.D. L. ARNBAK, J. a m Developing the space frontier; Proceedings of the —Space «rt ?tfP' of Automation, Robotics And Twenty-ninth Annual Conference, Houston, TX, October Improved orbit utilization using auxiliary feeds in existing Machine Intelligence Systems (ARAM IS). Volume 3, phase 25-27,1882 p 67 A84-15381 earth terminals p 46 A84-20647 2: Executive summary ALLEN, J. l_ JR. ARNDT, a D. [NASA-CR-3736] p 59 N84-10582 Deployable beam flight experiment (MAST) Application of beam power technology to a space p8 N84-17218 station p45 A84-15642 ARNIM, R. ALLER, R. O. The Franco-German DBS program TV-SAT/TDF-1' Lessons learned during the first year of theTDRSS [AIAA PAPER 84-0661 ] p 4 A84-25260 [AIAA PAPER 84-0687] p 74 A84-25319 NASA ARNOLD, D. REPORT PAGE AMBRUS, J. H. TITLE ACCESSION Investigation of electrodynamic stabilization and control NUMBER NUMBER High capacity power systems for space NUMBER of long orbiting tethers [IAF PAPER 83-421 ] p 44 A84-11816 [NASA-CR-170972] p 40 N84-17251 AMITAV, N. ARNOLD, G, S. Narrow multibeam satellite ground station antenna Reactions of high velocity atomic oxygen with carbon Listings in this index are arranged alphabetically by employing a linear array with a geosynchronous arc [AIAA PAPER 84-0549] p 53 A84-18159 coverage of 60 deg. II - Antenna design personal author. The title ol the document provides ARNOLD, W. F. p46 A84-17743 Controllability and observability criteria for multivariable the user with a brief description of the subject ANDERSON, J. L. linear second-order models p35 A84-25516 matter. The report number helps to indicate the Space station autonomy requirements AUGERSON, W. type of document listed (e.g., NASA report, [AIAA PAPER 83-2352] p 63 A84-10024 Human capabilities p11 N84-18282 translation, NASA contractor report). The page and ANDERSON, L. Tele-X - The first step in a satellite communications accession numbers are located beneath and to the system for the Nordic countries B right of the title. Under any one author's name the [AIAA PAPER 84-0713] p4 A84-25287 accession numbers are arranged in sequence with ANDERSON, M. S. BACKLUND, L. the AIAA accession numbers appearing first. Buckling and vibration of any prismatic assembly of shear Tele-X -The first step in a satellite communications and compression loaded anisotropic plates with an system for the Nordic countries arbitrary supporting structure p23 A84-14050 [AIAA PAPER 84-0713] p4 A84-25287 ANDERSON, R. H. BAGHERIAN, A. B. Application of laser interferometry to robotics Airborne antenna pattern calculations p58 A84-28541 [NASA-CR-173284] p 51 N84-17436 ANDING, D. BAILEY, W. ABRATE.S. ACOSS eleven (Active Control Of Space Structures), Space platform accommodations p 16 A84-22131 volume 2 Analysis ol large space structures p 18 N84-20621 BAINUM, P. M. [AD-A135676] p 41 N84-18312 ABT, B. The dynamics and control of large flexible space ANORONIKOU, A. M. A deployable 30/20 GHz multibeam ottset antenna structures, 6 Attitude control and dynamics of the space operations [AIAA PAPER 84-0658] p 20 A84-25258 [NASA-CR-174450] p 36 N84-10173 center p31 A84-11934 ADELMAN, H. M. ANOUINI, C. Environmental effects on the dynamics and control of Thermal analysis research applicable to space station Study on synthesis and characterization of large space an orbiting large flexible antenna system technology needs systems, phase 2. Part 2: Proposals for additions, [NASA-CR-175448] p 42 N84-20627 [NASA-TM-84658] p 25 N84-15426 modifications and new analytical methods, volume 2 BAIOCCHI, G. Static and dynamic structural-sensitivity derivative [ESA-CR(P)-1779-VOL-4] p 29 N84-21616 A parametric study of space transfer-propulsion calculations in the finite-element-based Engineering ANSELL, G. S. Analysis Language (EAL) system Composite structural materials [IAF PAPER 83-401] p61 A84-13397 [NASA-TM-85743] p 42 N84-20880 [NASA-CR-1 73259] p 56 N84-17293 BAKER, A. F. AGAPAKIS, J. E. ARDUINI, C. Sodium heat transfer system modeling Feasibility of remotely manipulated welding In space. Study on synthesis and characterization of large space [DE84-002051] p25 N84-16509 A step in the development of novel joining technologies systems, phase 2. Part 2: Proposals for additions, BALAKRISHNAN, A. V. [NASA-CR-175437] p 60 N84-20857 modifications and new analytical methods, volume 1 Research oo boundary feedback and control theories, AGNENI, A. [ESA-CR(P)-1779-VOL-3] p 43 N84-21611 1978 -1983 Assessment of the existing ground test technology and The solution of the dynamic problem of the periodic [AD-A136531] p41 N84-18987 confronting with the Large Space Structures (LSS) structures by cydosymmetric technique BALAS.U. J. requirements. Experimental techniques in structural p43 N84-21612 The spatial order reduction problem and its effect on analysis p 29 N84-21621 Computing the radiation pressure forces by adapting adaptive control of distrirbuted parameter systems AHMED, S. thermal design verification softwares p 28 N84-21613 p33 A84-19056 Thermal design verification of the large open truss Right test of a synthetic aperture radar antenna using BANDURSKI, R. S. structures. The local approach and the shadow problem STEP p9 N84-17237 The Alpha-Helix Concept Innovative utilization of the AIKENHEAO. B. A. p29 N84-2t6t7 Space Station Program. A report to the National Computational savings in view factor evaluation on mode Canadarm and the Space Shuttle p 57 A83-44602 Aeronautical and Space Administration requesting prescreening p29 N84-21618 AKIN, D. L. establishment of a Sensory Physiology Laboratory on the Space applications of Automation, Robotics And Interactive structuraMhermaJ-conlrol analytical Space Station Machine Intelligence Systems (ARAMIS). Volume 3, phase formulations p28 N84-21619 [NASA-CR-175436] p 14 N84-20610 Study on synthesis and characterization of large space 2: Executive summary BANERJEE, J. R. systems, phase 2. Pan 3: Experimental design verification [NASA-CR-3736] p 59 N84-10582 vibration characteristics of self-expanding stayed Space Applications of Automation, Robotics and columns for use in space p34 A84-21237 [ESA-CR(PM779-VOL-5] p 18 N84-21620 Machine Intelligence Systems (ARAMIS), phase 2. Volume Study on synthesis and characterization of large space BANKS, H. T. 1: Telepresence technology base development systems, phase 2. Part 1: Assessment of design Parameter identification in continuum models [NASA-CR-3734] p 59 N84-105B3 p 16 A84-2552S verification analytical methods. Volume t: Mechanical Space Applications ol Automation, Robotics and design Spline-based estimation techniques for parameters in Machine Intelligence Systems (ARAMIS), phase 2. Volume [ESA-CR(P)-1779-VOL-1] p 18 N84-21624 etOptic distributed systems 2: Telepresence project applications Study on synthesis and characterization of large space [NASA-TM-85439] p9 N84-17947 INASA-CR-3735] p 59 N84-10584 systems, phase 2. Part 1: Assessment of design BANSEMIR, H. AL-ASTBABADI, F. verification analytical methods. Volume 2: Thermal Local stability of sandwich structures with thin fibre Thermal control of tethered satellite in a very low altitude reinforced face skins for space application aerodynamic mission P 27 N84-19444 [ESA-CR(P)-1779-VOL-2) p 18 N84-21625 [MBB-UD-381-83-OE] p 19 A84-22859 B-1 BAR-KANA, I. PERSONAL AUTHOR INDEX

BAR-KANA, I. BINGHAM, N. BROWNE, E. R. Multivariable direct adaptive control for a general class Evolution of European telecommunication satellite Welded solar cell interconnection p 19 A84-22965 of time-varying commands p 33 A84-19118 pointing performance BRUMFIELD, M. L. Some applications of direct adaptive control to large [AIAA PAPER 84-0725] p 34 A84-25291 STEP Experiment Requirements structural systems p 34 A84-25496 BIRNBAUM, M. M. [NASA-CP-2294] p7 N84-17211 Direct multivariable model reference adaptive control Electrically conductive black optical paint BUBNOV, I. with applications to large structural systems p 55 A84-28553 Space vehicles p4 A84-21573 p38 N84-15840 BLOSSER, M. l_ BUCHANAN, H. J. BARAS, J. S. Operational modules for space station construction IPACS guidance navigation and control system Algorithms and computational aspects pertaining to [NASA-TM-85772] p 21 N84-21608 considerations and test activities p 37 N84-12245 BOFFEY, T. B. block diagonal dominance methods for design of BULLOCH, C. A heuristic method for the design of minimum weight decentralized feedback compensation Spaceflight to 2000 - Interavia looks forward from the p 15 A84-19108 trusses using discrete member sizes p 15 A84-16841 BOGGIATTO, D. present p 66 A84-14764 BARBERA, R. Development of a spacecraft infrared test technique as BUNNER, A. N. A standardized propulsion module for future an alternative to solar simulation: First steps on L-SAT Optical coating in space communications satellites in the 2000 to 3000 kg class thermal model p26 N84-19398 [NASA-CR-175441] p 56 N84-21290 [AIAA PAPER 84-0727] p 62 A84-25292 The thermal design of L-SAT large telecommunication BURATTI, P. BARBERIS, N. satellite p27 N84-19414 Development of a spacecraft infrared test technique as Design and development of the INTELSAT V BOGUS, K. an alternative to solar simulation: First steps on L-SAT graphite-epoxy central thrust tube p 19 A84-22153 Technology components of solar arrays for space thermal model p26 .N84-19398 BARBONI, R. platforms p 47 A84-22959 BURGHER, E. E. Tests and prediction of composite material viscoelastic BOLOTINA, N. E. Surface accuracy measurement sensor test on a behaviour for large space structure Motion of a symmetric satellite about the center of mass 50-meter antenna surface model [IAF PAPER 83-418] p 30 A84-11815 in circular orbit in the presence of flexible viscoelastic [NASA-TM-85689] p 17 N84-16427 BARBOUR, R. T. rods p35 A84-26977 BURKE, J. D. Development of Test Article Building Block (TABB) for BONELLE, G. J. Space manufacturing 1983; Proceedings of the Sixth employable platform systems p 21 N84-17226 Communications p 12 N84-18285 Conference, Princeton University, Princeton, NJ, May 9-12, BARNABA, A. BONHOMME, R. 1983 p76 A84-29852 Evaluation of bus impedance on the SPOT multimission Development and application of new technologies in the BURKE, W. R. platform p 44 A84-13521 ESA Olympus Programme Introduction to geostationary orbits BARNEY, J. [AIAA PAPER 84-0706] p 4 A84-25282 [ESA-SP-1053] p80 N84-21590 Coordinate transformation assembly BOOK, W. J. BURKETT, W. L, JR. Recursive lagrangian dynamics of flexible manipulator p 75 A84-28579 A design strategy for multiple payload pointing from a arms via transformation matrices BARON, W. R. three axis stabilized spacecraft [AD-A137345] p 60 N84-20316 Technical aspects of the Intelsat V solar array [AIAA PAPER 84-0566] p 33 A84-18168 p47 A84-22962 BORRIELLO, G. BUSH, H. G. BARTEK, R. J. Thermal control of the Tethered Satellite Module Stability, vibration and passive damping of partially [SAE PAPER 831138] p 24 A84-29067 . RF systems in space. Volume 2: Space-based radar restrained imperfect columns analyses Thermal control of tethered satellite in a very low altitude [NASA-TM-85697] p 37 N84-13608 aerodynamic mission p 27 N84-19444 [AD-A133735] p 49 N84-14394 Synchronously deployable truss structure BASHFORD, D. P. BOSS), J. A. [NASA-CASE-LAR-13117-1] p 59 N84-16250 A flexible structure controller design method using mode Review report of the third year's activities on the study A manned-machine space station construction residualization and output feedback p 32 A84-17369 survey of advanced materials concept [R878] p56 N84-21675 BOUCHEZ, J. P. [NASA-TM-85762] p 21 N84-19395 BAUER, H. Design and manufacturing of a heat rejection system BUSH, J. R., JR. The attitude and orbit control system for Eureca for advanced thermal control p27 N84-19434 A programmable power processor for high power space BOUQUET, F. l_ [DGLR PAPER 83-091] p 76 A84-29658 applications p 46 A84-18394 Simulated space radiation effects on dielectrics and BAUER, P. E. BUSSOLINO, L Spacecraft thermal control, design, and operation coatings p 54 A84-20682 Design and manufacturing of a heat rejection system BRADLEY, O. H., JR. p22 A84-10224 for advanced thermal control p 27 N84-19434 BAULORY, R. D. STEP mechanical systems p8 N84-17213 A hardware demonstration of control for a flexible BRADT, R. C. offset-feed antenna p 31 A84-13321 Fracture mechanics of ceramics. Volume 5 - Surface BEERS, B. L flaws, statistics, and microcracking p 54 A84-24501 Dielectric charging in space - Ground test data and model BRANDON, l_ CAMARDA, C. J. verification p 47 A84-20709 IPACS attitude control technology considerations Static and dynamic structural-sensitivity derivative BENHABIB, R. J. p37 N84-12238 calculations in the finite-element-based Engineering ACOSS Fourteen (Active Control of Space Structures) BREAKWELL, J. A. Analysis Language (EAL) system [AD-A133411] p38 N84-15181 The Toysat structural control experiment [NASA-TM-85743] p 42 N84-20880 BENNETT, W. H. p31 A84-13320 CAMERON, J. M. Algorithms and computational aspects pertaining to A hardware demonstration of control for a flexible Dynamics and control of a large space antenna block diagonal dominance methods for design of offset-feed antenna p 31 A84-13321 p32 A84-17361 decentralized feedback compensation BREAKWELL, J. V. CAMPBELL, T. G. p 15 A84-19108 Optimal low-thrust transfers to synchronous orbit Large deployable antenna flight experiment for the BERNASCONI, M. C. p 62 A84-24981 Space Technology Experiments Platform (STEP) Study on large, ultralight long-life structures in space, BRINKMANN, P. W. p8 N84-17232 phase 2C The Large Space Simulator (LSS) at ESA/ESTEC (a CANNON, R. H, JR. [TM-EKR3] p17 N84-17284 summary of the main characteristics) p27 N84-19458 Precise control of flexible manipulators BERRETTA, G. BROOKS, G. f. [NASA-CR-175389] p 60 N84-20175 Application of a common reflector configuration to a Surface accuracy measurement sensor test on a CAPEL.A. multimission satellite of the 90's 50-meter antenna surface model Evaluation of bus impedance on the SPOT multimission [IAF PAPER 83-60] p1 A84-11731 [NASA-TM-856B9] p 17 N84-16427 platform p44 A84-13521 BERRY, W. BROOKS, T. H. CAPP, J. D. Utilization of electric propulsion for communication ACOSS eleven (Active Control Of Space Structures), RF systems in space. Volume 1: Space antennas volume 2 frequency (SARF) simulation [AIAA PAPER 84-0729] p 62 A84-25293 [AD-A135676] p 41 N84-18312 [AD-A133734] p 49 N84-14395 BERTRAM, A. BROOME, P. A. CARL, J. R. Development of procedures for component mode Space operations center communications path A definition of STS accommodations for attached synthesis obscuration p3 A84-1569S payloads [DFVLR-IB-232-82-C-09] p 30 N84-21626 CASS, J. R, JR. [NASA-CR-172223] p 17 N84-10114 BESTE.D. Discontinuous low thrust orbit transfer RF systems in space. Volume 2: Space-based radar BROSE, H. F. [AD-A136908] p 63 N84-19474 Environmental control and life support (ECLS) design analyses CASTELLAN), A. optimization approach p 73 A84-24637 [AD-A133735] p 49 N84-14394 Tests and prediction of composite material viscoelastic BHAT, R. B. The complementary roles of existing and advanced behaviour for large space structure Computer aided synthesis of a satellite antenna structure environmental, thermal control and life support technology [IAF PAPER 83-418] p 30 A84-11815 with probabilistic constraints p 21 N84-19899 for space stations p 79 N84-19429 CASWELL, R. D. Dynamic behaviour of a satellite antenna structure in BROWN, S. M. MSAT mobile communication demonstration satellite random vibration environment p 42 N84-19900 Scale model testing for control system parameters of system and bus tradeoff considerations BHAVNAN1, K. H. large structures [AIAA PAPER 84-0751] p 48 A84-25306 Sheath ionization model of beam emissions from large [AD-A135652] p 41 N84-18313 CHAMBERS, G. J. spacecrafts BROWN, W. C. The Toysat structural control experiment [AD-A137181] p52 N84-19463 An electric propulsion transportation system from p31 A84-13320 BIGNIER, M. low-earth orbit to geostationary orbit utilizing beamed A hardware demonstration of control for a flexible Spacelab's development p 66 A84-13901 microwave power p61 A84-21485 offset-feed antenna p 31 A84-13321

B-2 PERSONAL AUTHOR INDEX FARRAR, A.

CHANDLER, D. CRELUN, E. DONAHUE, T. M. Space telescope: Solar array primary development Derivation and combination of impedance matrices for Use of space station for science p 72 A84-24629 mechanism P 51 N84-18458 flexible satellites DORSEY, J. T. CHAO, C. C. [ESA-STR-209] p43 N84-21604 A manned-machine space station construction Semiautonomous stationkeeping of geosynchronous CREMA, L. B. concept satellites p32 AB4-17359 Tests and prediction of composite material viscoelastie [NASA-TM-85762] p 21 N84-19395 CHARHUT, D. behaviour for large space structure DRACHENBERG, F. Space station needs, attributes and architectural [IAF PAPER 83-418] p 30 A84-11815 Unfurlable offset antenna design for multipurpose options. Summary of major study activities and results. CRIUI, P. applications Space station program observations Aeroelastic stability and response of flexible tactical [AIAA PAPER 84-0659] p 16 A84-25259 [NASA-CR-173345] pit N84-18275 DRAKE, G. CHIARELU, C. [AIAA PAPER 84-0392] p 32 A84-18060 Crew and life support ECLSS p 11 N84-18280 DRESSER, K. J. Thermal control of tethered satellite in a very low altitude CROUTHAMEU M. S. aerodynamic mission p 27 N84-19444 Regenerable non-venting thermal control subsystem for Spacecraft thermal design using interactive graphics extravehicular activity CHICHESTER, F. [AIAA PAPER 84-0143] p 23 A84-17910 Exhibit D modular design attitude control system study [SAE PAPER 831151] p 24 A84-29076 [NASA-CR-170993] p 42 N84-20625 CROWLEY, J. H. DUPAS, A. P. Parameter identification in continuum models CHICHESTER, F. D. Market potential and possible limitations for satellite p 16 A84-25525 Modular design attitude control system solar power stations p 70 A84-21481 [NASA-CR-170996] p 41 N84-19392 CUCCIA, C. L. DURRETT, R. CHUN, H. M. Space station communications p 73 A84-24636 NASA's geostationary communications platform Closed-form solutions for feedback control with terminal program constraints p36 A84-29471 [AIAA PAPER 84-0702] pS A84-25326 CLAVERIE, M. J. Market potential and possible limitations for satellite solar power stations p 70 A84-21481 DALTON, M. C. CLELAND, E. L. Habitability design elements for a space station Electrically conductive black optical paint [AAS PAPER 83-200] p7 A84-29853 ECHOLS, F. L. p55 A84-28553 DAMMANN, R. E. A definition of STS accommodations for attached COCCA.A.A. Effects of combined ultraviolet and oxygen plasma payloads Consequences of transmission of solar energy from environment on spacecraft thermal control materials [NASA-CR-172223] p 17 N84-10114 outer space p68 A84-17076 p27 N84-19449 EDGECOMBE, D. S. CODEN, M. H. DANIEL, P. L Space logistics Communications, tracking, and docking on the Space Spline-based estimation techniques for parameters in [IAF PAPER 83-24] p 64 A84-11719 Station p45 AM-15640 elliptic distributed systems EDWARDS, p. W. COFFMAN, P. E. [NASA-TM-85439] p9 N84-17947 Space station: Policy, planning and utilization; A parametric study of space transfer-propulsion DANIELL, R. G. Proceedings of the Symposium, Arlington. VA, July 18-20, Canadarm and the Space Shuttle p 57 A83-44602 1983 p72 A84-24626 [IAF PAPER 83-401] p 61 A84-13397 DARMON, C. A. EILERS, D. COHEN, H. A. Validation methods for mathematical models of flexible Microgravity conditions on orbital platforms Sheath ionization model of beam emissions from large satellite dynamics [DGLR PAPER 83-90] p 76 A84-29657 spacecrafts [ESA-CR(P)-1794] p40 N84-17241 EKMAN, A. [AD-A137181] p52 N84-19463 DAVENPORT, R. Tele-X - The first step in a satellite communications COLIZZI, E. Software quality assurance Spacelab experience and system for the Nordic countries The thermal design of L-SAT large telecommunication future trends p 17 N84-14759 [AIAA PAPER 84-0713] p4 A84-25287 satellite p 27 N84-19414 DAVID, S. S. ELAM, F. M. COLLET, J. A simulator to study dynamic interaction of the Space Space station control requirements and flywheel system ESA space station activities Shuttle on-orbit flight control system with deployed flexible weights tor combined momentum and energy storage [IAF PAPER 83-30] p 64 A84-11722 payloads p35 A84-26717 p37 N84-12236 COLLJCOTT, H. E. DAVIS, F. M. ELDEN, N. C. Spacecraft thermal control, design, and operation Canadarm and the Space Shuttle p 57 A83-44602 Integrated water management system - Description and DE CACQUEREY, A. p22 A84-10224 test results Management of large space projects - Quality assurance COLOMBO, G. [SAE PAPER 831111 ] p 6 A84-29046 or'product assurance' p3 A84-15310 Investigation of electrodynamic stabilization and control ELDRED, C. H. DE GRAAUW, T. of long orbiting tethers Capture-ejector satellites Coherent arrays of separate optical telescopes in space [NASA-CR-170972] p 40 N84-17251 [NASA-TM-85686] p7 N84-15179 project Trio p3 A84-15363 CONAWAY, A. E. DEBICCARI, A. ELMS, R. V. A comparison of linear and geometrically nonlinear finite Feasibility of remotely manipulated welding in space. Solar array Shuttle flight experiment - Hardware element analyses applied to large space structures A step in the development of novel joining technologies development and testing p 47 A84-22961 [AIAA PAPER 84-0069] p 16 A84-19887 [NASA-CR-175437] p 60 N84-20857 EMERY, A. F. CONNELL, E. B. DEERING, A. M. Radiation-conduction interaction in large space Data system architecture considerations for a space International competition in commercial aerospace structures station markets [AIAA PAPER 84-0144] p 23 A84-17911 [AIAA PAPER 83-2346] p 63 A84-10066 [AAS PAPER 83-244] p 77 A84-29883 ERCHINGER, D. A. CONRAD, P. DELMAS, M. G. Scale model testing for control system parameters-'of Development of procedures for component mode Human organization p2 A84-15303 large structures synthesis DELORENZO, M. L [AD-A135652] p 41 N84-18313 [DFVLR-IB-232-82-C-09] p 30 N84-21626 Selection of noisy sensors and actuators for regulation ERWIN, H. O. COOQAN, C. O. of linear systems Communications, tracking, and docking on the Space [AD-A135442] p 51 N84-17931 Station p 45 A84-15640 [IAF PAPER 83-24] . p 64 A84-11719 DERYDER, D. D. ESTADIEU, B. COOK, C. W. Interactive geometry modeling of space station The progression of projects p2 A84-15305 National security implications of a U.S. space station conceptual designs p 18 N84-22191 EVANS, A. G. p73 A84-2463S Geometric modeling of large space antenna Fracture mechanics of ceramics. Volume 5 - Surface CORBETT, R. deployment p22 N84-22225 flaws, statistics, and microcracking p54 A84-24501 Power p12 N84-18288 DESAUSSURE, H. Determination of applicable law to living and working EVANS, R. T. CORMIER, L. Scale model testing for control system parameters of The space van and its potential impact on the design in space [IAF PAPER 82-IISL-45] p 68 A84-17058 large structures of communications satellites [AD-A135652] p 41 N84-18313 [AIAA 84-0758] p 74 A84-25309 DESKEVICH, J. Leasecraft - An innovative space vehicle COUGNET, C. p5 A84-27945 Application of a common reflector configuration to a DIAMOND, G. S. multimission satellite of the 90's On the dynamics of a subsatellite system supported by [IAF PAPER 83-60] p1 A84-11731 two tethers FABRIZI, A. COX, R. L. [AIAA PAPER 84-0062] p 32 A84-17854 A parametric study of space transfer-propulsion Flexible radiator system: Executive summary DIEDERIKS-VERSCHOOR, I. H. PH. [NASA-CR-1717B6] p 28 NB4-20624 Legal aspects of solar power satellites impact on the [IAF PAPER 83-401] p 61 A84-13397 CRAIG, A. D. environment p 68 A84-17077 FALKENBURG, D. R. Evolution of European telecommunication satellite OISHER, J. H. Dynamics of nonrigid articulated robot linkages pointing performance Overview of space station operations p58 A84-25531 [AIAA PAPER 84-0725] p 34 A84-25291 [IAF PAPER 83-38] p 64 A84-11723 FARRAR, A. CRAWLEY, E. F. DOETSCH,K.H. Assessment of satellite power flux-density limits in the General requirements for Shuttle flight experiments Space station - A Canadian perspective 2025-2300 MHz frequency range, part 1 p8 N84-17221 [IAF PAPER 83-55] p 65 A84-11728 [PB84-129402] p 51 N84-18532

B-3 FAWCETT, C. A. S. PERSONAL AUTHOR INDEX

FAWCETT, C. A. S. GREENBERG, H. S. Financing a solar power satellite project Development of employable structures for large space p70 A84-21482 GABRIEL, C. platform systems. Volume 1: Executive summary FEDOR, J. V. Design and development of the INTELSAT V [NASA-CR-170913] p 20 N84-10175 Thermally induced spin rate ripple on spacecraft with graphite-epoxy central thrust tube p 19 A84-22153 Development of deployable structures for large space long radial appendages GADDIS, J. L platforms. Volume 2: Design development [NASA-TM-85058] p 39 N84-16249 Hyperfiltration wash water recovery subsystem - Design [NASA-CR-170914] p 20 N84-10176 FEKETE.L. and test results Development of Test Article Building Block (TABS) for Determination of applicable law to living and working [SAE PAPER 831112] p 6 A84-29047 deployable platform systems p 21 N84-17226 in outer space GALANTE, F. M. GREENWOOD, L. R. An overview of the institutional and regulatory aspects [IAF PAPER 82-IISL-44] p 68 A84-17057 The role of space station in earth sciences and their impact on system design FENNELL, J. F. p72 A84-24631 [IAF PAPER 83-82] p 65 A84-11737 A review of SCATHA satellite results: Charging and GREGORY, C, JR. GANS, M. J. discharging p 50 N84-17254 Matrix(X) - Application to large space structure control Narrow multibeam satellite ground station antenna design problems p 16 A84-19129 FEOKTISTOV, K. employing a linear array with a geosynchronous arc GRIGORENKO, IA. M. Space vehicles p4 A84-21573 coverage of 60 deg. II - Antenna design Numerical solution of several classes of nonlinear FEREBEE, M. J, JR. p46 A84-17743 flexible shell theory problems p35 A84-25586 Interactive geometry modeling of space station GARBA, J. A. conceptual designs p 18 N84-22191 GROOM, N. J. The 55-meter-structure flight experiment Integrated Flywheel Technology, 1983 FERREIRA, D. L. p8 N84-17233 [NASA-CP-2290] p 78 N84-12228 Sensithnty analysis of the influence of the flexibility of GARCIA, N. F. Advanced Control and Power System (ACAPS) solar panels on the attitude dynamics of artificial Technology requirements for large flexible space technology program p 37 NB4-12243 satellites structures GROSJEAN, O. [INPE-2763-PRE/337] p 39 N84-16232 [IAF PAPER 83-404] p2 A84-11811 Payload placing using an operational support platform GARRETT, L B. Capture of satellite stabilized by gravity gradient with a [IAF PAPER 83-44] p1 A84-11724 Mathematical synthesization of complex structures flexible mast during and after deployment GROTEN, E. [INPE-2749-PRE/32S] p 41 N84-19383 p 19 N84-22224 Geodetic aspects of ESA projects, studies and GARTRELL, C. F. FESTA.A. Investigations - p78 N84-16677 A future solar orbital transfer vehicle concept Unfurlable offset antenna design for multipurpose GULKIS, S. applications p61 A84-16116 Large Deployable Reflector (LDR) - A concept for an [AIM PAPER 844659] p 16 A84-25259 GATES, R. L. orbiting submillimeter-infrared telescope for the 1990s FESTER, D. Geometric modeling of large space antenna p66 A84-14586 Fluid management p11 N84-18284 deployment p22 N84-22225 GUSTAN, E. FEWELL, M. E. GAZENKO, O. G. Probable missions and transportation scenarios to use Man in space - An overview p67 A84-15161 Sodium heat transfer system modeling regenerative life support systems GERARD, M. [DE84-002051] p25 NB4-16509 [MS PAPER 83-201] p 76 A84-29854 Space station: Policy, planning and utilization; GUYENNE, D. FILEP, R. T. Proceedings of the Symposium, Arlington, VA, July 18-20, Commercial communications satellite market and Spacecraft/plasma interactions and their influence on 1983 p72 A84-24626 field and particle measurements technology in the 90's GERSHUNI, G. Z. [IAF PAPER 83-86] p 65 A84-11739 [ESA-SP-198] p56 N84-17253 Second All-Union Seminar on Hydromechanics and FISCHER, C.-P. GUYENNE, T. D. Heat-Mass Transfer in Weightlessness. Abstracts of Environmental and thermal control systems for space A cylindrical near-field test facility for large satellite reports: Table of contents antennas vehicles [NASA-TM-77534] p 26 N84-18576 [ESA-SP-200] p26 N84-19396 [MBB-UR-628-83-OE] p 72 A84-22862 GILLARD, C. W. FLASHNER, H. K. Application of laser interierometry to robotics ACOSS Fourteen (Active Control of Space Structures) p58 A84-28541 H [AD-A133411] p38 N84-15181 GLASER, P. E. FLEMING, M. L. Evolution of the solar power satellite concept - The HAANAPPEL, P. A contact conductance interface for a space utilization of energy from space p 70 A84-21478 Determination of applicable law to living and working constructable heat pipe radiator An electric propulsion transportation system from in space [SAG PAPER 831A 01 ] p 24 A84-29036 low-earth orbit to geostationary orbit utilizing beamed [IAF PAPER 82-IISL-4S} p 68 A84-17058 FLOERY, E. microwave power p 61 A84-21485 HABLANI, H. B. Radiation characteristics of array antennas with GLUSHANKOV, E. I. Dynamics and control of a deformable gyrostat, utilizing disturbed aperture coverage p48 A84-26516 Characteristics of the microprocessor implementation continuum vehicle modes p 31 A84-12488 FLOOK.L of algorithms for the processing of radio signals and noise HALL, W. B. Evolution of European telecommunication satellite in large antenna arrays p 48 A84-28067 An evaluation of Techroll seal flexible joint material pointing performance GOLDSWORTHY, W. B. p56 N84-16037 [AIAA PAPER 84-0725] p 34 A84-25291 The development of a composite beam building machine HALLAUER, W. l_ JR. FOGEL.E. for on-site construction of large space structures Experimental study of active vibration control ACOSS eleven (Active Control Of Space Structures), [MS PAPER 83-217] p 20 A84-29862 [AD-A133818] p 38 N84-14546 volume 1 GOOD, W. A. HAMIDI, M. [AD-A135675] p 40 N84-18311 International competition in commercial aerospace Use of electromagnetic models in the optimal control markets of large space antennas p 35 A84-25552 FORD, F. E. [MS PAPER 83-244] p 77 A84-29883 Assessment of potential for batteries in space HANKS, B. R. GOROVE, S. Deployable beam flight experiment (MAST) applications p48 N84-12246 Energy from space - Legal implications of the use of p8 N84-17218 FORWARD, R. L. the geostationary orbit p68 A84-17075 HARRIS, J. E. Roundtrip interstellar travel using laser-pushed Major concerns of private enterprise regarding recent Space Technology Experiments Platform (STEP) lightsails p62 A84-27443 developments in space law overview p8 N84-17212 FRAUNDORF, P. [MS PAPER 83-221] p 77 A84-29865 HARTUNG, W. Erosion of mylar and protection by thin metal films GOSLEE, J. W. Materials and construction techniques for large [AIM PAPER 83-2636] p 52 A84-10949 Adaptive microwave reflector pSO N84-17235 spacecraft structures p 53 A84-17768 FREDERICK, D. H. Microwave reflector characterization using simple HASLETT, B. A methodology to include static and kinetic friction instruments in EVA p 50 N84-17236 Thermal control p 25 N84-18289 effects in Space Shuttle payload transient loads analysis GOUNDER, R. N. HASSELMAN, D. P. H. [AIM PAPER 83-2654] p 30 A84-10956 Advanced composite antenna reflectors for Fracture mechanics of ceramics. Volume 5 - Surface FREEUAND, R. communications satellites p53 A84-17151 flaws, statistics, and microcracking p54 A84-24501 The 55-meter-structure flight experiment GRAHAM, W. R. HAVILAND, J. K. p8 N84-17233 Simulation of the motion of a Shuttle-attached flexible Digital control system for space structural dampers FREELAND, R. E. manipulator arm p57 A84-11935 [NASA-CR-175355] p 39 N84-16246 Technology requirements for large flexible space GRAHN.S. HAWKINS, F. J. structures Tele-X - The first step in a satellite communications Stariab Ground System guidelines document [IAF PAPER 83-404] p 2 A84-11811 system for the Nordic countries [NASA-CR-175192] p 14 N84-20435 FREEMAN, J. R. [AIAA PAPER 84-0713] p4 A84-25287 HAYATI, S. A. RF systems in space. Volume 1: Space antennas GRAN, R. Science platform and attitude subsystem in-flight frequency (SARF) simulation Number crunching on the ACOSS Model No. 2 calibration for the Galileo spacecraft p32 A84-17355 [AD-A133734] p 49 N84-14395 p33 AS4-19128 HAYES, S. M. FREEMAN, J. W. GRAVES, J. R. Structural parameter identification for flexible Energy from space; Proceedings of the Symposium on A programmable power processor for high power space spacecraft Solar Energy from Space, Vienna, Austria, August 9-21, applications p46 A84-18394 [AIAA PAPER 84-0060] p 23 A84-17853 1982 p69 A84-21476 GREELEY, R. HEACOCK, E. L FULTON, R. E. Feasibility study to conduct windblown sediment Space applications at the crossroads; Proceedings of Computer-Aided Geometry Modeling experiments aboard a space station the Twenty-first Goddard Memorial Symposium, Greenbelt, [NASA-CP-2272] p 18 N84-22179 [N ASA-CR-175434 ] p 15 N84-21586 MD, March 24, 25, 1983 p 64 A84-10883

B-4 PERSONAL AUTHOR INDEX KLINE, R.

HEARD, W. U JR. HUNT, J. JUANG, J. N. Erectable beam experiment p60 N84-17219 Spacecraft/plasma interactions and their influence on Static shape forming for an electrostatically controlled HEENAN, A. T. field and particle measurements membrane mirror p 16 A84-25551 Alternative strategies for space station financing [ESA-SP-198] p56 N84-17253 JUANG, J.-N. [NASA-CR-175412] p 80 N84-21437 Spacelab data book Closed-form solutions for feedback control with terminal HEGG, D. R. [ESA-BR-14] p79 N84-18315 constraints p 36 A84-29471 ACOSS eleven (Active Control Of Space Structures), HUNT, J. J. JUDO, R. P. volume 1 Environmental and thermal control systems for space Dynamics of nonrigk) articulated robot linkages [AD-A135675] p 40 N84-183I1 vehicles p58 A84-25531 HENDERSON, T. C. [ESA-SP-200] p26 N84-19396 JUNKINS, J. L. A large space structure benchmark problem - ACOSS Structural parameter identification for flexible HUNTER, M. W, II Model No. 2 p 33 A84-19127 spacecraft Transportation - Options and high payoff choices HENDRICKS, S. L. p 61 A84-21484 [AIAA PAPER 84-0060] p 23 A84-17853 Structural parameter identification for flexible Identification of large flexible structures mass/stiffness spacecraft HUSTON, R. L. and damping from orvorbit experiments [AIAA PAPER 84-0060] p 23 A84-17853 Multibody dynamics - Analysis of flexibility effects p34 A84-24995 Identification of large flexible structures mass/stiffness [AD-A132533] p 36 A84-29145 and damping from orvorbit experiments p34 A84-24995 K HENKEL, E. E. A methodology to include static and kinetic friction KAHAT, H. P. IBRAHIM, A. H. Optimization of shallow trusses against limit point effects in Space Shuttle paytoad transient loads analysis Transient dynamics during the orbiter based deployment [AIAA PAPER 83-2654] p 30 A84-10956 instability p 20 A84-23366 of flexible members HENRY, W. A. Identification of large flexible structures mass/stiffness [AIAA PAPER 84-0061 ] p 34 A84-21285 and damping from on-orbit experiments Reid repair of graphite epoxy skin panels on the ILES.P.A. p 34 A84-24995 spaceship Columbia pS2 A84-17120 Large area, low cost space solar cells KAPELL, M. H. HEPPNER, D. B. p47 A84-22979 Space station communications and tracking equipment Electrochemical and steam-desorbed amine OO2 IRUDAYASAUY, J. management/control system p45 A84-15639 concentration Subsystem comparison Time domain analysis and synthesis of robust controllers KAPUSTKA, R. E. [SAE PAPER 831120] p6 A84-290S4 for large scale LOG (Linear Quadratic Gaussian) A programmable power processor for high power space HERBEN, M. H. A. J. regulators applications p 46 A84-18394 Improved orbit utilization using auxiliary feeds in existing [AD-A137760] p 43 N84-21172 KARAM, R. D. earth terminals p 46 A84-20647 rro, Y. Thermal control of tubular composite structures in space HERBERT, J. J. Computer tools for optimizing orbit use environment p22 A84-10440 Technology needs of advanced Earth observation [AIAA PAPER 84-0651 ] p 74 A84-25318 KASSING, D. spacecraft IVANOV, A. European questions related to satelite power systems [NASA-CR-3698] p9 N84-I724B For the first time p 16 A84-21564 p70 A84-21483 HERBIG, H. IVERSEN, J. D. KATZ.I. Unfurlable offset antenna design for multipurpose Feasibility study to conduct windblown sediment Plasma sheath structure surrounding a large powered applications experiments aboard a space station spacecraft [AIAA PAPER 84-0659] p 16 A84-25259 [NASA-CR-175434] p 15 N84-21586 [AIAA PAPER 84-0329] p 46 A84-18025 HERDAN, B. L. IVES, S. T. KAUFMAN, H. Development and application of new technologies in the Dielectric charging in space - Ground test data and model Mulfjvariable direct adaptive control for a general class ESA Olympus Programme verification p47 A84-20709 of time-varying commands p 33 A84-19118 [AIAA PAPER 84-0706] p4 A84-25282 Some applications of direct adaptive control to large HILBRANDT, E. structural systems p 34 A84-25496 Study on damping representation related to spacecraft KEAFER, L S. Large inflated-antenna system p9 N84-17234 structural design JACKSON, L. R. KECKLER, C. R. [EMSB-18/83] p38 N84-15182 Operational modules for space station construction HILL, B. R. [NASA-TM-85772] p 21 N84-21608 Integrated Flywheel Technology, 1983 [NASA-CP-2290] p 78 N84-12228 Remote manipulators in space p 57 A84-22336 JACOBS, B. D. Advanced Control and Power System (ACAPS) HILL, H. C. Advanced composite antenna reflectors for technology program p37 N84-12243 Solar array Shuttle flight experiment - Hardware communications satellites p53 A84-17151 vibration isolation technology experiment development and testing p 47 A84-22961 JALMARSSON, L. p39 N84-17228 HINSON, W. F. Tele-X - The first step in a satellite communications system for the Nordic countries Integrated Power/Attitude Control System (IPACS) Large inflated-antenna system p 9 N84-17234 technology experiment p 39 N84-17229 [AIAA PAPER 84-0713] p4 A84-25287 HIXON, C. W. KEEFE, J. R. Flexible radiator thermal vacuum test report JANKOVIC, M. S. Comments on 'Dynamics of a spacecraft during Gravitational biology on the space station [NASA-CR-171764] p 28 N84-20622 [SAE PAPER 831133] p 75 A84-29063 extension of flexible appendages' p32 A84-17370 HODGSON, E. W, JR. KELLERMEIER, H. JANKOWITSCH, P. Regenerate non-venting thermal control subsystem for Energy from space - A vision of the future A standardized propulsion module for future extravehicular activity p69 A84-21477 communications satellites in the 2000 to 3000 kg dass [SAE PAPER 831151 ] p 24 A84-29076 [AIAA PAPER 84-0727] p 62 A84-25292 JANSSENS, F. KEMPF, R. F. HOLDEMAN, J. D. Derivation and combination of impedance matrices for Space Shuttle, private enterprise and intellectual On modeling dilution jet flowfields flexible satellites [AIAA PAPER 84-1379] p 58 A84-44183 (ESA-STR-209J p 43 N84-216O4 properties in the context of space manufacturing p72 A84-22341 HOOK.W. R. JASPER, W. J. KHANG, V. T. An alternate concept for expanding man's presence in Control of large space structures Software production in a large space project The SPOT [AIAA PAPER 84-0081] p 32 A84-17866 mission center p78 N84-14752 [NASA-TM-64617] p7 N84-15172 JHA.V. K. KHOT, N. S. HORSTEIN, M. Computer aided synthesis of a satellite antenna structure Optimization of shallow trusses against limit point Land-mobile communications satellite system design with probabilistic constraints p 21 N84-19899 [AIAA PAPER 844)753] p5 A84-2S308 Dynamic behaviour of a satellite antenna structure in instability p20 A84-23366 KIBBLEWHITE, J. HOSENBALL, S. N. random vibration environment p 42 N84-19900 Coherent arrays of separate optical telescopes in space Space Shuttle, private enterprise and intellectual JOHANSEN, K. F. project Trio p3 A84-15363 properties in the context of space manufacturing A hardware demonstration of control for a flexible KIDD, A. M. p72 A84-22341 offset-feed antenna p 31 A84-13321 MSAT mobile communication demonstration satellite JOHNSON, T. L HUANG, C.-C. system and bus tradeoff considerations Aggregate models for distributed parameter systems Application of laser interferometry to robotics [AIAA PAPER 84-0751 ] p 48 A84-25306 with applications to flexible air and spacecraft p58 A84-28541 KIEHNE, N. p31 A84-11945 Coordinate transformation assembly The German Spacelab mission D1 p69 A84-17762 p 75 A84-28579 JOHNSTON, R. S. Crew and life support EVA p11 N84-18279 KIYA, M. HUANG, W. JONGEWARD, a A. Large Deployable Reflector (LDR) - A concept for an Static shape forming for an electrostatically controlled Plasma sheath structure surrounding a large powered orbiting sutamlllimeter-infrared telescope for the 1990s membrane mirror p 16 A84-25551 p66 A84-14586 HUBER.G. [AIAA PAPER 84-0329] p 46 A84-18025 KLEINAU, W. Effect of temperature, moisture and radiation exposures JORGENSEN, P. Servicing vehicle for satellites and platforms in low earth on composite mechanical properties p 55 A84-28900 Autonomous navigation of geosynchronous satellites orbits HUGHES, P. C. using the Navstar Global Positioning System [DGLR PAPER 83-102] p6 A84-29666 Torque from solar radiation pressure gradient during p45 A84-15671 KLINE, R. eclipse p31 A84-12489 JOSUN, D. A program to develop efficient manned operations in Attitude stability for the yaw-wheel class of orbiting Mechanical wraparound contacted cell for low cost gyrostats p33 A84-19675 space arrays p 48 A84-22982 [AAS PAPER 83-207] p 76 A84-29857

B-5 KLUESENER, M. F. PERSONAL AUTHOR INDEX

KLUESENER, M. f. LARSON, V. R. LONGUSKI, J. M. The effects of the space environment on damping A parametric study of space transfer-propulsion Simulation of the Galileo spacecraft axial - Delta-V materials and damping designs on flexible structures algorithm p66 A84-11938 p56 N84-17217 [IAF PAPER 83-401] p61 A84-13397 LOOKE, T. D. KNABE, W. LAUB, A. J. Stability enhancement of a flejrjble robot manipulator The residual gravitational field of orbital space stations Controllability and observability criteria for multivariable [AD-A134185] s p 59 N84-16807 [DGLR PAPER 83-089] p 75 A84-29656 linear second-order models p 35 A84-25516 LOURENCAO, P. T. D. M. KNEPP, D. l_ LAUX, U. Sensitivity analysis of the influence of the flexibility of The effects of aperture antennas after signal propagation The thermal design of the European complement of solar panels on the attitude dynamics of artificial through anisotropic ionized media FSLP satellites [ AD-A138286] p 52 N84-21781 [SAE PAPER 831144] p 24 A84-29071 [INPE-2763-PRE/337] p 39 N84-16232 LEE, Y. W. KOCH, D. G. Capture of satellite stabilized by gravity gradient with a New elements for analysis of space frames with tapered A large-area gamma-ray imaging telescope system flexible mast during and after deployment members p 20 N84-14561 [NASA-CR-175435] p 14 N84-20604 [INPE-2749-PRE/325] p 41 N84-19383 LEGENDRE, P. KOELLE, D. E. LOUSHA, J. R. Analytical model of the evolution of orbit parameters GEO space platform economics - Impact of concept, The role of man in space p 72 A84-24627 of a quasi geostationary satellite size, launch mode and lifetime LOVE, G. [IAF PAPER 83-316] p 65 A84-11787 [AIAA PAPER 84-0704] p 74 A84-25281 Data management p 12 N84-18287 LEGER, L. J. LU, B. P. A standardized propulsion module for future Low earth orbit atomic oxygen effects on surfaces Space operations center communications path communications satellites in the 2000 to 3000 kg class [AIAA PAPER 84-0548] p 53 A84-19912 [AIAA PAPER 84-0727] p 62 A84-25292 obscuration p3 A84-15695 LEUNG, M. S. LUDWIG, A. C. Reusable commercial space processing platforms A review of SCATHA satellite results: Charging and [AAS PAPER 83-208] p7 A84-29858 RF systems in space. Volume 1: Space antennas discharging p 50 N84-17254 frequency (SARF) simulation KOONS, H. C. LEVY, J. [AD-A133734] p 49 N84-14395 A review of SCATHA satellite results: Charging and Potential military applications of space platforms and LUMPE, G. discharging .'\: p 50 N84-17254 space stations p 2 A84-13330 Geometrically nonlinear analysis of beam-in-space LEVY, M. E. KOPS, L structures Manufacturing in space; Proceedings of the Winter Rnancing large space projects p 67 A84-15321 [MITT-28] p22 N84-21914 LEY, W. Annual Meeting, Boston, MA, November 13-18,1983 LUNDSTROM, L.-I. p 71 A84-22327 European utilisation aspects for a space station Tele-X - The first step in a satellite communications [IAF PAPER 83-54] p 64 A84-11727 KREEB, H. system for the Nordic countries Heat pipes for the L-SAT communications module LIANG, R. C. [AIAA PAPER 84-0713] p4 A84-25287 The effect of pressure and temperature on radiators p 26 N84-19405 LUST, R. V. time-dependent changes in graphite/epoxy composites KRIKORIAN, A. D. Approximations method for space frame synthesis below the glass transition p 54 A84-21775 Gravitational biology on the space station p 19 A84-10141 [SAE PAPER 831133] p 75 A84-29063 LIKINS, P. W. KRISHNA, R. A degree of controllability definition - Fundamental Environmental effects on the dynamics and control of concepts and application to modal systems M p34 A84-24991 an orbiting large flexible antenna system [NASA-CR-175448] p 42 N84-20627 Manipulator interactive design with interconnected MACCONOCHIE, I. O. KUKULKA, J. flexible elements p 58 A84-25484 Capture-ejector satellites Large area, low cost space solar cells LIN, C. [NASA-TM-85686] p7 N84-15179 p47 A84-22979 Regenerate non-venting thermal control subsystem for MACHLES, G. W. extravehicular activity KULPER, T. B. H. Study of auxiliary propulsion requirements for large Large Deployable Reflector (LDR) - A concept for an [SAE PAPER 831151 ] p 24 A84-29076 space systems. Volume 1: Executive summary orbiting submillimeter-infrared telescope for the 1990s LIN, C. H. [NASA-CR-168193-VOL-1] p 63 N84-12226 p66 A84-14586 Systems engineering aspects of a preliminary Study of auxiliary propulsion requirements for large KUMINECZ, J. F. conceptual design of the space station environmental space systems, volume 2 Low earth orbit atomic oxygen effects on surfaces control and life support system [NASA-CR-168193-VOL-2] p 63 N84-13218 [AIAA PAPER 84-0548] p 53 A84-19912 [SAE PAPER 831109] p5 A84-29044 MACKAY, M. K. KURTH, W. S. LIN, J. C. Active control of large flexible space structures Interpretation of STS-3/plasma diagnostics package ACOSS eleven (Active Control Of Space Structures), p37 N84-14235 results in terms of large space structure plasma volume 1 MACLEAN, B. J. interactions [AD-A135675] p 40 N84-18311 Thermal-mechanical behavior of graphite/magnesium [NASA-CR-173266] p 78 N84-16991 LINDBERG, R. E. composites p 24 A84-28237 KURTZMAN, C. R. Actuator placement considerations for the control of SiC-reinforced-aluminum alloys for aerospace Space applications of Automation, Robotics And large space structures p 20 N84-11199 applications p 54 A84-28242 MAEHL, R. Machine Intelligence Systems (ARAMIS). Volume 3, phase LINDBERG, R. E., JR. The Tiros-based asteroid mission p 2 A84-14762 2: Executive summary On the number and placement of actuators for MAHANEY, J. [NASA-CR-3736] p 59 N84-10582 independent modal space control p 34 A84-24990 Self-shadowing of orbiting trusses Space Applications of Automation, Robotics and UNDSEY, W. C. [NASA-CR-173215] p 25 N84-16565 Machine Intelligence Systems (ARAMIS), phase 2. Volume User manual of the CATSS system (version 1.0) 1: Telepresence technology base development MAHARANA, P. K. communication analysis tool for space station Stability of large flexible damped spacecraft modeled [NASA-CR-3734] p 59 N84-10583 [NASA-CR-171728] p 51 N84-17431 as elastic continua p 35 A84-26845 Space Applications of Automation, Robotics and UNDSTROM, 0. Machine Intelligence Systems (ARAMIS), phase 2. Volume MANDELL, M. J. Erosion of mylar and protection by thin metal films Plasma sheath structure surrounding a large powered 2: Telepresence project applications [AIAA PAPER 83-2636] p 52 A84-10949 [NASA-CR-3735] p 59 N84-10584 spacecraft UPPNER, G. [AIAA PAPER 84-0329] p 46 A84-18025 The attitude and orbit control system for Eureca MANN, J. A. [DGLR PAPER 83-091 ] p 76 A84-29658 New component development for multM 00 kW low-cost LOEWY, R. G. solar array applications p 47 A84-22963 LABEYRIE, A. . Composite structural materials MANOHARAN, M. G. Coherent arrays of separate optical telescopes in space [NASA-CR-173259] p 56 N84-17293 Control structure interactions in large space structures project Trio p3 A84-15363 LOGSDON, J. M. Analysis using energy approach p 35 A84-27934 LAI, J. Y. Space stations - A key to socio-economic benefits from MANSHADI, F. Science platform and attitude subsystem in-flight ..space? p69 A84-19850 Use of electromagnetic models in the optimal control calibration for the Galileo spacecraft p32 A84-17355 Solar power satellites - The institutional challenge of large space antennas p 35 A84-25552 LAI, S. T. p70 A84-21479 MANSOUR, W. M. Analysis and design of leaf-spring flexible joints for Sheath ionization model of beam emissions from large Space stations - The next step in space? driving gyroscopic rotors p 19 A84-11922 spacecrafts [AAS PAPER 83-202] p 76 A84-29855 [AD-A137181] p52 N84-19463 MARDESICH, N. LOMBARD), P. LANGE, f. F. Mechanical wraparound contacted cell for low cost The small transmitter receiver stations in the Sirio Fracture mechanics of ceramics. Volume 5 - Surface space arrays p 48 A84-22982 experiment flaws, statistics, and microcracking p 54 A84-24501 MARSHALL, P. F. [FUB-50-1982] p49 N84-15386 LANIER, J. R, JR. Thermal management system technology development A programmable power processor for high power space LONGDON, N. for space station applications applications p46 A84-18394 Spacelab data book [SAE PAPER 831097] p 24 A84-29032 LANUSSE, A. [ESA-BR-14] p79 N84-18315 MARTIN, A. R. Study of artificial intelligence techniques - Realization LONGMAN, R. W. Mankind's interstellar future p 71 A84-21499 of a highly autonomous experimental robot system On the number and placement of actuators for MARTIN, J. A. p58 A84-25828 independent modal space control p 34 A84-24990 Vertical ascent from earth to geosynchronous orbit LARSEN, R. L A degree of controllability definition - Fundamental [AIAA PAPER 84-0509] p 61 A84-1B141 NASA research in teleoperation and robotics concepts and application to modal systems Capture-ejector satellites p58 A84-28523 p 34 A84-24991 [NASA-TM-85686] p7 N84-15179

B-6 PERSONAL AUTHOR INDEX NOORDAM, J.

MASTRANTONIO, 6. METZLER, E. C. On transient dynamics and stability of large space Orbiting wire as a dynamo: Auxiliary power possibilities Electrically conductive black optical paint structures p 36 A84-29143 for space platforms pSS A84-28553 MOORMAN, J. C. (IFSI-83-3) p49 N84-12653 MEYER, M. S. STEP experiment integration p8 N84-17215 UASUBUCHI, K. Systems engineering aspects of a preliminary MORAIS, B. G. Feasibility of remotely manipulated welding in space. conceptual design of the space station environmental Attitude, control and stabilization p 40 N84-18281 A step in the development of novel joining technologies control and life support system MORTAZAVI, H. R. [NASA-CR-175437] p 60 N84-20857 (SAE PAPER 831109] p5 A84-29O44 Radiation-conduction interaction in large space MATHEWS, M. E. MICHAELS, D. structures Scale model testing for control system parameters of Mechanical wraparound contacted cell for low cost [AIAA PAPER 84-0144] p 23 A84-17911 large structures space arrays p 48 A84-22982 MOSES, J. [AD-A135652] p 41 N84-18313 MIELKE, R. R. Implementation of MACLISP on a large address space MATL0FF, a l_ Airborne antenna pattern calculations computer Interstellar solar sailing - Consideration ot teal and (NASA-CR-173284) p 51 NB4-17436 [DE84-005042] p79 N84-21145 projected sail materials p 62 A84-25344 MIGUORINI, P. MOSES, P. L. MATSUDA, H. S. The small transmitter receiver stations in the Sirio Operational modules for space station construction New fabric structures of carbon fiber experiment [NASA-TM-85772] p 21 N84-21608 p52 A84-17108 [FUB-50-1982] p 49 N84-15386 MOSLEY, W. C. MATTHEWS, P. S. MIJOVIC, J. Space station data management - A system evolving Remote manipulators in space p 57 A84-22336 The effect of pressure and temperature on from changing requirements and a dynamic technology MAYS, C. R. time-dependent changes in graphite/epoxy composites base Space Station Technology. 1983 below the glass transition p 54 A84-21775 (AIAA PAPER 83-2338] p 43 A84-10016 [NASA-CP-2293] p11 N84-18277 MIKULAS, M. M, JR. MOSS.R. MAZZIO, V. F. Stability, vibration and passive damping of partially Using the outgassing test to screen materials for Effect of temperature, moisture and radiation exposures restrained imperfect columns contamination potential p 53 A84-17174 on composite mechanical properties p 55 A84-28900 [NASA-TM-85697] p 37 N84-13608 MRST1K, A. V. MCBRAYER, R. O. Synchronously deployable truss structure RF systems in space. Volume 2: Space-based radar Launch processing for Spacelab 1 [NASA-CASE-LAR-13117-1] p 59 N84-16250 analyses [AIAA PAPER 83-2622] p 64 A84-10965 A manned-machine space station construction [AD-A133735] p 49 N84-14394 HCCARGO, M. concept MULUN, J. P. Effects of combined ultraviolet and oxygen plasma [NASA-TM-85762] p 21 N84-19395 High capacity power systems for space environment on spacecraft thermal control materials MILLER, R. A. [ IAF PAPER 83-421 ] p 44 A84-11816 p27 N84-19449 Simulation of the motion of a Shuttle-attached flexible MURAKAMI, M. HCCLAMROCH, H. manipulator arm p 57 A84-11935 Thermofluidynamics of heat pipes p 27 N84-19423 AGOSS eleven (Active Control Of Space Structures), MILLJGAN, R. J. MURATANI, T. volume 1 Effects of combined ultraviolet and oxygen plasma Computer tools for optimizing orbit use [AD-A135675] p 40 N84-18311 environment on spacecraft thermal control materials [AIAA PAPER 844651 ] p 74 A84-25318 MCCLAMROCH, N. H. p27 N84-19449 Sampled data control of large space structures using MILLS-CURRAN, W. C. constant gain velocity feedback - A negative view Approximations method for space frame synthesis N p46 A84-19169 p 19 A84-10141 NADER), F. MCDONNELL, D. MINSKY, M. L An advanced generation land mobile satellite system The US space station: Potential base for a spacebome Space applications of Automation, Robotics And and its critical technologies p3 A84-15634 microwave facility p 78 N84-16420 Machine Intelligence Systems (ARAMIS). Volume 3, phase NAGATOMO.M. MCCREARY, T. 2: Executive summary Space station - An early experimental solar power Study of a tracking and data acquisition system for the [NASA-CR-3736] p 59 N84-10582 satellite p 70 A84-21487 1990's. Volume 3: TDAS Communication Mission Space Applications of Automation, Robotics and NALBANDIAN, S. J. Model Machine Intelligence Systems (ARAMIS), phase 2. Volume Low concentration ratio solar array structural [NASA-CR-175195] p 79 N84-19371 1: Telepresence technology base development configuration p 17 N84-17225 [NASA-CR-3734] p 59 N84-10583 MCELROY, J. H. NAUCK, J. Space Applications of Automation, Robotics and Space applications at the crossroads; Proceedings of Development trends in Europe on satellite clusters and Machine Intelligence Systems (ARAMIS), phase 2. Volume the Twenty-first Goddard Memorial Symposium, Greenbelt, geostationary platforms 2: Telepresence project applications MO. March 24, 25. 1983 p 64 A84-10883 [AIAA PAPER 84-0703] p 75 A84-25327 (NASA-CR-3735) p 59 N84-10584 MCGEE, G. C. MIRT1CH, M. J. NAUMANN, A. Attitude control and dynamics of the space operations Developing the space frontier; Proceedings of the Resistojet propulsion for large spacecraft systems center p 31 A84-11934 Twenty-ninth Annual Conference. Houston, TX. October [NASA-TM-83489] p 63 N84-11206 MCKAY, C. P. 25-27,1982 p 67 A84-15381 MISEL, J. E. Mission to Mars - The case for a settlement NAZEMETZ, J. A methodology to include static and kinetic friction p67 A84-15092 Geometric modeling of large space antenna effects in Space Shuttle payload transient loads analysis deployment p 22 N84-22225 MCMIUIN, M. L [AIAA PAPER 83-2654] p 30 A84-10956 NEFF, O. Interactive geometry modeling of space station MISRA, A. K. Modem software development tools in space projects conceptual designs p 18 N84-22191 On modeling and simulation of the dynamics of tether on the example of a Spacelab experiment MEESE, R. A. connected satellite systems p30 A84-11933 p49 N84-14761 Welded solar cell interconnection p 19 A84-22965 On the dynamics of a subsatellite system supported by MEI, C. two tethers NEIN, M. E, Component mode synthesis and large deflection [AIAA PAPER 84-0062] p 32 A84-17854 Space platform accommodations p 16 A84-22131 vibrations of complex structures MISRA, M. S. NESMITH, M. F. [NASA-CR-173338] p 21 N84-18680 Thermal-mechanical behavior of graphite/magnesium Self-locking telescoping manipulator arm MEINER, R. C. composites p24 A84-28237 [NASA-CASE-MFS-25906-1] p 59 N84-11761 The solar power satellite - A programme for SiC-reinforced-aluminum alloys for aerospace NETO, O. M. development aid p68 A84-17074 applications p 54 A84-28242 Sensitivity analysis of the Influence of the flexibility ot MEINTEL, A. J, JR. MITCHELL, P. M. solar panels on the attitude dynamics of artificial NASA research in telooperation and robotics Low cost space science and astronomy platforms in satellites p 58 A84-28523 orbit [INPE-2763-PRE/337] p 39 N84-16232 MEIROVITCH, L. [AIAA PAPER 844297] p4 A84-18005 NGUYEN, N. C. MITSUMA, H. Control of large flexible spacecraft by the independent A hardware demonstration of control for a flexible modal-space control method Evaluation of modal testing techniques for spacecraft offset-feed antenna p31 A84-13321 structures p 28 N84-19906 [NASA-CR-3760] p 40 N84-18262 NICAISE, P. 0. MIZERA, P. F. MENG, C. I. Space station attitude control system concept and A review of SCATHA satellite results: Charging and Large space instrumentation to measure the interaction requirements p 37 N84-12234 discharging p SO N84-17254 between space structures and the environment NISHIMOTO, T. S. MIZUNO, T. [AD-A129990] p77 N84-10179 A deployable structure and solar array controls Computer tools for optimizing orbit use experiment for STEP p 39 N84-17227 MESSICK, D. L [AIAA PAPER 84-0651) p 74 AS4-25318 Surface analysis of graphite fiber reinforced polyimide MODI, V. J. NISH1UURA, A. New fabric structures ot carbon fiber composites Some aspects ot simulation studies in spacecraft p52 A84-17108 [NASA-TM-85700] p 55 N84-11220 dynamics p 15 A84-11930 MESSIDORO, P. On modeling and simulation of the dynamics of tether NOOR, A. K. Development of a spacecraft infrared test technique as connected satellite systems p30 A84-11933 Instability analysis of space trusses an alternative to solar simulation: First steps on L-SAT Satellite attitude dynamics and control in the presence p32 A84-16885 thermal model p26 N84-19398 of environmental torques - A brief survey Potential of minicomputer-array processor system for METZ, R. N. p31 A84-12483 nonlinear finite-element analysis p46 A84-20583 Radiating dipole model of interference induced in Transient dynamics during the orbiter based deployment NOORDAM, J. spacecraft circuitry by surface discharges of flexible members Coherent arrays of separate optical telescopes in space [NASA-TP-2240] p 50 N84-16247 [AIAA PAPER 844061] p 34 A84-21285 project Trio p3 A84-15363

B-7 NOWLAN, M. J. PERSONAL AUTHOR INDEX

NOWLAN, M. J. PAUL, W. H. Assessment of the existing ground test technology and Large area space solar cell assemblies Integrity control of carbon fiber reinforced plastics confronting with the Large Space Structures (LSS) p 61 A84-22980 structural elements, phase 1 report requirements. Experimental techniques in structural [TB-TS-11-01/82-A] p56 N84-18416 analysis p 29 N84-21621 PAZICK, P. M. Assessment of the existing ground test technology and RF systems in space. Volume 2: Space-based radar confronting with the Large Space Structures (LSS) analyses requirements. Thermal test techniques ODONNELL, T. [AD-A133735] p 49 N84-14394 p29 N84-21622 Evaluation of spacecraft materials and processes for PEDERSEN, A. Proposals for additions, modifications, and new optical degradation potential p 54 A84-28458 Spacecraft/plasma interactions and their influence on experimental methods. Part 1: Ground tests. Part 2: OKEEFE, K. J. field and particle measurements Flight tests p 15 N84-21623 [ESA-SP-198] p56 N84-17253 The 55-meter-structure flight experiment Study on synthesis and characterization of large space PEDERSEN, K. S. p 6 N84-17233 systems, phase 2. Part 1: Assessment of design OLCOTT, T. International aspects of commercial space activities verification analytical methods. Volume 1: Mechanical Hyperfiltration wash water recovery subsystem - Design [AAS PAPER 83-222] p 77 A84-29866 design PELUS, G. and test results [ESA-CR(P)-1779-VOL-1] p 18 N84-21624 Thermal control of the Tethered Satellite Module [SAE PAPER 831112] p6 A84-29047 Study on synthesis and characterization of large space OLEARY, B. [SAE PAPER 831138] p 24 A84-29067 Thermal control of tethered satellite in a very low altitude systems, phase 2. Part 1: Assessment of design Project space station - Plans for a permanent manned verification analytical methods. Volume 2: Thermal space center p69 A84-21344 aerodynamic mission p27 N84-19444 PENNINGS, N. H. design OLLENDORF, S. [ESA-CR(P)-1779-VOL-2] p 18 N84-21625 Thermal energy management process experiment A Variable Conductance Heat Pipe (VCHP) radiator system for communications payloads p27 N84-19406 POPOVSKII, V. V. p25 N84-17222 Characteristics of the microprocessor implementation Recent and planned developments at the Goddard PEPLJNSKI, D. R. Reactions of high velocity atomic oxygen with carbon of algorithms for the processing of radio signals and noise Space Flight Center in thermal control technology in large antenna arrays p 48 A84-28067 p26 N84-19402 [AIAA PAPER 84-0549] p 53 A84-18159 PERBOS, J. U POSTUCHOW, J. R. OLMSTEAD, O. Technology needs of advanced Earth observation Telecommunication systems for large-scale space Application of a common reflector configuration to a multimission satellite of the 90's spacecraft manufacturing activity [NASA-CR-3698] p9 N84-17248 [AAS PAPER 83-216] p 48 A84-29861 [IAF PAPER 83-60] p1 A84-11731 PERONI, I. POUX, C. OLSEN, D. E. Tests and prediction of composite material viscoelastic Thermal cycling tests in space environment simulation The effect of mass and stiffness changes on the damping chambers p 26 N84-19401 factor in a large space structure as represented by the behaviour for large space structure [IAF PAPER 83-418] p 30 A84-11815 POWELL, L E. CSDL 2 model Architectural options and development issues [AD-A136984] p 42 N84-19465 PEROTTO, V. Heat pipes for the L-SAT communications module p4 A84-24633 OLSON, R. PRADO, J. V. Probable missions and transportation scenarios to use radiators p26 N84-19405 PERRET, A. Management of the radiolink of the solar sail spacecraft regenerative life support systems by radio-amateurs [AAS PAPER 83-201J p 76 A84-29854 Management of the radiolink of the solar sail spacecraft by radio-amateurs [IAF PAPER 83-447] p 44 A84-11823 OREN, J. A. PREUSS, L. A contact conductance interface for a space [IAF PAPER 83-447] p 44 A84-11823 PETERS, G. Spacecraft thermal control selection for seven years of constructable heat pipe radiator lifetime in synchronous orbit [SAE PAPER 831101] p24 A84-29036 ESA space station activities [IAF PAPER 83-30] p 64 A84-11722 [MBB-UR-584-82-OE] p 25 N84-11200 Flexible radiator thermal vacuum test report PRICE, D. F. [NASA-CR-171764] p 28 N84-20622 PETERS, J. M. Integrated water management system - Description and Flexible radiator system Instability analysis of space trusses test results [NASA-CR-171765] p 28 N84-20623 p32 A84-16885 [SAE PAPER 831111] p6 A84-29046 OREN, J. R. PETERS, R. Hyperfiltration wash water recovery subsystem - Design Flexible radiator system: Executive summary Digital technologies and systems for geostationary orbit and test results [NASA-CR-171766] p 28 N84-20624 satellites [SAE PAPER 831112] p6 A84-29047 ORLANDO, N. E. [AIAA PAPER 84-0749] p 74 A84-25304 PRICE, G. A. A system for intelligent teleoperation research PFEIFER, K. A flexible structure controller design method using mode [AIAA PAPER 83-2376] p 57 A84-10070 Local stability of sandwich structures with thin fibre residualization and output feedback p32 A84-17369 OSBORNE, R. S. reinforced face skins for space application PRITCHARD, E. B. An alternate concept for expanding man's presence in [MBB-UD-381-83-OE] p 19 A84-22859 Overview of NASA space station activities PFEIFFER, B. R. K. [IAF PAPER 83-48] p1 A84-11726 [NASA-TM-84617] p7 N84-1S172 The Spacelab program - The management of the Integrated requirements for a space station OSHIMA, K. program, problems encountered and the solutions p4 A84-24628 Thermofluidynamics of heat pipes p 27 N84-19423 adopted p3 AB4-15325 PROGAR, D. J. OTT, J. H. PHILLIPS, A. Surface analysis of graphite fiber reinforced polyimide MultJbeam phased arrays - Application to Simulated space radiation effects on dielectrics and composites SOC/Free-Flyer communication system coatings p54 A84-20682 [NASA-TM-85700] p 55 N84-11220 p45 A84-15641 PIGNOLET, G. PRUETT, E. C. Making the high frontier highly visible with a solar sail Space telescope race to the moon [NASA-CR-170948] p 78 N84-16097 [AAS PAPER 83-226] p 62 A84-29869 PURDY, D. Structures and mechanisms p 21 N84-18286 PACK, G. J. PILAND, R. O. PURVIS, C. K. New component development for multi-100 kW low-cost A system study of the solar power satellite concept The role of potential barrier formation in spacecraft solar array applications p 47 A84-2Z963 p70 A84-21480* charging p 50 N84-17269 PAILER, N. PINE, V. W. Erosion of mylar and protection by thin metal films Dielectric charging in space - Ground test data and model [AIAA PAPER 83-2636] p 52 A84-10949 verification p 47 A84-20709 PANtTZ, H. J. POLLARD, H. E. Operational planning, simulation, and performance of Technical aspects of the Intelsat V solar array OUATTRONE, P. D. the German Spacelab mission D1 p 69 A84-17763 p 47 A84-22962 Environmental Control and Life Support for an PAPACCIA, M. PONTOPPIDAN, K. evolutionary Space Station Heat pipes for the L-SAT communications module Unfuriable offset antenna design for multipurpose [SAE PAPER 831108) p5 A84-29043 radiators p26 N84-19405 applications QUIRK, J. A. PAPA0IANNIS, M. D. [AIAA PAPER 84-0659] p 16 A84-25259 Control of flexible spacecraft by optimal model Natural selection of stellar civilizations by the limits of following p 36 N84-12222 growth PONZI, U. [IAF PAPER 83-272] p 65 A84-11779 Study on synthesis and characterization of large space PARKINSON, R. C. systems, phase 2. Part 2: Proposals for additions, Manned planetary missions? p71 A84-21497 modifications and new analytical methods, volume 1 PATACCIA, M. [ESA-CR(P)-1779-VOL-3] P 43 N84-21611 RAAB.B. Development of a spacecraft infrared test technique as Simplified models and computational schemes of the The Fairchild Leasecraft system - A an alternative to solar simulation: First steps on L-SAT aerodynamic load p 28 N84-21614 commercially-operated platform for science and business thermal model p 26 N84-19398 Study on synthesis and characterization of large space in space PATTERSON, R. E. systems, phase 2. Part 2: Proposals for additions, [IAF PAPER 83-232] p 65 A84-11773 Study of multi-kilowatt solar arrays for Earth orbit modifications and new analytical methods, volume 2 RADANY, E. applications [ESA-CR(P)-1779-VOL-4] p 29 N84-21616 Potential military applications of space platforms and [NASA-CR-170939] p 49 NS4-12634 Study on synthesis and characterization of large space space stations p2 A84-13330 PAUL, G. R. systems, phase 2. Part 3: Experimental design verification RAJARAM, N. S. Cracked inner layer foil in high-density multilayer printed techniques Knowledge based systems for intelligent robotics wiring boards p 53 A84-17200 [ESA-CR(P)-1779-VOL-5] p 18 N84-21620 p57 A84-15667

B-8 PERSONAL AUTHOR INDEX SHARP, P. W.

RAJ ARAM, S. ROBINSON, U M. SAUNDERS, C. a Identification of large flexible structures mass'stiftness Lessons learned during the first year of the TDRSS Surface accuracy measurement sensor test on a and damping from on-orbtt experiments [AIAA PAPER 84-0687] p 74 A84-25319 50-meter antenna surface model p34 AS4-24995 RODRIGUEZ, G. [NASA-TM-85689] p 17 N84-18427 HAULER, J. Model error estimation for distributed systems described SAVAGE, C. J. NASA's geostationary communications platform by elliptic equations p 15 A84-11946 A Variable Conductance Heat Pipe (VCHP) radiator program RODRIGUEZ, G. E. system for communications payloads p27 N84-19408 [AIAA PAPER W-0702] p5 A84-25326 Integrated Flywheel Technology, 1983 SAX, H. RANEY, W. P. [NASA-CP-2290] p78 N84-12228 European utilisation aspects for a space station [IAF PAPER 83-54] p 64 A84-11727 Space station architectural issues as viewed by the user ROEBELEN, G. J, JR. community • Applications p 4 A84-24634 Regenerable non-venting thermal control subsystem for SAZONOV, V. V. RANKIN, 0. G. extravehicular activity Periodic osculations ol a gyrostat satellite with respect to the centers of mass in a circular orbit Thermal manaBement system technology development [SAE PAPER 831151 ] p 24 A84-29076 for space station applications p33 A84-19728 ROEDERER, A. [SAE PAPER 831097] p 24 A84-29032 SCHAECHTER, D. B. Unfuriable offset antenna design for multipurpose RATH, J. A hardware demonstration of control for a flexible applications Photovoltaic solar arrays leading to a candidate space offset-feed antenna p 31 A84-13321 [AIAA PAPER 84-0659] p 16 A84-25259 power system in the regime beyond 100 kW SCHAEFER, W. [IAF PAPER 83-422] P 44 AB4-11817 ROGERS, R. P. Unturtable offset antenna design for multipurpose RAZZAO, Z. IRSIM: A program for the calculation of infrared flux applications Stability, vibration and passive damping of partially intensity incident on a spacecraft inside a test chamber [AIAA PAPER 84-0659] p 16 A84-2S259 restrained imperfect columns p26 NB4-1940Q SCHAELUG.R. [NASA-TM-85697] p 37 N84-13608 ROSE, J. T. Unfuriable offset antenna design for multipurpose REDOING, D. C. Role of a space station in pharmaceutical applications Highly efficient, very low-thrust transfer to manufacturing p 73 A84-24632 [AIAA PAPER 844)659] p 16 A84-25259 geosynchronous orbit - Exact and approximate solutions ROSENBERG, S. D. SCHARTEL, W. A. p 61 A84-24980 Auxiliary propulsion p11 N84-18283 Technology needs of advanced Earth observation Optimal low-thrust transfers to synchronous orbit ROSSI, M. spacecraft p 62 A84-24981 Number crunching on the ACOSS Model No. 2 [NASA-CR-3698] p9 N84-17248 REED, W. p33 A84-19128 SCHMIDT, R. Space telescope ROTHBLATT, M. A. Modern software development tools in space projects [NASA-CR-170948] p 78 NB4-16097 Telecommunication systems for large-scale space on the example of a Spacelab experiment REIBALDI, G. manufacturing activity p49 N84-14761 Thermo-mechanical behaviour of CFRP tubes for space [MS PAPER 83-216] p 48 A84-29861 SCHMIT, l_ A. Approximations method for space frame synthesis structures A legal charter for non-governmental space [IAF PAPER 83-417] p 22 A84-11814 industrialization p19 A84-10141 REINEL, K. [AAS PAPER 83-225] p 77 A84-29868 SCHNEIDER, H. J. Hardware simulation of spacecraft dynamics and Modem software development tools in space projects ROUSSEL, H. control p30 A84-11932 on the example of a Spacelab experiment Coherent arrays of separate optical telescopes in space RENNER, U. p49 N84-14761 project Trio p3 A84-15363 Development trends in Europe on satellite clusters and SCHNEIDER, W. C. geostationary platforms ROWNTREE, R. A. Overview of space station operations [AIAA PAPER 84-0703] p 75 A84-25327 Thermal conductance and torque of thin section [IAF PAPER 83-38] p 64 A84-11723 RENTON, J. D. four-point contact ball bearings in vacuum SCHOLL, F. W. The beam-like behavior of space trusses [ESA-ESTL-54] p 25 N84-15562 Communications, tracking, and docking on the Space p 19 A84-21517 RUNAVOT, J. J. Station p 45 A84-1S640 REYNAUD, A. H. Payload placing using an operational support platform SCHUBERT, F. H. Canadian Attitude Sensing Experimental Package [IAF PAPER 83-44] p1 A84-11724 Electrochemical and steam-desorbed amine CO2 (CASEP) p70 N84-17223 RUNGE, F. C. concentration Subsystem comparison REYSA, R. P. STEP flight experiments Large Deployable Reflector [SAE PAPER 831120] p6 A84-29054 Integrated water management system - description and (LDR) telescope ~p8 N84-17231 Phase change water recovery techniques - Vapor test results RUSSELL, D. A. compression distillation and thermoelectric/membrane [SAE PAPER 831111] p6 A84-29046 Simulated space radiation effects on dielectrics and concepts [SAE PAPER 831122] p6 A84-29056 Hyperflltration wash water recovery subsystem - Design coatings p 54 A84-20682 and test results SCIESZKO, J. L [SAE PAPER 831112] p6 A84-29047 Analysis and design of leaf-spring flexible joints for driving gyroscopic rotors p 19 A84-11922 RHODES, M. D. SOOTT-MONCK, J. A manned-machine space station construction SACCHI, E. New directions in solar array development concept p47 A84-22958 [NASA-TM-85762] p 21 N84-19395 The thermal design of L-SAT large telecommunication satellite p27 N84-19414 SCOTT, S. J. Construction concept for erecting an offset-fed SACKETT, l_ L. Operational modules for space station construction antenna A simulator to study dynamic interaction of the Space [NASA-TM-85772] p 21 NB4-21608 [NASA-TM-85774] p 60 N84-20626 Shuttle on-orbit flight control system with deployed flexible SEIBERT, G. RICE, J. S. payloads p35 A84-26717 Utilisation of the European retrieval carrier EURECA for Multibeam phased arrays - Application to SADIN, S. R. life science research p65 A84-11753 SOC/Free-Ryer communication system NASA priority technologies SELG, R. J. P45 A84-15641 [IAF PAPER 83-345] p1 A84-11793 Experiment data communications (48 Mbit/s) between RICE, R. R. SAGE.K. Spacelab, the Space Shuttle and the ground Space station energy sizing p4() N84-12233 Geometric modeling of large space antenna p44 A84-10396 The Boeing flywheel study p37 N84-1223S deployment p22 N84-22225 SESSIONS, B. RIED, R. C. SAGGESE.E. Heat pipes for the L-SAT communications module Control structure interactions in large space structures The small transmitter receiver stations in the Sirio radiators p26 N84-19405 Analysis using energy approach p 35 A84-27934 experiment SEYL, J. W. RIEDLER, W. [FUB-50-1982] p49 N84-15386 Space station communications and tracking equipment Radiation characteristics of array antennas with SAINT-AUBERT, P. management/control system p 45 AB4-15639 disturbed aperture coverage p 40 A84-26516 Application of a common reflector configuration to a SGUBINI, S. RIEGER, R. muttimission satellite of the 90's Finite element formulations for tensioned members Digital technologies and systems for geostationary orbH [IAF PAPER 83-60] p1 A84-11731 p21 N84-21615 SAINT-AUBERT, PR satellites Computational savings in view factor evaluation on mode [AIAA PAPER 84-0749] p 74 A84-25304 Utilization of electric propulsion lor communication prescreening p 29 N84-21618 RILEY, V. SHAH, S. [AIAA PAPER 844)729] p 62 A84-25293 A voice interactive system for aiding and documentation MatrixpQ - Application to large space structure control SAMUELS, R. of space-based tasks design problems p 16 A84-19129 The STEP/STAC8EAM experiment technology [AIAA PAPER 83-2355] p 43 A84-10025 development for very large solar array deployers SHANBHAG, R. M. RUTER, J. E, JR. p8 N84-17220 Tme domain analysis and synthesis of robust controllers Assessment of reliability of ceramic materials SANDAR, T. S. for large scale LOG (Linear Quadratic Gaussian) p54 A84-24508 Dynamic behaviour of a satellite antenna structure in regulators ROBERTSON, K. a random vibration environment p 42 N84-19900 [AD-A137760] p 43 N84-21172 SM4DFOm>,S. SHARP, Q.L. [NASA-CR-170948] p 78 N84-16097 Erosion of mylar and protection by thin metal films Reduced domestic satellite orbit spacing ROBINSON, J. C. [AIAA PAPER 83-2636] p 52 A84-10949 [AIAA PAPER 844)652] p 73 A84-2S253 Effects of combined ultraviolet and oxygen plasma SANKAR, T. S. SHARP, P. W. environment on spacecraft thermal control materials Computer aided synthesis o< a satellite antenna structure Evolutionary concepts for a space station and the P27 N84-19449 with probabilistic constraints p 21 N84-19899 relevant utilisation potential p 5 A84-26926 B-9 SHEFFIELD, J. W. PERSONAL AUTHOR INDEX

SHEFFIELD, J. W. STANLEY, A. TAYLOR, T. C. Weight characteristics of future spacecraft thermal Digital technologies and systems for geostationary orbit Low cost space science and astronomy platforms in management systems satellites orbit [AIAA PAPER 84-0054] p 23 A84-17850 [AIAA PAPER 84-0749] p 74 A84-25304 [AIAA PAPER 84-0297] p 4 A84-18005 SHENAR, J. STATLER, R. L TEASDALE, W. E. Control of large flexible spacecraft by the independent Prediction of solar cell performance in space A communications system conceptual design for a low modal-space control method p48 A84-22997 earth orbiting Manned Space Station p 45 A84-15643 [NASA-CR-3760] p40 N84-18262 STEELS, R. TEMPLEMAN, A. B. SHEPPARD, J. S. Development and application of new technologies in the A heuristic method for the design of minimum weight Design and development of an advanced solar array ESA Olympus Programme trusses using discrete member sizes p 15 A84-16841 drive mechanism p 17 N84-18457 [AIAA PAPER 84-0706] p 4 A84-25282 TENNEN, l_ I. SHERMAN, A. STEIMLE, H. Jurisprudential philosophies of the art of living in space NASA needs and trends in cryogenic cooling The German Spacelab mission D1 p 69 AB4-17762 The transnational imperative p25 N84-15329 STEINBRONN, O. [IAF PAPER 82-IISL-38] p 68 A84-17054 SHIRAKI, K. Space station needs, attributes and architectural TEREKHOVA, G. A. Evaluation of modal testing techniques for spacecraft options. Summary of major study activities and results. Geodetic control of the reflectors of large antennas structures p 28 N84-19906 Space station program observations p31 A84-15785 SHOOSMITH, J. N. [NASA-CR-173345] p11 N84-18275 TESTER, R. R. Computer-Aided Geometry Modeling STERN, T. G. Space logistics [NASA-CP-2272] p 18 N84-22179 Photovoltaic concentrator pointing dynamics and plasma [IAF PAPER 83-24] p 64 A84-11719 SHRIVASTAVA, S. K. interaction study p 50 N84-17224 Satellite attitude dynamics and control in the presence THIEL, E. D. STERNS, P. M. Space applications of Automation, Robotics And of environmental torques - A brief survey Jurisprudentjal philosophies of the art of living in space p31 A84-12483 Machine Intelligence Systems (ARAMIS). Volume 3, phase The transnational imperative 2: Executive summary Stability of large flexible damped spacecraft modeled [IAF PAPER 82-IISL-38] p 68 A84-17054 as elastic continua p 35 A84-26845 [NASA-CR-3736] p 59 N84-10582 STILLWELL, R. P. Control structure interactions in large space structures Space Applications of Automation, Robotics and Current collection from the space plasma through Analysis using energy approach p 35 A84-27934 Machine Intelligence Systems (ARAMIS), phase 2. Volume defects in high voltage solar array insulation SHU, C. F. 1: Telepresence technology base development p49 N84-15970 Advanced composite antenna reflectors for [NASA-CR-3734] p 59 N84-10583 communications satellites p 53 A84-17151 STOFEL, E. J. Space Applications of Automation, Robotics and SIMMONS, B. J. Welded solar cell interconnection p 19 A84-22965 Machine Intelligence Systems (ARAMIS), phase 2. Volume Scale model testing for control system parameters of STOKER, C. 2: Telepresence project applications large structures Mission to Mars - The case for a settlement [NASA-CR-3735] p 59 N84-10584 [AD-A135652] p 41 N84-18313 p67 A84-15092 THOMPSON, B. S. SIMPSON, J. A. STOY, I. B. A variational theorem for the viscoelastodynamic Pyroelectric materials as electronic pulse detectors of Power-economical considerations for the integration of analysis of high-speed linkage machinery fabricated from ultraheavy nuclei p 72 A84-23440 terrestrial and extraterrestrial solar generators into existing composite materials SINCARSIN, G. B. power generation systems p 71 A84-21488 [ASME PAPER 83-DET-6] p 55 A84-29101 Torque from solar radiation pressure gradient during STROHKORB, G. A. THORNTON, E. A. eclipse p31 A84-12489 Potential of minicomputer-array processor system for Self-shadowing of orbiting trusses SINGH, N. nonlinear finite-element analysis p 46 A84-20583 [NASA-CR-173215] p 25 N84-16565 The Alpha-Helix Concept Innovative utilization of the STUART, D. G. THYFAULT, D. V. Space Station Program. A report to the National Automation, Robotics, and Machine Intelligence Decentralized control of a large space structure using Aeronautical and Space Administration requesting Systems (ARAMIS) in space manufacturing direct output feedback establishment of a Sensory Physiology Laboratory on the p58 A84-22337 [AD-A136781] p 41 N84-19464 Space Station STUMP, C. W. TILTON, E. I-, Ml [NASA-CR-175436] p 14 N84-20610 Surface accuracy measurement sensor test on a Overview of NASA space station activities SINGH, R. P. 50-meter antenna surface model [IAF PAPER 83-48] p1 A84-11726 Manipulator interactive design with interconnected [NASA-TM-85689] p 17 N84-16427 flexible elements p 58 A84-25484 TODD, M. J. SKELTON, R. E. STURTIVANT, G. J. Thermal conductance and torque of thin section BAe reaction wheels for Olympus p 17 N84-18475 Determination of critical parameters in large flexible four-point contact ball bearings in vacuum space structures with uncertain modal data SU, Y. T. [ESA-ESTL-54] p 25 N84-15562 p33 A84-20047 User manual of the CATSS system (version 1.0) TONG, 0. SKOOG, A. I. communication analysis tool for space station Time phased introduction of advanced technologies - The complementary roles of existing and advanced [NASA-CR-171728] p 51 N84-17431 Its impact on orbit/spectrum conservation environmental, thermal control and life support technology SUDDATH, J. H. [AIAA PAPER 84-0653] p 74 A84-25254 for space stations p79 N84-19429 Application of beam power technology to a space TSANG, C. S. SLONE, H. O. station p45 A84-15642 User manual of the CATSS system (version 1.0) NASA priority technologies SUNG, C. K. communication analysis tool for space station [IAF PAPER 83-345] p1 A84-11793 A variational theorem for the viscoelastodynamic [NASA-CR-171728] p 51 N84-17431 SMITH, S. O. analysis of high-speed linkage machinery fabricated from TU.K. Radiation-conduction interaction in large space composite materials A communications system conceptual design for a low structures [ASME PAPER 83-DET-6] p 55 A84-29101 earth orbiting Manned Space Station p45 A84-15S43 [AIAA PAPER 84-0144] p 23 A84-17911 SWAN, P. TUNG, F. C. SMITH, W. W. Erosion of mylar and protection by thin metal films ACOSS Fourteen (Active Control of Space Structures) Study of auxiliary propulsion requirements for large [AIAA PAPER 83-2636] p 52 A84-10949 [AD-A133411] ' p38 N84-15181 space systems. Volume 1: Executive summary SWANSON, P. N. TURNER, J. D. [NASA-CR-168193-VOL-1] p 63 N84-12226 Large Deployable Reflector (LDR) - A concept for an Closed-form solutions for feedback control with terminal Study of auxiliary propulsion requirements for large orbiting submillimeter-infrared telescope for the 1990s constraints p36 A84-29471 space systems, volume 2 p66 A84-14586 [NASA-CR-168193-VOL-2] p 63 N84-13218 TUTTLE, J. Potential military applications of space platforms and SOLLFREY, W. space stations p2 A84-13330 The flexural behavior of PACSAT (passive TUZZOUNO, A. J. communication satellite) in orbit Pyroelectric materials as electronic pulse detectors of [AD-A131406] p36 N84-1119S TAN, a B. T. ultraheavy nuclei p72 A84-23440 SOOP, E. M. Spacecraft thermal balance testing using infrared lamps Introduction to geostationary orbits on a dummy spacecraft p 26 N84-19399 [ESA-SP-1053] p80 NS4-21590 TANKERSLY, B. C. u SPERBER, R. Large deployable antenna flight experiment for the Why don't we use ton propulsion? UEDA, N. [AIAA PAPER 84-0730] p 62 A84-25294 Space Technology Experiments Platform (STEP) p8 N84-17232 New fabric structures of carbon fiber SPIERS, R. B. p52 A84-17108 Surface accuracy measurement sensor test on a TAUSSIG, R. T. 50-meter antenna surface model Multi-megawatt space power thermal management [NASA-TM-85689] p 17 N84-16427 system requirements SPITZER, M. B. [AIAA PAPER 84-0056] p 23 A84-21284 Large area space solar cell assemblies TAUTZ, M. F. VALEUTIAN, D. p 61 A84-22980 Sheath ionization model of beam emissions from large Utilization of electric propulsion for communication SRINIVASAN, R. spacecrafts satellites On modeling dilution jet flowfields [AD-A137181] p52 N84-19463 [AIAA PAPER 84-0729] p 62 A84-25293 [AIAA PAPER 84-1379] p 58 A84-44183 TAVARES, S. A. VAN GRIETHUYSEN, V. J. STAHLE, C. V., JR. Capture of satellite stabilized by gravity gradient with a Weight characteristics of future spacecraft thermal Investigation of articulated panel dynamics flexible mast during and after deployment management systems p40 N84-17230 [INPE-2749-PRE/325] p 41 N84-19383 [AIAA PAPER 84-0054] p 23 A84-17850

B-10 PERSONAL AUTHOR INDEX ZINNER, E.

VAN SPAENDONK, R. A. C. M. WALKER, D. H. Improved orbit utilization using auxiliary feeds in existing Prediction of solar cell performance in space earth terminals p 46 A84-20647 p48 A84-22997 XU, D. M. VANDERVELDE, W. E. WALKER, J. B. On modeling and simulation of the dynamics of tether Reliability issues in active control of large flexible space Spacecraft thermal balance testing using infrared lamps connected satellite systems p 30 A84-11933 structures on a dummy spacecraft p 26 N84-19399 [NASA-CR-175341] p 39 N84-16248 WALKER, R. VANHEMS, M. M. Erosion of mylar and protection by thin metal films The contract p2 A84-15304 [AIAA PAPER 83-2636] p 52 A84-10949 VANVAUCENBURG, C. N. YATES, D. F. Matrix(X) - Application to large space structure control A heuristic method for the design of minimum weight Space telescope design problems p 16 A84-19129 [NASA-CR-170948] p 78 N84-16O97 trusses using discrete member sizes p 15 A84-16841 WALKLET, D. C. VEIT, A. YEDAVALU, R. K. Alternative strategies for space station financing Space telescope: Solar array primary development Determination of critical parameters in large flexible [NASA-CR-175412] p 80 N84-21437 mechanism p 51 N84-18458 space structures with uncertain modal data VELMAN, J. R. WALLSOM, R. E. p33 A84-20047 A design strategy for multiple payload pointing from a Synchronously deployable truss structure Time domain analysis and synthesis of robust controllers three axis stabilized spacecraft [NASA-CASE-LAR-13117-1] p 59 N84-16250 for large scale LOG (Linear Quadratic Gaussian) [AIAA PAPER 84-0566] p 33 A84-18168 A manned-machine space station construction regulators VELUPILLAI, D. concept [AD-A137760] p43 N84-21172 Space 1991 p 71 A84-21720 [NASA-TM-85762] p 21 N84-19395 YOUNG, L E. VENDURA, G. J. WANG, S. J. Solar array Shuttle flight experiment - Hardware Welded solar cell interconnection p 19 A84-22965 Dynamics and control of a large space antenna development and testing p 47 A84-22961 VENERI, R. p 32 A84-17361 The thermal design of L-SAT large telecommunication WEEKS, G. E. satellite p 27 N84-19414 Finite element analysis of a deployable space VENKAYYA, V. B. structure p 38 N84-16056 ZHUKHOVITSKIY, Y. M. Optimization of shallow trusses against limit point WEIGELT, G. Second All-Union Seminar on Hydromechanics and instability p 20 A84-23366 Coherent arrays of separate optical telescopes in space Heat-Mass Transfer in Weightlessness. Abstracts of VESTEWIG, R. project Trio p3 A84-15363 reports: Table of contents A voice interactive system for aiding and documentation WEIJERS, G. A. [NASA-TM-77534] p 26 N84-18576 of space-based tasks Experiment data communications (48 Mbit/s) between ZILANI, M. [AIAA PAPER 83-2355] p 43 A84-10025 Spacelab, the Space Shuttle and the ground Design and development of the INTELSAT V VIGERON, F. R. p44 A84-10396 graphite-epoxy central thrust tube p 19 A84-22153 Flight test of a synthetic aperture radar antenna using WELLS, R. ZIMCIK, D. G. STEP p9 N84-17237 Molecular contamination math model support Right test of a synthetic aperture radar antenna using VIGNERON, F. R. [NASA-CR-170899] p 77 N84-10174 STEP p 9 N84-17237 Simulation of the motion of a Shuttle-attached flexible WESTPHAL, W. ZIMMERMAN, R. J. manipulator arm p 57 A84-11935 Photovoltaic solar arrays leading to a candidate space A communications system conceptual design for a low VILKE, V. G. power system in the regime beyond 100 kW earth orbiting Manned Space Station p 45 A84-15643 Motion of a symmetric satellite about the center of mass [IAF PAPER 83-422] p 44 A84-11817 ZINNER, E. in circular orbit in the presence of flexible viscoelastic WHITE, F. Erosion of mylar and protection by thin metal films rods p35 A84-26977 Understanding space settlements as human systems [AIAA PAPER 83-2636] p 52 A84-10949 VILLAEYS, J. [AAS PAPER 83-204] p 76 A84-29856 Management of the radiolink of the solar sail spacecraft WHITE, K. P., Ill by radio-amateurs Systems considerations in mosaic focal planes [IAF PAPER 83-447] p 44 A84-11823 p 75 A84-28576 VINOPAL, T. WHITT, A. S. Probable missions and transportation scenarios to use Space manufacturing 1983; Proceedings of the Sixth regenerative life support systems Conference, Princeton University, Princeton, NJ, May 9-12, [AAS PAPER 83-201] p 76 A84-29854 1983 p 76 A84-29852 VISENTINE, J. T. WIBERLEY, S. E. Low earth orbit atomic oxygen effects on surfaces Composite structural materials [AIAA PAPER 84-0548] p 53 A84-19912 [NASA-CR-173259] p 56 N84-17293 VISWANATHAN, C. N. WIGHTMAN, J. P. A degree of controllability definition - Fundamental Surface analysis of graphite fiber reinforced polyimide concepts and application to modal systems composites p34 A84-24991 [NASA-TM-85700] p 55 N84-11220 VOLAND, R. T. WIGOTSKY, V. Stability, vibration and passive damping of partially Higher temperature composite joints survive elimination restrained imperfect columns tests p55 A84-29565 [NASA-TM-85697] p 37 N84-13608 Graphite/polyimide joints extend temperature limits VON OER LJPPE, J. K. p55 A84-29572 The Spacelab test program WILLIAMS, F. W. [AIAA PAPER 83-2685] p 66 A84-13376 Buckling and vibration of any prismatic assembly of shear VON PUTTKAMER, J. and compression loaded anisotropic plates with an With the Space Shuttle towards space industrialization arbitrary supporting structure p 23 A84-14050 p75 A84-28975 vibration characteristics of self-expanding stayed VONALT, C. columns for use in space p 34 A84-21237 Feasibility of remotely manipulated welding in space. WINKLER, H. E. A step in the development of novel joining technologies Integrated water management system - Description and [NASA-CR-175437] • p 60 N84-20857 test results VONTIESENHAUSEN, G. [SAE PAPER 831111] p6 A84-29046 Tethers in space: Birth and growth of a new avenue WOLLENHAUPT, H. to space utilization A deployable 30/20 GHz muttibeam offset antenna [NASA-TM-82571 ] p 18 N84-21607 [AIAA PAPER 84-0658] p 20 A84-25258 WOODCOCK, a R. Space solar power in perspective p 71 A84-21489 W Systems/operations technology p11 N84-18278 WOODCOCK, a R. WADA, B. K. Manufacturing space systems in space Technology requirements for large flexible space p 71 A84-22338 structures WOODS, A. [IAF PAPER 83-404] p2 A84-11811 The 55-meter-structure flight experiment p8 NS4-17233 The 55-meter-structure flight experiment WRIGHT, C. J. p8 N84-17233 Budding and vibration of any prismatic assembly of shear WAGNER-BARTAK, C. a and compression loaded anisotropic plates with an Remote manipulators in space p 57 A84-22336 arbitrary supporting structure p 23 A84-14050 WAGNER-BARTAK, C. G. J. WRIGHT, R. l_ The Shuttle remote manipulator system: CANADARM Space Station Technology, 1983 - A robot arm in space p 57 A84-21486 [NASA-CP-2293] p 11 N84-18277 WAGNER, D. WYNVEEN, R. A. Integrity control of carbon fiber reinforced plastics Environmental Control and Life Support for an structural elements, phase 1 report evolutionary Space Station [TB-TS-11-01/82-A] p 56 N84-18416 [SAE PAPER 831108] . p5 A84-29043 B-11 CORPORATE SOURCE INDEX

TECHNOLOGY FOR LARGE SPACE SYSTEMS / A Bibliography (Supplement 11) JANUARY 1985

Typical Corporate Source Index Listing

Discontinuous lew thrust orbit transfer [AD-A136S08] p 63 N84-19474 CORPORATE SOURCE | Alabama Unlv, HuntsvOle. California Unlv, Los Angeles. Finite element analysis of a deployabte space Approximations method for space frame synthesis structure p 38 N84-16056 p 19 A84-10141 Active control of large flexible space structures Applied Physics Lab, Johns Hopkins Unlv, Laurel, Md. p37 N84-14235 Large space instrumentation to measure the interaction Research on boundary feedback and control theories, between space structures and me environment 1978 -1983 [AD-A129990] p 77 N84-10179 AlrFo I \ T** . Hanscofn AFB, Mass. [AD-A136531] p 41 N84-18987 iGeophyi Applied Solar Energy Corp, City of Industry, Calif. — Sheath kxnzation model of beam emissions from large CAP SogetJ Loglclel, Toulouse (France). Large area, low cost space solar cells Software production in a large space project The SPOT spacecrafts p 47 A84-22979 [AD-A137181] p52 N84-19463 mission center p 78 N84-14752 Arizona State Unlv, Tempe. Carnegie-Mellon Unlv, Pittsburgh, Pa J Feasibility study to conduct windblown sediment Recursive lagrangian dynamics of flexible manipulator experiments aboard a space station arms via transformation matrices [NASA-CR-175434] p IS N84-21586 [AD-A137345] p 60 N84-20316 | Astro Research Corp, Carplnteria, Calif. Case Western Reserve Unlv, Cleveland, Ohio. The STEP/STACBEAM experiment technology Gravitational biology on the space station NASA REPORT PAGE development for very large solar array deployers [SAE PAPER 831133] p 75 A84-29063 TITLE ACCESSION p8 N84-17220 NUMBER NUMBER Centre National d'Etudes SpatJales, Toulouse (France). NUMBER Avco Systems Dlv, Lowell, Mass. A Maltese cross shaped mobile thermal control Maintenance and operational enhancement of the shutter p 27 N84-194S4 flexible spacecraft dynamics program Chicago Untv, III. [NASA-CR-175211] p 41 N84-19394 Pyroelectric materials as electronic pulse detectors of ultraheavy nuclei p 72 A84-23440 Listings in this index are arranged alphabetically Clemson Unlv, S.C. by corporate source. The title of the document B Hyperfiltration wash water recovery subsystem - Design is used to provide a brief description otthe subject and test results [SAE PAPER 831112] p6 A84-29047 matter. The page number and the accession Bendlx Corp, Teterboro, N J. Modular design attitude control system Colorado State Unhr, Fort Collins. number are included in each entry to assist the [NASA-CR-170996] p 41 N84-19392 Current collection from the space plasma through defects in high voltage solar array insulation user in locating the abstract in the abstract Exhibit D modular design attitude control system study p49 N84-15970 [NASA-CR-170993] p 42 N84-2062S section. If applicable, a report number is also Columbia Unhr, New York. included asan aid in identifying thedocument. Boeing Aerospace Co., Houston, Tex. A degree of controllability definition - Fundamental Integrated water management system - Description and concepts and application to modal systems test results p 34 A84-24991 [SAE PAPER 831111] p6 A84-29046 Actuator placement considerations for the control of Hyperfiltration wash water recovery subsystem - Design large space structures p 20 N84-11199 and test results Committee on Appropriations (U. S. Senate). [SAE PAPER 831112] p 6 A84-29047 Department of Housing and Urban Boeing Aerospace Co, Seattle, Wash. Development-independent agencies appropriations for Aerttalla &pA, Torino (Italy). Study of auxiliary propulsion requirements for large 1984: National Aeronautics and Space Administration Development of a spacecraft infrared test technique as space systems. Volume 1: Executive summary p 80 N84-21440 an alternative to solar simulation: First steps on L-SAT [NASA-CR-168193-VOL-1 ] p 63 N84-12226 Com mitt GO on Cornrnorco, Sdonco, ond Transportation thermal model p26 N84-19398 Study of auxiliary propulsion requirements for large (U. S. Senate). Heat pipes for the L-SAT communications module space systems, volume 2 Civil space station radiators p26 N84-19405 [NASA-CR-168193-VOL-2] p 63 N84-13218 [S-REPT-98-523] p 79 N84-20613 The thermal design of L-SAT large telecommunication Space station needs, attributes and architectural options National Aeronautics and Space Administration satellite p27 N84-19414 study. Volume 1: Executive study Authorization Act, 1985 p80 N84-21443 Design and manufacturing of a heat rejection system [NASA-CR-173334] p9 N84-1826S Coimill ttoo on Science And TocnnoiOQy (U. S. Houso). for advanced thermal control p27 N84-19434 Space station needs, attributes and architectural options NASA's space station activities Thermal control of tethered satellite in a very low attitude study. Volume 2: Mission analysis [GPO-27-393] p7 N84-14234 National Aeronautics and Space Administration Act, aerodynamic mission p 27 N84-19444 [NASA-CR-173333] p9 N84-18266 1985 p9 N84-18116 Space station needs, attributes and architectural options Aerojet-General Corp, Sacramento, Calif. Authorizing appropriations to the National Aeronautics study. Volume 3: Requirements Auxiliary propulsion p11 N84-18283 and Space Administration for fiscal year 1985 [NASA-CR-173332] p 10 N84-18267 Aerospace Corp., Los Angeles, Calif. [H-REPT-98-629] p 80 N84-21441 A review of SCATHA satellite results: Charging and Space station needs, attributes and architectural options Review of the National Aeronautics and Space Act of study. Volume 4: Architectural options, subsystems, discharging p SO NS4-17254 1958 Air Force Academy, Colo. technology and programmatics [GPO-28-915] p80 N84-21442 Parameter identification in continuum models [NASA-CR-173331] p 10 N84-18268 National Aeronautics and Space Administration p16 A84-25525 Space station needs, attributes and architectural options Authorization Act, 1985 Scale model testing for control system parameters of study. Final executive review [H-REPT-98-629] p 80 N84-21444 large structures [NASA-CR-173335] p 10 N84-18269 Communications Satellite Corp, Washington, D.C. [AD-A13S652] p41 N84-18313 Systems/operations technology p11 N84-18278 Space station needs, attributes and architectural Air Force Geophysics Lab, Hanscom AFB, Mass. Boeing Scientific Research Lans., SesttJe, Wash. options. Part 1: Summary Sheath kmization model of beam emissions from large Simulated space radiation effects on dielectrics and [NASA-CR-175382] p 10 N84-18270 coatings p 54 A84-20682 Concordla Unrv, Montreal (Quebec). [AD-A137181] p52 N84-19463 British Aerospace Dynamics Group, Stevenage Computer aided synthesis of a satellite antenna structure Air Force Inst of Tech, Wright-Patterson AFB, Ohio. (England). with probabilistic constraints p21 N84-19899 Selection of noisy sensors and actuators for regulation Design and development of an advanced solar array Dynamic behaviour of a satellite antenna structure in of linear systems drive mechanism p 17 N84-184S7 random vibration environment p42 N84-19900 [AD-A135442] p 51 N84-17931 BAe reaction wheels for Olympus p 17 N84-18475 Consulenze General] Roma (Italy). Decentralized control of a large space structure using British Aerospace Public Ltd. Cos Bristol (England). Study on synthesis and characterization of large space direct output feedback Buckling and vibration of any prismatic assembly of shear systems, phase 2. Part 2: Proposals for additions, (AD-A138781] p 41 N84-19464 and compression loaded anisotropic plates with an modifications and new analytical methods, volume 1 The effect of mass and stiffness changes on the damping arbitrary supporting structure p 23 A84-14050 [ESA-CR(P>-1779-VOL-3] P 43 N84-21611 factor in a large space structure as represented by the Brown Unlv, Providence, R. I. The solution of the dynamic problem of the periodic CSDL 2 model Parameter identification in continuum models structures by cydosymmetric technique [AD-A136984] p 42 N84-19465 p 16 A84-25525 p43 N84-21612

C-1 Contraves Corp., Zurich (Switzerland). CORPORA TE SOURCE

Computing the radiation pressure forces by adapting An Attached Payload Operations Center (APOC) at the Space station needs, attributes and architectural thermal design verification softwares p 28 N84-21613 Goddard Space Flight Center (GSFC), volume 1 options. Part 1: Summary Simplified models and computational schemes of the [NASA-CR-175160] p 79 N84-20605 [NASA-CR-175382] p 10 N84-18270 aerodynamic load p 28 N84-21614 Erno Raumfahrttechnlk G.m.b.H, Bremen (West Thermal control p 25 N84-18289 Finite element formulations for tensioned members Germany). Space Station needs, attributes and architectural p 21 N84-21615 Software quality assurance Spacelab experience and options. Volume 2, book 1, part 1: Mission Study on synthesis and characterization of large space future trends p 17 N84-14759 requirements systems, phase 2. Part 2: Proposals for additions, Integrity control of carbon fiber reinforced plastics [NASA-CR-173312J p 13 N84-18296 modifications and new analytical methods, volume 2 structural elements, phase 1 report Space Station needs, attributes and architectural [ESA-CR(P)-1779-VOL-4] p 29 N84-21616 [TB-TS-11-01/82-A] p 56 N84-18416 options. Volume 2, book 1, part 2, task 1: Mission Essex Corp, Huntsvllle, Ala. requirements Thermal design verification of the large open truss Analysis of large space structures assembly: [NASA-CR-173313] p 13 N84-18297 structures. The local approach and the shadow problem Man/machine assembly analysis Space Station needs, attributes and architectural p 29 N84-21617 [NASA-CR-3751 ] p59 N84-13208 options. Volume 2, book 1, part 3: Manned Space Station Computational savings in view factor evaluation on mode Space telescope relevance to commercial telecommunications satellites prescreening p 29 N84-21618 [NASA-CH-170948] p 78 N84-16097 [NASA-CR-173314] p 13 N84-18298 Interactive structural-thermal-control analytical European Space Agency, Parts (France). Space Station needs, attributes and architectural formulations p 29 N84-21619 Spacecraft/plasma interactions and their influence on options. Volume 2, book 1, part 4: Payload element Study on synthesis and characterization of large space field and particle measurements mission data sheets systems, phase 2. Part 3: Experimental design verification [ESA-SP-198] p56 N84-17253 [NASA-CR-173315] p 13 N84-18299 techniques Spacelab data book Space Station needs, attributes and architectural [ESA-CR(P)-1779-VOL-5] p 18 N84-21620 [ESA-BR-14] p79 N84-18315 options. Volume 2, book 2, parti: Mission implementation Assessment of the existing ground test technology and Environmental and thermal control systems for space concepts confronting with the Large Space Structures (LSS) vehicles [NASA-CR-173316] p 13 N84-18300 requirements. Experimental techniques in structural [ESA-SP-200] P26 N84-19396 Space Station needs, attributes and architectural analysis p 29 N84-21621 Thermal cycling tests in space environment simulation options. Volume 2, book 2, part 2, Task 2: Information Assessment of the existing ground test technology and chambers p26 N84-19401 management system confronting with the Large Space Structures (LSS) Introduction to geostationary orbits [NASA-CR-173317] p 13 N84-18301 requirements. Thermal test techniques [ESA-SP-1053] p80 N84-21590 Space Station needs, attributes and architectural p29 N84-21622 Derivation and combination of impedance matrices for options. Volume 2, book 2, part 3: Communication system Proposals for additions, modifications, and new flexible satellites experimental methods. Part 1: Ground tests. Part 2: [ESA-STR-209J p 43 N84-21604 [NASA-CR-173318] p 14 N84-18302 Right tests p 15 N84-21623 European Space Research and Technology Center, Space Station needs, attributes and architectural NoordwIJk (Netherlands). options, volume 2, book 2, part 4: International reports Study on synthesis and characterization of large space Spacecraft thermal balance testing using infrared lamps [NASA-CR-173319] p 14 N84-18303 systems, phase 2. Part 1: Assessment of design on a dummy spacecraft p 26 N84-19399 Space Station needs, attributes and architectural verification analytical methods. Volume 1: Mechanical options, volume 2, book 3: Cost and programmatics design IRSIM: A program for the calculation of infrared flux intensity incident on a spacecraft inside a test chamber [NASA-CR-173320] p 14 N84-18304 [BSA-CR(P)-1779-VOL-1] p18 N84-21624 p26 N84-19400 Study on synthesis and characterization of large space systems, phase 2. Part 1: Assessment of design The Large Space Simulator (LSS) at ESA/ESTEC (a H verification analytical methods. Volume 2: Thermal summary of the main characteristics) p 27 N84-19458 design Honeywell, Inc., Clear-water, Fla. [ESA-CR(P)-1779-VOL-2] p 18 N84-21625 Manipulator interactive design with interconnected Contraves Corp., Zurich (Switzerland). flexible elements p 58 A84-25484 Study on large, ultralight long-life structures in space, Howard Unlv, Washington, D. C. phase 2C Fondazlone Ugo Bordonl, Rome (Italy). The dynamics and control of large flexible space [TM-EKR3] p 17 N84-17284 The small transmitter receiver stations in the Sirio structures, 6 experiment Space telescope: Solar array primary development [NASA-CR-174450] p 36 N84-10173 [FUB-50-1982] p 49 N84-15386 mechanism p 51 N84-18458 Environmental effects on the dynamics and control of Fulmer Research Inst Ltd, Stoke Poges (England). an orbiting large flexible antenna system Review report of the third year's activities on the study [NASA-CR-175448] p 42 N84-20627 survey of advanced materials Hughes Aircraft Co, Los Angeles, Calif. [R87B] p 56 N84-21675 Welded solar cell interconnection p 19 A84-22965 Dayton Unlv, Ohio. The effects of the space environment on damping materials and damping designs on flexible structures p56 N84-17217 General Dynamlcs/Convalr, Fort Worth, Tex. Indian InsL of Science, Bangalore. Department of Communications, Ottawa (Ontario). Space station needs, attributes and architectural Control structure interactions in large space structures Canadian Attitude Sensing Experimental Package options. Summary of major study activities and results. Analysis using energy approach p 35 A84-27934 (CASEP) p79 N84-17223 Space station program observations Instttut National de Recherche d'lnformatlque et Right test of a synthetic aperture radar antenna using [NASA-CR-173345] p11 N84-18275 d'AutomatJque, Rocquencourt (France). STEP p9 N84-17237 Validation methods for mathematical models of flexible Definition of technology development missions for early Deutsche Forschungs- und Versuchsanstalt fuer Luft- space stations orbit transfer vehicle serving. Phase 2, satellite dynamics und Raumfanrt, GoetUngen (West Germany). task 1: Space station support of operational OTV [ESA-CR(P)-1794] p40 N84-17241 Development of procedures for component mode Institute of Space and Astronautlcal Science, Tokyo servicing (Japan). synthesis [NASA-CR-170984] p 14 N84-19377 [DFVLR-IB-232-82-C-09] p 30 N84-21626 Thermofluidynamics of heat pipes p27 N84-19423 General Dynamics Corp, San Diego, Calif. Domter-Werke am.b.H, Frtedrichshafen (West Institute de Pesqulsas Espadals, Sao Jose dos Germany). Photovoltaic concentrator pointing dynamics and plasma Campos (Brazil). Modem software development tools in space projects interaction study pSO N84-17224 Sensitivity analysis of the influence of the flexibility of on the example of a Spacelab experiment Crew and life support ECLSS p11 N84-18280 solar panels on the attitude dynamics of artificial p49 N84-14761 General Electric Co, Falrfleld, Conn. satellites Study on damping representation related to spacecraft Space station needs, attributes and architectural [INPE-2763-PRE/337] p 39 N84-16232 structural design options. Part 1: Summary Capture of satellite stabilized by gravity gradient with a [EMSB-18/83] p38 N84-1S182 [NASA-CR-175382] p 10 N84-18270 flexible mast during and after deployment The complementary roles of existing and advanced General Electric Co, Philadelphia, Pa. [INPE-2749-PRE/325] p 41 N84-19383 environmental, thermal control and life support technology Investigation of articulated panel dynamics lot» Unlv, Iowa City. for space stations p 79 N84-19429 p40 N84-17230 Interpretation of STS-3/plasma diagnostics package Draper (Charles Stark) Lab, Inc, Cambridge, Mass. Structures and mechanisms p21 N84-18286 results in terms of large space structure plasma Closed-form solutions for feedback control with terminal Space Station needs, attributes and architectural interactions constraints p 36 A84-29471 options. Volume 2, book 2, part 2, Task 2: Information [NASA-CR-173266] p 78 N84-16991 ACOSS eleven (Active Control Of Space Structures), management system Istttuto dl Rlcerca e Tecnotogla per to Studio del volume 1 [NASA-CR-173317] p 13 N84-18301 Plasma NeDo Spazto, FrascaU (Italy). [AD-A135675] p 40 N84-18311 Orbiting wire as a dynamo: Auxiliary power possibilities General Research Corp, Santa Barbara, Calif. ACOSS eleven (Active Control Of Space Structures), RF systems in space. Volume 2: Space-based radar for space platforms volume 2 ' [IFSI-83-3] p49 N84-12653 analyses [AD-A135676] p 41 N84-18312 [AD-A133735] p 49 N84-14394 RF systems in space. Volume 1: Space antennas E frequency (SARF) simulation [AD-A133734] p 49 N84-14395 Jet Propulsion Lab, California Inst of Tech, Engineering and Economics Research, Inc, Vienna, Grumman Aerospace Corp, Bethpage, N.Y. Pasadena. Va. Orbiter-based construction equipment study. The Technology requirements for large flexible space Stariab Ground System guidelines document HPA/DTA technology advancement plan structures [NASA-CR-175192] p 14 N84-20435 [NASA-CR-174605] p 17 N84-14233 [IAF PAPER 83-404] p2 A84-11811

C-2 CORPORA re SOURCE NASA. Lyndon B. Johnson Space Center, Houston, Tex.

Simulation of the Galileo spacecraft axial - Delta-V Space station needs, attributes and architectural N algorithm p 66 A84-11938 options. Volume 1. attachment 2: Supporting data and Model error estimation for distributed systems described analysis reports National Aeronautics and Space Administration, by elliptic equations p 15 A84-11946 [NASA-CR-173336] p 13 N84-18294 Washington, D. C. Large Deployable Reflector (LOR) - A concept for an Space station autonomy requirements orbiting subrnillimeter-infrared telescope for the 1990s [AIAA PAPER 83-2352] p 63 A84-10024 p66 A84-14S86 NASA priority technologies An advanced generation land mobile satellite system M [IAF PAPER 83-345] p1 A84-11793 and its critical technologies p3 A84-15634 High capacity power systems for space Science platform and attitude subsystem in-flight Martin Marietta Aerospace, Bethesda Md. [IAF PAPER 83-421] p 44 A84-11816 calibration for the Galileo spacecraft p 32 A84-17355 Space station needs, attributes and architectural options Space Shuttle, private enterprise and intellectual Dynamics and control of a large space antenna study. Briefing material: Final review and executive properties in the context of space manufacturing p32 A84-17361 summary p72 A84-22341 Simulated space radiation effects on dielectrics and (NASA-CFt-173321] p 10 N84-18273 Architectural options and development issues coatings p 54 A84-20682 Martin Marietta Aerospace, Denver, Colo. p4 A84-24633 New directions in solar array development Static shape forming for an electrostatically controlled Space station architectural issues as viewed by the user p47 A84-22958 membrane mirror p 16 A84-25551 community - Applications p 4 A84-24634 Use of electromagnetic models in the optimal control Technology needs of advanced Earth observation Lessons learned during the first year of the TDRSS of large space antennas p 35 A84-25552 [AIAA PAPER 84-0687] p 74 A84-25319 spacecraft Evaluation of spacecraft materials and processes for [NASA-CR-3698J 9 N84-17248 NASA research in teleoperation and robotics optical degradation potential p54 A84-28458 P p58 A84-28523 Electrically conductive black optical paint Martin Marietta Corp, Denver, Colo. International aspects of commercial space activities p55 A84-28553 Molecular contamination math model support [AAS PAPER 83-222] p 77 A84-29866 Space manufacturing 1983: Proceedings of the Sixth (NASA-CR-170899] p 77 N84-10174 The US space station: Potential base for a spacebome Conference, Princeton University, Princeton, NJ, May 9-12, Evaluation and prediction of long-term environmental microwave facility p 78 N84-16420 1983 p76 A84-29852 effects of nonmetallic materials, second phase Second Ail-Union Seminar on Hydromechanics and The 55-meter-structure flight experiment [NASA-CR-170915] p 56 N84-11595 Heat-Mass Transfer in Weightlessness. Abstracts of p8 N84-17233 Fluid management p11 N84-18284 reports: Table of contents [NASA-TM-77534] p 26 N84-18576 Massachusetts Inst of Tech, Cambridge. National Aeronautics and Space Administration. Ames Space applications of Automation, Robotics And Research Center, Moffett Field, Calif. Machine Intelligence Systems (ARAMIS). Volume 3, phase Large Deployable Reflector (LDR) - A concept for an La Jolla InsL, Calif. 2: Executive summary orbiting subrnillimeter-infrared telescope for the 1990s Identification of new potential scientific and technology [NASA-CR-3736] p 59 N84-10582 p66 A84-14586 areas for DoD application. Summary of activities Space Applications of Automation, Robotics and Environmental Control and Life Support for an [AD-A134372] p 78 N84-17050 Machine Intelligence Systems (ARAMIS), phase 2. Volume evolutionary Space Station Lehigh Univ., Bethlehem, Pa 1: Telepresence technology base development [SAE PAPER 831108] pS A84-29043 A degree of controllability definition - Fundamental [NASA-CR-3734] p 59 N84-10583 National Aeronautics and Space Administration. Earth concepts and application to modal systems Space Applications of Automation, Robotics and Resources Labs., Bay St. Louis, Miss. p 34 A84-24991 Machine Intelligence Systems (ARAMIS), phase 2. Volume Overview of NASA space station activities Manipulator interactive design with interconnected 2: Telepresence project applications [IAF PAPER 83-48] p1 A84-11726 flexible elements p 58 A84-25484 [NASA-CR-3735] p 59 N84-10584 National Aeronautics and Space Administration. Life Systems, Inc., Cleveland, Ohio. Goddard Space Right Center, Greenbelt, Md. Environmental Control and Life Support for an Reliability issues in active control of large flexible space structures Data system architecture considerations for a space evolutionary Space Station station [NASA-CR-175341] p 39 N84-16248 [SAE PAPER 831108] p5 A84-29043 [AIAA PAPER 83-2346] p 63 A84-10066 UnCom Corp, Los Angeles, Calif. General requirements for Shuttle flight experiments Assessment of potential for batteries in space User manual of the CATSS system (version 1.0) p8 N84-17221 applications p48 N84-12246 communication analysis tool for space station Feasibility of remotely manipulated welding in space. NASA needs and trends in cryogenic cooling [NASA-CR-171728] p 51 N84-17431 A step in the development of novel joining technologies p25 N84-15329 Little (Arthur D.), Inc., Cambridge, Mass. [NASA-CR-175437] p 60 N84-20857 Thermally induced spin rate ripple on spacecraft with Human capabilities p11 N84-18282 Implementation of MACLISP on a large address space long radial appendages Lockheed Aircraft Corp., Burbank, Calif. computer [NASA-TM-85058] p 39 N84-16249 On-orbit spacecraft/stage servicing during STS life [DEB4-005042] p 79 N84-21145 Thermal energy management process experiment p25 N84-17222 cycle Max-Planck-lnsL fuer Kemphyslk, Heidelberg (West Spacelab Data Processing Facility [NASA-CR-171775] p 79 N84-20617 Germany). [NASA-TM-85S56] p 51 N84-19382 Lockheed Engineering and Management Services Co, Erosion of mylar and protection by thin metal films Recent and planned developments at the Goddard Inc., Houston, Tex. [AIAA PAPER 83-2636] p 52 A84-10949 A communications system conceptual design for a low Space Flight Center in thermal control technology McDonnell-Douglas Astronautics Co, Huntingdon earth orbiting Manned Space Station p 45 A84-15643 p26 N84-19402 Beach, Calif. National Aeronautics and Space Administration. Knowledge based systems for intelligent robotics STEP flight experiments Large Deployable Reflector Lyndon B. Johnson Space Center, Houston, Tex. p57 A84-15667 (LDR) telescope p8 NB4-17231 Space station communications and tracking equipment Lockheed Missiles and Space Co, Palo Alto, Calif. Space Station needs, attributes and architectural management/control system p 45 A84-15639 Hyperfiltration wash water recovery subsystem - Design options: Summary briefing Communications, tracking, and docking on the Space and test results [NASA-CR-173328] p 10 N84-18271 Station p45 A84-15640 [SAE PAPER 831112] p6 A84-29047 Data management p 12 N84-18287 Application of beam power technology to a space Effects of combined ultraviolet and oxygen plasma station p45 A84-15642 environment on spacecraft thermal control materials McDonnell-Douglas Technical Services Co, Inc., A communications system conceptual design for a low p27 N84-19449 Huntsvllle, Ala. earth orbiting Manned Space Station p45 A84-15643 Lockheed Missiles and Space Co, Sunnyvale, Calif. A definition of STS accommodations for attached Low earth orbit atomic oxygen effects on surfaces Technology requirements for large flexible space paytoads [AIAA PAPER 84-0548] p 53 A84-19912 structures [NASA-CR-172223] p 17 N84-10114 A system study of the solar power satellite concept [IAF PAPER 83-404] p2 A84-11811 Messerschmltt-Boelkow-eiohm G.m.b.H, Ottobrunn p70 A84-21480 Solar array Shuttle flight experiment - Hardware (West Germany). The role of man in space p 72 A84-24627 development and testing p 47 A84-22961 Spacecraft thermal control selection for seven years of Control structure interactions in large space structures New component development for muttj-100 kW low-cost lifetime in synchronous orbit Analysis using energy approach p 35 A84-27934 solar array applications p 47 A84-22963 [MBB-UR-584-82-OE] p 25 N84-11200 Thermal management system technology development Attitude, control and stabilization p40 N84-18281 Michigan State Untv, East Lansing. for space station applications [SAE PAPER 831097] p 24 A84-29032 Power p 12 N84-1B288 The Alpha-Helix Concept Innovative utilization of the Space Station Program. A report to the National Systems engineering aspects of a preliminary Space station needs, attributes and architectural conceptual design of the space station environmental options. Volume 4, attachment 1: Task 2 and 3 mission Aeronautical and Space Administration requesting establishment of a Sensory Physiology Laboratory on the control and life support system implementation and cost [SAE PAPER 831109] pS A84-29044 [NASA-CR-173330] p 12 N84-18290 Space Station [NASA-CR-175436] p 14 N84-20610 Integrated water management system - Description and Space station needs, attributes and architectural test results Mission Research Corp, Santa Barbara, Calif. options. Volume 2, attachment 2: Supporting data and [SAE PAPER 831111] p6 A84-29046 analysis reports The effects of aperture antennas after signal propagation Hyperfiltration wash water recovery subsystem - Design through anisotropic ionized media [NASA-CR-173329] p 12 N84-18291 and test results [AD-A138286] p 52 N84-21781 Space station needs, attributes and architectural [SAE PAPER 831112] p6 A84-29047 options. Volume 1: Executive summary NASA Mississippi State Untv, State College. Regenerable non-venting thermal control subsystem for [NASA-CR-172792] p 12 N84-18292 An evaluation of Techroll seal flexible joint material extravehicular activity Space station needs, attributes and architectural p56 NB4-16037 [SAE PAPER 831151] p 24 A84-29076 options. Volume 1, attachment 1: Executive summary Monsanto Research Corp, St Louts, Mo. Habitability design elements for a space station NASA Erosion of mylar and protection by thin metal films [AAS PAPER 83-200] p7 A84-29853 [NASA-CR-173337] p 12 N84-18293 [AIAA PAPER 83-2636] p 52 A84-10949 Space station energy sizing p48 N84-12233

C-3 NASA. John F. Kennedy Space Center, Cocoa Beach, Fla. CORPORA TE SOURCE

The Boeing flywheel study p37 N84-12235 Geometric modeling of large space antenna Rensselaer Polytechnic Inst, Troy, N. Y. Space station control requirements and flywheel system deployment p22 N84-22225 The spatial order reduction problem and its effect on weights for combined momentum and energy storage National Aeronautics and Space Administration. Lewis adaptive control of distributed parameter systems p37 N84-12236 Research Center, Cleveland, Ohio. p33 A84-19056 National Aeronautics and Space Administration. John NASA priority technologies Some applications of direct adaptive control to large F. Kennedy Space Center, Cocoa Beach, Fla [IAF PAPER 83-345] p 1 A84-11793 structural systems p 34 A84-25496 STS-9: Orbital workshop spacelab to fly on ninth Shuttle NASA's geostationary communications platform Direct multivariable model reference adaptive control mission program with applications to large structural systems [NASA-TM-85497] p 78 N84-16242 tAIAA PAPER 84-0702) p5 A84-25326 p38 N84-15840 National Aeronautics and Space Administration. On modeling dilution jet flowfields Composite structural materials Langley Research Center, Hampton, Va. [AIAA PAPER 84-1379] p 58 A84-44183 [NASA-CR-173259] p 56 N84-17293 A system for intelligent teleoperation research Resistojet propulsion for large spacecraft systems [NASA-TM-83489] p 63 N84-11206 Rockwell International Corp., Downey, Calif. [AIAA PAPER 83-2376] p 57 A84-10070 Development of deployable structures for large space Overview of NASA space station activities Radiating dipole model of interference induced in spacecraft circuitry by surface discharges platform systems. Volume 1: Executive summary [IAF PAPER 83-48] p1 A84-11726 [NASA-CR-170913] p20 N84-10175 Buckling and vibration of any prismatic assembly of shear [NASA-TP-2240] p 50 N84-16247 Development of deployable structures for large space and compression loaded anisotropic plates with an The role of potential barrier formation in spacecraft platforms. Volume 2: Design development arbitrary supporting structure p 23 A84-140SO charging p 50 N84-17269 [NASA-CR-170914] p 20 N84-10176 Vertical ascent from earth to geosynchronous orbit National Aeronautics and Space Administration. Development of Test Article Building Block (TABS) for [AIAA PAPER 84-0509] p 61 A84-18141 Marshall Space Right Center, Huntsvllle, Ala. deployable platform systems p 21 N84-17226 Integrated requirements for a space station Launch processing for Spacelab 1 p4 A84-24628 [AIAA PAPER 83-2622] p 64 A84-10965 A deployable structure and solar array controls experiment for STEP p39 N84-17227 Static shape forming for an electrostatically controlled A programmable power processor for high power space Space Station needs, attributes, and architectural membrane mirror p 16 A84-25551 applications p46 A84-18394 options study NASA research in teleoperation and robotics Space platform accommodations p 16 A84-22131 p58 AB4-28523 Solar array Shuttle flight experiment - Hardware [NASA-CR-173327] p11 N84-18274 Closed-form solutions for feedback control with terminal development and testing p 47 A84-22961 Shuttle interaction study [NASA-CR-173400] p 80 N84-21592 constraints p 36 A84-29471 NASA's geostationary communications platform Shutter interaction study extension Surface analysis of graphite fiber reinforced polyimide program [NASA-CR-173401] p 81 N84-21593 composites [AIAA PAPER 84-0702] p5 A84-25326 [NASA-TM-85700] p 55 N84-11220 Self-locking telescoping manipulator arm Shuttle interaction study extension [NASA-CR-173398] p 81 N84-21594 Research and technology, 1983 [NASA-CASE-MFS-25906-1 ] p 59 N84-11761 Shutter Interaction Study [NASA-TM-85702] p7 N84-12026 Space station attitude control system concept and [NASA-CR-173402] p 81 N84-21595 Integrated Flywheel Technology, 1983 requirements p 37 N84-12234 Shuttle interaction study extension [NASA-CP-2290] p 78 N84-12228 IPACS attitude control technology considerations [NASA-CR-173403] p 81 N84-21596 Advanced Control and Power System (ACAPS) p37 N84-12238 Rockwell International Corp, Seal Beach, Calif. technology program p37 N84-12243 IPACS guidance navigation and control system Low concentration ratio solar array structural Stability, vibration and passive damping of partially considerations and test activities p37 N84-12245 configuration p 17 N84-17225 restrained imperfect columns Significant scientific and technical results at Marshal Royal Netherlands Aircraft Factories Fokker, [NASA-TM-85697] p 37 N84-13608 Space Flight Center Schlphol-Oost An alternate concept for expanding man's presence in [NASA-TM-82562] p 78 N84-16075 A Variable Conductance Heat Pipe (VCHP) radiator space Tethers in space: Birth and growth of a new avenue system for communications payloads p 27 N84-19406 [NASA-TM-84617] p7 N84-15172 to space utilization Capture-ejector satellites [NASA-TM-82571] p 18 N84-21607 [NASA-TM-85686] p7 N84-15179 National Centre of Trlbology, Rlsley (England). Thermal analysis research applicable to space station Thermal conductance and torque of thin section technology needs four-point contact ball bearings in vacuum Sandla Labs., Uvermore, Calif. [NASA-TM-84658] p 25 N84-15426 [ESA-ESTL-54] p 25 N84-15562 Sodium heat transfer system modeling Synchronously deployable truss structure National Space Development Agency, Tokyo (Japan). [DE84-002051] p25 N84-16509 [NASA-CASE-LAR-13117-1] p 59 N84-16250 Evaluation of modal testing techniques for spacecraft Smithsonian Astrophysics! Observatory, Cambridge, structures p 28 N84-19906 Surface accuracy measurement sensor test on a Mass. 50-meter antenna surface model National Telecommunications and Information Investigation of electrodynamic stabilization and control Administration, Annapolis, Md. [NASA-TM-85689] p 17 N84-16427 of long orbiting tethers STEP Experiment Requirements Assessment of satellite power flux-density limits in the [NASA-CR-170972] p 40 N84-17251 [NASA-CP-2294] p7 N84-17211 2025-2300 MHz frequency range, part 1 A large-area gamma-ray imaging telescope system Space Technology Experiments Platform (STEP) [PB84-129402] p 51 N84-18532 [NASA-CR-175435] p 14 N84-20604 overview p8 N84-17212 Naval Academy, Annapolis, Md. Southern Methodist Univ., Dallas, Tex. STEP mechanical systems p8 N84-17213 Stability enhancement of a flexible robot manipulator Parameter identification in continuum models STEP experiment integration p8 N84-17215 [AD-A134185] p59 N84-16807 p 16 A84-25525 Deployable beam flight experiment (MAST) Nebraska Univ., Lincoln. Space Communications Co, Gattheroburg, Md. p8 N84-17218 New elements for analysis of space frames with tapered Study of a tracking and data acquisition system for the Erectable beam experiment p60 N84-17219 members p 20 N84-14561 1990's. Volume 3: TDAS Communication Mission Vibration isolation technology experiment Model p39 NB4-17228 [NASA-CR-175195] p 79 N84-19371 Integrated Power/Attitude Control System (IPACS) Spire Corp, Bedford, Mass. technology experiment p39 N84-17229 Large area space solar cell assemblies Large deployable antenna flight experiment for the Old Dominion Unrv, Norfolk, Va. p 61 A84-22980 Space Technology Experiments Platform (STEP) Self-shadowing of orbiting trusses Stanford Telecommunications, Inc, McLean, Va. p8 N84-17232 [NASA-CR-173215] p 25 N84-16565 Study of a tracking and data acquisition system for the Large inflated-antenna system p9 N84-17234 Airborne antenna pattern calculations 1990's. Volume 3: TDAS Communication Mission Adaptive microwave reflector pSO N84-17235 [NASA-CR-173284] p51 N84-17436 Model Microwave reflector characterization using simple Component mode synthesis and large deflection [NASA-CR-175195] p 79 N84-19371 instruments in EVA p 50 N84-17236 vibrations of complex structures Stanford Unrv, CalH. Spline-based estimation techniques for parameters in [NASA-CR-173338] p 21 N84-18680 Control of flexible spacecraft by optimal model elliptic distributed systems following p36 N84-12222 INASA-TM-85439] p9 N84-17947 Precise control of flexible manipulators Space Station Technology, 1983 [NASA-CR-175389] p 60 N84-20175 [NASA-CP-2293] p11 N84-18277 State Univ. of New York, Stony Brook. A manned-machine space station construction Perkm-Elmer Corp., Danbury, Conn. Gravitational biology on the space station concept Optical coating in space [SAE PAPER 831133] p 75 A84-29063 [NASA-TM-85762] p 21 N84-19395 [NASA-CR-175441] p 56 N84-21290 Stevens Inst of Tech, Hoboken, N. J. Construction concept for erecting an offset-fed Time domain analysis and synthesis of robust controllers Purdue Unhr, Lafayette, Ind. antenna for large scale LOG (Linear Quadratic Gaussian) Analysis of large space structures p 18 N84-20621 [NASA-TM-85774] p 60 N84-20626 regulators Static and dynamic structural-sensitivity derivative [AD-A137760] p 43 N84-21172 calculations in the finite-element-based Engineering Systems Science and Software, La Jolla, Calif. Analysis Language (EAL) system Plasma sheath structure surrounding a large powered [NASA-TM-85743] p 42 N84-20880 spacecraft Operational modules for space station construction RAND Corp, Santa Monica, Calif. [AIAA PAPER 84-0329] p 46 A84-18025 [NASA-TM-85772] p 21 N84-21608 The flexural behavior of PACSAT (passive Computer-Aided Geometry Modeling communication satellite) in orbit [NASA-CP-2272] p 18 N84-22179 [AD-A131406] p36 NB4-11195 Interactive geometry modeling of space station RCA Astro-Electronics Dlv, Princeton, N. J. conceptual designs p 18 N84-22191 A degree of controllability definition - Fundamental Technlscne Univ., Darmstadt (West Germany). Mathematical synthesization of complex structures concepts and application to modal systems Geodetic aspects of ESA projects, studies and p 19 N84-22224 p 34 A84-24991 investigations p 78 N84-16677

C-4 CORPORA TE SOURCE Washington Univ., St Louis, Mo.

Tectmlsche Univ., Hanover (West Germany). Geometrically nonlinear analysts of beam-in-space structures [MnT-28] p22 N84-21914 Teledyne Brown Engineering, Huntsvllle, Ala. Space platform accommodations p 16 A84-22131 Payload missions integration [NASA-CR-170949] p7 N84-15171 Terra-Mar, Mountain View, Calif. Alternative strategies for space station financing [NASA-Cfl-175412] p 80 N84-21437 Texas Woman's Univ., Houston. Crew and We support EVA p11 N84-18279 TRW Electronic Systems Group, Redondo Beach, Cam. Communications p 12 N84-18285 TRW Space Technology Labs, Redondo Beach, Cain. Study of multi-kilowatt solar arrays for Earth orbit applications [NASA-CR-170939] p 49 N84-12634 ACOSS Fourteen (Active Control of Space Structures) [AD-A133411] p38 N84-15181 Space station needs, attributes and architectural options study. Final review executive summary briefing [NASA-CR-173674] p 10 N84-18272 u United Technologies Corp, Windsor Locks, Conn. Regenerate non-venting thermal control subsystem for extravehicular activity [SAE PAPER 831151] p 24 A84-29076

Virginia Polytechnic Inst and State Unlv, Blacksburg. Experimental study of active vibration control [AD-A133818] p 38 N84-14546 Control of large flexible spacecraft by the independent modal-space control method [NASA-CR-3760] p 40 N84-18262 Virginia Univ., Chariottesvllle. Digital control system for space structural dampers [NASA-CR-175355] p 39 N84-16246 Vought Corp., Dallas, Tex. Rexible radiator thermal vacuum test report [NASA-CR-171764] p 28 N84-20622 Rexible radiator system [NASA-CR-171765] p 28 N84-20623 Rexible radiator system: Executive summary [NASA-CR-171766] p 28 N84-20624 w Wales Univ. Inst ot Science and Technology, Cardiff. Buckling and vibration of any prismatic assembly of shear and compression loaded anisotropic plates with an arbitrary supporting structure p 23 A84-14050 Washington Unlv, Seattle. Radiation-conduction interaction in large space structures [AIAA PAPER 84-0144] p 23 A84-17911 Washington Unlv, St. Louis, Mo. Erosion of mylar and protection by thin metal films [AIAA PAPER 83-2636] p 52 A84-10949

C-5 CONTRACT NUMBER INDEX

TECHNOLOGY FOR LARGE SPACE SYSTEMS / A Bibliography (Supplement 11) JANUARY 1985

Typical Contract Number Index Listing MIPR-FY7121-82-00007 p 77 N84-10179 p 81 N84-21594 NAGW-122 p52 A84-10949 p 81 N84-21595 NAG1-126 p 39 N84-16248 p 81 N84-21596 NAS9-16440 '. p 47 A84-22979 NAG1-171 p33 A84-19056 p 34 A84-25496 NAS9-16468 p 17 N84-14233 NAS8-33979 p 41 N84-19392 NAS9-16609 p 24 A84-29076 NAG1-225 p40 N84-18262 NAS9-16868 p 51 N84-17431 NAG1-248 p55 N84-11220 NCCW-000002 p23 A84-14050 NAG1-257 p25 N84-16565 NGL-14-001-006 p 72 A84-23440 NAG1-301 p21 N84-18680 NGL-14-001-258 p 72 A84-23440 NAG1-322 p60 N84-20175 NASA NGL-33-018-003 p 56 N84-17293 PAGE NAG1-349 p39 N84-16246 ACCESSION NSERC-A-0967 p 36 A84-29143 NUMBER NAG1-41 p23 A84-17911 NSERC-A-2181 p 36 A84-29143 NUMBER NAG3-449 p 78 N84-16991 NSERC-A-4183 p 31 A84-12489 NASW-3542 p26 N84-18576 NSERC-G-0662 p 36 A84-29143 NASW-3680 p9 N84-18265 NSF ECS-80-16173 p 33 A84-19056 p 9 N84-18266 p33 A84-19118 p 10 N84-18267 Listings in this index are arranged alphanumerically p 34 A84-25496 by contract number. Under each contract number, p 10 N84-18268 NSF MCS-82-05335 p 16 A84-25525 p 10 N84-18269 the accession numbers denoting documents that NSFMEA-81-01110 p 36 A84-29145 NASW-3681 p 10 N84-18272 NSF MEA-81-20211 p 54 A84-21775 have been produced as a result of research done NASW-3682 p 11 N84-18275 NSF MEA-82-16777 p 55 A84-29101 NASW-3683 p 11 N84-18274 under that contract are arranged in ascending NSG-1414 p36 N84-10173 NASW-3684 p 12 N84-18290 p 42 N84-20627 order with the AIAA accession numbers appearing p 12 N84-18291 NSG-1490 p 19 A84-10141 first. The accession number denotes the number by p 12 N84-18292 NSG-1655 p51 N84-17436 which the citation is identified in the abstract p 12 N84-18293 N00014-76-C-0139 p 36 A84-29145 p 13 N84-18294 section. Preceding the accession number is the S99-QAXH p52 N84-21781 NASW-3685 p 10 N84-18270 page number on which the citation may be found. 505-31-83-02 p 18 N84-22179 p 13 N84-18296 506-51-13-02 p 7 N84-15179 p 13 N84-18297 506-53-23-06 p 65 N84-11220 p 13 N84-18298 506-53-43-01 p 37 N84-13608 p 13 N84-18299 AF PRO). C654 p 38 N84-15181 p21 N84-19395 p 13 N84-18300 AFPROJ. C6SS p40 N84-18311 p 60 N84-20626 p41 N84-18312 p 13 N84-18301 506-53-43-12 p 17 N84-16427 p 14 N84-18302 AF PROJ. 2304 p 9 N84-17947 506-53-43 p 21 N84-21608 p41 N84-18987 p 14 N84-18303 506-53-53-07 p 42- N84-20880 p 14 N84-18304 p43 N84-21172 506-55-22 p63 N84-11206 NASW-3686 p 10 N84-18273 AFPROJ. 2307 p 38 N84-14546 506-55-72 p 50 N84-16247 AFPROJ. 2308 p41 N84-18313 NASW-3687 p 10 N84-18271 506-57-13-02 p36 N84-10173| AF PROJ. 4506 p 49 N84-14394 NASW-3740 p60 N84-20857 506-57-13-10 p78 N84-12228I p 49 N84-1439S NASW-3741 p 15 N84-21586 506-62-43-04 p 17 N84-10114I AFPROJ. 7661 p77 N84-10179 NASW-3748 p 14 N84-20610 506-62-43-91 p7 N84-17211 [ NASW-3750 p80 N84-21437 p52 N84-194S3 506^4-13 p11 N84-18277| AF-AFOSR-0198-81 p9 N84-17947 NASW-3753 p56 N84-21290 AF-AFOSR-0217-82 p 38 N84-14546 NAS1-15810 p 16 A84-25525 AF-AFOSR-3550-78 p 41 N84-18987 NAS1-16394 p 16 A84-25525 AF-AFOSR-81-0198 p 16 A84-25525 NAS1-16756 p9 N84-17248 AF-F04701-82-C-0083 p 50 N84-17254 NAS2-3743 p 14 N84-20604 AF-83-0139 p43 N84-21172 NAS3-22236 p 61 A84-22980 ARPA ORDER 3584-7 p 36 N84-11195 NAS3-23058 p 46 A84-18025 ARPA ORDER 3710 p 78 N84-17050 NAS3-23248 p 63 N84-12226 DAAG29-79-C-0161 p 16 A84-25S25 p63 N84-13218 DAAG29-81-K-0131 p 35 A84-25516 NAS5-26546 p 79 N84-19371 DARPA ORDER 3654 p 38 N84-15181 NAS5-26962 p 79 N84-20605 DE-AC02-79ER-10357 p 79 N84-21145 NAS5-27466 p 41 N84-19394 DE-AC04-76DP-00789 p 25 N84-16509 NAS5-27617 p 14 N84-20435 DFVLR-232-11 p30 N84-21626 NAS7-100 p66 A84-11938 DFVLR-3-719-101 p 30 N84-21626 NAS8-31352 p 47 A84-22961 DNA001-81-C-0006 p 52 N84-21781 NAS8-32212 p 34 A84-24991 ESA-4389/80/NL-AK(SC) p 56 N84-21675 NAS8-32350 p 17 N84-10114 ESA-4442/80/NL-AK(SC) p 56 N84-18416 NAS8-32712 p7 N84-15171 ESTEC-2991/76/NL-AK(SC) p 40 N84-17241 NAS8-32981 p 47 A84-22963 ESTEC-4099/79/NL-PP(SC) p 25 N84-15562 NAS8-32989 p 59 N84-13208 ESTEC-4348/80/NL-AK(SC) p 43 N84-21611 NAS8-33272 p 78 N84-16097 p29 N84-21616 NAS8-33S78 p 56 N84-11595 p 18 N84-21620 NAS8-33979 p 41 N84-19392 p 18 N84-21624 p 42 N84-20625 ESTEC-4348/80/NL-AL(SC) p 18 N84-21625 NAS8-34131 p49 N84-12634 ESTEC-4350/80/NL-PP p 30 N84-21626 NAS8-34381 p 59 N84-10582 ESTEC-4435/80/NL-AK(SC) p 38 N84-15182 p 59 N84-10583 ESTEC-5156/82/NL-PB(SC) p 17 N84-17284 p 59 N84-10584 F04701-82-C-0083 p 32 A84-17359 NAS8-34677 p 20 N84-10175 F30602-81-C-0119 p 49 N84-14394 p20 N84-10176 p 49 N84-14395 NAS8-34945 p 77 N84-10174 F30602-81-C-01BO p 40 N84-18311 NAS8-35036 p 40 N84-17251 p41 N84-18312 NAS8-35039 p 14 N84-19377 F30602-81-C-0194 p 38 N84-15181 NAS9-14776 p 28 N84-20622 F33615-79OS114 p 55 A84-28900 p 28 N84-20623 p 28 N84-20624 JPL-955426 p 54 A84-28458 NAS9-15800 pS7 A84-15667 JPL-956038 p 19 A84-22965 p 79 N84-20617 MOA903-82-C-0068 p 36 N84-11195 NAS9-16153 p80 N84-21592 MDA903-82-C-0376 p 78 N84-17050 p81 N84-21593

D-1 REPORT NUMBER INDEX

TECHNOLOGY FOR LARGE SPACE SYSTEMS / A Bibliography (Supplement 11) JANUARY 1985

Typical Report Number Index Listing

AIAA PAPER 83-2346 p 63 A84-10066 ' # E-1813 p63 N84-11206'* AIAA PAPER 83-2352 p 63 A84-10024 ' # AIAA PAPER 83-2355 p 43 A84-10025 # EMSB-18/83 p 38 N84-15182 # AIAA PAPER 83-2376 p 57 A84-10070 ' # ER-591 p 56 N84-21290 • # AIAA PAPER 83-2622 p 64 A84-10965 • # AIAA PAPER 83-2636 p 52 A84-10949 ' # ESA-BR-14 p79 N84-18315 # AAS PAPER 83-200 AIAA PAPER 83-2654 p 30 A84-10956 # AIAA PAPER 83-2685 p 66 A84-13376 # ESA-CR(P)-1770 p38 N84-15182 # AIAA PAPER 84-O054 p 23 A84-17850 # ESA-CR(P)-1772 p25 N84-15562 # NASA AIAA PAPER 84-0056 p 23 A84-21284 # ESA-CR(P)-1778 p 56 N84-18416 # PAGE AIAA PAPER 84-0060 p 23 A84-17853 # ACCESSION ESA-CR(P)-1779-VOL-1 p 18 N84-21624 # NUMBER AIAA PAPER 84-0061 p 34 A84-21285 # NUMBER ESA-CR(P)-1779-VOL-2 p 18 N84-21625 # AIAA PAPER 84-0062 p 32 A84-17B54 # ESA-CR(P)-1779-VOL-3 p 43 N84-21611 # AIAA PAPER 84-0069 p 16 A84-19887 # ESA-CR(P)-1779-VOL-4 p29 N84-21616 # AIAA PAPER 84-0081 p 32 A84-17866 # Listings in this index are arranged alphanumerically ESA-CR(P)-1779-VOL-5 p 18 N84-21620 # AIAA PAPER 84-0143 p 23 A84-17910 # ESA-CR(P)-1794 p40 N84-17241 # by report number. The page number indicates the AIAA PAPER 84-0144 p 23 A84-17911 ' # ESA-CR(P)-1796 p 17 N84-17284 # page on which the citation is located. The AIAA PAPER 84-0297 p 4 A84-1B005 # ESA-CR(P)-1826 p 30 N84-21626 # AIAA PAPER 84-0329 p 46 A84-18025 * # ESA-CR(P)-1838 P 56 N84-21675 # accession number denotes the number by which AIAA PAPER 84-0392 p 32 A84-18060 # the citation is identified. An asterisk (*) indicates AIAA PAPER 84-0509 p 61 A84-18141 * # ESA-ESTL-54 p 25 N84-15562 # that the item is a NASA report. A pound sign (#) AIAA PAPER 84-0548 p 53 A84-19912 • # indicates that the item is available on microfiche. AIAA PAPER 84-0549 p 53 A84-18159 # ESA-SP-1053 p80 N84-21590 # AIAA PAPER 84-0566 p 33 A84-18168 # ESA-SP-198 p56 N84-17253 # AIAA PAPER 84-0651 p 74 A84-25318 # ESA-SP-200 p 26 N84-19396 # AIAA PAPER 84-0652 p 73 A84-25253 # AIAA PAPER 84-0653 p 74 A84-25254 # ESA-STR-209 P43 N84-21604 ff AAS PAPER 83-200 p 7 A84-29853 * # AIAA PAPER 84-0658 p 20 A84-25258 # AAS PAPER 83-201 p 76 A84-29854 # AIAA PAPER 84-0659 p 16 A84-25259 # FJSRL-TR-83-0011 p 41 N84-18313 # AAS PAPER 83-202 p 76 A84-29855 # AIAA PAPER 84-0661 p 4 A84-25260 # AAS PAPER 83-204 p 76 A84-29856 # AIAA PAPER 84-0687 p 74 A84-25319 * # FUB-50-1982 p49 N84-15386 # AAS PAPER 83-207 p 76 A84-29857 # AIAA PAPER 84-0702 p 5 A84-25326 * # AIAA PAPER 84-0703 p 75 A84-25327 # AAS PAPER 83-208 p 7 A84-29858 # GDC-SP-83-067 P 14 N84-19377 * # AAS PAPER 83-216 p 48 A84-29861 # AIAA PAPER 84-0704 p 74 A84-25281 # AAS PAPER 83-217 p 20 A84-29862 # AIAA PAPER 84-0706 p 4 A84-25282 # GPO-27-393 p 7 N84-14234 # AAS PAPER 83-221 p 77 A84-29865 # AIAA PAPER 84-0713 p4 A84-25287 # GPO-28-915 p80 N84-21442 # AAS PAPER 83-222 p 77 A84-29866 * # AIAA PAPER 84-0725 p 34 A84-2S291 # GPO-29-426 p 79 N84-20613 # AAS PAPER 83-225 p 77 A84-29868 # AIAA PAPER 84-0727 p 62 A84-25292 # GPO-31-451 p80 N84-21441 # AAS PAPER 83-226 p 62 A84-29869 # AIAA PAPER 84-0729 p 62 A84-25293 # AIAA PAPER 84-0730 p 62 A84-25294 # AAS PAPER 83-244 p 77 A84-29883 # H-REPTT98-629 p 80 N84-21441 # AIAA PAPER 84-0749 p 74 A84-25304 # H-REPT-98-629 p 80 N84-21444 # AD-A129990 p 77 N84-10179 # AIAA PAPER 84-0751 p 48 A84-25306 # AD-A131406 p36 N84-11195 # AIAA PAPER 84-0753 p 5 A84-25308 # H-83-03 p 59 N84-13208 ' # AD-A132533 p 36 A84-29145 # AIAA PAPER 84-1379 p 58 AB4-441B3 * # H-83-06 p 78 N84-16097 * # AD-A133411 p38 N84-15181 # AD-A133734 p 49 N84-14395 # AIAA 84-0758 p 74 A84-25309 # IAF PAPER 82-IISL-38 p 68 AD-A133735 p 49 N84-14394 # IAF PAPER 82-IISL-44 p 68 AD-A133818 p 38 N84-14546 # ASME PAPER 83-DET-6 p 55 A84-29101 # IAF PAPER 82-IISL-45 p 68 AD-A134185 p 59 N84-16807 # IAF PAPER 83-232 p 65 AD-A134372 p 78 N84-17050 # CMU-RI-TR-83-23 p 60 N84-20316 # IAF PAPER 83-24 p 64 AD-A135109 p 9 N84-17947 # IAF PAPER 83-272 p 65 AD-A135442 p 51 N84-17931 # CONF-831111-9 p25 N84-16509 # IAF PAPER 83-30 p 64 AD-A135652 p 41 N84-18313 # IAF PAPER 83-316 p 65 AD-A135675 p 40 N84-18311 # CSDL-R-1598-VOL-1 p 40 N84-18311 # IAF PAPER 83-345 p 1 AD-A135676 p 41 N84-18312 # CSDL-R-1598-VOL-2 p 41 N84-18312 # IAF PAPER 83-38 p 64 AD-A136531 p 41 N84-18987 # IAF PAPER 83-401 p 61 AD-A136781 p 41 N84-19464 # DE84-002051 P 25 N84-16509 # IAF PAPER 83-404 p2 AO-A136908 p63 N84-19474 # DE84-005042 P 79 N84-21145 tt IAF PAPER 83-417 p 22 AD-A136984 p 42 N84-19465 # IAF PAPER 83-418 p 30 AD-A137181 p52 N84-19463 # DFVLR-IB-232-82-C-09 p 30 NB4-21626 # IAF PAPER 83-421 ..' p 44 AO-A137345 p 60 N84-20316 # IAF PAPER 83-422 p 44 AD-A137760 p43 N84-21172 # DGLR PAPER 83-089 p 75 A84-29656 # IAF PAPER 83-447 p 44 AD-A138286 p 52 N84-21781 # DGLR PAPER 83-091 p 76 A84-29658 # IAF PAPER 83-44 p 1 DGLR PAPER 83-102 p 6 A84-29666 # IAF PAPER 83-48 p 1 AO-E301332 p52 N84-21781 # DGLR PAPER 83-90 p 76 A84-29657 # IAF PAPER 83-54 p 64 IAF PAPER 83-55 p 65 AFGL-TR-83-0059 p 77 N84-10179 # DNA-TR-81-254 p 52 N84-21781 # IAF PAPER 83-60 p 1 AFGL-TR-83-0331 p 52 N84-19463 ft IAF PAPER 83-82 p 65 DOE/ER-10357/1 p79 N84-21145 # IAF PAPER 83-86 p 65 AFIT/a/NR-83-59D p 51 N84-17931 # DRD-SE957T p 17 N84-14233 • # IFSI-83-3 p49 N84-12653 # AFTT/GA/AA/83D-1 p 63 N84-19474 # AFIT/GA/AA/83D-8 p 41 N84-19464 # DRL-T-1701 p 17 N84-14233 • # INPE-2749-PRE/325 p 41 N84-19383 tt INPE-2763-PRE/337 p 39 N84-16232 # AFIT/GSO/AA/83D-2 p 42 N84-19465 # D180-27477-1-VOL-1 p 9 N84-18265 D180-27477-2-VOL-2 p 9 N84-18266 ISBN-0-833O-0490-5 p 36 N84-11195 tt AFOSR-83-0855TR p 38 N84-14546 # D180-27477-3-VOL-3 p 10 N84-18267 D180-27477-4-VOL-4 p 10 N 84-18268 AFOSR-83-0926TR p9 N84-17947 # ISSN-0073-O300 p22 N84-21914 # D180-27477-6 p 10 N84-18269 AFOSR-83-1240TR p 41 N84-18987 # ISSN-0250-1589 p 79 N84-18315 # D180-27728-1 p 63 N84-12226 AFOSR-84-0040TR p 43 N84-21172 # D180-27728-2 p 63 N84-13218 ISSN-0379-4067 p 43 N84-21604 # ISSN-0379-6566 p 56 N84-17253 # AIAA PAPER 83-2338 p43 A84-10016 # E-1775 pSO N84-16247 ' # ISSN-0379-6566 p 26 N84-19396 #

E-1 ISSN-0379-6S66 REPORT NUMBER INDEX

ISSN-0379-6566 P 80 N84-21590 # NAS 1.26:173329 p 12 N84-18291 *# NASA-CR-173334 p9 N84-18265 * # NAS 1.26:173330 p 12 N84-18290 • # NASA-CR-173335 p 10 N84-18269 ' # KSC-231-83 p 78 N84-16242 ' # NAS 1.26:173331 p 10 N84-18268 * # NASA-CR-173336 p 13 N84-18294 * # NAS 1.26:173332 p 10 N84-18267 * # NASA-CR-173337 p 12 N84-18293 • # L-15618 p 18 N84-22179 * # NAS 1.26:173333 p9 N84-18266 • # NASA-CR-173338 p 21 N84-18680 * # L-1S659 p42 N84-20880 * # NAS 1.26:173334 p9 N84-18265 * # NASA-CR-173345 p11 N84-18275 * # L-15707 p78 N84-12228** NAS 1.26:173335 p 10 N84-18269 • # NASA-CR-173398 p 81 N84-21594 * # L-15732 p 11 N84-18277 * # NAS 1.26:173336 p 13 N84-18294 • # NASA-CR-173400 p 80 N84-21592 * # L-15733 p7 N84-17211'# NAS 1.26:173337 p 12 N84-18293 * # NASA-CR-173401 p81 N84-21593 ' NAS 1.26:173338 p 21 N84-18680 * # NASA-CR-173402 p 81 N84-21595 ' LC-83-570 p36 N84-11195 # NAS 1.26:173345 p11 N84-18275 * # NASA-CR-173403 p 81 N84-21596 ' NAS 1.26:173398 : p 81 N84-21594 * # NASA-CR-173674 p 10 N84-18272 ' LCDS-83-22 p9 N84-17947 # NAS 1.26:173400 p 80 N84-21592 * # NASA-CR-174450 p 36 N84-10173 ' NAS 1.26:173401 p 81 N84-21593 • # NASA-CR-174605 p 17 N84-14233 ' UI-U-83-252 p78 N84-17050 # NAS 1.26:173402 p 81 N84-21595 * # NASA-CR-175160 p 79 N84-20605' NAS 1.26:173403 p 81 N84-21596 * # NASA-CR-175192 p 14 N84-20435 ' LMSC-D889718-VOL-1-ATTACH-1 p 12 N84-18293 * # NAS 1.26:173674 p 10 N84-18272 • # NASA-CR-175195 p 79 N84-19371 ' LMSC-0889718-V0L-1-ATTACH-2 p 13 N84-18294 * # NAS 1.26:174450 p 36 N84-10173 * # NASA-CR-175211 p 41 N84-19394 * # LMSC-D889718-VOL-1 p 12 N84-18292 " # NAS 1.26:174605 p 17 N84-14233 • # NASA-CR-175341 p 39 N84-16248 * # LMSC-D889718-VOL-2-ATTACH-2 p 12 N84-18291 * # NAS 1.26:175160 p 79 N84-20605 * # NASA-CR-175355 p 39 N84-16246 * # LMSC-D889718-VOL-4-ATTACH-1 p 12 N84-18290 * # NAS 1.26:175192 p 14 N84-20435 * # NASA-CR-175382 p 10 N84-18270 ' # LMSC-D931673 p 79 N84-20617 * # NAS 1.26:175195 p79 N84-19371 • # NASA-CR-175389 p 60 N84-20175 • # NAS 1.26:175211 p 41 N84-19394 * # NASA-CR-175412 p 80 N84-21437 ' MBB-UD-381-83-OE p 19 A84-22859 # NAS 1.26:175341 p 39 N84-16248 * # NASA-CR-175434 p 15 N84-21586 ' NAS 1.26:175355 p 39 N84-16246 * # NASA-CR-175435 p 14 N84-20604 ' MBB-UR-584-82-OE p 25 N84-11200 # NAS 1.26:175382 p 10 N84-16270 * # NASA-CR-175436 p 14 N84-20610 ' MBB-UR-628-83-OE p 72 A84-22862 # NAS 1.26:175389 p 60 N84-20175 * # NASA-CR-175437 p 60 N84-20857 ' NAS 1.26:175412 p 80 N84-21437 • # NASA-CR-175441 p 56 N84-21290 ' MCR-81-630 p9 N84-17248 * # NAS 1.26:175434 p 15 N84-21586 • # NASA-CR-175448 P 42 N84-20627 ' MCR-83-640 p 77 N84-10174 * # NAS 1.26:175435 p 14 N84-20604 • # NASA-CR-3698 P 9 N84-17248 * # MCR-83-643 p 56 N84-11595** NAS 1.26:175436 p 14 N84-20610 * # NASA-CR-3734 p 59 N84-10583 * # NAS 1.26:175437 p 60 N84-20857 * # NASA-CR-3735 p 59 N84-10584 ' # MDC-H0180A p 10 N84-18271 * # NAS 1.26:175441 p 56 N84-21290 * # NASA-CR-3736 p 59 N84-10582 * # NAS 1.26:175448 p 42 N84-20627 * # NASA-CR-3751 p 59 N84-13208 ' # MITT-28 p 22 N84-21914 # NAS 1.26:3698 p9 N84-17248 * # NASA-CR-3760 p 40 N84-18262 * # NAS 1.26:3734 p 59 N84-10583 * # MPR-3 p 81 N84-21593 * # NAS 1.26:3735 p 59 N84-10584 * # NASA-TM-77534 p 26 N84-18576 * # MPR-3 p 81 N84-21595 " # NAS 1.26:3736 p 59 N84-10582 * # NASA-TM-82562 p 78 N84-16075 • # NAS 1.26:3751 p 59 N84-13208 * # NASA-TM-82571 p 18 N84-21607 ' # MRC-R-744 p52 N84-21781 # NAS 1.26:3760 p 40 N84-18262 * # NASA-TM-83489 p 63 N84-11206'* NAS 1.55:2272 p 18 N84-22179 • # NASA-TM-84617 p7 N84-15172 ' # NAS 1.15:77534 p 26 N84-18576 * # NAS 1.55:2290 p 78 N84-12228 * # NASA-TM-84658 p 25 N84-15426 • # MAS 1.15:82562 p 78 N84-16075 * # NAS 1.55:2293 p 11 N84-18277 * # NASA-TM-85058 p 39 N84-16249 ' NAS 1.15:82571 p 18 N84-21607 * # NAS 1.55:2294 p7 N84-17211 '# NASA-TM-85439 p9 N84-17947 NAS 1.15:83489 p 63 N84-112061* NAS 1.60:2240 p 50 N84-16247 * # NASA-TM-85497 p 78 N84-16242 ' NAS 1.15:84617 p 7 N84-15172 * # NASA-TM-85556 p 51 N84-19382 ' NAS 1.15:84658 p 25 N84-15426 * # NASA-CASE-LAR-13117-1 p 59 N84-16250 • # NASA-TM-85686 p7 N84-15179 ' NAS 1.15:85058 p 39 N84-16249 * # NASA-TM-85689 p 17 N84-16427 ' NAS 1.15:85439 p9 N84-17947 # NASA-CASE-MFS-25906-1 p 59 N84-11761 * # NASA-TM-85697 p 37 N84-13608 ' NAS 1.15:85497 p 78 N64-16242 * # NASA-TM-85700 p 55 N84-11220' NAS 1.15:85556 p 51 N84-19382 * # NASA-CP-2272 p 18 N84-22179 * # NASA-TM-85702 p 7 N84-12026 ' # NAS 1.15:85686 p 7 N84-15179 * # NASA-CP-2290 p 78 N84-12228 * # NASA-TM-85743 p 42 N84-20880 * # NAS 1.15:85689 p 17 N84-16427 * # NASA-CP-2293 p11 N84-18277 ' # NASA-TM-85762 p 21 N84-19395 • # NAS 1.15:85697 p 37 N84-13608 * # NASA-CP-2294 p7 N84-17211 *# NASA-TM-85772 p 21 N84-21608 * # NAS 1.15:85700 p 55 N84-11220 * # NASA-TM-85774 p 60 N84-20626 • # NAS 1.15:85702 p7 N84-12026 * # NASA-CR-168193-VOL-1 p 63 N84-12226 * # NAS 1.15:85743 p 42 N84-20880 * # NASA-CR-168193-VOL-2 p 63 N84-13218 * # NASA-TP-2240 p 50 N84-16247 * # NAS 1.15:85762 p 21 N84-19395 * # NASA-CR-170899 p 77 N84-10174 * # NAS 1.15:85772 p 21 N84-21608 * # NASA-CR-170913 p 20 N84-10175 * # NTIA/REPT-83-135 P 51 N84-18532 # NAS 1.15:85774 p 60 N84-20626 * # NASA-CR-170914 p 20 N84-10176 * # NAS 1.2&168193-VOL-1 p 63 N84-12226 * # NASA-CR-170915 p 56 N84-11595 * # PB84-129402 p51 N84-18532 # NAS 1.2&168193-VOL-2 p 63 N84-13218 " # NASA-CR-170939 p 49 N84-12634 • # NAS 1.26:170899 p 77 N84-10174 * # NASA-CR-170948 p 78 N84-16097 * # PD80-55 p 80 N84-21592 • # NAS 1.26:170913 p 20 N84-10175 * # NASA-CR-170949 p7 N84-15171 '# PD81-20A p81 N84-21596 * # NAS 1.26:170914 p 20 N84-10176 * # NASA-CR-170972 p 40 N84-17251 *# PD82-1A p 81 N84-21594 * # NAS 1.26:170915 p 56 N84-11595** NASA-CR-170984 p 14 N84-19377 • # NAS 1.26:170939 p 49 N84-12634 * # NASA-CR-170993 p 42 N84-20625 * # PMIC-MA03-469-29 p 7 N84-15171 * # NAS 1.26:170948 p 78 N84-16097 * # NASA-CR-170996 p 41 N84-19392 * # NAS 1.26:170949 p7 N84-15171 ' # NASA-CR-171728 p 51 N84-17431 *# PO-83-506 P 7 N84-15171 ' # NAS 1.26:170972 p 40 N84-17251 '# NASA-CR-171764 p 28 N84-20622 * # NAS 1.26:170984 p 14 N84-19377 * # NASA-CR-171765 p 28 N84-20623 * # QR-1 p80 N84-21592 • # NAS 1.26:170993 p 42 N84-20625 * # NASA-CR-171766 p 28 N84-20624 * # NAS 1.26:170996 p 41 N84-19392 * # NASA-CR-171775 p 79 N84-20617 * # RADC-TR-83-158-VOL-1 p 40 N84-18311 # NAS 1.26:171728 p 51 N84-17431 '# NASA-CR-172223 p 17 N84-10114 • # RADC-TR-83-158-VOL-2 p 41 N84-18312 # NAS 1.26:171764 p 28 N84-20622 * # NASA-CR-172792 p 12 N84-18292 * # RADC-TR-83-51 p 38 N84-15181 # NAS 1.26:171765 p 28 N84-20623 * # NASA-CR-173215 p 25 N84-16565 * # RADC-TH-83-91-VOL-1 p 49 N84-14395 # NAS 1.26:171766 p 28 N84-20624 * # NASA-CR-173259 p 56 N84-17293 * # RADC-TR-83-91-VOL-2 p 49 N84-14394 # NAS 1.26:171775 P 79 N84-20617 * # NASA-CR-173266 p 78 N84-16991 * # NAS 1.26:172223 P 17 N84-10114 * # NASA-CR-173284 p 51 N84-17436 * # RAND/R-2936-ARPA p 36 N84-11195 # NAS 1.26:172792 P 12 N84-18292 * # NASA-CR-173312 p 13 N84-18296 * # NAS 1.26:173215 p 25 N84-16565 * # NASA-CR-173313 p 13 N84-18297 * # REPT-2-19200/3R-1062B p 28 N84-20624 • # NAS 1.26:173259 p 56 N84-17293 * # NASA-CH-173314 p 13 N84-18298 * # REPT-2-19200/3R-1195B p 28 N84-20623 * # NAS 1.26:173266 p 78 N84-16991 '# NASA-CR-173315 p 13 N84-18299 * # REPT-2-32300/IR-03 p 28 N84-20622 * # NAS 1.26:173284 p 51 N84-17436 * # NASA-CR-173316 p 13 N84-18300 * # REPT-2983-81 p 56 N84-21290 * # NAS 1.26:173312 p 13 N84-18296 * # NASA-CR-173317 p 13 N84-18301 * # REPT-38172-6001-UE-00 p 49 N84-12634 ' # NAS 1.26:173313 p 13 N84-18297 * # NASA-CR-173318 p 14 N84-18302 • # NAS 1.26:173314 p 13 N84-18298 * # NASA-CR-173319 p 14 N84-18303 • # R878 p56 N84-21675 # NAS 1.26:173315 p 13 N84-18299 * # NASA-CR-173320 p 14 N84-18304 • # NAS 1.26:173316 p 13 N84-18300 * # NASA-CR-173321 p 10 N84-18273 • # S-REPT-98-523 P79 N84-20613 # NAS 1.26:173317 p 13 N84-18301 * # NASA-CR-173327 p11 N84-18274 • # NAS 1.26:173318 p 14 N84-18302 * # NASA-CR-173328 p 10 N84-18271 • # SA-SPP-RP008-VOL-2-BK-1-PT-2 p 13 N84-18297 • # NAS 1.26:173319 p 14 N84-18303 * # NASA-CR-173329 p 12 N84-18291 * # NAS 1.26:173320 p 14 N84-18304 * # NASA-CR-173330 p 12 N84-18290 * # SA-SSP-RP008-VOL-2-BK-1-PT-1 p 13 N84-18296 * # NAS 1.26:173321 p 10 N84-18273 * # NASA-CR-173331 p 10 N84-18268 * # SA-SSP-RP008-VOL-2-BK-1-PT-3 p 13 N84-18298 * # NAS 1.26:173327 p 11 N84-18274 * # NASA-CR-173332 p 10 N84-18267 * # SA-SSP-RP008-VOL-2-BK-1-PT-4 p 13 N84-18299 ' # NAS 1.26:173328 p 10 N84-18271 '# NASA-CR-173333 p9 N84-18266 * # SA-SSP-RP008-VOL-2-BK-2-PT-1 p 13 N84-18300 ' #

E-2 REPORT NUMBER INDEX UVA/52824/MAE84/101

SA-SSP-RP008-VOL-2-BK-2-PT-2 p 13 N84-18301 ' tt SA-SSP-RP008-VOL-2-BK-2-PT-3 p 14 N84-18302 ' # SA-SSP-RP008-VOL-2-BK-2-PT-4 p 14 N84-18303 ' tt SA-SSP-RP008-VOL-2-BK-3 p 14 N84-18304 • ft SA-SSP-RP009-PT-1 p 10 N84-18270 ' tt

SAE PAPER 831097 p 24 A84-29032 " tt SAE PAPER 831101 p 24 A84-29036 tt SAE PAPER 831108 pS A84-29043 ' tt SAE PAPER 831109 p 5 A84-29044 • it SAE PAPER 831111 p6 A84-29046 ' tt SAE PAPER 831112 p 6 A84-29047 ' tt SAE PAPER 831120 p6 A84-29054 tt SAE PAPER 831122 p6 A84-29056 tt SAE PAPER 831133 p 75 A84-29063 ' tt SAE PAPER 831138 p 24 A84-29067 tt SAE PAPER 831144 p 24 A84-29071 tt SAE PAPER 831151 p 24 A84-29076 ' tt

SAND-83-1631C p 25 N84-16509 tt

SAPR-45 p56 N84-17293 ' ft

SOC-SE-02-02 P 10 N84-18273 * tt

SSD-83-0037 p11 N84-18274 ' tt SSCW3-0094-1-VOL-1 p 20 N84-10175 ' ft SSD-83-O094-2-VOL-2 p 20 N84-10176 * #

SSL-30-83 p59 N84-10583 * tt SSL-31-83 p59 N84-10584 * tt SSL-32-83-VOL-3-PHASE-2 p 59 N84-10582 * tt

STI/E-TR-25066-VOL-3 p 79 N84-19371 • tt

TB-TS-11-01/82-A p56 N84-18416 tt

TM-EKR3 p 17 N84-17284 ft

TR-1183-8314 p 51 N84-17431 •#

US-PATENT-APPL-SN-537757 p 59 N84-11761 ' tt US-PATENT-APPU-SN-556512 p 59 N84-16250 ' tt

USNA-TSPR-126 p59 N84-16807 ft

UVA/52824/MAE84/101 p 39 N84-16246 ' ft

E-3 ACCESSION NUMBER INDEX

TECHNOLOGY FOR LARGE SPACE SYSTEMS / A Bibliography (Supplement 11) JANUARY 1985

Typical Accession Number Index Listing A84-17910 # p23 A84-24636 #' p73 A84-29855 tt p76 A84-17911 '# P23 A84-24637 tt p73 A84-29856 # p76 A84-18005 tt P4 A84-24980 tt p61 A84-29857 # p76 A84-18025 A84-29858 # '# P46 AS4-24981 # p62 P? A84-18060 « P32 A84-29861 tt P48 A84-24990 # p34 A84-18141 '# p61 A84-29862 # p20 p34 A84-18159 # P53 A84-24991 ' # A84-29865 tt p77 A84-24995 # p34 A84-18168 # P33 AS4-29866 * # p77 A84-25251 # p73 A84-18394 *# P46 A84-29868 # P77 A84-25253 # p73 A84-19056 '# P33 A84-29869 # p62 A84-25254 # p74 A84-19108 # P15 A84-29883 tt P77 A84-25258 # p 20 A84-19118 # P33 AB4-44183 '# p58 A84-25259 # p16 A84-19127 # P33 A84-25260 # A84-19128 # p33 Pi N84-10114 '# P17 A84-25281 # p74 A84-19129 # p16 N84-10173 '# p36 A84-25282 # p4 A84-19169 # P46 N84-10174 '# P77 p4 A84-19675 # P33 A84-25287 # N84-10175 '# p20 A84-2S291 # p34 Listings in this index are arranged alphanumerically by A84-19728 # P33 N84-10176 '# p20 A84-25292 # p62 A84-19850 # p69 N84-10179 # P77 accession number. The page number listed to the right A84-25293 # p62 A84-19887 # P16 N84- 10582 '# p59 indicates the page on which the citation is located. An A84-25294 # p62 A84-19912 *# P53 N84-10583 * # P59 A84-25304 # 74 asterisk (*) indicates that the item is a NASA report. A A84-20047 # P33 P N84-10584 •# p59 A84-25306 # p48 A84-20583 tt p46 N84-11195 # P36 pound sign (#) indicates that the item is available on A84-25308 # p5 A84-20647 # P46 N84-11199 # p20 microfiche. A84-25309 tt p74 A84-20682 '# P54 N84-11200 # P25 A84-25318 # p74 A84-20709 # P47 N84-11206 *# p63 A84-25319 '# p74 A84-21237 # P34 N84-11220 *# P55 A84-25326 * # p5 A84-21284 # P23 N84-11595 '# p56 A84-25327 # P75 A83-44602 tt P57 A84-14586 '# p66 A84-21285 tt p34 N84-11761 *# P59 A84-25344 # p62 A84-10016 # p43 A84-14762 # P2 A84-21344 i» P69 N84-12026** p7 A84-10024 '# p63 A84-21476 # p69 A84-25484 • # pS8 N84-12222 # p36 A84-14764 # p66 34 A84-10025 tt p43 A84-21477 # P69 A84-25496 * # P N84-12226 '# p63 A84-1S092 # p67 p3S A84-10066 •tt p63 A84-21478 # P70 A84-25516 # N84-12228 '# p7S A84-15161 tt p67 A84-25525 * # p16 A84-10070 '# P57 A84-21479 # P70 N84-12233 *# p48 A84-15189 A84-25531 # 58 A84-10141 '# p19 # p67 A84-21480 •tt P70 P N84-12234 '# p37 A84-2S551 '# p16 A84-10224 tt p22 A84-1S301 tt P2 A84-21481 # p70 N84-12235'# p37 A84-15303 # A84-25552 * # p35 A84-10396 tt- P44 P2 A84-21482 # p70 N84-12236'# p37 A84-15304 # A84-25586 # p35 A84-10440 tt p22 P2 A84-21483 tt p70 N84-12238 *# P37 A84-2S828 # p58 A84-10883 # p64 A84-15305 # P2 A84-21484 # P61 N84-12243*# p37 A84-26516 # p48 A84-10949 '# p52 A84-15310 # p3 A84-21485 # P61 N84-12245** p37 A84-15321 A84-26717 # p35 A84-10956 # p30 # p67 A84-21486 # P57 N84-12246** p48 A84-15325 # P3 A84-26845 # p35 A84-10965 •it p64 A84-21487 0 p70 N84-12634'# P49 5 A84-11719 # p64 A84-15363 # p3 A84-21488 # P71 A64-26926 # P N84-12653 tt p49 A84-15381 tt p67 A84-26977 # P35 A84-11722 # P64 A84-21489 # P71 N84-13208 '# p59 A84-15623 p44 A84-27443 # p62 A84-11723 it P64 # A84-21497 » P71 N84-13218'# p63 p35 A84-11724 tt P1 A84-15634 'tt p3 A84-21499 # P71 A84-27934 * # N84-13608 '# p37 A84-15639 'tt p45 A84-27945 # p5 A84-11726 '# P1 A84-21517 # P19 N84-14233 '# P17 A84-15640 A84-28067 # p48 A84-11727 it p64 'tt p45 A84-21564 # P16 N84-14234 # p7 A84-15641 tt p45 A84-28237 # p24 A84-11728 tt p65 A84-21573 # P4 N84-14235 # P37 A84-15642 p45 A84-28242 # p54 A84-11731 it P1 'it A84-21720 # p71 N84-14394 # P49 A84-15643 A84-28458 • # 54 A84-11737 tt p65 '# p45 A84-21775 # P54 P N84-14395 # p49 A84-15667 A84-28523 '# p58 A84-11739 # p65 '# P57 A84-22131 '# P16 N84-14546 # p38 A84-15671 A84-11753 it p65 tt p45 A84-22153 # P19 A84-28541 # p58 N84-14561 # p20 A84-15695 A84-28553 • # A84.11773 it p65 tt P3 A84-22327 # P71 p55 N84-14752 # p78 A84- 15785 P31 A84-28S76 # p75 A84-11779 it p65 tt A84-22336 # p57 N84-14759 tt P17 A84-18116 tt P61 A84-28579 # p75 A84-11787 it p65 A84-22337 # p58 N84-14761 tt P49 A84-16841 A84-11793 '# P1 # P15 A84-22338 # P71 AB4-28900 # p55 N84-15171 '# p7 A84-16885 A84-28975 # p75 A84-11811 '# P2 # P32 A84-22341 '# P72 N84-15172'* P7 A84-17026 p67 A84-29032 •# p24 A84-11814 # p22 # AS4-22859 # P19 N84-15179** V^ A84-17054 p24 A84-11815 # p30 tt p68 A84-22862 # P72 AB4-29036 # N84-15181 tt p38 A84-17057 # p68 A84-29043 •# p5 A84-11816 •it p44 A84-22958 *# P47 N84-15182 tt P38 A84-17058 A84-29044 •# p5 A84-11817 it p44 tt P68 A84-22959 # p47 N84-15329-* p25 A84-17074 A84-29046'# p6 A84-11823 # p44 # p68 A84-22961 '# P47 N84-15386 tt p49 A84-17075 p68 A84-29047 '# p6 A84-11922 # P19 tt A84-22962 # P47 N84-15426 ' tt P25 A84-11930 # pis A84-17076 # p68 A84-22963 *# P47 A84-29054 # P6 N84-15562 # p25 A84-17077 A84-29056 # 6 A84-11932 tt p30 tt p68 A84-22965 *# P19 P N84-15840 tt p38 A84-17108 p52 A84-29063 '# 75 A84-11933 tt p30 tt A84-22979 '# P47 P N84-15970 # P49 A84-17120 p52 A84-29067 # P24 A84-11934 # p31 tt A84-22980 '# P61 N84-16037'* P56 AB4-11935 tt p57 A84-17151 # P53 A84-22982 # p48 A84-29071 # P24 N84-160S6 * tt p38 A84-29076 * # A84-11938 •it p66 A84-17174 # p53 A84-22997 # p48 p24 N84-16075 * tt p78 A84-17200 A84-11945 tt p31 tt P53 A84-23366 # P20 A84-29101 # pSS N84-16097 • tt p 78 A84-17355 p32 A84-29126 # p75 AB4-11946 •tt P15 '# A84-23440 '# p72 N84-16232 tt P39 A84-12483 tt p31 A84-17359 tt P32 A84-24501 # p54 A84-29143 tt p36 N84-16242 * # p 78 A84-17361 A84-29145 # A84-12488 it p31 'tt p32 A84-24508 # P54 p36 N84-16246 * tt p39 A84-17389 p32 A84-29471 •*> p36 A84-12489 tt p31 tt A84-24626 '# P72 N84-16247'* p50 A84-17370 p32 A84-29565 # p55 A84-13320 it p31 tt A84-24627 •# P72 N84-16248 • # p39 A84-17743 tt P46 A84-29572 # (.55 A84-13321 # p31 A84-24628 '# p4 N84-16249 • # P39 A84-17762 A84-296S6 tt A84- 13330 tt P2 tt p69 A84-24629 i» p72 P75 N84-16250 • # p59 A84-17763 p69 A84-29657 # p76 A84-13376 tt p66 it A84-24631 # P72 N84-16420 •# p78 A84- 17768 tt p53 A84-296S8 # p76 A84-13397 p61 A84-24632 # P73 N84-16427'# P17 tt A84-17850 tt p23 A84-29666 # p6 A84- 13521 ft p44 A84-17853 tt p23 AS4-24633 •l? P4 AS4-29852 • # p76 N84-16509 # P25 A84-13901 tt p66 A84- 17854 tt p32 A84-24634 •# P4 A84-29853 '# P7 N 84-16565 '# P25 A84- 14050 '» P23 AB4-17B66 tt p32 A84-24635 # P73 A84-29S54 # p76 N84-16677 # p78

F-1 N84-16807 ACCESSION NUMBER INDEX

N84-16807 # p59 N84-19392 '# p41 N84-16991 •# p78 N84-19394 • tt p41 N84-17050 # p78 N84-19395 * tt p21 N84-19396 # p26 N84-17211 '# P7 N84-19398 tt p26 N84-17212 p8 '# N84-19399 # p26 N84-17213 p8 '# N84-19400 tt p26 N84-17215 p8 '# N84-19401 # p26 N84-17217 p56 'tt N84-19402 '# p26 N84-17218 p8 '# N84-19405 # p26 N84-17219 'tt p60 N84-19406 # P27 N84-17220 8 •# P N84-19414 # p27 N84-17221 p8 '# N84-19423 # p27 N84-17222 25 •# P N84-19429 # p79 N84-17223 p79 '# N84-19434 # p27 N84-17224 50 '# P N84-19444 # p27 N84-17225 •tt P17 N84-19449 # p27 N 84-1 7226 21 '# P N84-19454 # 27 N84-17227 p39 P '# N84-19458 # p27 N84-17228 p39 '# N84-19463 # p52 N84-17229 •tt p39 N84-19464 # p41 N84-17230 p40 •# N84-19465 # p42 N84-17231 8 '# P N84-19474 # p63 N84-17232 p8 '# N84-19899 # p21 N84-17233 P8 '# N84-19900 # p42 N84-17234 9 '# P N84-19906 # p 28 N84-17235 50 '# P NB4-20175 '# p60 N84-17236 '# p50 N84-20316 tt p60 N84-17237 '# p9 N84-20435 * tt P14 N84-17241 # p40 N84-20604 • tt P14 N84-17248 p9 '# N84-20605 • tt p79 N84-17251 'tt p40 N84-20610 *# p14 N84-17253 # p56 N84-20613 # 79 N84-17254 pSO P tt N84-20617 •# 79 N84-17269 pSO P •# N84-20621 # p 18 N84-17284 P17 tt N84-20622 • tt p28 N84-17293 p56 •tt N84-20623 • # p28 N84-17431 p51 '# N84-20624 * tt p28 N84-17436 51 "# P N84-20625 * # 42 N84-17931 p51 P tt N84-20626 ' # p60 N84-17947 # p9 N84-20627 • # P42 N 84-1 81 16 # p9 N84-20857 * # p60 N84-18262 p40 'it N84-20880 ' # 42 N 84-1 8265 p9 P '# N84-21145 # 79 N84-18266 9 P •it P N84-21172 tt 43 N 84-1 8267 p10 P '# N84-21290 * tt p56 N 84-1 8268 p 10 '# N84-21437 * # pBO N84-18269 p10 '# N84-21440 # p80 N84-18270 p10 •# N84-21441 # p80 N84-18271 '# p10 N84-21442 # p80 N84-18272 •# p 10 N84-21443 # p80 N84-18273 '# p 10 N84-21444 # p80 N84-18274 '# P11 N84-21586 * tt p15 N84-18275 '# P11 N84-21590 # p80 N84-18277 '# P11 N84-21592 '# p80 N 84-18278 •# P11 N84-21593 '# p81 N84-18279 '# p11 N84-21594 " # p81 N84-18280 •# P11 N84-21595 •# p81 N84-18281 p40 •tt N84-21596'# p81 N84-18282 p11 •# N84-21604 # 43 N 84-18283 p11 P •it N84-21607*# p18 N84-18284 '# p11 N84-21608'* p21 N 84-18285 p12 '# N84-21611 # p43 N 84-18286 '# P21 N84-21612 # P43 N 84-18287 '# p12 N84-21613 tt p28 N 84-18288 •# P12 N84-21614 # p28 N 84-18289 '# p25 N84-21615 # p21 N 84-18290 'it P12 N84-21616 # p29 N 84-18291 '# p12 N84-21617 # p29 N 84-18292 '# P12 N84-21618 # p29 N 84-18293 '# P12 N84-21619 tt p29 N 84-18294 p13 '# N84-21620 tt p18 N 84-1 8296 p13 •if N84-21621 # p29 N 84-1 8297 p13 •tt N84-21622 # p29 N 84-1 8298 p13 •# N84-21623 tt p15 N 84-1 8299 p13 •# N84-21624 tt p18 N 84-1 8300 •# p13 N84-21625 # p 18 N 84-1 8301 p 13 •# N84-21626 tt p30 N 84-18302 p14 •# N84-21675 # pS6 N 84-1 8303 p14 •# N84-21781 tt pS2 N 84-18304 14 •# P N84-21914 ft p22 N 84-18311 40 # P N84-22179 '# p18 N84-18312 p41 # N84-22191 '# p 18 N 84-18313 # P41 N84-22224 * # P19 N84-18315 # P79 N84-22225 * tt P22 N 84-18416 # p56 N84-18457 #. P17 N 84-1 84 58 # P51 N84-18475 # P17 N 84-1 8532 # P51 N84-18576 •# p26 N 84-18680 •# P21 N 84-1 8987 # p41 N 84-1 9371 '# P79 N84-19377 '# p14 N 84-1 9382•# p51 N 84-1 9383 tt p41

F-2 1. Report No. 2. Government Accession No. 3. Recipient' s Catalog No. NASA SP-7046 (11) 4. Title and Subtitle 5. Report Date TECHNOLOGY FOR LARGE SPACE SYSTEMS January 1985 A Bibliography with Indexes 6. Performing Organization Code

7. Author! j) 8. Performing Organization Report' No.

10 Work Unit No 9. Performing Organization Name and Address

National Aeronautics and Space Administration 11. Contract or Grant No. Washington, D.C. 20546 13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address

14. Sponsoring Agency Code

15. Supplementary Notes Report prepared, in part, by personnel in the Space Technology Flight Experiments Office and the Technical Library Branch, Hampton, Virginia.

16. Abstract

This bibliography lists 539 reports, articles and other documents introduced into the NASA scientific and technical information system between January 1, 1984 and December 31, 1984. Its purpose is to provide helpful information to the researcher, manager, and designer in technology development and mission design in the area of Large Space System Technology. Subject matter is grouped according to system, interactive analysis and design, structural and thermal analysis and design, structural concepts and control systems, electronics, advanced materials, assembly concepts, propulsion, and solar power satellite systems.

17. Key Words (Suggested by Autftor(sl) 18. Distribution Statement Large Space Systems Large Space Structures Unclassified - Unlimited Large Space Antenna

19. Security dassif. (of this report) 20. Security Cassif. (of this page) 21. No. of Pages 2Z Price* Unclassified Unclassified 146 $14.50 HC

For sale by the National Technical Information Service, Springfield, Virginia 22161

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