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NASA SP-7046(13) Teehraology for March 1986 NASA Large Space Systems • A Bibliography with Indexes

{NASA-SP-70U6 (13) ) TECHNOLOGY FOB LARGE N86-24713 SPACE SYSTEHS: A BIBLJOGHAPHY HUH INDEXES {National Aeronautics and Space Administration) 111 p HC A06 CSCI 22A Onclas H1/12 13361 NASA SP-7046(13)

TECHNOLOGY FOR LARGE SPACE SYSTEMS

A BIBLIOGRAPHY WITH INDEXES

Supplement 13

Compiled by Technical Library Branch and Edited by Space Systems Division NASA Langley Research Center Hampton, Virginia

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 30,1985 in

Scientific and Technical Aerospace Reports (STAR) International Aerospace Abstracts (IAA)

Scientific and Technical Information Branch 1986 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 ($16 95 domestic; $33 90 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 (LSST). 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 399 reports, articles and other documents announced between January 1, 1985 and June 30, 1985 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 separate companion document "Space Station Systems Bibliography" (NASA SP-7056) incorporates space station technology not applicable to large space systems Space station systems technology that is also applicable to large space systems may be documented in both bibliographies Robert L Wright, Space Systems Divison Sue K Seward, Technical Library Branch 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 6 Includes interactive techniques, computerized technology design and development programs, dynamic analysis techniques, environmental modeling, thermal modeling, and math modeling.

Category 03 Structural Concepts 10 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 13 Includes structural analysis and design, thermal analysis and design, analysis and design techniques, and thermal control systems Category 05 Structural Dynamics and Control 17 Includes modeling, systems identification, attitude and control techniques, surface accuracy measurement and control techniques and systems, sensors and actuators. Category 06 Electronics 29 Includes techniques for power and data distribution, antenna RF performance analysis, communications systems, and spacecraft charging effects Category 07 Advanced Materials 35 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 41 Includes automated manipulator techniques, EVA, robot assembly, teleoperators, and equipment installation. Category 09 Propulsion 43 Includes propulsion concepts and designs utilizing solar sailing, solar electric, ion, and low thrust chemical concepts. Category 10 General 50 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 Foreign Technology Index D-1 Contract Number Index E-1 Report Number Index F-1 Accession Number Index G-1

PRECEDING PAGE BLANK NOT FILMED TECHNOLOGY FOR LARGE SPACE SYSTEMS A Bibliography (Suppl. 13)

MARCH 1986

01 A85-13016# UTILIZATION AND ECONOMICS OF A EUROPEAN LOW EARTH ORBIT SPACE PLATFORM SYSTEMS R C PARKINSON and I V FRANKLIN (Bntish Aerospace, PLC, Space and Communications Drv, Stevenage, Herts , England) Includes mission and program concepts and requirements, focus International Astronautical Federation, International Astronautical missions, conceptual studies, technology planning, systems Congress, 35th, Lausanne, Switzerland, Oct 7-13, 1984 7 p analysis and integration, and flight experiments (IAF PAPER 84-57) In addition to the manned, core station, the facilities of the Space Station are to include also a Teleoperated Service Vehicle, A85-12502# a cryogenic Orbit Transfer Vehicle, and unmanned Space Platforms SPACE EXPLOITATION - SPACELAB AN EASY APPROACH Following President Reagan's invitation for international FOR DEVELOPING COUNTRIES: PROSPECTIVES AND participation in the Space Station program, the Space Platform is SUGGESTIONS BY AERITALIA of particular interest to Europe A Space Platform is defined as E VALLERANI (Aentaha SpA, Turin, Italy) IN International an unmanned orbiting facility in which essential services are Scientific Conference on Space, 23rd, Rome, Italy, March 24, 25, supplied by a common Resources Module while payloads can be 1983, Proceedings Rome, Rassegna Internazionale Elettronica attached or recovered on a temporary basis The present Nucleate ed Aerospaziale, 1984, p 45-49 investigation is concerned with the extent of potential interest in The problem of access by developing countries to space Europe in using such a Platform, the associated costs of information and resources is discussed from the Italian point of development and operation, and the economic attractions to view The international cooperation involved in the development Europe of undertaking such a development It is concluded that of IRIS, Spacelab, and Eureca is considered, the ongoing the Space Platform (or Platforms) appears to represent a commercialization of space in the STS, Anane, and Space Station cost-effective area of participation in the U S Space Station programs is examined, and the need for careful planning and program, at a cost Europe could afford, and with a function useful preparation in the developing countnes to take advantage of future both to Europe and the U S G R space-exploitation opportunities is stressed It is proposed that Italian universities and industry provide assistance in training personnel and designing payloads to meet the needs of developing countnes T K

A85-13045# A85-130090 SOME RESULTS OF THE MSAT PHASE B STUDIES AND THEIR UTILIZATION OF A TELEOPERATED SERVICE VEHICLE FOR IMPACT ON SYSTEM DESIGN SPACECRAFT SERVICING J L MCNALLY, H R RAINE, and J D B KENT (Canadian C COUGNET (Matra, SA, Toulouse, France) and C BERGER Department of Communications, Communications Research Centre, (Matra, S A, Velizy-Villacoublay, Yvelmes, France) International Nepean, Ontano, Canada) International Astronautical Federation, Astronautical Federation, International Astronautical Congress, International Astronautical Congress, 35th, Lausanne, Switzerland, 35th, Lausanne, Switzerland, Oct 7-13, 1984 15 p Research Oct 7-13, 1984 10 p. refs supported by the European Space Agency (IAF PAPER 84-89) (IAF PAPER 84-48) In 1980, the Department of Communications (DOC) decided to Potential, commercially oriented European space missions are commence Phase A feasibility studies for a mobile satellite system discussed in terms of the required capabilities, equipment, and in the 800 MHz band The considered system would use a applications A trend toward heavier lift launch vehicles is foreseen, geostationary satellite to provide direct communication with vehicles together with an interface with a long-life orbital base of operations in nonurban areas throughout Canada including offshore coverage and teleoperated service vehicles (TSV) On-ortoit servicing of of temtonal waters. Promising results were obtained with respect satellites is inevitable for improving the reliability, mission duration, to potential market, system feasibility, and commercial viability It and cost effectiveness of space utilization hardware. The TSV was, therefore, decided to proceed with the second phase (Phase would operate out of a space station and be capable of orbital B Project Definition) in Apnl 1982 Phase B involved an examination transfer, rendezvous, and servicing functions It would place, of system architecture, spacecraft, mobile radios, ground stations, retrieve, and repair satellites and provide space station logistic Demand Assignment Multiple Access (DAMA) systems, and support. The TSV could also be either ground-based or expendable, business requirements The present investigation attempts to and in any case would be controlled via relay satellite, unless provide an outline of some of the results and to project some interfacing with the Shuttle or functioning in proximity to the Space plans for the future It is concluded that during the studies there Station Particularly frequent use would be made of the TSV in has been an evolution toward a commercially-realizable first servicing space-based matenals processing facilities M S K generation system G R

1 01 SYSTEMS

A85-13144# A85-20507 ECONOMICS OF PERMANENT POLAR PLATFORMS (PPP) FOR INTERNATIONAL SPACE PROGRAMMES AND POLICIES GLOBAL MONITORING N JASENTULIYANA, ED and R. CHIPMAN, ED Amsterdam, D E KOELLE (ERNO Raumfahrttechmk GmbH, Ottobrunn, West North-Holland, 1984, 571 p No individual items are abstracted in Germany) International Astronautical Federation, International this volume Astronautical Congress, 35th, Lausanne, Switzerland, Oct 7-13, The Second United Nations Conference on the Exploration 1984 8p and Peaceful Uses of Outer Space (UNISPACE) took place in (IAF PAPER 84-226) Vienna, Austria, from 9 to 20 August 1982 with 94 states Economic considerations in the development of a design for a participating Part I of this publication provides a report which was Permanent Polar Platform (PPP) for global monitoring are adopted at the Conference, taking into account the state of space discussed Attention is given to the need for interchaneability in science and technology, applications of space science and the design of various payload modules including propulsion system, technology, and international cooperation and the role of the United an auxiliary tank system, an equipment and avionics system and Nations The subjects discussed include expenments in the space an orbital crew cabin The costs of several different design environment, telecommunications, meteorology, remote sensing, configurations are compared with total LANDSAT system costs navigation, global positioning, geodesy, space transportation and are found to be competitive It is shown that the overall costs of space platform technologies, mobile communications, maritime and the system can be cut in half once the permanent platforms are aeronautical communication, satellite broadcasting, choices and in place I H difficulties in the use of space technology, mechanisms for enabling all states to benefit from space technology, and the compatibility of satellite systems Part II of the publication is concerned with the papers presented by 61 countries, while Part III provides a A85-13233# summary of the proceedings of the Conference along with the ORIENTATION AND TRENDS IN EUROPEAN TECHNOLOGY text of selected statements made at the Conference G R H STOEWER (ESA, Systems Engineering Dept, Noordwijk, Netherlands) International Astronautical Federation, International A85-20866*# National Aeronautics and Space Administration Astronautical Congress, 35th, Lausanne, Switzerland, Oct 7-13, Ames Research Center, Moffett Field, Calif 1984 13 p DETERMINATION OF ATMOSPHERIC DENSITY USING A (IAF PAPER 84-377) SPACE-LAUNCHED PROJECTILE The current status and future directions of technology G P MENEES, C PARK (NASA, Ames Research Center, Moffett development programs under the direction of the ESA Space Field, CA), K G BROWN (NASA, Ames Research Center, Moffett Research and Technology Center and on a national level in the Field, CA, USAF, Washington, DC), and J F WILSON (Informatics ESA member states are surveyed in a number of charts and tables General Corp, Palo Alto, CA) American Institute of Aeronautics and bnefly charactenzed Areas examined include data handling, and Astronautics, Aerospace Sciences Meeting, 23rd, Reno, NV, power generation, structures, controls, software, and robotics, to Jan 14-17, 1985 13 p refs serve missions including earth-space telematics, the Telecom (AIAA PAPER 85-0327) system, terrestrial remote sensing, deep-space exploration and A method is proposed that provides advance information about observation, microgravity utilization, space platforms, and m-orbit unpredictable atmospheric density dispersions that must be operations T K accommodated during random operations of aeroassisted-orbital-transfer vehicles (AOTVs) The principal feature is that a test or 'scout' projectile precedes the AOTV through the A85-13244# same region of the atmosphere as that of the predicted CONSTRUCTION OF LARGE PRECISION REFLECTORS USING transatmosphenc flight trajectory The atmospheric density structure THE AFT CARGO CARRIER is determined from the vehicle's aerodynamic deceleration J M HEDGEPETH (Astro Research Corp , Carpmtena, CA), T B characteristics by on-board or ground-based tracking equipment MOBLEY (Martin Marietta Aerospace, New Orleans, LA), and T The time lag between passage of the projectile and the AOTV C TAYLOR (Taylor and Associates, Inc, Wrightwood, CA) can be adjusted to only that time necessary to implement required International Astronautical Federation, International Astronautical guidance, navigation, and control (GN&C) corrections The various Congress, 351h, Lausanne, Switzerland, Oct 7-13, 1984 8 p strategies available to control the projectile's flight characteristics (IAF PAPER 84-389) are analyzed in detail The results are correlated with The Aft Cargo Garner (ACC) will provide a large-sized volume aerothermodynamic heating and matenals requirements to ensure for launching into orbit This paper reports a conceptual study the survival of the projectile and, consequently, the capability of aimed at examining approaches for using this capability in aiding the AOTV to navigate a variable upper atmosphere within specified the establishment of large precision reflectors in space Attention limits Author is paid, in particular, to infrared telescopes with decameter apertures The ACC is descnbed, and vanous stowage schemes A85-22577* Arizona Univ, Tucson are discussed A novel technique of compacting the backup DEPLOYABLE REFLECTOR CONFIGURATIONS structure during launch is explained Author A B MEINEL, M P. MEINEL (Anzona, University, Tucson, AZ), and N J WOOLF (Steward Observatory, Tucson, AZ) IN Deployable optical systems, Proceedings of the Meeting, Los Angeles, CA, January 18, 19, 1983 Bellmgham, WA, SPIE - The A85-16109*# National Aeronautics and Space Administration, International Society for Optical Engmeenng, 1983, p 2-10 Washington, 0 C (Contract JPL-955687, NAGW-121) THE FUTURE OF SPACE FLIGHT Both the theoretical reasons for considenng a non-circular J W MOORE (NASA, Washington, DC) International Air Transport format for the Large Deployable Reflector, and a potentially Association, Dr Albert Plesman Memonal Lecture, 9th, Technische realizable concept for such a device, are discussed The optimum Hogeschool Delft, Delft, Netherlands, Oct 26, 1984, Paper 61 p systems for diffraction limited telescopes with incoherent detection The history of the NASA space program is traced, and future have either a single filled aperture, or two such apertures as an plans are outlined Projects discussed include Mercury, Gemini, interferometer to synthesize a larger aperture For a single aperture Apollo, Skylab, Apollo-Soyuz, science-applications spacecraft of limited area, a reflector in the form of a slot can be used to (Ranger, Surveyor, Manner, Pioneer, and Voyager), the Space give increased angular resolution It is shown how a 20 x 8 meter Shuttle, the planned Space Station, orbital maneuvering vehicles, telescope can be configured to fit the Space Shuttle bay, and lunar bases, and planetary exploration Numerous photographs and deployed with relatively simple operations The relationship between drawings are provided T K the sunshield design and the inclination of the orbit is discussed 01 SYSTEMS

The possible use of the LOR as a basic module to permit the up to now earned solely by France Work will continue on the construction of supergiant space telescopes and interferometers matching launch vehicle, the Anane 5 and on free-flying platforms both for IR/submm studies and for the entire ultraviolet through which will be visited only periodically and which will carry mm wave spectral region is discussed. Author proof-of-technology expenments. The construction of modules for the US Space Station is hoped to provide a technology and A85-25117 manufacturing base for building a European space station at some A METHODOLOGY FOR ORGANIZING PERFORMANCE unspecified epoch in the future M S K REQUIREMENTS FOR COMPLEX DYNAMICAL SYSTEMS H. L MALCHOW and S. R CROOPNICK (Charles Stark Draper A85-26771# Laboratory, Inc, Cambridge, MA) IEEE Transactions on THE COMMUNICATION-SATELLITE MARKET TO THE YEAR Engineering Management (ISSN 0018-9391), vol EM-32, Feb 2000 [DE COMMUNICATIESATELLIETMARKT TOT HET JAAR 1985, p. 10-15 refs 2000] Management of the development of complex dynamical systems R. J VAN DUINEN (Fokker, Schiphol, Netherlands) Ruimtevaart, includes the tasks of establishing system performance vol 33, Aug-Oct 1984, p. 130-141 In Dutch. requirements These requirements are typically obtained from a The developmental history of communication satellites (CSs) nonsystematic process, which often results in premature is traced, the demands placed on industry by the increasing constraining of system design This paper describes an orderly sophistication of CS payloads, the need to adapt the CS to different methodology for establishing performance requirements for launchers (STS or Anane), and the requirement of longer service complex systems The methodology uses a 'top-down' approach life are reviewed, and the evolution of the markets for fixed Connections between the system high level mission requirements (telephone, telex, and facsimile), video, business, and broadcasting and the lower level functional performance requirements are made service is projected over the period 1980-2000 and illustrated with in a series of steps The steps include identification of system tables and graphs It is predicted that the worldwide market, activities, identification of activity-derived state vector elements, expressed in terms of the demand for 36-Mhz transponders, will definition of state maintenance functions, and identification of increase from 426 in 1980 to 1410 in 1985, 3100 in 1990, 5580 functional components Author in 1995, and 9870 in 2000, with the mam increase in transponders for voice communications The potential for Netherlands A85-25697 participation in the growth of the CS market is evaluated, and the SPACE - THE FUTURE OF MANKIND need for government leadership and for active promotion efforts G MUELLER Spaceflight (ISSN 0038-6340), vol 27, March 1985, is stressed T K p 104-107 Major advances in the fields of communication and air and A85-27375 space travel over the course of this century are reviewed, and COMMERCIALIZATION OF SPACE - INCENTIVES, the future plans concerning space travel are looked into for two IMPEDIMENTS AND ALTERNATIVES decades ahead Among the future programs mentioned are: a H R MARSHALL, JR (U S Department of State, Bureau of Oceans continuously manned modular space station, with each module and International Environmental and Scientific Affairs, Washington, being capable of accommodating 12 people, which would be the DC) Journal of Space Law, vol 12, Fall 1984, p 163-173 refs prototype of the lunar and planetary expedition modules; a The major issues concerned with the development of nuclear-powered mterorbital shuttle, and the possibility of creating commercial enterpnses in space are considered Attention is given a lunar colony L T to the need to streamline redundant national and international regulations to permit greater cooperation between firms in the A85-25700 development of such projects as the NASA Space Station, the SALYUT MISSION REPORT ELV, SPOT, and the Anane ELV project The possibility of impeding N KIDGER Spacefhght (ISSN 0038-6340), vol. 27, March 1985, the growth of space enterpnses through excessive concern for p 132-134 the political implications of technology transfer is discussed I H The 237-day flight of three Soviet cosmonauts, completed on October 2, 1984, is detailed, descnbing the mission objectives A85-27695# and the effects of such a long-term mission on the cosmonauts DEVELOPMENT AND APPLICATION OF NEW TECHNOLOGIES Salyut-7 docking with the Progress 23 cargo craft is also briefly IN ESA'S OLYMPUS PROGRAMME descnbed Some of the objectives of the mission included an R BONHOMME and R STEELS (ESA, Olympus Programme Office, attempt to determine the temperature profile of the Cygnus X-1 Noordwijk, Netherlands) ESA Journal (ISSN 0379-2285), vol 8, black-hole accretion disk and to observe X-ray pulsars and the no 4, 1984, p 357-379 Crab nebula. Over 500 expenments were conducted and 5500 A number of examples of how new designs and technologies earth photographs were taken; six EVAs were also performed, are being applied in the ESA Olympus program in both the totalling 22 hours and 50 mm The cosmonauts' condition upon spacecraft platform and the payloads are given, and results on return was described as a state of medium seventy, such the latest development and test activities are reported. The abnormalities as spine elongation (up to 5-6 cm total increase in subsystems considered include the solar array subsystem, height) and calcium losses in bones are noted to have been combined propulsion subsystem, altitude and orbit control foreseen L T subsystem, structure subsystem, and thermal subsystem on the platform, and the Specialized Services element, the television A85-26011 broadcast element, the Propagation Package element, the TV EUROPE IN SPACE 1985-2000 [EUROPE SPATIALE broadcast antenna, low-noise receivers, and traveling wave-tube 1985-2000] amplifiers on the payload A brief review is given of prospects for P LANGEREUX Air et Cosmos (ISSN 0044-6971), vol 22, Feb large spacecraft derived from the Olympus design, emphasizing 9, 1985. p 45-47, 50, 53 (3 ff) In French multimission applications C D Projects planned by the 13-member ESA in the last part of the century are surveyed, with particular note taken of the West A85-28275 German and French views The activities will proceed in the areas CRC HANDBOOK OF SPACE TECHNOLOGY: STATUS AND of science, remote sensing, telecommunications, microgravity PROJECTIONS matenals processing, participation in the U S Space Station effort, R M HORD (General Research Corp, McLean, VA) Boca Raton, and the development of new launch and space vehicles A desire FL, CRC Press, Inc. 1985, 296 p refs has been expressed to build the unmanned polar orbiting segment This volume presents trends and forecasts for figures of ment of the Space Station, the Columbus The member nations will all which may be used to characterize technological capabilities in contnbute to design studies for the mini-Shuttle, Hermes, a project the major discipline areas of space technology. The trends are 01 SYSTEMS based on historical data, and the forecasts represent the consensus station, the basis for charging users for services received from opinions of experts who are active contributors in their respective the space station, and the types of support that NASA might be fields The major discipline areas included in this volume are willing to provide to assist private industry in carrying out such a transportation systems, spacecraft systems, information systems, venture are discussed R J F chemical propulsion, electric propulsion, aerothermodynamics, power, matenals and structures, automation, guidance, control, N85-11911# Committee on Science and Technology (U S sensors, communications, data processing, and human factors House) The trends and forecasts presented generally consist of a graphical INTERNATIONAL COOPERATION AND COMPETITION IN display for each relevant figure of merit, accompanied by a SPACE descriptive narrative The projections show the expected Washington GPO 1984 230 p refs Hearing before the improvement in each of the discipline areas over the next twenty Comm on Sci and Technol, 98th Congr, 2d Sess, No 104, 25 years C D Jul 1984 (GPO-38-001) Avail Subcommittee on Space Science and N85-10871# Committee on Appropriations (U S Senate) Applications NATIONAL AERONAUTICS AND SPACE ADMINISTRATION Testimony and dialogue from a meeting of the House In its Department of Housing and Urban Development and Certain Subcommittee on Space Science and Applications are presented Independent Agencies for Fiscal Year 1985, Pt 2 p 1075-1241 The Subcommittee met to survey the status of and prospects for Washington GPO 1984 international cooperation and competition in space Avail Committee on Appropnations Appropriations for the space station, space transportation N85-12084*# Boeing Aerospace Co, Seattle, Wash capability development, space science and applications, technology DEFINITION OF TECHNOLOGY DEVELOPMENT MISSIONS FOR utilization, aeronautical research and technology, space research EARLY SPACE STATIONS: LARGE SPACE STRUCTURES Final and technology, tracking and data advanced system, shuttle Report production and operational capability, space and ground networks, 31 May 1983 108 p refs communication and data systems, and construction of facilities (Contract NAS8-35043) are detailed B G (NASA-CR-171209, NAS 1 26 171209, D180-27677-1) Avail NTIS HC A06/MF A01 CSCL 22B M85-10872# Committee on Appropriations (U S Senate) The testbed role of an early (1990-95) manned space station OFFICE OF TECHNOLOGY ASSESSMENT in large space structures technology development is defined and In its Department of Housing and Urban Development and Certain conceptual designs for large space structures development Independent Agencies Appropnations for Fiscal Year 1985, Pt 2 missions to be conducted at the space station are developed p 1233-1241 Washington GPO 1984 Emphasis is placed on defining requirements and benefits of Avail Committee on Appropriations development testing on a space station in concert with ground Three major issues were addressed how best to push toward and shuttle tests M G more capable automated space systems and the wider use thereof, how to determine the optimum division of responsibility between N85-12932*# National Aeronautics and Space Administration people and machines, and how to estimate the importance of Langley Research Center, Hampton, Va space automation to Earth applications B G CONCEPTUAL DESIGN FOR SCALED TRUSS ANTENNA FLIGHT EXPERIMENT N85-11011*# National Aeronautics and Space Administration W H LEE Nov 1984 40 p refs Marshall Space Flight Center, Huntsville, Ala (NASA-TM-85804, L-15838, NAS 1 1585804) Avail NTIS HC SECOND SYMPOSIUM ON SPACE INDUSTRIALIZATION A03/MF A01 CSCL 22B C M JERNIGAN, ed Oct 1984 427 p refs Symp held in The conceptual design for a scaled truss antenna structures Huntsville, Ala, 13-15 Feb 1984 Sponsored in cooperation with experiment program (STASEP) is presented The hardware analysis AIAA and Alabama Univ of the scaled truss antenna structure (STAS) was performed by (NASA-CP-2313, M-464, MAS 1 55 2313) Avail NTIS HC interactive design and evaluation of advanced spacecraft (IDEAS) A19/MFA01 CSCL22A computer aided, interactive, design and analysis program Four The policy, legal, and economic aspects of space STAS's were designed to be launched by the Shuttle, tested by industrialization are considered along with satellite communications, using the space technology experiments platform (STEP) and space matenal processing, remote sensing, and the role of space earners transportation system (STS), and then free flown in short lifetime and a space station in space industrialization orbits Data were gathered on deployment, structural characteristics, geometric accuracies, thermal performance, and N85-11035*# Booz-Allen and Hamilton, Inc , Arlington, Va drag and lifetime as an orbiting spacecraft Structural and thermal CONCEPT FOR A COMMERCIAL SPACE STATION properties were determined for the STAS, including mass LABORATORY properties, thermal loading, structural natural frequencies, and P W WOOD and P M STARK In NASA Marshall Space mode shapes The necessary analysis, scaling, and ground testing Flight Center 2nd Symp on Space Industrialization p 204-215 are discussed E A K Oct 1984 Avail NTIS HC A19/MF A01 CSCL 22B M85-13886*# National Aeronautics and Space Administration The concept of a privately owned and operated fee-for-service Lewis Research Center, Cleveland, Ohio laboratory as an element of a civil manned space station, MISSIONS/PLANNING PANEL envisioned as the venture of a group of private investors and an J S FORDYCE In its Space Power p 57 Apr 1984 experienced laboratory operator to be undertaken with the Avail NTIS HC A14/MF A01 CSCL 22A cooperation of NASA is discussed This group would acquire, outfit, A panel discussion was held to develop a viewpoint of space activate, and operate the labortory on a fee-for-service basis, power technology needs and state of readiness for future mission providing laboratory services to commercial firms, universities, and scenarios Among the points made in the discussion, it was agreed government agencies, including NASA This concept was that missions, particularly the far term ones, do serve to drive developed to identify, stimulate, and assist potential commercial technology, however, as the missions become nearer term, issues users of a manned space station A number of the issues which of schedule and cost severely limit the willingness to accept nsk would be related to the concept, including the terms under which There are, in fact, no rewards to a mission manager for introducing NASA might consider permitting private ownership and operation new technology Mission downscalmg is the usual response to of a major space station component, the policies with respect to technology limitations All panelists agreed that there exists a international participation in the construction and use of the space senous gap between when technologists feel their job is done 01 SYSTEMS and what mission managers need for decis'on Typically a two to N85-19205# Joint Publications Research Service, Arlington, Va three year engmeenng development gap exists It is essential to COMMERCIAL SPACE: EUROPE SHOULD HAVE take technologies to the engmeenng model level and conduct a INDEPENDENT STRATEGY flight demonstration to close this gap All agreed that increased In its West Europe Rept. Set and Technol (JPRS-WST-85-004) effort should be made to achieve stronger interactions between p 1-5 30 Jan. 1985 Transl into ENGLISH from Aarde and planners and technologists and that workshops like the present Kosmos (Netherlands), Nov. - Dec 1984 p 518-522 one are a step in the right direction Technologists need mission Avail NTIS HC A04/MF A01 credibility and vice versa R J F The impact of space commercialization on Europe is discussed Advantages and disadvantages are discussed with emphasis on the following areas competition, legal liabilities, economics, and development of European spacecraft B G

N85-13908'# Hughes Aircraft Co, Canoga Park, Calif N85-20341*# National Aeronautics and Space Administration ENVIRONMENTAL INTERACTIONS WORKING GROUP Marshall Space Flight Center, Huntsville, Ala. REPORT TETHERED SATELLITE SYSTEM PROJECT OVERVIEW N J STEVENS and M WISKERCHEN (NASA, Washington, D C) J H LADE In its Appl of Tethers in Space, Vol 1 16 p Mar In NASA Lewis Research Center Space Power p 323-326 Apr 1985 1984 Avail NTIS HC A13/MF A01 CSCL 131 Avail NTIS HC A14/MF A01 CSCL 10B The Skyhook concept is reviewed and the use of a tethered Interactions between spacecraft systems and the space charged satellite system (TSS) to enable scientific investigations from the particle environment are reviewed and recommendations are shuttle using a closed loop control system is examined The presented for both near-term and far-term research considerations. tethered satellite system has capabilities for deployment toward Transient environment models, large space structures, solar and or away from Earth, for multiple round trip missions, and for nuclear power systems/environment interactions, single event deployment at distances up to 100 KN from the orbiter The upsets, matenal degradation, and planetary missions are deployer, which consists of an entendable boom, a reel for the addressed M G tether, and the tether itself, permits deployment and retrieval at a safe distance, allows alignment of the force vector of the tether through the center of gravity of the shuttle, and gives some initial gravity gradient separation to aid in deployment and ultimate N85-14002# Messerschmitt-Boelkow-Blohm GmbH, Ottobrunn retrieval of the tethered satellite Charts show TSS activities in terms of systems studies, key guidelines, Italian and US (West Germany) Space Div responsibilities, user activities, and major science and applications OFFSET UNFURLABLE ANTENNA CONCEPTS accommodation features Scientific objectives for TSS-1 and TSS-2 H KELLERMEIER, W SCHAEFER, and H VORBRUGG In ESA verification missions and the current status of the project are also Workshop on Mech Technol for Antennas p 19-25 Sep 1984 given A R H refs Avail NTIS HC A09/MF A01 A design definition study for an unfurlable offset antenna N85-20343*# Consiglio Nazionale delle Ricerche, Rome (Italy) applicable to a wide mission spectrum of communication satellites TSS SATELLITE OVERVIEW was earned out A radial rib reflector concept with auxiliary G MANARINI In NASA Marshall Space Flight Center Appl of adjustment nbs, and a three dimensional scissors truss concept Tethers in Space, Vol 1 21 p Mar 1985 were considered The radial nb reflector is seen to provide the Avail NTIS HC A02/MF A01 CSCL 131 greatest versatility The foldable nbs can be deployed and latched The responsibilities of NASA and PSN/CNR in the tethered up by redundant cables dnven by a central electric drive unit The satellite system cooperative program are listed and PSN/CNR-AIT design has a built-in retraction capability Author (ESA) system support and technologies studies are summarized Results are given for investigations of active vs passive satellite trade offs, analysis of alternative maneuvers, satellite attitude and position determination analysis failure modes analysis, moveable boom dynamic analysis, double tethered satellite system, and N85-16990*# National Aeronautics and Space Administration, thermo/dynamic analysis for 100 km to 120 km altitude range Washington, D.C Objectives for the space plasma science mission and its NASA OAST PERSPECTIVE applications are outlined and the TSS satellite configuration is F STEPHENSON In NASA. Lewis Research Center OTV highlighted Programmatic aspects are included A R H Propulsion Issues p 1-14 Apr 1984 refs Avail NTISHCA13/MF A01 CSCL 22B N85-20346*# Rome Univ (Italy) An advanced OTV is one of a number of advanced STS vehicles SCIENCE APPLICATIONS, PART 1 that the NASA OAST Space Systems Division Transportation F MARIANI In NASA Marshall Space Flight Center Appl of Systems Office identified as candidates for future vehicle Tethers in Space, Vol 1 11 p Mar 1985 refs development. Vehicle requirements as well as technology needs Avail NTIS HC A13/MF A01 CSCL 22A and need dates were established and technology programs initiated The tethered satellite system mission can allow direct to support those potential developments in a timely manner It is observation of the structure and the dynamics of the lower assumed that advanced OTV will be space based and fully reusable atmosphere, as well as answer some basic questions on the for low cost operations, use aeroassist for return to low-Earth-orbit, chemical composition of the atmosphere, the coupling mechanisms and evolve to a man-rated system The propulsion system will between small and large scale motions, the global wind field of need to maintain high performance over a wide thrust range for the lower atmosphere, and how it is influenced by waves and mission flexibility, ranging from the transfer of large, acceleration tides, the mass, momentum, and energy fluxes in the lower limited structures from LEO to GEO, to demanding high reliability thermosphere, how the above are affected by externally perturbed round-tnp manned missions Technology advances are needed in conditions (for example by magnetic storms, solar wind and its propulsion, aerobrakmg, low-gravity cryogenic fluid management, variability, etc), and the pattern of electric current circulation and and in environmentally compatible, low-loss cryogenic tankage In its relationship with the magnetosphenc environment. Fundamental addition, diagnostic instrumentation for monitonng the health of plasma processes can also be studied Similarity of conditions in on-board components and systems, and automated check-out other plasmas in space makes it possible to get information on capability will enhance low-cost space based OTV operations. the magnetospheres of the giant planets or more generally on Author the solar system The electrodynamic phenomena associated with 01 SYSTEMS

the Jovian satellite lo (radioemission, UV emission, energetic A85-12995# electron precipitation) can be examined by simple scaling to the ARCHITECTURE AND IMPLEMENTATION OF AN IN-ORBIT terrestrial case A R H INFRASTRUCTURE P MOLETTE and C COUGNET (Matra, S A, Toulouse, France) International Astronautical Federation, International Astronautical N85-20347*# National Aeronautics and Space Administration, Congress, 35th, Lausanne, Switzerland, Oct 7-13, 1984 14 p Washington, D C Research supported by the European Space Agency SCIENCE APPLICATIONS, PART 2 (IAF PAPER 84-29) J P MURPHY In NASA Marshall Space Flight Center Appl The analysis of future commercial space-processing and of Tethers in Space, Vol 1 18 p Mar 1985 earth-observation missions indicates that their implementation in Avail NTIS HC A13/MF A01 CSCL 22A space, their operational utilization as well as their maintenance The goals of the Geopotential Research Program are to will advantageously be supported by a common m-orbit contribute to the understanding of the solid earth, the origin and infrastructure (IOI) Thus, a space-processing mission will be evolution of the earth, its internal structure and the dynamics of accommodated on a platform in LEO and will require dedicated the core and the mantle, the movements and deformations of the vehicle and servicing equipment to ensure its logistic resupply, tectonic plates that make up the surface of the earth, its rotational the maintenance and exchange of payload facilities, and the dynamics, the changes in the rotation rate of the earth, the maintenance and refueling of the platform This space-processing orientation of the pole in space, vanations of the gravity and mission is the most demanding one, and the definition of the magnetic field of the earth, the origin of the earth and the way in architecture of the IOI is based on its requirements The IOI has which the solid earth interacts with the oceans and the to fulfill several functions, and the repartition of the tasks among atmosphere Author some of or all its elements will depend on the scenario of utilization of the platform and on the time frame Three candidate IOI architectures are proposed which differ in their level of utilization N85-21225# Committee on Commerce, Science, and of U S facilities, and a scenano of implementation of a European Transportation (U S Senate) IOI is proposed It is split into three successive steps which allow COMMERCIAL SPACE LAUNCHES Europe to benefit from participation in the U S Space Station on Washington GPO 1984 19 p Rept to accompany H R the way to complete independence in supporting commercial 3942 presented by the Comm on Com, Sci, and Transportation, missions and manned flights Author 98th Congr, 2nd Sess , 3 Oct 1984 (S-REPT-98-656, GPO-51-010) Avail US Capitol, Senate Document Room A85-13100# This bill is to establish a framework within which expendable IMPACTS OF LIFE SUPPORT SYSTEM ON SPACE STATION ' launch vehicles (ELVs) and their associated facilities and launch DESIGN services may be licensed for commercial launches This legislation W G NELSON, L R PRICE, and M M YAKUT (McDonnell also designates the Department of Transportation (DOT) as the Douglas Astronautics Co, Huntmgton Beach, CA) International lead Federal agency to facilitate and expedite the issuance and Astronautical Federation, International Astronautical Congress, transfer of commercial space launch licenses Author 35th, Lausanne, Switzerland, Oct 7-13, 1984 8 p (IAF PAPER 84-166) It is pointed out that recent NASA and U S industry activity has been directed toward a manned Space Station as the next major U S space venture Identified needs and attributes regarding 02 a space station include low cost, long life, and ample resources for mission support Environmental Control/Life Support Systems ANALYSIS AND DESIGN TECHNIQUES (ECLSS) requirements for the Space Station Architecture are considered along with a parametric data base The data base developed includes a hierarchy of information necessary to resolve Includes interactive techniques, computenzed technology design the key issues associated with Space Station ECLSS Loop closure and development programs, dynamic analysis techniques, represents a key variation in the ECLSS design options The four environmental modeling, thermal modeling, and math modeling options compared are related to no water or O2 recovery, wash and condensate water recovery, all water recovery, and all water plus partial O2 recovery Attention is also given to the effect of A85-12992# incremental increases in capability, centralized versus decentralized DESIGN CONSIDERATION OF SPACE CONSTRUCTION ECLSS equipment arrangements, optimum ECLSS concepts, and FACILITY concepts for ECLSS evolution Author M NAGATOMO (Tokyo, University, Tokyo, Japan), T YAMANAKA (National Aerospace Laboratory, Chofu, Tokyo, Japan), and S SONOYAMA (National Space Development Agency of Japan, A85-13247# Tokyo, Japan) International Astronautical Federation, International DEPLOYABLE REFLECTOR ANTENNAS - MECHANICAL Astronautical Congress, 35th, Lausanne, Switzerland, Oct 7-13, DESIGN OF THE REFLECTIVE SURFACE 1984 9 p refs C SIRMAIN, J -N GIRAUDBIT, and A LIEUTIER (Centre National (IAF PAPER 84-26) d'Etudes Spatiales, Toulouse, France) International Astronautical Space operation and space construction are unique capabilities Federation, International Astronautical Congress, 35th, Lausanne, of the Space Station These activities involve the utilization of the Switzerland, Oct 7-13, 1984 9 p vicinity space of the space station A preliminary study on the (IAF PAPER 84-393) requirements of space construction and their interfaces with space A review is given of CNES R&D on 1-10 GHz mesh deployable operation indicated that the work of space construction includes reflector antennas, 5-30 meters in diameter The analysis fabncation, assembly, testing, and operation Choices of installation, philosophy and the LIMA surface computation program are commonality, dynamics of Space Station, and interface with described The features of this program include modulanty, transportation have been considered as design factors of a computation of the gndded surface, the pillow effect, BFP/RMS, space-construction facility A configuration study has been made and reflector cut, model adjustment and interpolations, and to see how the facility is related to the total Space-Station system application to all faceted surfaces, even nonparaboloid ones concerning these design factors For future evolution, space Consideration is also given to surface contour faults, geometrical construction will be a central function of the Space Station, which imperfection sensitivity, contour optimization, and coupling between should be so designed Author the backing structure and the mesh contounng system L M

6 02 ANALYSIS AND DESIGN TECHNIQUES

A85-14429 four-boom flexible structure The mass and stiffness distnbutions SPACE STATION/SPACE PLATFORM SYSTEM DESIGN of the booms are determined as part of the optimization problem CONSIDERATIONS Author A. E SABROFF and R. E. SHARPLES (TRW Electronics and Defense Sector, Redondo Beach, CA) IN EASCON '83; A85-19600# Proceedings of the Sixteenth Annual Electronics and Aerospace COMPUTER AIDED DESIGN OF MULTIPLE INPUT/OUTPUT Conference and Exposition, Washington, DC, September 19-21, CONTROL SYSTEMS FOR MULTIBODY FLEXIBLE SPACE 1983 New York, Institute of Electncal and Electronics Engineers, STATION 1983, p 17-26 H C GELDERLOOS and B S HECK (Honeywell, Inc , Clearwater, The Space Applications Board of the National Research Council FL) Amencan Institute of Aeronautics and Astronautics, Aerospace conducted a summer study in mid-August 1982 at Crestwood, Sciences Meeting, 23rd, Reno, NV, Jan 14-17, 1985 10 p. refs Colorado This paper summarizes the findings of the System Design (AIAA PAPER 85-0223) Panel, one of six panels formed to do the study, and augments With the advent of Space Station on the horizon, several these findings with results from recent NASA space station mission technical requirements have surfaced that are unique to the analysis studies The paper is organized into discussions of four problem of controlling large space structures As the space station major categories cost/benefit system design issues, user design grows from a single module with solar panels to multiple modules requirements, manned system design issues, and technology with attached bodies and experiments, a control analysis tool with design issues For each category, the recommendations of the emphasis on high-fidelity modeling of multi-body flexible structures Panel are summarized and illustrated Key results include the ideas is required The computer aided design tool descnbed in this paper that man-in-space is an application in its own nght with significant easily generates nonlinear structural models for different future potential, and that an appropriate first step in the evolution configurations and onentations The control system design and of man working in space should be the development of a 'space analysis tool includes structural dynamics, coupling of attached service station' capability Author bodies, mass property changes, articulation of payloads and docking transients Multiple input/output optimal control systems A85-15496# for the linear models are developed with modern and classical SOME DESIGN CONCEPTS FOR INTELSAT VII control techniques using the computer aided design tools G R WELTI (COMSAT Laboratories, Clarksburg, MD) IN Preliminary results of a Space Station attitude controller are International Conference on Digital Satellite Communications, 6th, presented Author Phoenix, AZ, September 19-23, 1983, Proceedings New York, Institute of Electncal and Electronics Engineers, 1983, p. XI-1 to A85-22579 XI-8 Research sponsored by the Communications Satellite Corp DESIGN CONCEPTS FOR REFLECTOR ANTENNA refs STRUCTURES Cost-effective architectures for Intelsat VII spacecraft are J M HEDGEPETH (Astro Research Corp, Carpmtena, CA) IN descnbed These spacecraft yield a capacity of 228,000 channels Deployable optical systems, Proceedings of the Meeting, Los in the Atlantic Operating Region primary mission by reusing the Angeles, CA, January 18, 19, 1983 Bellmgham, WA, SPIE - The expanded Ku-band spectrum four times, using wideband International Society for Optical Engineering, 1983, p 21-31 beam-hopping transponders with twenty-six 0 7-deg spot beams refs The spacecraft mass is 23 percent greater than that of Intelsat Attention is given to the structural configurations of future large VI Author space antennas whose diameter/wavelength ratios are typically of the order of less than 10,000, as required by submillimeter A85-16648 wave and IR astronomy An example of such a reflector is the PRINCIPAL COMPONENT ANALYSIS OF FLEXIBLE SYSTEMS Large Deployable Reflector IR telescope's 20-m pnmary mirror, - OPEN-LOOP CASE which is off-axis Cassegramian design with focal length equal to E A JONCKHEERE (Southern California, University, Los Angeles, aperture diameter In order to reduce system noise, the reflecting CA) IEEE Transactions on Automatic Control (ISSN 0018-9286), surfaces are maintained at very low temperatures by means of vol AC-29, Dec 1984, p 1095-1097 refs multilayer insulation-based thermal shielding Emphasis is presently (Contract AF-AFOSR-80-0013) given to telescope deployment concepts, active control of the A genenc class of flexible systems, charactenzed by finitely hexagonal reflector panels, and the intrinsic accuracy7 of many lightly damped harmonic oscillators, is analyzed by means truss-structure reflectors O C of the 'open-loop pnncipal component analysis', that is, singular value analysis and Gramian balancing As the mam result, it is A85-22685* National Aeronautics and Space Administration shown that, as the damping ratio goes to zero, the balanced Ames Research Center, Moffett Field, Calif state coordinates are decoupled and coincide with the modal A MODULAR APPROACH TO DEVELOPING A LARGE coordinates Further, simple formulas expressing the 'asymptotic DEPLOYABLE REFLECTOR singular values' as functions of the modal parameters are R PITTMAN, C LEIDICH, F MASCY, and B SWENSON (NASA, derived Author Ames Research Center, Advanced Studies Office, Moffett Field, CA) IN Infrared technology IX, Proceedings of the Ninth Annual A85-18338# Meeting, San Diego, CA, August 23-25, 1983 Bellmgham, WA, OPTIMAL SIMULTANEOUS STRUCTURAL AND CONTROL SPIE - The International Society for Optical Engmeenng, 1983, p DESIGN OF MANEUVERING FLEXIBLE SPACECRAFT 115-128 refs A. L HALE, W E DAHL (Illinois, University, Urbana, IL), and R NASA is currently explonng the feasibility of developing a large J LISOWSKI (US Air Force Academy, Colorado Spnngs, CO, deployable reflector (LDR) astronomical facility to perform Illinois, University, Urbana, IL) Journal of Guidance, Control, and astrophysical studies in the mid 1990's in the IR and submillimeter Dynamics (ISSN 0731-5090), vol 8, Jan-Feb 1984, p 86-93 portion of the spectrum This paper examines a combmaton of refs automatic deployment and on-orbit assembly that may reduce the An optimization problem for maneuvering flexible spacecraft is technological complexity and cost of the LDR system Two Shuttle discussed wherein both structural parameters and active control volume budget scenanos are examined to assess the potential of forces are to be determined so that a specific cost functional is vanous technological tools to reduce the LDR system complexity. minimized The problem is an application of the general theory of It is noted that the LDR design must be flexible and allow one optimal control of parametnc systems For simplicity, only subsystem to be modified without adversely affecting the entire maneuvers from a specified initial state to a specified final state system. One way to achieve this flexibility is a modular design in a specified time interval are considered Numencal examples approach (MDA) in which the major subsystems are physically are presented for single-axis slew maneuvers of a symmetric separated during launch and assembled on orbit NASA is defining 02 ANALYSIS AND DESIGN TECHNIQUES

a technology development plan for LOR that will identify the equivalent continuum is characterized by its strain and kinetic technology advances that are required It is concluded that the energies from which the constitutive relations and the equations MDA offers the flexibility to easily incorporate these advances of motion can be denved A simple method to model large rigid into the design B J jointed lattices as continuous media with couple stresses is presented The transition from the discrete system to the A85-24908 continuous medium is achieved by expanding the displacements SPACE FRAME DESIGN, DEVELOPMENT AND OPTIMIZATION and the rotations of the nodal points in a Taylor senes about a Of ANTENNA PLATFORM STRUCTURE FOR A MOBILE 3D suitable chosen origin Basic kinematic assumptions are introduced RADAR to insure that the assumptions used in deriving the governing K VAJRAVELU (Bharat Electronics, Ltd, Bangalore, India) IN equations of the modeled continuum are satisfied The number of International Radar Symposium, Bangalore, India, October 9-12, terms retained in the Taylor senes expansion will depend upon 1983, Proceedings Bangalore, India, Institution of Electronics and the properties to be evaluated This implies that the kind of Telecommunication Engineers, 1983, p 544-549 refs continuum needed to model from the discrete lattice, before the actual properties are denved was to predetermined E A K A85-26675 INTERNATIONAL FEM-CONGRESS, BADEN-BADEN, WEST GERMANY, NOVEMBER 14, 15, 1983, PROCEEDINGS N85-10677*# Boeing Aerospace Co , Kent, Wash Stuttgart, West Germany, IKO Software Service GmbH, 1983, 412 IAC USER MANUAL p In English and German No individual items are abstracted in R G VOS, D L BESTE, and J GREGG Jul 1984 391 p this volume refs Vanous papers on the Finite Element Method (FEM) are (Contract NAS5-25767) presented The topics addressed include experimental and (NASA-CR-175300, NAS 1 26 175300) Avail NTIS HC A17/MF theoretical evaluation of pipe systems in nuclear reactors under A01 CSCL 09B blowdown conditions, reduction of a special The User Manual for the Integrated Analysis Capability (IAC) thermoviscoelastoplastic problem from 3-D to 2-D, a general, Level 1 system is presented The IAC system currently supports nonlinear FE program system, nonlinear analysis and the the thermal, structures, controls and system dynamics technologies, optimization of a microswitch wire snap, satellite structural analysis and its development is influenced by the requirements for with ASKA calculative method, and application of calculation and design/analysis of large space systems. The system has many test methods to fortuitously excited vibrations in space flight Also features which make it applicable to general problems in considered are interactive coupling of CAD system and structural engineering, and to management of data and software Information mechanics, CAD/FEM coupling, equilibrium modelling in the closed includes basic IAC operation, executive commands, modules, mesh of a finite element analysis, effective evaluation of a stress solution paths, data organization and storage, IAC utilities, and concentration problem, modal coordinates in FE dynamic module implementation MAC calculations, application of the PISCES code for nuclear safety problems, general and simplified FE models for crankshaft N85-11050*# Martin Marietta Aerospace, New Orleans, La calculations, use of finite elements to optimize machine parts, EXTERNAL TANK AFT CARGO CARRIER Abstract Only and use of FEM with CAD/CAM system C D T B MOBLEY In NASA Marshall Space Flight Center 2nd Symp on Space Industrialization p 348 Oct 1984 A85-27696# Avail NTIS HC A19/MF A01 CSCL 22B SPACECRAFT SYSTEMS ENGINEERING AND GEOMETRY The External Tank (ET) Aft Cargo Carrier (ACC) is a low cost, MODELLING - THE ESABASE-MATVIEW APPROACH low risk augmentation of the Space Transportation System (STS) J G FERRANTE, P COFFINIER, B AUBE (Matra, S A , Toulouse, It almost doubles the cargo volume of the STS while minimally France), and J DE KRUYF (ESA, Mathematical Support Div, impacting other STS elements (orbiter, ET and solid rocket boosters Noordwijk, Netherlands) ESA Journal (ISSN 0379-2285), vol 8, SRBs, launch facilities and STS operations In addition to increasing no 4, 1984, p 381-394 refs the potential volume of cargo carried on a Shuttle launch, the The use of two software packages, ESABASE and MATVIEW, ACC provides the following additional benefits (1) Increased STS in the design of spacecraft is discussed The former provides a competitiveness for payloads, (2) Increased cargo manifest multkJisciplmary framework for integrated systems engineering, flexibility, (3) Increased spacecraft design options, (4) Alternate whjle^the latter supports ESABASE geometry modeling and manifesting for special payloads, and (5) Future space interacts with a wide range of systems-analysis applications The platform/station design options Author ESABASE approach to spacecraft design is reviewed, introducing integrated computer-aided engmeenng concepts into the design of complex earth-orbiting spacecraft Background information and N85-11570*# Computer Sciences Corp , Hampton, Va the rationale for MATVIEW's decomposition of geometrical shapes SMP: A SOLID MODELING PROGRAM into discrete planar finite elements are given Some current and D P RANDALL, K H JONES, W H VONOFENHEIM, and R L future system-level applications analyses that are being integrated GATES Hampton, Va NASA Langley Research Center Nov into ESABASE are descnbed The VWHEAT and SINDA thermal 1984 138 p refs application module coupled to ESABASE at the subsystem level (Contract NAS1-16078) is discussed in detail C D (NASA-CR-172473, NAS 1 26 172473, TAO-34100) Avail NTIS HC A07/MF A01 CSCL 09B N85-10391*# Grand Valley State Coll, Allendale, Mich A prototype solid modeling program, SMP, developed by CSC SHEAR DEFORMATION PLATE CONTINUA OF LARGE for Langley Research Center (LaRC) is documented in this paper DOUBLE-LAYERED SPACE STRUCTURES The SMP software is employed by the System and Expenments M S HEFZY and A H NAYFEH (Cincinnati Univ) In NASA Branch (SEB) of the Space Systems Division (SSD) for preliminary Langley Research Center Res in Struct and Dyn, 1984 p space station design, but is intended as a general purpose tool 197-217 Oct 1984 refs The SMP document provides details concerning the basic (Contract NSG-1185) geometnc modeling primitives and associated operators, the data Avail NTIS HC A18/MFA01 CSCL 20K representation scheme utilized to structure the geometnc model, The energy equivalence to construct equivalent continua for the available commands for both editing and displaying the solid the actual lattice structure is descnbed An energy equivalent model, the interactive user interface and the input/output interfaces continuum is defined as that which has the same amount of strain to external software, and the utility of the package in the LaRC and kinetic energies stored in it as the onginal lattice structure computing environment The document is sufficiently detailed to when both are subjected to the same loading conditions The serve both as a user's guide and reference manual B W

8 02 ANALYSIS AND DESIGN TECHNIQUES

N85-13838*# Control Dynamics Co, Huntsville, Ala capability is obtained adopting a modular concept of the satellite DEFINITION OF GROUND TEST FOR VERIFICATION OF LARGE such to allow for easy reconfiguration, easy refurbishment, and SPACE STRUCTURE CONTROL Rnal Report, 30 Sep. 1980 - cost and schedule minimization The modular concept is realized 31 Jul. 1984 with a paytoad module (PM), a service module (SM), and an G B. DOANE, III, J R. GLAESE, D K TOLLISON, T. G auxiliary propulsion module (APM) The satellite configuration for HOWSMAN, S. CURTIS, ed, and B BANKS Nov 1984 157 p the electrodynamic and atmosphenc missions is descnbed as well refs as its mechanized capabilities Payload dedicated electrical (Contract NAS8-34700) facilities, satellite position determination accuracy, attitude control (NASA-CR-171208, NAS 1 26 171208) Avail NTIS HC A08/MF and measurement accuracy and attitude oscillation charactenstics A01 CSCL 22B are summanzed A R H Control theory and design, dynamic system modelling, and simulation of test scenarios are the main ideas discussed The overall effort is the achievement at Marshall Space Flight Center Of a successful ground test experiment of a large space structure A simplified planar model of ground test expenment of a large space structure A simplified planar model of ground test verification was developed The elimination from that model of the uncontrollable rigid body modes was also examined. Also studied was the hardware/software of computation speed N85-21232*# National Aeronautics and Space Administration Marshall Space Flight Center, Huntsville, Ala NATURAL ENVIRONMENT DESIGN CRITERIA FOR THE SPACE N85-14011# British Aerospace Dynamics Group, Stevenage STATION DEFINITION AND PRELIMINARY DESIGN (England) Space and Communications Div W W VAUGHAN and C E GREEN Mar 1985 16 p BAE ANTENNA HARDWARE TECHNOLOGY FOR CURRENT Revised SATELLITE PROJECTS (NASA-TM-86498, NAS 1 15 86498) Avail NTIS HC A02/MF R K EMERY In ESA Workshop on Mech Technol for Antennas A01 CSCL 22B p 77-82 Sep 1984 The natural environment design cntena for the Space Station Avail NTIS HC A09/MF A01 Program (SSP) definition and preliminary design are presented The mechanical design, development and manufacture of Information on the atmosphenc, dynamic and thermodynamic antenna hardware for satellite solid reflectors up to 3 2m diameter, environments, meteoroids, radiation, magnetic fields, physical feed chains, antenna pointing mechanisms, antenna deployment constants, etc is provided with the intension of enabling all groups subsystems, and antenna support structures are discussed The involved in the definition and preliminary design studies to proceed technology involved and problems encountered are summarized with a common and consistent set of natural environment criteria Author (ESA) requirements The space station program elements (SSPE) shall be designed with no operational sensitivity to natural environment N85-19011*# Rockwell International Corp, Pittsburgh, Pa Space conditions dunng assembly, checkout, stowage, launch, and orbital Station Systems Div. operations to the maximum degree practical M G GROUND TEST ARTICLE FOR DEPLOYABLE SPACE STRUCTURE SYSTEMS Bimonthly Report G D MALLOY Jan. 1985 7 p (Contract NAS8-34657) (NASA-CR-171301, NAS 1 26 171301, BMR-5) Avail NTIS HC A02/MF A01 CSCL 228 Santek's ability to recover from a schedule slip was reviewed and found satisfactory Diagonal member bond joints were subjected to static load to failure tests Results are considered N85-21262*# National Aeronautics and Space Administration adequate B G Johnson (Lyndon B) Space Center, DESIGN STUDY OF AN INTEGRATED AEROBRAKING ORBITAL N85-19013*# National Aeronautics and Space Administration TRANSFER VEHICLE Marshall Space Flight Center, Huntsville, Ala. C D SCOTT, B B ROBERTS, K NAGY, P TAYLOR, J D GROUND TEST EXPERIMENT FOR LARGE SPACE GAMBLE, C J CEREMELI, K R KNOLL, C P LI, and R C STRUCTURES REID Mar 1985 40 p refs D K TOLLISON (Control Dynamics Co) and H B WAITES Feb (NASA-TM-58264, S-542, NAS 1 15 58264) Avail NTIS HC 1985 11 p A03/MF A01 CSCL 22B (NASA-TM-86489, NAS 1 15 86489) Avail NTIS HC A02/MF An aerobraking orbital transfer vehicle (AOTV) concept, which A01 CSCL 22B has an aerobrake structure that is integrated with the propulsion In recent years a new body of control theory has been stage, is discussed The concept vehicle is to be assembled in developed for the design of control systems for Large Space space and is space-based The advantages of aeroassist over an Structures (LSS) The problems of testing this theory on LSS all propulsive vehicle are discussed and it is shown that the vehicle hardware are aggravated by the expense and nsk of actual in considered is very competitive with inflatable and deployable orbit tests Ground tests on large space structures can provide a concepts from mass and performance aspects The aerobrake proving ground for candidate control systems, but such tests require geometry is an ellipsoidally blunted, raked-off, elliptical wide-angle a unique facility for their execution The current development of cone with a toroidal skirt Propellant tanks, engines, and such a facility at the NASA Marshall Space Flight Center (MSFC) subsystems are integrated into a closed, isognd aerobrake structure is the subject of this report Author which provides ngidity The vehicle has two side-firing, gimbaled RL-10 type engines and cames 38,000 kg of useable propellent. N85-20344*# Aentalia S p A , Naples (Italy) The trajectory dunng aerobraking is determined from an adaptive SATELLITE MODULE DESIGN guidance logic, and the heating is determined from engineering M VIGNOLI In NASA Marshall Space Flight Center Appl of correlations as well as 3-D Navier-Stokes solutions The AOTV is Tethers in Space, Vol 1 19 p Mar 1985 capable of placing 13,500 kg payload into geosynchronous Earth Avail NTIS HC A02/MF A01 CSCL 228 orbit (GEO) or carrying a LEO-GEO-LEO round-tnp payload of The tethered satellite system (TSS) satellite is a multimission 7100 kg A two-stage version considered for lunar missions results vehicle able to carry scientific payloads aways from the shuttle in a lunar surface delivery capability of 18,000 kg or a round-tnp orbiter in the range of 130 to 330 km in altitude The multimission capability of 6800 kg with 3860 kg delivery-only capability. M G

9 03 STRUCTURAL CONCEPT &

03 manipulator arm having multiple degrees of freedom is discussed The resulting VGT manipulator can be programmed to retreat and STRUCTURAL CONCEPTS deploy and take a position in any desired configuration The basic kinetic geometry of the VGT manipulator is established Author Includes erectable structures (|°|nts> struts, and columns), deployable platforms and booms, solar sail, deployable reflectors, A85-18435# space fabrication techniques, and protrusion processing MODULAR COMPUTER SYSTEM CUTS SPACECRAFT SIMULATION COSTS S E TICE, J L ZELON, and R A REPIC (Rockwell International A85-12933 Corp, Space Station Systems Div , Pittsburgh, PA) Aerospace THE STRONGEST STRUCTURES WITH MACROSTIFFNESS Amenca (ISSN 0740-722X), vol 23, Jan 1985, p 82-86 CONSTRAINTS The capabilities and applications of the space-vehicle J HOLNICKI-SZULC (Polska Akademia Nauk, Instytut computer-based design system (SVCDS) are described The Podstawowych Problemow Techntki, Warsaw, Poland) Journal of growing complexity of space operations has driven the need for Structural Mechanics (ISSN 0360-1218), vol 12, no 2, 1984, p incorporating higher-order primitives for displaying and manipulating 181-197 refs realistic hardware and anthropomorphic shapes The SVCDS An example of a truss structure with limited global stiffness, provides for rapid geometric analysis, kinematics calculations, measured by some parameter k, is discussed The optimal structural geometric reform, database interfacing and English language design problem of maximizing the external load intensity, with axial commands Cross-sectional points are entered and structures are stresses in the rods of the truss remaining within an allowable built in stacks using either surface points or quartics, the latter range, is well known and leads to a statically determinate solution permitting a parametnc design approach Factors such as the with uniformly loaded elements However, if one takes into account aerodynamic center of gravity, lift and moment can also be the additional constraint on stiffness k, the problem is open and estimated for lifting bodies with a high degree of accuracy at the the solution leads, in general, to a redundant truss The paper first cut The system interfaces with a vanety of aerodynamic, presents this problem and proposes its application to optimal design fluid dynamic and finite element structural codes A kinematics of supporting structures Author program module serves in generating models for added features, eg, a manipulator arm SVCDS has been used to study configurations for the Shuttle, OTV, the Space Station, and A85-13240# serviceability for the Navstar and P-80-1 satellites M S K INFLATABLE SPACE-RIGIOIZED STRUCTURES - RECENT DEVELOPMENTS OF THE MATERIAL TECHNOLOGY M C BERNASCONI (Contraves AG, Zunch, Switzerland), W SEIZ A85-18694# (Ciba-Geigy AG, Marly, Switzerland), and G G REIBALDI (ESA, MINIMUM WEIGHT DESIGN OF TRUSS STRUCTURES WITH Mechanical Systems Div, Noordwijk, Netherlands) International GEOMETRIC NONLINEAR BEHAVIOR Astronautical Federation, International Astronautical Congress, N S KHOT (USAF, Flight Dynamics Laboratory, Wright-Patterson 35th, Lausanne, Switzerland, Oct 7-13, 1984 13 p Sponsorship AFB, OH) and M P KAMAT (Virginia Polytechnic Institute and European Space Agency refs State University, Blacksburg, VA) (Structures, Structural Dynamics (Contract ESA-4023/79-NL-AK) and Materials Conference, 24th, Lake Tahoe, NV, May 2-4, 1983, (IAF PAPER 84-384) Collection of Technical Papers Part 1, p 383-391) AIAA Journal Trends related to the growing industnal significance of space (ISSN 0001-1452), vol 23, Jan 1985, p 139-144 Previously cited systems point to the need for structures whose size substantially in issue 12, p 1739, Accession no A83-29767 refs exceeds the linear dimensions of the transportation vehicle The large elements required may be obtained on the basis of a use of A85-23663* Jet Propulsion Lab, California Inst of Tech, expandable or erectable structures Inflatable, space-ngidized Pasadena structures represent a class of expandable structures with a number SURVEY OF DEPLOYABLE ANTENNA CONCEPTS of significant advantages The wall of an inflatable, R E FREELAND (California Institute of Technology, Jet Propulsion chemically-ngidized object consists of a thin, fiber-reinforced Laboratory, Pasadena, CA) IN Satellite communication antenna composite lamina This 'balloon' is assembled and launched with technology Amsterdam, North-Holland, 1983, p 613-652 the wall in its flexible, prepegged state, to enable its folding for Previously announced in STAR as N83-26872 refs stowage in the transportation vehicle Attention is given to details Deployable space antenna concepts are surveyed Precision regarding inflatable structures in space, aspects of matenal reflector antennas, stiffened membrane antennas, truss antennas, selection, and materials development tests G R infrared antennas, and electrostatically figured membrane reflectors are described R.J F A85-13248# VARIABLE GEOMETRY TRUSS AND ITS APPLICATION TO A85-24817 DEPLOYABLE TRUSS AND SPACE CRANE ARM DEVELOPMENT OF ADVANCED COMPOSITE TUBULAR K MIURA (Tokyo, University, Tokyo, Japan), K SUZUKI (Godo STRUCTURES FOR ANTENNA REFLECTOR Works Co, Ltd , Tokyo, Japan), and H FURUYA International G ALBERINI, G GERMAN!, and A NOVELLINO (Selenia S p A, Astronautical Federation, International Astronautical Congress, Rome, Italy) IN High performance composite matenals. New 35th, Lausanne, Switzerland, Oct 7-13, 1984 10 p applications and industrial production, Proceedings of the Fourth (IAF PAPER 84-394) International Conference and Exhibition, Bordeaux, France, October The purpose of this paper is to explain the 17-20, 1983 Chatou, Yvelmes, France, Society for the vanable-geometry-truss (VGT) concept and to discuss its Advancement of Matenals and Process Engineering, 1983, p applications to deployable linear and curvilinear trusses and a 199-208 manipulator arm The VGT consists of the repetition of an An advanced composite tubular structure was developed for a octahedral truss module longitudinally The geometrical antenna reflector used on a spacecraft Matenals and processing transformation of an octahedron is the basis of the present concept development is described as well as design aspects of the The pnncipal mechanical feature of the truss is that the lateral composite tubular element High modulus unidirectional graphite members of the truss are variable-length beams, while the diagonal fiber, Fibente HYE-1534, with low thermal expansion coefficient members are fixed-length beams Through such mechanisms, the was selected Among some lay-up onentations a lay-up truss can be transformed to vaneties of configurations Both (0,45,0,-45)s was chosen Cured laminate properties of used simultaneous and sequential modes of transformation (that is, matenals and results of mechanical tests of tubular structure are deployment) are shown An application of the concept to a reported Author

10 03 STRUCTURAL CONCEPTS

A85-28489 N85-11363 Connecticut Unrv, Storrs. MULTICR1TICAL OPTIMIZATION OF A LARGE SPACE EFFECTS OF MEMBER IMPERFECTIONS ON THE BEHAVIOR STRUCTURE [MNOGOKRITERIAL'NAIA OPTIMIZATSIIA OF SPACE TRUSSES Ph.D. Thesis KRUPROGABARITNOI KOSMICHESKOI KONSTRUKTSII] G D SMITH 1984 254 p B. V SAZYKIN Kosmicheskie Issledovanua (ISSN 0023-4206), Avail Unrv. Microfilms Order No. DA8416109 vol 23, Jan-Feb 1985, p 84-91 In Russian refs The effects of imperfections on the behavior of a compression Interactive programming is used for the multicntical optimization member were determined as well as the effects of the member of a large space structure with a tetrahedral base element. A imperfections on the behavior of pin-ended space trusses Based mathematical model of a structure in circular orbit is constructed, on the results, quantitative conclusions were made as to the effects taking into account the effect of gravitational forces, optical of the member imperfections, as well as qualitative conclusions radiation pressure, and concentrated dynamic loads. The bending An analytical model is developed to predict the behavior of an dynamics is described by a differential equation for the vibrations axially loaded compression member that is restrained by a structure of a circular plate with free-contour boundary conditions The surrounding it, has initial out-of-straightness, is eccentrically loaded optimality conditions are obtained, and optimization results are at its ends, and/or has residual stresses present. The member presented for the load-beanng shell of the large space structure cross-sections modelled are tubular and built-up cruciforms The BJ behavior includes both elastic and inelastic pre-bucklmg behavior, the formation of a plastic hinge, and the post-buckling behavior of the member A computer model approximating the analytical member model developed, is presented The Multiple-Step-Up Linearization method, developed dunng this research to N85-10099# Spectra Research Systems, Inc., Huntsville, Ala approximate the member's inelastic behavior, is described The RESEARCH ON LARGE, HIGHLY ACCURATE, INFLATABLE member computer model developed is used to predict the behavior REFLECTORS Final Report, 30 Sep. 1983 - 30 May 1984 and ultimate load capacity of eight truss configurations R BRADFORD Jul .1984 97 p Dissert Abstr (Contract F04611-83-C-0053) (AD-A145080, SRS-TR84-015-CU40; AFRPL-TR-84-040) Avail N85-12200*# Astro Research Corp, Carpmtena, Calif NTIS HC A05/MF A01 CSCL 13H LARGE-DIAMETER ASTROMAST DEVELOPMENT Final Report Very large and accurate reflective surfaces are required for L A FINLEY 19 Jul 1984 43 p future space applications such as solar rocket propulsion, radar, (Contract NAS8-34547) laser power transmission and relay, solar energy collection, (NASA-CR-171201, NAS 1 26 171201, ARC-TN-1132) Avail telescopes, and others Present techniques used to construct highly NTIS HC A03/MF A01 CSCL 13B accurate reflectors are limited in application to diameters of a few The 15-m-long by 0 75-diameter deployable supermast was meters Metallized thin film membranes have the potential to satisfy delivered The performance characteristics, design parameters, and the requirements of most future applications with minimum weight developmental work associated with this mast are described The systems The objective of this research was to identify materials, main differences, besides the length of these two mast sections, construction and control techniques to improve the surface are a change in the longeron matenal (the principal structural accuracy of inflatable reflectors Film joining and forming, support member) to a circular cross section and the incorporation of a structure design options, surface accuracy measurement system lanyard-bridle system which makes unaided deployment and options and electrostatic surface configuration control techniques retraction possible in zero gravity B G were investigated Prototype models were designed, built, and tested to demonstrate film forming techniques, support structure N85-13999# European Space Conference, Pans (France) deployment, and electrostatic membrane configuration control WORKSHOP ON MECHANICAL TECHNOLOGY FOR utilizing segmented charge plates and an electron gun A laser ANTENNAS ray-tracing technique was employed to measure surface accuracies T D GUYENNE, ed and J J HUNT, ed Sep 1984 180 p These demonstrations venfied the feasibility of the concepts refs Worshop held at Noordwijk, Netherlands, 26-28 Jun 1984 Author (GRA) (ESA-SP-225, ISSN-0379-6566) Avail NTIS HC A09/MF A01 Deployable/furlable antennas, inflatable antennas, antenna design; antenna testing, and spacecraft structures/antenna control system interactions were discussed

N85-11031*# Boeing Aerospace Co., Seattle, Wash N85-14000# European Space Agency European Space MODULAR EXPERIMENTAL PLATFORM FOR SCIENCE AND Research and Technology Center, ESTEC, Noordwijk APPLICATIONS (Netherlands) Structures and Configuration Section A. S HILL In NASA. Marshall Space Flight Center 2nd Symp ANTENNA MECHANICAL TECHNOLOGIES WITHIN ESA on Space Industrialization p 136-148 Oct 1984 refs G G REIBALDI In ESA Workshop on Mech Technol for Avail NTISHCA19/MFA01 CSCL 22B Antennas p 3-10 Sep 1984 refs A modulanzed, standardized spacecraft bus, known as MESA, Avail NTIS HC A09/MF A01 suitable for a variety of science and applications missions is Spaceborne antenna technologies for telecommunication, discussed The basic bus consists of a simple structural remote sensing and scientific missions are reviewed Solid, arrangement housing attitude control, telemetry/command, depfoyable, furlable and inflatable reflectors are descnbed Antenna electncal power, propulsion and thermal control subsystems The technology support concepts in materials, analysis, testing, general arrangement allows extensive subsystem adaptation to manufacturing, mechanisms and attitude control system/structures mission needs Kits provide for the addition of tape recorders, coupling are presented The need for technology commonality increased power levels and propulsion growth Both 3-axis and between different requirements is stressed An ESA technology spin stabilized flight proven attitude control subsystems are flight demonstration program is summanzed Author (ESA) available The MESA bus can be launched on Anane, as a secondary payload for low cost, or on the STS with a PAM-D or N85-14001# Astro Research Corp, Carpmtena, Calif other suitable upper stage Multi-spacecraft launches are possible HIGH PERFORMANCE DEPLOYABLE ANTENNA STRUCTURES with either booster Launch vehicle integration is simple and J M HEDGEPETH In ESA Workshop on Mech Technol for cost-effective. The low cost of the MESA bus is achieved by the Antennas p 13-18 Sep 1984 refs extensive utilization of existing subsystem design concepts and Avail NTIS HC A09/MF A01 equipment, and efficient program management and test integration Design requirements of large, deployable, spacebome antennas techniques M G are discussed The deployable structures used for the Solar

11 03 STRUCTURAL CONCEPTS

Maximum Mission Satellite high gain antenna, and the SEASAT modes, techniques involving base excitation with an electrodynamic SAR array are described A tetrahedral truss structure for antennas exciter, base excitation with a hydraulic exciter, impact and step requiring high dimensional precision at low cost is proposed relaxation techniques were needed The MODAL-PLUS software Author (ESA) was used for parameter identification It was observed to support impact and step relaxation testing fully, but to have limitations for N85-14004# Contraves Corp, Zurich (Switzerland) the base excitation methods The expenmentally-identrfied modal LARGE SPACEBORNE ANTENNA REFLECTORS USING frequencies were compared with results produced by a finite INFLATABLE SPACE RIGIDIZED STRUCTURES element model and a continuum model M G M C BERNASCONI In ESA Workshop on Mech Technol for Antennas p31-36 Sep 1984 refs Sponsored by ESA Avail NTIS HC A09/MF A01 Center and offset fed reflectors for space applications were studied Stiffness and temperature distribution of scale models of a 10 m inflatable reflector were examined A feasibility study of a 20 m reflector for the QUASAT very long baseline interferometry mission was performed A manufactunng concept for a large offset N85-19004*# Astro Research Corp , Carpmtena, Calif antenna was developed The studies indicate that large inflatable EFFICIENT STRUCTURES FOR GEOSYNCHRONOUS antennas with good performance, high stiffness (317 Hz lowest SPACECRAFT SOLAR ARRAYS Final Report frequency at 20 m aperture) and thermal stability (04 mm rms L R ADAMS 27 Sep 1983 29 p refs worst case at 20 m aperture) are feasible Manufacturing accuracy (Contract NAS7-918, JPL-955847) and packaging efficiency can be achieved at low cost (NASA-CR-174448, JPL-9950-980, NAS 1 26174448, Author (ESA) ARC-TN-1125) Avail NTIS HC A03/MF A01 CSCL 22B A prototype deployer for the STACBEAM (Stacking Triangular N85-14007# National Space Development Agency, Ibaraki Articulated Compact Beam) is being developed The STACBEAM (Japan) Space Center is an accordian-folded solar array blanket The prototype was STRUCTURAL ASPECTS OF SAR ANTENNA FOR JAPANESE constructed as a point design for support of a 23 9-kW blanket EARTH RESOURCES SATELLITE 1 and is described B G H MITSUMA In ESA Workshop on Mech Technol for Antennas p 53-58 Sep 1984 refs Avail NTIS HC A09/MF A01 Research and development to establish the basic technology of Synthetic Aperture Radar (SAR) for the Japanese Earth Resources Satellite-1 are described The solar array paddle technologies (honeycomb sandwich panel and deployment N85-21495 Department of the Air Force, Washington, D C mechanism) were applied to the SAR antenna Structural and DEPLOY ABLE FOLDED ANTENNA APPARATUS Patent mechanical component tests, and thermal distortion tests are F V BILEK and D N BUELL, inventors (to Air Force) 13 Nov discussed Author (ESA) 1984 10 p (AD-D011503, US-PATENT-4,482,900, N85-17428# AEG-Telefunken, Wedel (West Germany) US-PATENT-APPL-SN-417726, US-PATENT-CLASS-417-726) Anlagentechnik Aktiengesellschaft Avail US Patent and Trademark Office CSCL 09E DEVELOPMENT OF A FOLDLINE CONCEPT FOR AUTOMATIC An antenna apparatus for use in space which is foldable into REFOLDING OF A FLEXIBLE BLANKET (FOLDING ANALYSIS) a small package for storage in a space vehicle is described The Final Report antenna apparatus utilizes a plurality of hinged members and W SCHMITZandT HEMPEL Pans ESA 1984 149 p refs diagonal tapes forming parallelogram frames, two opposite sides (Contract ESTEC-5198/82/NL-PB(SQ) of which are hinged at the center to fold the frames in a given (ESA-CR(P)-1933) Avail NTIS HC A07/MF A01 plane Similar frames are hinged on the first frames in a second The technical viability of a solar array refolding system was plane whereby a plurality of cubes are formed when all are established and a mathematical model to give input data and unfolded Author (GRA) suggestions for the manufacture of test samples was developed Steps leading to the design parameters of the larger demonstration model are descnbed together with the final outlook resulting from the functional investigation of this object The basic elements of the refolding system are blanket-integrated springs, which perform deflections normal to the blanket plane when the pre-tension is applied The stiffness of these springs must be lower than that of the blanket since a relatively great spring-way is required to support N85-21697# Tokyo Univ. (Japan) large deflections in the fold line area for defined refolding VARIABLE GEOMETRY TRUSS CONCEPT Author (ESA) K MIURA Sep 1984 20 p refs (REPT-614, ISSN-0285-6808) Avail NTIS HC A02/MF A01 N85-18352 Communications Research Centre, Ottawa (Ontario) A concept for a one-dimensional deployable truss structure is MODELLING AND IDENTIFICATION OF THE STRUCTURAL presented The deployed configuration of the structure consists of PROPERTIES OF AN ASTROMAST the repetition of an octahedral truss module longitudinally, and Y SOUCY and F R VIGNERON Nov 1983 91 p refs thus it is exactly the so-called geodesic beam structure The (CRC-1374) Avail Issuing Activity principal mechanical feature of the truss is that the lateral members Analytical modeling and identification of static and dynamic comprising the lateral triangular truss are telescoping beams (modal) parameters for an Astromast are descnbed The Contracting of the lateral members results in the deployment of fundamental bending modes in the X and Y directions, three higher the truss structure The geometric transformation of this truss of order transverse bending modes, and two modes in torsion, were variable geometry is presented It is shown that both simultaneous identified in tests in the frequency range 1 8 to 46 Hz The and sequential modes of transformation are possible The validity associated damping factors range between 1 2 and 8 5 percent of the transformation applied to the deployment is venfied through The factors associated with the fundamental bending and torsion design of a conceptual model The applications of the concept to modes were found to be the same in vacuum and in air No a curvilinear truss and a space manipulator arm are previewed single configuration and technique was able to identify all of the Author 04 STRUCTURAL AND THERMAL ANALYSIS

04 A85-13252# THERMAL ANALYTICAL MODEL OF BIDIMENSIONAL AND STRUCTURAL AND THERMAL ANALYSIS UNIDIMENSIONAL STRUCTURAL ELEMENTS IN A SPACE ENVIRONMENT C ARDUINI (Roma, Universita, Rome, Italy) International Includes structural analysis and design, thermal analysis and Astronautical Federation, International Astronautical Congress, design, analysis and design techniques, and thermal control 35th, Lausanne, Switzerland, Oct. 7-13, 1984 23 p refs systems (IAF PAPER 84-399) Global analytical thermal conductive-radiative modelling of one and two dimensional structural elements is proposed, based on A85-12884 approximations of the temperature field analogous to those made EVALUATION OF EFFICIENTLY COMPUTED EXACT for displacements problems concerning elasticity The resulting VIBRATION CHARACTERISTICS OF SPACE PLATFORMS models, their uses, and their limitations are discussed C D ASSEMBLED FROM STAYED COLUMNS J R. BANERJEE and F W WILLIAMS (University of Wales Institute of Science and Technology, Cardiff, Wales) Journal of Sound and Vibration (ISSN 0022-460X), vol 95, Aug 8, 1984, p 405-414 A85-13253# Research supported by the Science and Engineering Research HEAT CONDUCTION PROBLEMS IN LARGE SPACE Council refs STRUCTURE The exact stiffness matrix method computer program BUNVIS P SANTINI and A PAOLO2ZI (Roma, Universita, Rome, Italy) finds the natural frequencies and modes of vibration of rigidly International Astronautical Federation, International Astronautical jointed three dimensional frames which contain stayed columns Congress, 35th, Lausanne, Switzerland, Oct 7-13, 1984 27 p very efficiently, by using substructunng and simple substitute' (IAF PAPER 84-400) columns to compute the stayed column stiffnesses BUNVIS is The general equations of transient heat conduction in a large descnbed and applied to a tetrahedral truss which was designed space structure consisting of barhke members are written For for use in space and which has stayed columns as its members repetitive bays, and using Laplace-transform techniques, an exact and 21 966 degrees of freedom at its nodes Locating the first solution is obtained, giving the temperature at any point and at 4978 natural frequencies needed 2 h of VAX-11/780 CPU time any time An illustrative example based on a very simple geometry and 5860 array locations These natural frequencies appeared in shows the influence of the various parameters involved in the groups for which the associated modes are discussed Author analysis The solution for special cases (e g, unit step of heat source) is also written Numencal examples are provided Author

A85-13146# A85-18321# MASS OPTIMISATION OF TELECOMMUNICATIONS SPACE STATION THERMAL CONTROL - AN INTERVIEW WITH SATELLITES ROBERT HASLETT J A VANDENKERCKHOVE (ESA, Pans, France) International T BAER Mechanical Engineering (ISSN 0025-6501), vol 106, Astronautical Federation, International Astronautical Congress, Dec 1984, p 22-33 35th, Lausanne, Switzerland, Oct 7-13, 1984 8 p The development of two-phase monogroove-heat-pipe thermal (IAF PAPER 84-230) radiators for potential use in the NASA Space Station is descnbed The mass optimization of geostationary communications on the basis of an interview with the head of the Grumman satellites is considered by analyzing a number of cases varying in Advanced Thermal Systems Group and illustrated with the number and type of payloads, the platform scale factor, the photographs, diagrams, and drawings The current design calls lifetime, and the platform and payload reliabilities The results for 50-ft-long 2-kW modular elements (making up arrays to meet suggest that the optimal mass rarely exceeds 4000 kg BOL In the eventual 300-kW Station heat-dissipation requirement) filled most cases, the improvement in cost effectiveness that would with NH3 for operation at 40-120 F, assembly in space using the result by exceeding 2500 kg is marginal and is probably not worth Shuttle manipulator arm, automated performance monitoring and the complication of adding another payload to the platform B J damage detection, and wall thickness sufficient to limit the threat to the system from micrometeoroids or space debns An advanced fin containing numerous small heat pipes and a rotating gimbal attachment to keep the radiator panels parallel to incoming sunlight A85-13243*# National Aeronautics and Space Administration are also being developed as NASA funding and commitment to Langley Research Center, Hampton, Va the heat-pipe design approach are increased T K LARGE SPACE STRUCTURES GROUND AND FLIGHT PROGRESS L D PINSON (NASA, Langley Research Center, Structural Dynamics Branch, Hampton, VA) International Astronautical A85-18812 Federation, International Astronautical Congress, 35th, Lausanne, MASS PROPERTIES ANALYSIS AND CONTROL OF ADVANCED Switzerland, Oct 7-13, 1984 9 p refs SPACE STRUCTURES THROUGH COMPUTERIZED (IAF PAPER 84-388) INTEGRATION WITH DESIGN AND STRUCTURAL ANALYSIS Unprecedented challenges arise in connection with the design J H NAKAI and W D HONEYCUTT (General Dynamics Corp, and certification of space systems which are too large to be Convair Div , San Diego, CA) Society of Allied Weight Engineers, transported into orbit fully assembled Special situations ansmg in Annual Conference, 42nd, Anaheim, CA, May 23-25, 1983 23 p the case of such systems make it necessary to rely much more (SAWE PAPER 1527) on analysis than in past programs The present investigation is The architecture of a computerized mass properties and control concerned with the status of some research activities onented system program network for analyzing advanced space structures primarily to the improvement of analysis capabilities through is descnbed The network is a set of programs for every stage coordinated ground and flight testing Aspects of system from preliminary design to finished product The applications include identification are explored, taking into account an eigensystem trade-off studies, new design analysis, record keeping, trend realization algorithm, and the Hoop-Column Antenna concept plotting, report generation, and data base filing for structural studies Attention is also given to a suitable method for analyzing the Sample procedures for analysis of tetrahedral trusses with the Hoop-Column antenna structure, a deployment analysis, NASTRAN code are discussed, along with programs for geometric certification issues for large space structures, a genenc space ray tracing, deployable truss beam synthesis analysis, and station model, and the use of actuators G R curve/surface fitting efforts M S K

13 04 STRUCTURAL AND THERMAL ANALYSIS

A85-19493*# Rockwell International Corp, Seal Beach, Calif A85-21829*# National Aeronautics and Space Administration. THERMAL STORAGE ANALYSIS FOR LARGE MANNED SPACE Ames Research Center, Moffett Field, Calif PLATFORMS TRAJECTORY ANALYSIS OF RADIATIVE HEATING FOR A M LEHTINEN and J A SADUNAS (Rockwell International Corp , PLANETARY MISSIONS WITH AEROBRAKING OF Seal Beach, CA) American Institute of Aeronautics and SPACECRAFT Astronautics, Aerospace Sciences Meeting, 23rd, Reno, NV, Jan G P MENEES (NASA, Ames Research Center, Moffett Field, 14-17, 1985 11 p refs CA) Journal of Spacecraft and Rockets (ISSN 0022-4650), vol (Contract NAS9-16782) 22, Jan-Feb 1985, p 37-45 Previously cited in issue 05, p. 602, (AIAA PAPER 85-0066) Accession no A83-16696 refs High electrical power and waste heat rejection is projected for future manned low earth orbit space platforms, such as Space Station The high heat rejection, optical coating degradation, long operating life with minimum maintenance requirements pose a challenging thermal management design problem System A85-25145*# Virginia Polytechnic Inst and State Univ, optimization, with respect to radiator area and weight, indicate the Blacksburg requirement for thermal storage This paper examines the thermal AN ANALYTICAL INVESTIGATION OF SHAPE CONTROL OF storage benefits, determines the characteristics as applied to LARGE SPACE STRUCTURES BY APPLIED TEMPERATURES different IMS concepts (e g, centralized, decentralized), and R T HAFTKA (Virginia Polytechnic Institute and State University, examines the similarities and differences of thermal storage Blacksburg, VA) and H M ADELMAN (NASA, Langley Research integration with single-phase and two-phase systems for a study Center, Interdisciplinary Research Office, Hampton, VA) (Virginia baseline 75 kWe low earth orbit platform Author Polytechnic Institute and State University and American Institute of Aeronautics and Astronautics, Symposium on Dynamics and Control of Large Structures, 4th, Blacksburg, VA, June 6-8, 1983, Paper) AIAA Journal (ISSN 0001-1452), vol 23, March 1985, p A85-19553# 450-457 Previously cited in issue 21, p 3098, Accession no GENERALIZED TRANSFORM METHODS BASED FINITE A83-43891 refs ELEMENT METHODOLOGY - THERMAL/STRUCTURAL DYNAMIC APPLICATIONS K K TAMMA, C C SPYRAKOS (West Virginia University, Morgantown, WV), and M A LAMBI American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting, 23rd, N85-12313*# National Aeronautics and Space Administration Reno, NV, Jan 14-17, 1985 12 p refs Langley Research Center, Hampton, Va (AIAA PAPER 85-0155) EXPERIMENTAL AND PREDICTED HEATING DISTRIBUTIONS A method for interfacing interdisciplinary fields to perform FOR BICONICS AT INCIDENCE IN AIR AT MACH 10 thermal/structural analyses with transform methods finite element C G MILLER, III Nov 1984 118p refs (TMFE) techniques is outlined The object of the thermal/structural (NASA-TP-2334, L-15785, NAS 1 602334) Avail NTIS HC approach is to predict the performance characteristics of complex A06/MF A01 CSCL 20D space structures now in the developmental stage TMFE considers Heating distributions were measured on a 1 9-percent-scale transient effects with Laplace transformations covering both heat model of a genenc aeroassisted vehicle proposed for missions to transfer and structural mechanics, eg, the arousal of thermally a number of planets and for use as a moderate lift-drag ratio induced oscillations Governing equations are provided for a beam Earth orbital transfer vehicle This vehicle is spherically blunted, element and sample results are given for simple-supported and 12 84 deg/7 deg biconic with the fore-cone bent upward 7 deg to cantilever beams, the latter with and without an end mass provide self-trim capability A straight biconic with the same nose MSK radius and the same half-angles was also tested The free-stream Reynolds numbers based on model length were equal to about 2 x 10(5) or 9 x 10 (5) The angle of attack, referenced to the aft-cone, was vaned from 0 deg to 20 deg Heating distributions predicted with a parabolized Navier-Stokes (PNS) code are A85-19895 compared with the measurements for the present Reynolds GEOMETRICALLY NONLINEAR ANALYSIS OF SPACE FRAMES numbers and range of angles of, attack Leeward heating was BY AN INCREMENTAL ITERATIVE TECHNIQUE greatly affected by Reynolds number, with the heating increasing J L MEEK and H. S TAN (Queensland, University, Brisbane, with decreasing Reynolds number for attached flow (low incidence) Australia) Computer Methods in Applied Mechanics and The opposite was true for separated flow, which occurred when Engineenng (ISSN 0045-7825), vol 47, Dec 1984, p 261-282 the fore-cone angle of attack exceeded 08 times the fore-cone refs half-angle Windward heating distributions were predicted to within 10 percent with the PNS code Leeward heating distnbutions were predicted qualitatively for both Reynolds numbers, but quantitative agreement was poorer than on the windward side M G A85-20916 FORMEX CONFIGURATION PROCESSING IN STRUCTURAL ENGINEERING H NOOSHIN (Surrey, University, Guildford, England) London and New York, Elsevier Applied Science Publishers, 1984 282 p N85-13895*# National Aeronautics and Space Administration The concepts of formex algebra are presented in context of Johnson (Lyndon B) Space Center, the analysis of space structures The discussion of the THERMAL MANAGEMENT TECHNOLOGY STATUS fundamentals of formex algebra includes some recently evolved R C PARISH In NASA Lewis Research Center Space Power ideas, such as the concept of rapportance and a new approach p 189-203 Apr 1984 refs in defining a formex Some new useful functions are described Avail NTIS HC A14/MF A01 CSCL 20D which include nndle, pexum, and medulla functions The discussion The thermal control requirements of a large space station are also covers formex graphics, node numbenng, and formex collation considered Motivations for advanced thermal technology are The book is intended for structural engineers, architects, designers, discussed Two test programs, designed to evaluate the analytical and researchers dealing with any aspect of computer-aided and theoretical basis from which thermal technology directions structural evaluation and design V L are determined, are descnbed R.S F

14 04 STRUCTURAL AND THERMAL ANALYSIS

N85-13900'# Washington Univ, Seattle. and locking mechanisms; and thermal control equipment Catena THE LIQUID DROPLET RADIATOR - AN ULTRALIGHTWEIGHT assumed to satisfy antenna payload (commonality, AM orientation, HEAT REJECTION SYSTEM FOR EFFICIENT ENERGY reflectors folding according to the fairing volume, folding and CONVERSION IN SPACE kinematic constraints) are descnbed Thermal control concepts, A. T MATTICK and A. HERTZBERG In NASA Lewis Research analysis, performances, and alignment techniques are Center Space Power p 261-274 Apr 1984 refs summarized Author (ESA) Avail NTIS HC A14/MF A01 CSCL 10B A heat rejection system for space is described which uses a N85-14016# Saab-Scania, Unkoping (Sweden) recirculating free stream of liquid droplets in place of a solid surface STRUCTURAL DESIGN AND THERMAL STABILITY OF TELE-X to radiate waste heat By using sufficiently small droplets ( 100 ANTENNA TOWER micron diameter) of low vapor pressure liquids the radiating droplet B MOERTBERG In ESA Workshop on Mech Technol for sheet can be made many times lighter than the lightest solid Antennas p 117-120 Sep 1984 surface radiators (heat pipes) The liquid droplet radiator (LOR) is Avail NTIS HC A09/MF A01 less vulnerable to damage by micrometeoroids than solid surface The design, analysis and manufacturing of the TELE-X satellite radiators, and may be transported into space far more efficiently antenna tower are descnbed The tower has to sustain loads dunng Analyses are presented of LOR applications in thermal and launch and in-orbit deployments, fulfill stiffness requirements, fulfill photovoltaic energy conversion which indicate that fluid handling environmental requirements with respect to other subsystems, and components (droplet generator, droplet collector, heat exchanger, fulfill thermal distortion requirements The antenna system is based and pump) may comprise most of the radiator system mass Even on a Cassegram design consisting of a feed, subreflector and the unoptirnized models employed yield LOR system masses less mam reflector The structure can withstand temperature gradients than heat pipe radiator system masses, and significant improvement of 25 C between structural elements, and 70 C between upper is expected using design approaches that incorporate fluid handling and lower platform Author (ESA) components more efficiently Technical problems (e g, spacecraft contamination and electrostatic deflection of droplets) unique to N85-14017# Rome Univ (Italy) Dept of Aerospace this method of heat rejectioon are discussed and solutions are ANALYTICAL THERMAL FORMULATIONS FOR ANTENNA suggested M G DISHES C ARDUINI In ESA Workshop on Mech Technol for Antennas N85-13906*# National Aeronautics and Space Administration p 125-131 Sep 1984 refs Johnson (Lyndon B) Space Center, Avail NTIS HC A09/MF A01 HEAT REJECTION WORKING GROUP SYNOPSIS Thermostructural analysis of spaceborne antenna dishes using R C PARISH and R. HASLETT (Grumman Aerospace Corp) In interactive thermal-structural-control unified analytical formulations NASA Lewis Research Center Space Power p 309-316 Apr is discussed Displacement and temperature are represented by a 1984 Taylor series Results which describe how antenna dishes can be Avail NTIS HC A14/MF A01 CSCL 10B thermally analyzed under general hypotheses by a completely Heat rejection system requirements of specific mission types analytical radiative-conductive formulation are shown (space station, planetary exploration, commercial, very high power, Author (ESA) and military missions) are discussed Heat pipe radiators, weight and volume reduction, stable coatings, and working fluids are N85-15796*# National Aeronautics and Space Administration addressed M G Langley Research Center, Hampton, Va SPACE STATION TRUSS STRUCTURES AND CONSTRUCTION N85-14009# Messerschmitt-Boelkow-Blohm GmbH, Munich CONSIDERATIONS (West Germany). M. M MIKULAS, JR, S D CROOMES, W SCHNEIDER, H G. MECHANICAL/THERMAL DESIGN OF A POLARIZATION BUSH, K NAGY, T PELISCHEK, M S LAKE, and C SENSITIVE REFLECTOR WESSELSKI Jan 1985 119 p refs Prepared in cooperation H J HUETTMANN, T FISCHER, H POPP, and W SCHAEFER with NASA Johnson Space Center In ESA Workshop on Mech. Technol for Antennas p 67-72 (NASA-TM-86338, NAS 1 1586338) Avail NTIS HC A06/MF Sep 1984 refs A01 CSCL 22B (Contract ESTEC-5494/84/NL-GM) Although a specific configuration has not been selected for Avail NTIS HC A09/MF A01 the Space Station, a gravity gradient stabilized station as a basis Mechanical/thermal design features of a reflector for frequency upon which to compare various structural and construction reuse by orthogonal polarization are outlined The reflector concepts is considered The Space Station primary truss support configuration consists of two Kevlar fiber sandwich shells oriented structure is descnbed in detail Three approaches (see sketch A) one behind the other and joined by a Kevlar fiber nng The reflector which are believed to be representative of the major techniques shell surfaces are covered with conductive stnp gnds which are for constructing large structures in space are also descnbed in oriented perpendicularly with respect to each other Further detail so that salient differences can be highlighted B W stiffening can be achieved by four nbs The preferred thermal design has a Sun shield in front of the reflector and multilayer N85-16066*# National Aeronautics and Space Administration insulation on its rearside Author (ESA) Langley Research Center, Hampton, Va REDUCTION METHOD FOR THERMAL ANALYSIS OF COMPLEX N85-14012# Societe Nationale Industnelle Aerospatiale, Les AEROSPACE STRUCTURES Mureaux (France) C P SHORE Jan 1985 31 p refs TECHNOLOGY AND PERFORMANCES OF STRUCTURAL (NASA-TP-2373, L-15777, NAS 1602373) Avail NTIS HC THERMAL MECHANICAL EQUIPMENT USED FOR ANTENNA A03/MF A01 CSCL 20D OF TV.SAT-TDF 1 PROGRAM A reduction method which combines classical Rayleigh-Ritz G MORIO, B VEREZ, J NESA, J L PETTEX, S AUCEL, and H modal superposition techniques with contemporary finite-element DAGEVILLE In ESA Workshop on Mech. Technol for Antennas methods is applied to transient nonlinear thermal analysis of p 83-91 Sep 1984 refs aerospace structures The essence of the method is the use of a Avail. NTIS HC A09/MF A01 few thermal modes from eigenvalue analyses as basis vectors to The mechanical-thermal technologies of the TV SAT-TDF 1 represent the temperature response in the structure The method antenna module are described The module is housed in a tower is used to obtain approximate temperature histones for a portion structure, with 2 reflectors (Tx at 12 GHz, Rx at 18 GHz), 2 of the Shuttle orbiter wing subject to reentry heating and for a antenna fine pomtng mechanisms with their associated electonics, large space antenna reflector subject to heating associated with 2 reflector folding and release mechanisms, 2 reflector deployment a low Earth orbit The reduction method has excellent potential

15 04 STRUCTURAL AND THERMAL ANALYSIS

for significant size reduction for radiation-dominated problems such N85-17020*# Lockheed Missiles and Space Co, Palo Alto, as the antenna reflector However, for conduction-dominated Calif Thermal Sciences Lab problems such as the Shuttle wing, especially those with complex PASSIVE ORBITAL DISCONNECT STRUT (PODS 3) spatial and temporal vanations in the applied heating, additional STRUCTURAL TEST PROGRAM work appears necessary to find alternate sources of basis vectors R T PARMLEY Jan 1985 112p refs which will permit significant problem size reductions Author (Contract NAS2-10848) (NASA-CR-177325, NAS 1 26 177325) Avail NTIS HC A06/MF N85-17012# Office National d'Etudes et de Recherches A01 CSCL 22B Aerospatiales, Toulouse (France) Dept d'Etudes et de A passive orbital disconnect strut (PODS-3) was analyzed Recherches en Technologic Spatiale structurally and thermally Development tests on a graphite/epoxy SPACE ENVIRONMENT SIMULATION TO TEST SATELLITE orbit tube and S glass epoxy launch tube provided the needed THERMAL CONTROL COATINGS, VOLUME 1 Final Report data to finalize the design A detailed assembly procedure was [ESSAIS OE SIMULATION D'ENVIRONNEMENT SPATIAL SUR prepared One strut was fabricated Shorting loads in both the REVETEMENTS DE CONTROLE THERMIQUE DE SATELLITES, axial and lateral direction (vs load angle and location) were TOME 1] measured The strut was taken to design limit loads at both ambient M DUTAT, J MARCO, and A PAILLOUS Pans ESA Oct and 78 K (cold end only) One million fatigue cycles were performed 1983 138 p refs In FRENCH Report will also be announced at predicted STS loads (half in tension, half in compression) with as translation (ESA-TT-891-Vol-1) 3 Vol the cold end at 78 K The fatigue test was repeated at design (Contract ESTEC-4577/81/NL-DG, ESTEC-5144/82/NL-DG) limit loads Six struts were then fabricated and tested as a system (CERT-4128-VOL-1, ESA-CR(P)-1870-VOL-1) Avail NTIS HC Axial loads, side loads, and simulated asymmetric loads due to A07/MF A01 temperature gradients around the vacuum shell were applied Optical solar reflector coatings were tested in a vacuum Shorting loads were measured for all tests Author chamber by irradiation with electrons, protons and ultraviolet radiation to simulate 5 years of geostationary orbit The effect of N85-17323*# OAO Corp , Greenbelt, Md contamination from adhesive RTV 566 was studied to explain the CAPILLARY PUMP LOOP (CPL) HEAT PIPE DEVELOPMENT performance degradation in OTS2 and other satellites Optical STATUS REPORT reflectance was measured by spectrometers The variation in solar Aug 1982 42 p absorption as a function of time is given for four types of coating (Contract NAS5-26660) material The contaminated samples show a degradation of solar (NASA-CR-175273, NAS 126175273) Avail NTIS HC A02/MF absorption three to four times larger than controls Author (ESA) A01 CSCL 20D The capillary pump loop (CPL) was re-introduced as a potential N85-17013# Office National d'Etudes et de Recherches candidate for the management of large heat loads It is currently Aerospatiales, Toulouse (France) Dept d'Etudes et de recherches being evaluated for application in the thermal management of large en Technology Spatiale space structures Test efforts were conducted to establish the SPACE ENVIRONMENT SIMULATION TO TEST SATELLITE feasibility of the CPL heat pipe design B G THERMAL CONTROL COATINGS. VOLUME 2: ANNEX 1 [ESSAIS DE SIMULATION D'ENVIRONMENT SPATIAL SUR REVETEMENTS DE CONTROLE THERMIQUE DE SATELLITES. N85-17382# Shock and Vibration Information Center (Defense), TOME 2, ANNEXE 1] Washington, D C Pans ESA 1983 137 p In FRENCH Report will also be THE SHOCK AND VIBRATION DIGEST, VOLUME 16, NO. 11 announced as translation (ESA-TT-891-Vol-2) 3 Vol Monthly Report (Contract ESTEC-4577/81/NL-DG, ESTEC-5144/82/NL-DG) J NAGLE-ESHLEMAN, ed Nov 1984 108 p refs (ESA-CR(P)-1870-VOL-2) Avail NTIS HC A07/MF A01 (AD-A148466) Avail SVIC, Code 5804, Naval Research Lab , Optical properties measured in situ at -35C and at various Washington, D C 20375 CSCL 20K exposure stages up to one year are tabulated for thermal control Publications on design and testing of shock waves, earthquakes coatings tested during space environment simulation Results show and vibration on large are presented Topics discussed include (1) spectral reflectance for 13 wavelengths, (2) variation with the influence of vibration on composite materials, weightlessness, respect to the initial measurement, i e, before irradiation and stimulation, structures, solar panel stiffness, and payloads It is deposition, (3) solar reflectance including ultraviolet, visible, and suggested that better techniques to be developed for scale model infrared radiation, as well as the total spectrum (295 to 4,000 tests, analytical prediction models, in-orbit testing of structures nm), (4) variations of solar reflectance with respect to initial values, like solar panels flower on the shuttle, and tabulation of data on (5) solar absorptance (calculated as a complement at 1 00 of damping properties of the new composite matenals solar reflectance in the same wavelength domain), and (6) variations of these solar reflectances with respect to initial values N85-21209*# National Aeronautics and Space Administration Transl by A R H Johnson (Lyndon B) Space Center, PARAMETRIC ANALYSIS: SOC METEOROID AND DEBRIS N85-17014# Office National d'Etudes et de Recherches PROTECTION Aerospatiales, Toulouse (France) Dept d'Etudes et de R KOWALSKI In its Orbital Debris p 287-294 Mar 1985 Recherches en Technologic Spatiale refs SPACE ENVIRONMENT SIMULATION TO TEST SATELLITE Avail NTIS HC A20/MF A01 CSCL 22B THERMAL CONTROL COATINGS. VOLUME 2: ANNEXES 2, The meteoroid and man made space debris environments of 3, 4 [ESSAIS DE SIMULATION D'ENVIRONMENT SPATIAL SUR an Earth orbital manned space operations center are discussed REVETEMENTS DE CONTROLE THERMIQUE DE SATELLITES. Protective shielding thickness and design configurations for TOME 2: ANNEXES 2, 3, 4] providing given levels of no penetration probability were also Pans ESA 1983 259 p In FRENCH Report will also be calculated Meteoroid/debns protection consists of a radiator/shield announced as translation (ESA-TT-891-Vol-3) 3 Vol thickness, which is actually an outer skin, separated from the (Contract ESTEC-4577/81/NL-DG, ESTEC-5144/82-NL-DG) pressure wall, thickness by a distance An ideal shield thickness, (ESA-CR(P)-1870-VOL-3) Avail NTIS HC A12/MF A01 will, upon impact with a particle, cause both the particle and shield Initial and post irradiation measurements obtained under vacuum to vaponze, allowing a minimum amount of debns to impact the and at -35C are tabulated for satellite thermal control coatings pressure wall itself A shield which is too thick will crater on the The measurements were obtained before deposition and at various outside, and release small particles of shield from the inside causing periods after deposition up to 5 08 simulated years damage to the pressure wall Inversely, if the shield is too thin, it Transl by A R H will afford no protection, and the backup must provide all necessary

16 05 STRUCTURAL DYNAMICS AND CONTROL protection It was concluded that a douole wall concept is most the same model Actuators and sensors were found to be required effective R.J F on two of the six bodies for effective attitude control Author

A85-11087* Bendix Corp , Teterboro, N J DEVELOPING SENSITIVITY COEFFICIENTS FOR A STATE 05 VARIABLE MODEL OF A FLEXIBLE SPACECRAFT WITH MODULAR ATTITUDE CONTROL F. D CHICHESTER (Bendix Corp, Guidance Systems Drv, STRUCTURAL DYNAMICS AND CONTROL Teterboro, NJ) IN Modeling and simulation Volume 14 - Proceedings of the Fourteenth Annual Pittsburgh Conference, Includes modeling, systems identification, attitude and control Pittsburgh, PA, Apnl 21, 22, 1983 Parts 1-2 Research Tnangle techniques and systems, surface accuracy measurement and Park, NC, Instalment Society of Amenca, 1983, p 521-525 control techniques and systems, sensors, and actuators (Contract NAS8-33979) The numencal value for the sensitivity coefficient of each scalar state vanable with respect to each parameter of a five body model A85-10071 of the rotational dynamics of a flexible spacecraft with modular THE DECENTRALIZED CONTROL OF LARGE FLEXIBLE SPACE attitude control is generated The maximum magnitudes of these STRUCTURES sensitivity coefficients are arranged in descending order in one G S WEST-VUKOVICH (Dynacon Enterprises, Ltd , Toronto, table while the final time (steady state) values of these sensitivity Canada), E J DAVISON, and P C HUGHES (Toronto, University, coefficients are arranged in order of descending magnitude in a Toronto, Canada) IEEE Transactions on Automatic Control (ISSN second table Author 0018-9286), vol AC-29. Oct 1984, p 866-879 Research supported by Canada Council, Natural Sciences and Engmeenng Research A85-12434# Council of Canada, refs ALLEVIATION OF OBSERVATION SPILLOVER IN CONTINUOUS (Contract NSERC-A-4396, NSERC-A-4183) STRUCTURES The decentralized robust servomechanism problem with A V METCALFE and J S BURDESS (Newcastle-upon-Tyne, constant disturbances/set points is considered for large flexible University, Newcastle-upon-Tyne, England) IN International space structures (LFSS) It is shown that for LFSS which have Conference on Recent Advances in Structural Dynamics, 2nd, colocated, mutually dual sensors and actuators, the decentralized Southampton, England, Apnl 9-13, 1984, Proceedings Volume 1 fixed modes of the system are precisely equal to the centralized Southampton, England, University of Southampton, 1984, p fixed modes of the system Simple necessary and sufficient 97-106 refs conditions are then obtained for a solution to exist for the robust The contamination of the input to the observer by observation decentralized servomechanism problem for the system A controller spillover is a cause of stability problems in complex systems (e g , is demonstrated which, for this class of LFSS systems, eliminates large-scale space structures) This paper proposes a method for the 'spillover problem' A two-hundredth-order numencal example estimating and alleviating such contamination It is suggested that Of an LFSS control problem using the Purdue model is included this can be done by augmenting the observer with a further dynamic to illustrate the results Author system which can be described as a disturbance observer Examples demonstrating the application of this approach are A85-11082* Jet Propulsion Lab, California Inst of Tech, presented B J Pasadena DYNAMIC ISOLATION OF A SPACECRAFT SCIENCE A85-12442# PLATFORM VIA MOMENTUM COMPENSATION THE IMPROVEMENT OF FREE-MODE METHODS IN D BOUSSALIS (California Institute of Technology, Jet Propulsion COMPONENT MODE SYNTHESIS TECHNIQUES AND ITS Laboratory, Guidance and Control Section, Pasadena, CA) IN ACCURACIES Modeling and simulation Volume 14 - Proceedings of the Z. W WANG and M PETYT (Southampton, University, Fourteenth Annual Pittsburgh Conference, Pittsburgh, PA, April 21, Southampton, England) IN International Conference on Recent 22, 1983 Parts 1-2 Research Tnangle Park, NC, Instrument Advances in Structural Dynamics, 2nd, Southampton, England, April Society of Amenca, 1983, p 465-471 9-13, 1984, Proceedings Volume 1 Southampton, England, (Contract NAS7-100) University of Southampton, 1984, p 221-228 refs The dynamic isolation of a two degree of freedom mertially Free-mode methods in component mode synthesis techniques stabilized science platform from the spacecrft basebody is are improved by the use of the concept of 'positive static' residuals, examined The important implications of a momentum compensated which are developed according to the theorems given in this paper platform for pointing performance and cost are discussed, and The technique of assembly of complicated structures is also the concept of a new system called the Integrated Platform Pointing presented The convergence of the improved free-mode method and Attitude Control Subsystem utilizing the above property is is related to the so-called 'eigenfrequency coefficient n', which is presented The results established in this paper are demonstrated generally greater than 1 0 and smaller than 1 4 Author by a computer simulation Author A85-12455# A85-11086* Bendix Corp, Teterboro, N J APPLICATION OF MODAL SYNTHESIS CONCEPTS TO COMPARING ATTITUDE CONTROL EFFECTIVENESS FOR SPACECRAFT DESIGN VERIFICATION ACTUATORS ON TWO BODIES OF A SIX BODY MODEL OF A A BERTRAM (Deutsche Forschungs- und Versuchsanstalt fuer FLEXIBLE SPACECRAFT WITH THAT FOR ACTUATORS Luft- und Raumfahrt, Institut fuer Aeroelastik, Goettingen, West RESTRICTED TO A SINGLE BODY Germany) IN International Conference on Recent Advances in F D CHICHESTER and I S EMMANUEL (Bendix Corp , Guidance Structural Dynamics, 2nd, Southampton, England, Apnl 9-13, 1984, Systems Div, Teterboro, NJ) IN Modeling and simulation Volume Proceedings Volume 2 Southampton, England, University of 14 - Proceedings of the Fourteenth Annual Pittsburgh Conference, Southampton, 1984, p 395-414 refs Pittsburgh, PA, Apnl 21, 22, 1983 Parts 1-2 Research Tnangle The modal description of structural dynamics is considered with Park, NC, Instrument Society of Amenca, 1983, p 515-519 attention given to modal synthesis methods, coupling conditions, (Contract NAS8-33979) and structural modifications The achievement of the orthogonality A ten ngid body model of a prototype flexible space platform condition and a sufficient convergence is discussed, the selection was approximated by a six body model to facilitate comparison of of suitable modes, test data requirements, convergence attitude control effectiveness for actuators on two bodies with improvement, the consideration of residual terms, and the realistic control effectiveness for actuators restricted to a single body of description of the interface are covered It is concluded that modal

17 05 STRUCTURAL DYNAMICS AND CONTROL synthesis methods can be very efficient and useful tools in the A85-13220*# Howard Unrv, Washington, D C spacecraft design verification procedure The methods presented ENVIRONMENTAL EFFECTS ON THE DYNAMICS AND here may be suitable even for complex and large spacecraft In CONTROL OF AN ORBITING LARGE FLEXIBLE ANTENNA addition, it is noted that the applicability of the modal correction SYSTEM method is limited to cases where the mode shapes of the modified R KRISHNA and P M BAINUM (Howard University, Washington, structure can be sufficiently descnbed by the modes of the DC) International Astronautical Federation, International measured configuration The successful application of the modal Astronautical Congress, 35th, Lausanne, Switzerland, Oct 7-13, coupling approach appears to depend on how realistically the 1984 9p Previously announced in STAR as N84-20627 refs coupling conditions were simulated in the test and in the coupling (Contract NSG-1414) approach B J (IAF PAPER 84-358) Solar radiation pressure on the vibrating antenna structure, temperature gradients induced by solar heating, and stabilizing A85-12478# gravity-gradient torques were considered when the linear regulator CONTINUUM MODELLING OF DAMPING IN LARGE SPACE STRUCTURES theory was used to obtain onentation and shape control of a S ABRATE and C. T SUN (Purdue University, West Lafayette, hoop/column antenna system being considered for the land mobile satellite system A finite element model of the antenna system IN) IN International Conference on Recent Advances in Structural Dynamics, 2nd, Southampton, England, April 9-13, 1984, which includes all six ngid modes and seven flexible modes was used Results show that the environmental disturbances affect Proceedings Volume 2 Southampton, England, University of Southampton, 1984, p 877-885 refs only the rigid modes of the structure The effect of solar radiation pressure interacting with the vibrating system is smaller than the Candidate models for internal damping in large space structures solar radiation pressure acting on the thermally deformed structure (LSS) composed of penodic lattices are explored analytically To reduce control effect in order to maintain shape and orientation, Differential models incorporate stress, strain, and their time derivatives as factors, while hysteretic models describe matrices thermal deformations must be minimized in the preliminary design of the system A R H with time-independent damping characteristics The Timoshenko beam model and a continuum model are also possibilities for LSS analytical tools The finite element method models damping in A85-13221# trusses and frames and in terms of equations of motion for all DYNAMICS OF THE ORBITER BASED CONSTRUCTION OF types of modes The lack of experimental data on LSS is stressed, STRUCTURAL COMPONENTS noting the concommitant difficulty in verifying any of the models V J MODI and A M IBRAHIM (British Columbia, University, Sample calculations are provided for the steady-state damping Vancouver, Canada) International Astronautical Federation, responses of a truss and a cantilevered beam M S K International Astronautical Congress, 35th, Lausanne, Switzerland, Oct 7-13, 1984 34 p Sponsorship Natural Sciences and Engineering Research Council of Canada refs A85-13023# (Contract NSERC-67-066) AN OPTIMAL SHAPE CONTROL OF A LARGE FLEXIBLE (IAF PAPER 84-359) RADIATOR IN SPACE A relatively general formulation for studying lib-rational dynamics A DANES! and M SILVI (Roma, Universita, Rome, Italy) of a large class of spacecraft dunng deployment of arbitrarily International Astronautical Federation, International Astronautical onented beam and plate type flexible members has been Congress, 35th, Lausanne, Switzerland, Oct 7-13, 1984 10 p developed The formulation is applicable to a variety of missions (IAF PAPER 84-64) ranging from deployment of antennas, booms and solar panels to Radiator active shape control is evaluated for a laser package manufacturing of trusses for space platforms using the Space transmitting high optical energy flux from geosynchronous orbit to Shuttle Here, the procedure is applied to the Space Shuttle based a specific ground or space target The proposed multifeedback deployment of plate-like members Results suggest substantial control strategy is implemented via a decentralized low-authority influence of the flexural rigidity of the appendages, deployment control system, while a high-authority system is used to damp the velocity, initial conditions, and appendage onentation on the system modal behavior of the antenna feed structure supporting the laser response Deployment maneuvers in conjunction with a typical package Particular emphasis is placed on a description of the controlled time history of permissible librational rates suggest control system configuration and on the role of the control process flexible plate members to be stable In general, the instability is in reducing the effect of structural flexibility on the radiator pointing triggered through roll excitation leading to unbounded yaw due to accuracy Simulation results show that the proposed active control coupling The results should prove useful in planning of the Orbiter is capable of improving the antenna pointing accuracy to meet based expenments aimed at studying dynamics and control of the design requirements B J flexible, deployable structural components needed in construction of space platforms Author A85-13206# STABILITY OF A RING OF CONNECTED SATELLITES A85-13245# V V BELETSKII (Akademna Nauk SSSR, Institut Prikladnoi DYNAMICAL MODELLING OF A GRAVITY-LOADED Matematiki, Moscow, USSR) and E M LEVIN (Akademna Nauk RECTANGULAR PLATE AS A TEST CONFIGURATION FOR SSSR, Institut Mashmovedenua, Moscow, USSR) International ATTITUDE CONTROL OF LARGE SPACE STRUCTURES Astronautical Federation, International Astronautical Congress, B SCHAEFER (Deutsche Forschungs- und Versuchsanstalt fuer 35th, Lausanne, Switzerland, Oct 7-13, 1984 6 p Luft- und Raumfahrt, Oberpfaffenhofen, West Germany) (IAF PAPER 84-342) International Astronautical Federation, International Astronautical The stability of a ring of connected satellites is examined for Congress, 35th, Lausanne, Switzerland, Oct 7-13, 1984 8 p vanous tether tension laws as functions of the distance between Sponsorship European Space Research and Technology Centre the satellites Maxwsell's theory of stable rotation in such a system refs when the interactive force between the satellites decreases (Contract ESTEC-5310/82/NL/BI) sufficiently at a certain distance magnitude exists between the (IAF PAPER 84-391) satellites formed the basis of the study A control law was examined An analytical study is performed of the design of a structural for adjusting the tension of the tethers It was found that stability element which would have dynamic charactenstics similar to those is possible if the tension is less than the weight of the tethered employed on large space structures (LSS) The design object is satellite divided by the weights of all the other satellites, and based on a wire-suspended rectangular plate, and the goal is to tension will decrease with increasing mtersatellite spacing The define control laws which respond to outputs of sensors and formulas are applied to descnbmg the persistence of the Jovian actuators on the LSS The analysis was required to define a and Uranian nng systems M S K geometnc distribution of suspending cables which would allow

18 05 STRUCTURAL DYNAMICS AND CONTROL generation of mode shapes expected in LSS Suspension generates resolved by optimizing this performance measure over the pendulous, low-frequency oscillations A Rayleigh-Ritz method is admissible set of locations. The variation of this optimized applied to the structural vibrations and the model is extended to performance measure with number of actuators (sensors) is helpful ngid body oscillations. Calculations yield the lowest 20 eigenmodes in deciding how many components to use. Author Of the structural element M.S K

A85-13249# A85-13636*# Rensselaer Polytechnic Inst., Troy, N Y ELASTIC WAVES PROPAGATION IN BOUNDED PERIODIC SOME APPLICATIONS OF DIRECT ADAPTIVE CONTROL TO STRUCTURES LARGE STRUCTURAL SYSTEMS S. SGUBINI, F. GRAZIANI, and A AGNENI (Roma, Universita, I BAR-KANA and H KAUFMAN (Rensselaer Polytechnic Institute, Rome, Italy) International Astronautical Federation, International Troy, NY) Journal of Guidance, Control, and Dynamics (ISSN Astronautical Congress, 35th, Lausanne, Switzerland, Oct 7-13, 0731-5090), vol 7, Nov-Dec 1984, p. 717-724 Previously cited 1984. 5 p refs in issue 10, p 1450, Accession no A84-25496 refs (IAF PAPER 84-395) (Contract NSF ECS-80-16173, NAG1-171) The differences between continuum and periodic models of modular structures are assessed with respect to elastic wave propagation, with particular reference to the use of such models A85-13638*# National Aeronautics and Space Administration to analyze repetitive lattice gnds (used in the design of large Langley Research Center, Hampton, Va. space structures) Continuum models appear to be more attractive OPTIMAL DESIGN OF A PASSIVE VIBRATION ABSORBER FOR from the point of view of numerical evaluation, and yield satisfactory A TRUSS BEAM solutions for low frequencies But as the frequency increases, they J-N JUANG (NASA. Langley Research Center, Structural conceal the filtenng effect and greatly distort the steady-state Dynamics Branch, Hampton, VA) (Guidance and Control response Hence, periodic models are concluded to be more Conference, Gathnburg, TN, August 15-17, 1983, Collection of adequate for the simulation of the behavior of modular structures Technical Papers, p 794-804) Journal of Guidance, Control, and In addition, periodic models involve neither difficult numencal Dynamics (ISSN 0731-5090), vol 7, Nov-Dec 1984, p 733-739 calculations nor excessive computational storage, since recursive Previously cited in issue 19, p 2816, Accession no A83-41750 algorithms are used. B J refs

A85-13293# ROBUST ATTITUDE CONTROL OF A LARGE COMMUNICATION A85-13641# SATELLITE WITH FLEXIBLE SOLAR ARRAYS MODAL DECOUPLING CONDITIONS FOR DISTRIBUTED J LIANG (Chansha Institute of Technology, Changsha, Hunan, CONTROL OF FLEXIBLE STRUCTURES People's Republic of China) International Astronautical Federation, D J INMAN (New York, State University, Buffalo, NY) Journal International Astronautical Congress, 35th, Lausanne, Switzerland, of Guidance, Control, and Dynamics (ISSN 0731-5090), vol 7, Oct 7-13, 1984 10 p refs Nov-Dec 1984, p 750-752 {IAF PAPER 84-ST-06) (Contract AF-AFOSR-82-0242) The controllability and observability of the attitude dynamics Meirovitch and Baruh (1982) have proposed a scheme for the equation of a large communication satellite with flexible solar arrays optimal control of a certain class of conservative distributed is discussed, and a simple condition of the controllability and parameter systems without resorting to discretization In particular, observability is presented In order to define a mode suitable for they considered the control of self-adjoint conservative systems control purposes, the large-dimensional mode is decomposed into having known eigensolutions The present investigation has the a nominal component and a residual component A design objective to point out that the results of Meirovitch and Baruh are procedure for a reduced order control system is investigated, and applicable to a more general class of problems which includes the robustness and stability of this system to system perturbation nonconservative forces It is also noted that the necessary and residual modes are analyzed using singular values of the conditions are available for the existence of decoupling control matrices It is shown that by appropriately choosing the feedback laws Decoupling control laws are control laws dependent only on gam matnx and the observer gam matrix, the control observation the modal state vector of the decoupled equation G R spillover of residual modes can be suppressed in the reduced order control system Some numerical simulation results are presented and a method applicable to the general large space ASS-13893 structure control problem is suggested C D A SIGNED SWITCHING TIME BANG-BANG ATTITUDE CONTROL LAW FOR FINE POINTING OF FLEXIBLE A85-13634*# Massachusetts Inst of Tech , Cambndge SPACECRAFT NUMBER AND PLACEMENT OF CONTROL SYSTEM S J DODDS (Marconi Space and Defense Systems, Ltd , Satellite COMPONENTS CONSIDERING POSSIBLE FAILURES Div, Portsmouth, England) and S E WILLIAMSON (Surrey, W E VANDER VELDE and C R CARIGNAN (MIT, Cambndge, University, Guildford, England) International Journal of Control MA) Journal of Guidance, Control, and Dynamics (ISSN (ISSN 0020-7179), vol 40, Oct 1984, p 795-811 Research 0731-5090), vol 7, Nov.-Dec 1984, p 703-709 refs supported by the Royal Aircraft Establishment (Contract NAG 1-126) Classical approaches to the control of flexible spacecraft make One of the first questions facing the designer of the control use of linear control compensators which avoid excitation of the system for a large space structure is how many components flexure modes on the basis of either (1) notch filter charactenstics actuators and sensors - to specify and where to place them on or (2) simple bandwidth limitation Certain difficulties arise in the structure This paper presents a methodology which is intended connection with both approaches Moreover, the classical to assist the designer in making these choices A measure of approaches are not directly applicable with gas jet actuators of controllability is defined which is a quantitative indication of how fixed control level The problems related to an employment of the well the system can be controlled with a given set of actuators classical approaches can be overcome with the aid of the Similarly, a measure of observability is defined which is a bang-bang control principle, which is considered in the present quantitative indication of how well the system can be observed investigation. In the discussed principle, the flexure modes are with a given set of sensors Then the effect of component actively controlled together with the mean spacecraft attitude and unreliability is introduced by computing the average expected rate. It is pointed out that the developed control law has potential degree of controllability (observability) over the operating lifetime application for high-precision gas jet attitude control systems for of the system accounting for the likelihood of various combinations spacecraft with several modes of flexural vibration which may have of component failures. The problem of component location is negligible damping G.R

19 05 STRUCTURAL DYNAMICS AND CONTROL

A85-15254 The state of such a system can be described by using sets of STABILITY OF THE STATIONARY MOTIONS OF A TETHERED hybrid (concentrated and distributed) coordinates Here, a general SYSTEM OF TWO BODIES IN ORBIT UNDER THE EFFECT OF approach to the mathematical modeling of space vehicles is GRAVITATIONAL AND AERODYNAMIC FORCES [OB proposed which is an extension of the method developed by USTOICHIVOSTI STATSIONARNYKH DVIZHENII SVIAZKI Plimmer (1976) for a limited class of systems The method proposed DVUKH TEL NA ORBITE POD DEISTVIEM here can be used for arbitrary stationary linear systems, and in GRAVITATSIONNYKH I AERODINAMICHESKIKH SIL] particular, for systems with damping provisions and inertia! and E M LEVIN Kosmicheskie Issledovanna (ISSN 0023-4206), vol gyroscopic cross coupling between channels V L 22, Sept-Oct 1984, p 675-682 In Russian refs The motion of a tethered system of two satellites in geocentric A85-18331*# National Aeronautics and Space Administration orbit is examined The mam satellite is assumed to move in circular Langley Research Center, Hampton, Va orbit at a height of 200-250 km above the earth's surface, while CLOSED-FORM SOLUTIONS FOR FEEDBACK CONTROL WITH the subsatellite-probe, attached to the main satellite by a thin TERMINAL CONSTRAINTS tether, is assumed to orbit the earth at a height of 100-150 km J-N JUANG (NASA, Langley Research Center, Structural In the dynamic analysis the subsatellite is considered as a material Dynamics Branch, Hampton, VA), J D TURNER, and H M CHUN point, while the tether is considered as an extensible and (Charles Stark Draper Laboratory, Inc , Cambridge, MA) (Virginia ponderable flexible filament Aerodynamic forces acting on the Polytechnic Institute and State University and American Institute probe and tether are considered, and it is noted that the stationary of Aeronautics and Astronautics, Symposium on Dynamics and motions of the system consist in its uniform revolution as a rigid Control of Large Flexible Structures, 4th, Blacksburg, VA, June body about the earth The stability of these stationary motions is 6-8, 1983, Paper) Journal of Guidance, Control, and Dynamics analyzed, and it is shown that constraints imposed on the tether (ISSN 0731-5090), vol 8, Jan-Feb 1984, p 39-43 Previously parameters by the stability requirement are more ngorous than cited in issue 12, p 1790, Accession no A84-29471 refs constraints on tether strength B J A85-18337*# Jet Propulsion Lab, California Inst of Tech, A85-15745 Pasadena RECURSIVE LANGRANGIAN DYNAMICS OF FLEXIBLE HIGH PRECISION ACTIVE NUTATION CONTROL OF A MANIPULATOR ARMS MOMENTUM BIASED SPACECRAFT WITH FLEXIBLE W J BOOK (Georgia Institute of Technology, Atlanta, GA) APPENDAGES International Journal of Robotics Research (ISSN 0278-3649), vol R A LASKIN and E H KOPF (California Institute of Technology, 3, Fall 1984, p 87-101 Research supported by Carnegie-Mellon Jet Propulsion Laboratory, Pasadena, CA) Journal of Guidance, University and Georgia Institute of technology refs Control, and Dynamics (ISSN 0731-5090), vol 8, Jan-Feb 1984, Nonlinear equations of motion are developed for flexible p 78-85 NASA-supported research Previously cited in issue 13, manipulator arms consisting of rotary joints that connect pairs of p 1844, Accession no A84-30541 refs flexible links Kinematics of both the rotary-pint motion and the link deformation are described by 4 x 4 transformation matrices A85-18672 The link deflection is assumed small so that the link transformation CLOSED FORM OPTIMAL CONTROL SOLUTIONS FOR can be composed of summations of assumed link shapes The CONTINUOUS LINEAR ELASTIC SYSTEMS resulting equations are presented as scalar and 4x4 matrix S B SKAAR (Iowa State University of Science and Technology, operations ready for programming The efficiency of this formulation Ames, IA) Journal of the Astronautical Sciences (ISSN is compared to ngid-link cases reported in the literature Author 0021-9142), vol 32, Oct-Dec 1984, p 447-461 refs A new approach to the optimal control of continuous linear A85-15992 elastic systems is presented Unlike discretization schemes such APPLICATION OF DAMPING TO SPACECRAFT STRUCTURES as the method of assumed modes, the control solutions are exact C V STAHLE and J A STALEY (GE Valley Forge Space Center, and have the form of a convergent series of time-varying terms Philadelphia, PA) IN Technology vectors, Proceedings of the The method makes use of a convolution integral descnption of Twenty-ninth National SAMPE Symposium and Exhibition, Reno, the response of points within a flexible system to an arbitrary NV, April 3-5, 1984 Covma, CA, Society for the Advancement of force or torque input Two example performance indices are Material and Process Engineering, 1984, p 185-194 refs considered the integral over time of the control squared, and the This paper presents a discussion of the need for and benefits integral over time of the time derivative of the control squared from applying damping treatments to satellite equipment panels Interesting properties of trajectories which result from the to reduce failures due to component vibration dunng launch anad minimization of these quantities ae discussed and illustrated using ground testing Discussions on the use of viscoelastic damping a simple elastic system configuration Author materials for control of spacecraft vibration and the benefits of the resulting improvements in reliability are presented Use of the A85-18692*# Massachusetts Inst of Tech , Cambridge OCTAVE code to estimate cost savings and improved reliability EXPERIMENTAL MEASUREMENTS OF MATERIAL DAMPING IN by using viscoelastic damping in equipment support structures is FREE FALL WITH TUNABLE EXCITATION described Use of finite element/modal strain energy and simpler E F CRAWLEY and D G MOHR (MIT, Cambndge, MA) AIAA methods of analysis to develop designs for damping treatments Journal (ISSN 0001-1452), vol 23, Jan 1985, p 125-131 Research are discussed Results of the paper show that significant supported by the Aerospace Corp Previously cited in issue 14, p improvements in satellite cost and reliability can be achieved by 1985, Accession no A83-32796 refs design of damping treatments using currently available matenals (Contract NAGW-21) and analytical tools Author A85-19462# A85-17054 EQUATIONS OF MOTION GOVERNING THE DEPLOYMENT OF THE DEVELOPMENT OF A FREQUENCY METHOD FOR THE A FLEXIBLE LINKAGE FROM A SPACECRAFT MATHEMATICAL MODELING OF THE MOTION OF AN ELASTIC T R KANE (Stanford University, Stanford, CA) and S DJERASSI SPACE VEHICLE [RAZVITIE CHASTOTNOGO METODA American Institute of Aeronautics and Astronautics, Aerospace POSTROENIIA MATEMATICHESKOI MODEL! DVIZHENIIA Sciences Meeting, 23rd, Reno, NV, Jan 14-17, 1985 6 p refs UPRUGOGO KOSMICHESKOGO APPARATA] (AIAA PAPER 85-0023) IU A BOGOMOLOV Aviatsionnaia Tekhmka (ISSN 0579-2975), The equations of motion for the deployment of a flexible linkage no 2, 1984, p 16-21 In Russian from a spacecraft are derived analytically using two theorems In accordance with a current physical model, a space vehicle associated with the dynamical equations of Kane et al (1983) is treated as a combination of ngid bodies and elastic beams Generalized speeds are introduced for each body of a genenc

20 05 STRUCTURAL DYNAMICS AND CONTROL

n-body system, and the resulting expressions (the sums of A85-19S95# generalized active and mertial forces for each generalized speed) EFFICIENT INCLINATION CONTROL FOR GEOSTATIONARY are combined with constraint equations A typical SATELLITES linkage-deployment problem is constructed and analyzed, and the D D SLAVINSKAS, W. J. BENDEN (AT&T Bell Laboratones, results of a numerical simulation are presented graphically T K Murray Hill, NJ), and G K JOHNSON Amencan Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting, 23rd, Reno, NV, Jan 14-17, 1985 11 p refs (AIAA PAPER 85-0216) A85-19468*# National Aeronautics and Space Administration Theory and in-orbit experience are presented for an efficient Marshall Space Flight Center, Huntsville, Ala. method of inclination control for geostationary satellites Solar AUTONOMOUS MOMENTUM MANAGEMENT FOR THE COG perturbations with a period of six months can cause a PLANAR SPACE STATION station-keeping fuel consumption overhead which vanes between M. HOPKINS (NASA, Marshall Space Flight Center, Huntsville, 2 3 and 4 0 percent The proposed method controls a component AL) and E HAHN (Bendix Corp, Guidance Systems Div, Teterboro, of these perturbations while completely avoiding the fuel penalty NJ) American Institute of Aeronautics and Astronautics, Aerospace This is equivalent to a service life extension of three to four months Sciences Meeting, 23rd, Reno, NV, Jan 14-17, 1985 11 p refs for a typical 10-year satellite Author (Contract NAS8-35349) (AIAA PAPER 85-0031) A85-19693# This paper discusses momentum management for the COG ANALYTICAL AND EXPERIMENTAL RESEARCH IN LARGE Planar Space Platform The external torques on the Space Station SPACE STRUCTURES CONTROL are assumed to be gravity gradient and aerodynamic with both J -N AUBRUN (Lockheed Research Laboratones, Palo Alto, CA) having bias and cyclic terms The integrals of the cyclic torques Amencan Institute of Aeronautics and Astronautics, Aerospace are the cyclic momenta which will be stored in the momentum Sciences Meeting, 23rd, Reno, NV, Jan 14-17, 1985 16 p refs storage actuator Vanous techniques to counteract the bias torques (AIAA PAPER 85-0356) and center the cyclic momentum were investigated including gravity In the late 1970's, spacecraft concepts with unfavorable gradient desaturabon by adjusting vehicle attitude, aerodynamic dynamics were evolved One problem of immediate concern was desaturation using solar panels and radiators and the deployment related to the interaction between the attitude control system and of flat plates at the end of long booms generating aerodynamic spacecraft structural modes In the new generation spacecraft, torques Author the separation of the controller bandwidth from the structural vibration spectrum could no longer be maintained Research was conducted with the objective to overcome the arising problems An outline is presented of the new methodology developed, taking A85-19528*# National Aeronautics and Space Administration into account the mam approaches to actively control vibrations Marshall Space Flight Center, Huntsville, Ala and handle flexible dynamics in general Attention is given to an NASA/MSFC GROUND EXPERIMENT FOR LARGE SPACE optimal control approach, the integrated High Authonty Control STRUCTURE CONTROL VERIFICATION (HAC)/Low Authonty Control (LAC) approach, a model control H B WAITES (NASA, Marshall Space Flight Center, Huntsville, problem, early experimental demonstrations, and control AL), S M SELTZER, and D K TOLLISON (Control Dynamics experiments G R Co , Huntsville, AL) American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting, 23rd, Reno, NV, Jan A85-22584 14-17, 1985 13 p refs ACTIVE VIBRATION CONTROL FOR LASERS AND (AIAA PAPER 85-0115) SPACECRAFT NASA Marshall Space Flight Center has developed a facility in J PEARSON (USAF, Wright Aeronautical Laboratones, which closed loop control of Large Space Structures (LSS) can Wright-Patterson AFB, OH) IN Deployable optical systems, be demonstrated and venfied The main objective of the facility is Proceedings of the Meeting, Los Angeles, CA, January 18, 19, to verify LSS control system techniques so that on-orbit 1983 Bellmgham, WA, SPIE - The International Society for Optical performance can be ensured The facility consists of an LSS test Engineering, 1983, p 66-74 article which is connected to a payload mounting system that Problems in the active vibration control of structural modes in provides control torque commands It is attached to a base extremely flexible space structures and in precisely pointed optics excitation system which will simulate disturbances most likely to are identified and addressed by the U S Air Force's Vibration occur for Orbiter and DOD payloads A control computer will contain Control of Space Structures program, which has assumed the calibration software, the reference system, the alignment responsibility for sensor/actuator/structure dynamic interaction procedures, the telemetry software, and the control algorithms problems Within the program, benchless laser tests and an The total system will be suspended in such a fashion that LSS airborne laser mirror control development effort are aimed at the test article has the charactenstics common to all LSS Author active control of high energy laser mirrors System identification and testing matters are the responsibility of the Experimental Modal Analysis and Component Synthesis program and the Large Space Structure Dynamics program On-orbit dynamics testing aboard the A85-19529# NASA Space Shuttle is under consideration O C ON DYNAMICAL FORMULATIONS OF A TETHERED SATELLITE SYSTEM WITH MASS TRANSPORT AS5-22585 F C LIU (Alabama, University, Huntsville, AL) American Institute STRUCTURAL CONTROL RESEARCH AT AFOSR of Aeronautics and Astronautics, Aerospace Sciences Meeting, A K AMOS (USAF, Office of Scientific Research, Boiling AFB, 23rd, Reno. NV, Jan. 14-17, 1985 8 p refs DC) IN Deployable optical systems. Proceedings of the Meeting, (AIAA PAPER 85-0117) Los Angeles, CA, January 18, 19, 1983 Bellmgham, WA, SPIE - Two satellites connected by a long flexible tether along the The International Society for Optical Engineering, 1983, p 75-80. earth radial direction comprise a stable equilibrium state This paper refs deals with formulations of in-plane motion of the tether connected Attention is given to the U S Air Force Office of Scientific satellites with a third mass transporting from one satellite to the Research Matenals and Structures plan, which addresses other Systems of equations of motion formulated by two methods, spacecraft structural mechanics issues generally and those involved Lagrange equations and D'Alembert's Principle, are presented and in large optical arrays specifically. The program encompasses methods for numerical solutions are proposed Initial conditions structural charactenzation, control of dynamic response, and for inward and outward transfers are derived Author system optimization and validation Structural dynamics

21 05 STRUCTURAL DYNAMICS AND CONTROL characterization methods uniquely suited to large flexible spacecraft A85-26350# are actively sought in the program, as are active control methods TORSIONAL VIBRATION OF BOOMS WITH OPEN CROSS intimately linked with the vibrational modes of a structure, and SECTION CAUSED BY UNIDIRECTIONAL RADIANT HEATING combined analytical simulation/experimental data-input methods M MUROZONO and S SUMI Kyushu University, Technology of validation O C Reports (ISSN 0023-2718), vol 57, Oct 1984, p 681-688 In Japanese, with abstract in English refs Long extendibfe satellite appendage (boom) subjected to solar radiant heating is modeled as a thin-walled long cylinder of split A85-22586* National Aeronautics and Space Administration, non-overlapping section Tip mass is attached to one end which Washington, D C is free to warp and other is fixed The unidirectional solar radiation ACTIVE CONTROL TECHNOLOGY DEVELOPMENT AT NASA is assumed to be normal to the boom's longitudinal axis The J B DAHLGREN (NASA, Office of Aeronautics and Space equation of thermally-induced torsional vibration of this system is Technology, Washington, DC) IN Deployable optical systems, formulated by considering the coupling effect of mechanical and Proceedings of the Meeting, Los Angeles, CA, January 18, 19, thermal phenomena as one-degree-of-freedom system because it 1983 Bellmgham, WA, SPIE - The International Society for Optical yet demonstrates the basic behavior The charactenstic equation Engineenng, 1983, p 81-87 is evaluated using the Routh-Hurwitz stability criterion and it is It is noted that the large space systems deployable by means found that the stability charactenstics are dependent upon, along of the Space Shuttle will have increased flexibility, and therefore with three system parameters, the direction of the radiant heating unprecedented interaction between control and other subsystems The boundary curves, which divide the parameter plane into regions Open loop performance in such systems would be grossly of stability and instability according to a direction of radiation, and inadequate, prompting active control method development to some typical responses based on the closed-form solution are achieve the required performance levels The structures in question also included Author encompass those of projected science and communications platforms, interplanetary space transportation systems, and manned permanent space stations O C

A85-22587* National Aeronautics and Space Administration A85-26433# Langley Research Center, Hampton, Va POLES AND TRANSMISSION ZEROS OF FLEXIBLE STRUCTURAL CONTROL RESEARCH AND EXPERIMENTS AT SPACECRAFT CONTROL SYSTEMS NASA/LARC T KIDA, Y OHKAMI (National Aerospace Laboratory, Tokyo, R C MONTGOMERY (NASA, Langley Research Center, Hampton, Japan), and S SAMBONGI (National Space Development Agency VA) IN Deployable optical systems, Proceedings of the Meeting, of Japan, Tokyo, Japan) Journal of Guidance, Control, and Los Angeles, CA, January 18, 19, 1983 Bellmgham, WA, SPIE - Dynamics (ISSN 0731-5090), vol 8, Mar-Apr 1985, p 208-213 The International Society for Optical Engineering, 1983, p 88-97 refs refs A method is presented for numerically determining multivanable Research progress in the area of structural dynamics and control poles and zeros of nonspmnmg flexible space structures consisting using the flexible beam facility at the NASA Langley Research of one ngid part and elastic appendages Among many definitions Center is reviewed Particular attention is placed on the progress of system zeros, transmission zeros are investigated relating the in adaptive control and reliability improvements using advanced force/torque input applied at an arbitrary point and the control concepts Both theoretical and experimental results are translational/angular displacement output at another point given to indicate the nature of the work being undertaken In the Computation algorithms are obtained for the cases when the modal adaptive control area, emphasis is placed on parameter and system data are given in terms of constrained modes and unconstrained identification and in companson of competing on-line algonthms modes Investigations on duality and equivalency of these two Also, results are presented for on-line modal control laws that are approaches are made, and the relations of the numerical structures interfaced to a parameter identification scheme This provides an of the algorithms to controllability and observability conditions are on-line distributed adaptive control system In the reliability area, also clarified The proposed algorithms are demonstrated for a a design process is outlined that incorporates reliability over the simple numencal model Author design mission life Author

A85-24949 DYNAMIC CHARACTERISTICS OF A SPACE REFLECTOR SUPPORT STRUCTURE C A MAZZOLA, R J RECK (McDonnell Douglas Astronautics A85-26434# Co, Huntmgton Beach, CA), and R SHEPHERD (California, FLEXURAL VIBRATION OF GRAVITY-STABILIZED, University, Irvine, CA) IN International Conference on Space STRUCTURALLY DAMPED, LARGE FLEXIBLE SATELLITES Structures, 3rd, University of Surrey, Guildford, Surrey, England, S K SHRIVASTAVA and P K MAHARANA (Indian Institute of September 4-14, 1984, Proceedings London and New York, Science, Bangalore, India) Journal of Guidance, Control, and Elsevier Applied Science Publishers, 1984, p 522-527 Research Dynamics (ISSN 0731-5090), vol 8, Mar.-Apr 1985, p 214-222 supported by the McDonnell Douglas Astronautics Co refs refs The need to provide large reflector structures suitable for use The stability and response of the in-plane flexural motion of in a vanety of space missions prompted the investigation of a gravity-stabilized, structurally damped, large flexible satellites in representative three-dimensional space truss The finite element circular and eccentnc orbits are analyzed Employing the method model used idealizes the truss members as uniaxial rod elements of strained parameters, the stability analysis shows that the critical with pinned end connections In this paper compansons of natural damping is sensitive to the satellite inertia ratio It is noted that frequencies and mode shapes for vanous geometrical the orbital eccentricity excites motion in several high and low configurations and material properties are made The accuracy of frequencies and generally descreases the stability of the system the model idealization is verified by companng results for a uniformly An analytical expression for flexural response is obtained using loaded beam situation It is concluded that the technique proposed the multiple-scales techniques Finally, stability charts and response is viable in the design of large reflector space structures Author are presented for a range of the system parameters Author

22 05 STRUCTURAL DYNAMICS AND CONTROL

A85-26435*# National Aeronautics and Space Administration oscillations and rotations of the orbital system about the longitudinal Langley Research Center, Hampton, Va. axis, approximately directed along the local vertical The motions ADAPTIVE MODAL CONTROL OF STRUCTURAL DYNAMIC belonging to these integral surfaces can be considered as nominal SYSTEMS USING RECURSIVE LATTICE FILTERS unperturbed motions of the system in the regime of gravity gradient N SUNDARARAJAN, J P WILLIAMS, and R C MONTGOMERY stabilization (GGS) It is shown that these surfaces can be unstable (NASA, Langley Research Center, Flight Dynamics and Control due to the effect of the nonpotential component of the aerodynamic Div , Hampton, VA) (Guidance and Control Conference, Gatlmburg, moment. Under an appropnate selection of initial conditions of TN, August 15-17,1983, Collection of Technical Papers, p 599-605) motion, this instability is slight and does not disrupt the GGS, at Journal of Guidance, Control, and Dynamics (ISSN 0731-5090), least over several weeks B J vol. 8, Mar -Apr 1985, p 223-229 Previously cited in issue 19, p 2892, Accession no A83-41721 refs A85-28903 A85-26606 THE DYNAMICS OF THE ATTITUDE CONTROL AND SPECTRAL CHARACTERISTICS OF RADAR ECHOES FROM STABILIZATION SYSTEMS OF SPACECRAFT WITH A AIRCRAFT-DISPENSED CHAFF CONTROLLED GRAVITY GRADIENT STABILIZER [DINAMIKA W J ESTES, R H FLAKE (Texas. University, Austin, TX), and C SISTEM ORIENTATSII I STABILIZATSII KOSMICHESKIKH C. PINSON (Pmson Associates, Inc, Austin, TX) IEEE APPARATOV S UPPRAVLIAEMYM GRAVITATSIONNYM Transactions on Aerospace and Electronic Systems (ISSN STABILIZATOROM] 0018-9251), vol AES-21, Jan 1985, p 8-20 refs E. M POTAPENKO Akademiia Nauk SSSR, Izvestiia, Mekhanika (Contract DAAD07-82-C-0230) Tverdogo Tela (ISSN 0572-3299), Jan-Feb 1985, p 22-30 In Experimental amplitude and phase measurements of radar Russian refs echoes from chaff both in the wake of the dispersing aircraft The paper is concerned with the dynamics of a spacecraft (new chaff) and after the aircraft has left the area (mature chaff) with a controlled gravity gradient stabilizer in the form of a long are descnbed UHF and X-band coherent radars are used to obtain thin-walled boom having a load at its free end and mounted in a experimental data for both continuously-dispensed chaff and two-degrees-of-freedom controlled suspension at the other end discrete chaff units The mean radial velocity nu-0 and the velocity The use of various auxiliary mechanisms for vibration damping, standard deviation sigma-nu of the chaff cloud are estimated from such as flywheels, gyroscopes, jet engines, and electromagnets, complex-envelope spectral density estimates For mature chaff, is discussed Attention is also given to the effect of the elasticity sigma-nu ranges from 0 3 to 1 2 per ms. For new chaff, both and deflections of the stabilizer boom on the stability of the sigma-nu and nu-0 depend on the position in the wake At 150 m spacecraft motion Expressions are obtained allowing the analysis, behind the aircraft, sigma-nu varies from 2 0 to 2 7 per ms and at synthesis, and comparison of the systems under study V L 450 m, sigma-nu vanes from 0 8 to 15 per ms No apparent correlation between the magnitude of sigma-nu and either radar frequency or chaff type is found An expression is denved which shows the effect of conical scanning on the complex envelope A85-28906 spectral density Author STABILITY OF THE ROTATION OF A BODY SUSPENDED BY MEANS OF A SYSTEM OF RODS CONNECTED IN SERIES [OB A85-27238 USTOICHIVOSTI VRASHCHENIIA TELA, PODVESHENNOGO LOG BALANCING AND REDUCED LOG COMPENSATION OF POSREDSTVOM SISTEMY POSLEDOVATEL'NO SYMMETRIC PASSIVE SYSTEMS SOEDINENNYKH STERZHNEI] PH OPDENACKER and E. A JONCKHEERE (Southern California, V A STOROZHENKO Akademiia Nauk SSSR, Izvestiia, University, Los Angeles, CA) International Journal of Control Mekhanika Tverdogo Tela (ISSN 0572-3299), Jan-Feb. 1985, p (ISSN 0020-7179), vol 41, Jan 1985, p. 73-109 refs 45-52 In Russian refs (Contract NSF ECS-82-12479) In some of the studies dealing with the stability of the rotational In this paper, a technique for balancing a system in a closed-loop motions of rigid bodies suspended on a stnng, the string is assumed fashion is developed This technique is referred to as 'LOG to have no mass and offer no resistance to torsion In actual balancing', for it assumes that the system to be balanced is closed design, however, in systems using a stnng suspension, the string up with a standard LOG feedback loop This paper focuses on usually transmits rotational motion from an engine to a body For LOG balancing of symmetric passive systems, such systems are bodies of considerable size, the string has a sufficiently large used to model large vibrating structures with collocated rate sensors mass, which should be allowed for in the analysis of the body and actuators A balancing characterization of reciprocity, passivity motion, particularly in the case of high angular velocities A possible and losslessness is provided A new method for reducing both implementation of a ponderable nontwisting string is examined the plant and the LOG compensator is developed It is shown, V.L using a hyperstability argument, that the loop made up with the full plant and any reduced LOG compensator is stable and has acceptable feedback properties Author A85-29144# DISPLACEMENT CONTROL OF FLEXIBLE STRUCTURES USING A85-28488 ELECTROHYDRAULIC SERVO-ACTUATORS EFFECT OF AERODYNAMIC MOMENT ON THE REGIME OF N H MCCLAMROCH (Michigan, University, Ann Arbor, Ml) ASME, THE GRAVITY GRADIENT STABILIZATION OF THE SALYUT-6 Transactions, Journal of Dynamic Systems, Measurement, and SOYUZ ORBITAL SYSTEM [VLIIANIE Control (ISSN 0022-0434), vol 107, March 1985, p 34-39 refs AERODINAMICHESKOGO MOMENTA NA REZHIM (Contract NSF CEE-82-07375, F49620-82-C-0089) GRAVITATSIONNOI ORIENTATSII ORBITAL'NOGO A general mathematical approach, involving linear feedback of KOMPLEKSA 'SALIUT-6' - 'SOIUZ'] the measured structural displacements and of the actuator control V A. SARYCHEVandV V SAZOROV Kosmicheskie Issledovamia forces, to the displacement or position control of a nonlinear flexible (ISSN 0023-4206), vol 23, Jan-Feb 1985, p 63-83 In Russian structure, using electrohydraulic servo actuators, is developed refs Closed-loop stability is mathematically descnbed, taking account The equations of the rotational motion of the Salyut-6 - Soyuz of the special case when the feedback is decentralized It is shown system under the effect of gravitational and restoring aerodynamic that the use of decentralized force (or pressure) and displacement moments admit a natural inclusion of a small parameter the ratio feedback can stabilize any structure with incremental positive of longitudinal to transverse moments of inertia The stiffness if the feedback gains are chosen to satisfy certain simple Krylov-Bogoliubov method is used to construct the formal inequalities Attention is also given to proper selection of the two-parameter integral surfaces of these equations descnbing the feedforward function to achieve zero steady-state error - L.T

23 05 STRUCTURAL DYNAMICS AND CONTROL

N85-10098*# Bendix Corp, Teterboro, N J Guidance Systems Also, the use of the method and the level of accuracy obtained is Div illustrated in a case study of the Hermes spacecraft The synthesis MODULAR DESIGN ATTITUDE CONTROL SYSTEM Final procedure is demonstrated for a spacecraft configuration consisting Report, 1 Oct. 1983-31 Aug 1984 of a central rigid body, solar array substructures, a momentum F D CHICHESTER 5 Oct 1984 79 p refs wheel and a liquid mercury damping device The synthesized (Contract NAS8-33979) spacecraft modal data is obtained by eigenproblem analysis of a (NASA-CR-171182, NAS 1 26 171182) Avail NTIS HC A05/MF system model that is constructed from submodels of the A01 CSCL 22B components The system modes are the natural (unconstrained) A sequence of single axismodels and a series of reduced state modes with damping and gyroscopic stiffness accounted for linear observers of minimum order are used to reconstruct Numerical experiments show that the procedure is not sensitive inaccessible variables pertaining to the modular attitude control of to errors in or to omission of damping factors of the higher order a rigid body flexible suspension model of a flexible spacecraft substructure modes Damping factors for the nutational mode are The single axis models consist of two, three, four, and five rigid confirmed by an independent analysis Author bodies, each interconnected by a flexible shaft passing through the mass centers of the bodies Modal damping is added to each N85-12586*# National Aeronautics and Space Administration model Reduced state linear observers are developed for Goddard Space Flight Center, Greenbelt, Md synthesizing the inaccessible modal state variables for each modal A USER'S GUIDE TO THE FLEXIBLE SPACECRAFT DYNAMICS model MAC AND CONTROL PROGRAM J V FEDOR Jul 1984 151 p refs N85-11381*# National Aeronautics and Space Administration, (NASA-TM-87389, X-712-84-8, NAS 1 1587389) Avail NTIS Washington, D C HC A08/MF A01 CSCL 09B MEASUREMENT OF THE INERTIAL CONSTANTS OF A RIGID A guide to the use of the Flexible Spacecraft Dynamics Program OR FLEXIBLE STRUCTURE OF ARBITRARY SHARE THROUGH (FSD) is presented covering input requirements, control words, A VIBRATION TEST orbit generation, spacecraft description and simulation options, and D ENGRAND and J CORTIAL Aug 1983 23 p refs Transl output definition The program can be used in dynamics and control into ENGLISH from La Rech Aerospatiale (France), no 4, Jul - analysis as well as in orbit support of deployment and control of Aug 1970 p 213-219 Original language doc previously announced spacecraft The program is applicable to inertially oriented spinning, in IAA as A70-41408 Transl by Kanner (Leo) Associates, Earth oriented or gravity gradient stabilized spacecraft Internal Redwood City, Calif and external environmental effects can be simulated M G (Contract NASW-3199) (NASA-TM-77557, NAS 1 1577557) Avail NTIS HC A02/MF N85-12931*# Allied Bendix Aerospace, Teterboro, N J Guidance A01 CSCL 20K Systems Div The inertia! constants of an aircraft rocket, or of any other AUTONOMOUS MOMENTUM MANAGEMENT FOR SPACE structure, are defined without materializing any rotating axis The STATION Final Report, 1 Oct. 1983 - 31 Aug. 1984 necessary equipment is very similar to that used normally for ground E HAHN 15 Oct 1984 70 p refs vibration tests An elastic suspension is used to obtain the total (Contract NAS8-35349) natural modes corresponding to the motions of the structure as a (NASA-CR-174065, NAS 1 26 174065) Avail NTIS HC A04/MF solid From the measurements of the generalized masses of these A01 CSCL 22B modes it is possible to compute the inertia! constants (1) center Momentum management for the CDG planar space platform is of inertia, (2) tensor of inertia, and (3) mass When the structure discussed It is assumed that the external torques on the space is not strictly ngid a purification process, based on the mean station are gravity gradient and aerodynamic, both have bias and square method makes it possible to rigidity it at the pnce of some cyclic terms The integrals of the cyclic torques are the cyclic approximations and a few more measurements Eventual additional momenti which will be stored in the momentum storage actuator masses, that are not parts of the structure, can be taken into Techniques to counteract the bias torques and center the cyclic account MAC momentum and gravity gradient desaturation by adjusting vehicle attitude, aerodynamic desaturation using solar panels and radiators N85-11382# State Univ of New York, Buffalo Buffalo Amherst and the deployment of flat plates at the end of long booms Dept of Mechanical and Aerospace Engineering generating aerodynamic torques are investigated E A K QUALITATIVE RESULTS FOR DISTRIBUTED SYSTEMS WITH DISCRETE DAMPING AND STIFFNESS WITH APPLICATION TO N85-13837 Stanford Univ, Calif CONTROL Interim Report, 1 Jul. 1983 - 30 Jun. 1984 EXPERIMENTS IN CONTROL OF FLEXIBLE STRUCTURES D J INMAN 20 Jul 1984 9p WITH UNCERTAIN PARAMETERS Ph.D. Thesis (Contract AF-AFOSR-0242-82) D ROSENTHAL 1984 180p (AD-A145525, AFOSR-84-0724TR) Avail NTIS HC A02/MF Avail Univ Microfilms Order No DA8420612 A01 CSCL 20K Control requirements for large flexible space structures are Distributed parameter models of large flexible space structures difficult to meet in the presence of model uncertainty The control subject to various control techniques have been studied The main system is particularly sensitive to spacecraft properties when the thrust has been to develop qualitative results which are independent sensor and actuator used for control are separated by structural of truncation or discretization approaches by treating the fully flexibility, i e, they are noncolocated A laboratory structure was distributed model Emphasis has been on controlling the transient built which incorporates several aspects of the problem posed by response of non-conservative linear partial differential equation large space structures (1) the laboratory system has extremely models of such structures subject to a few point actuators low damping ratios in the vibration modes, (2) the system is Author (GRA) equipped with noncolocated sensor and actuator, (3) some of the system parameters can be changed abruptly while the system is N85-12082# Communications Research Centre, Ottawa (Ontario) under closed loop control The laboratory system provides a setting Space Technology and Applications Branch in which suitable control algorithms can be developed and tested, DAMPING SYNTHESIS FOR A SPACECRAFT USING for providing control which is insensitive or robust to plant model SUBSTRUCTURE AND COMPONENT DATA errors Controllers were synthesized using gradient search K W LIPS and F R VIGERON Aug 1984 88 p refs programs Experimental results are presented which indicate the (CRC-1365) Avail NTIS HC A05/MF A01 extent to which nominal performance must be traded off to achieve A method for the synthesis of modal damping factors and robustness These results are also compared to results that can other modal data for a spacecraft in orbit is demonstrated It is be obtained using classical control theory and modern optimal based on input information at the component/substructure level control methods Dissert Abstr

24 05 STRUCTURAL DYNAMICS AND CONTROL

N85-13839*# Control Dynamics Co., Huntsville, Ala N85-13843*# Control Dynamics Co , Huntsville, Ala LEVEL OF EFFORT SPEED TEST RESULTS AND HARDWARE/SOFTWARE STUDY In its Definition of Ground Test for Verification of Large Space OF COMPUTATIONAL SPEED PROBLEM, APPENDIX D Struct Control p 2-13 Nov 1984 refs In its Definition of Ground Test for Venfication of Large Space Avail NTIS HC A08/MF A01 CSCL 22B Struct Control 5 p Nov 1984 The generation of a planar model of the ground test experiment Avail NTIS HC A08/MF A01 CSCL 22B structure is examined. This was done by adapting an in-house The HP9845C is a desktop computer which is tested and modal analysis code (Gimbalflex) to allow placement of sensors evaluated for processing speed A study was made to determine and actuators at certain locations on the structure The next step the availability and approximate cost of computers and/or hardware in the development of this model was to adapt if for use with the accessories necessary to meet the 20 ms sample penod speed control pole placement algorithm The uncontrollable rigid body requirements Additional requirements were that the control mode was removed from the model This uncontrollable mode algorithm could be programmed in a high language and that the was due to the pointing of the gimbal Control system design for machine have sufficient storage to store the data from a complete the planar model was also initiated A digital controller was planned experiment E R utilizing the Control Pole Placement technique The existence of rate of state feedback was assumed Once this controller and other control algonthms were developed, it became necessary to conduct speed tests A study was then made of additional N85-13844*# Control Dynamics Co, Huntsville, Ala hardware/software necessary to meet the speed requirement SECTION 1. METHOD OF DETERMINING MODE SHAPES AND ER. NATURAL FREQUENCIES OF THE NASA UNMODIFIED TEST STRUCTURE. SECTION 2. CONTINUOUS BEAM CLOSED N85-13840*# Control Dynamics Co., Huntsville, Ala FROM SOLUTION TO THE NASA-LSS ASTROMAST ORAL PRESENTATION OF FIRST YEAR FINAL REPORT, TORSIONAL VIBRATION, APPENDIX E APPENDIX A In its Definition of Ground Test for Venfication of Large Space In its Definition of Ground Test for Venfication of of Large Space Struct Control 26 p Nov 1984 Struct Control 28 p Nov 1984 Avail NTIS HC A08/MF A01 CSCL 22B Avail NTIS HC A08/MF A01 CSCL 22B The methods used to determine the lower natural frequencies Plans for self contained in-house capability to test Large Space and their corresponding mode shapes of the NASA-LSS Astromast Structures (LSS) and their control prior to flight are presented A (Unmodified Test Structure), and the mass integrals associated ground test facility which demonstrates and validates LSS control with the mode shapes are illustrated The test structure is modeled theory is defined An experiment is designed which assures a as a cantilever beam with 91 lumped masses and without the tip high success rate for flight test A strapdown algorithm is developed mass on the free end of the bram This uncouples the torsion Research on the astromast is reported, as is the development of and bending modes and allows for them to be determined an overall system model E R separately The frequency range was limited to an upper bound of 100 rad/sec (1592 Hz) In this range from 0-100 rad/sec, N85-13841*# Control Dynamics Co, Huntsville, Ala three bending frequencies and one torsion frequency was found Author SIMPLIFIED PLANAR MODEL OF GROUND TEST VERIFICATION STRUCTURE, APPENDIX B Monthly Progress Report, 1-31 Oct. 1982 In its Definition of Ground Test for Venfication of Large Space Struct Control 2 p Nov 1984 N85-13845*# Control Dynamics Co , Huntsville, Ala. Avail NTIS HC A08/MF A01 CSCL 22B DEFINITION OF GROUND TEST FOR LARGE SPACE The planar version of the structure is shown for which a model STRUCTURE (LSS) CONTROL VERIFICATION, APPENDIX G was developed The model is 12th order including 6 structural In its Definition of Ground Test for Venfication of Large Space modes One mode results from the base translation, one from the Struct Control 44 p Nov 1984 gimbal rotation, three from the flex characteristics of the Astromast Avail NTIS HC A08/MF A01 CSCL 22B Boom and gyro package, and one from the tether and tnpod The A Large Space Structure (LSS) ground test facility was model includes one input, one disturbance and one output which developed to help verify LSS passive and active control theories are a control torque at the gimbal, a translational force at the The facility also perform (1) subsystem and component testing, base, and the rotation rate of the Astromast tip, respectively (2) remote sensing and control, (3) parameter estimation and model Author verification, and (4) evolutionary modeling and control The program is examined as is and looks at the first expenment to be performed N85-13842*# Control Dynamics Co, Huntsville, Ala in the laboratory E R ELIMINATION OF UNCONTROLLABLE RIGID BODY MODE, APPENDIX C In its Definition of Ground Test for Venfication of Large Space Struct Control 6 p Nov 1984 N85-13846'# Control Dynamics Co , Huntsville, Ala Avail' NTIS HC A08/MF A01 CSCL 22B REVIEW OF TECHNICAL PAPERS, APPENDIX H The planar system model is examined which reveals two rigid In its Definition of Ground Test for Venfication of Large Space body modes One is due to the pure translation of the whole Struct Control 10 p Nov 1984 refs experiment assembly and is uncontrollable because the only control Avail NTIS HC A08/MF A01 CSCL 22B input is a torque at the gimbal The other ngid body mode is due Ten (10) papers reviewed deal directly with control systems of to the pointing of the gimbal and is the one for which control is large space structures, such as observer designs or closed loop sort. The problem arises from the Vector V2 which relates the pole placement methods Of the ten papers there are three principle control input to the modal coordinates Since its fifth and sixth concepts treated observers, closed loop pole placement and a elements are both nonzero, neither body mode can be thrown disturbance isolation technique Three of the ten papers were away as is The two ngid body modes must be transformed so selected for critical review as they embodied the three basic that one is unaffected by the control input and one is left concepts The objectives of the review were (1) Check and verify controllable The uncontrollable mode can then be eliminated from the equations and derivations, (2) Relate these new techniques to the model for design purposes A process is described to standards in the literature, (3) Identify strengths and weaknesses accomplish the elimination of the uncontrollable ngid body mode of the methods, and (4) Determine suitable topics for further study ER using these methods Author

25 05 STRUCTURAL DYNAMICS AND CONTROL

N85-13850*# National Aeronautics and Space Administration antennas with diameters of 1 6 and 40m The DCAP results Langley Research Center, Hampton, Va indicate satisfactory performance for the main body and antenna AN ASSESSMENT OF INTEGRATED FLYWHEEL SYSTEM pointing control loop for a small antenna structure with low mass TECHNOLOGY and inertia For large antennas, antenna pointing mechanism C R KECKLER, ed , R T BECHTEL, ed (NASA Marshall Space stepping can make the antenna-satellite system unstable Flight Center), and N J GROOM, ed Washington Nov 1984 Author (ESA) 419 p refs Workshop held in Huntsville, Ala , 7-9 Feb 1984 (NASA-CP-2346, L-15876, NAS 1 552346) Avail NTIS HC A18/MF A01 CSCL 10B The current state of the technology in flywheel storage systems N85-14021# Teldix Luftfahrt-Ausruestungs G m.b H, Heidelberg and ancillary components, the technology in light of future (West Germany) requirements, and technology development needs to rectify these HEMISPHERICAL ANTENNA POINTING MECHANISM shortfalls were identified Technology efforts conducted in Europe W AUER and H SCHULZ In ESA Workshop on Mech Technol and in the United States were reviewed Results of developments for Antennas p 153-157 Sep 1984 in composite material rotors, magnetic suspension systems, Avail NTIS HC A09/MF A01 motor/generators and electronics, and system dynamics and A hemispherical pointing mechanism, including its drive and control were presented The technology issues for the vanous control electronics, was designed for spaceborne payloads of up disciplines and technology enhancement scenanos are discussed to 30 kg, and 1 arcmm pointing accuracy It has 2 axes with a 45 A summary of the workshop, and conclusions and deg (or higher) angle between them for hemispherical coverage recommendations are presented Around the azimuth, a first member, which has a provision to turn a second member around an axis which is 45 deg inclined can W85-13854*# Rockwell International Corp, Downey, Calif be rotated A rotation around the latter axis changes elevation DYNAMICS AND CONTROLS WORKING GROUP SUMMARY and azimuth The same elevation angle can be generated with an R E OGLEVIE In NASA Langley Research Center An equally positive or negative rotational angle from the basic position, Assessment of Integrated Flywheel System Techno! p 39-48 but with associated different azimuth angles This ambiguity can Nov 1984 be easily resolved by allowing only, for instance, positive rotation Avail NTIS HC A18/MF A01 CSCL 10B between 0 and 90 deg Author (ESA) The technology status of the dynamics and controls discipline as it applies to energy storage wheel systems was evaluated No problems were identified for which an adequate solution could not M85-14856 Stanford Univ, Calif. be proposed Design issues that influence control were addressed DISTURBANCE PROPAGATION IN STRUCTURAL NETWORKS; The dynamics and control aspects associated with the energy CONTROL OF LARGE SPACE STRUCTURES Ph.D. Thesis storage system concept and its vanous constituent parts, and the A H VONFLOTOW 1984 160 p control tasks attendant to large, manned spacecraft are Avail Univ Microfilms Order No. DA8420632 discussed E A K It is assumed that large space structures may be modelled as networks of slender structural members interconnecting massive M85-14019# Rome Univ (Italy) Dipt Aerospaziale bodies Several types of members are considered Truss-work ELASTIC DISPERSION EFFECTS ON DYNAMICS AND members may be modelled by equivalent continuum models or by CONTROL OF LARGE MODULAR ANTENNAS more exact methods based upon the transfer matrix of a single F GRAZIANI, S SGUBINI, and A AGNENI In ESA Workshop cell Members which are treated with continuum models may be on Mech Technol for Antennas p 141-146 Sep 1984 refs uniform or have slow spatial variation Bodies are modelled as Avail NTIS HC A09/MF A01 elastic, with a finite number of degrees of freedom The dynamics The dispersion equation and the steady state harmonic of such structures are described in two complementary ways A response of a modular structure were analyzed to study elastic method is developed for deriving exact transcendental transfer effects such as distortion and filtering on large space antennas functions for arbitrary network topology The network may include The relations between the wave numbers and the frequencies any number of members and bodies The method is tested on were examined Due to the strong nonlmeanty of these relations, examples and is found to be computationally stable The dynamics phase velocity strongly depends on frequency, so that each of such structures are also investigated in the time domain via harmonic of a wave packet travels with a different speed the travelling wave mathematics Wave propagation on structural packet shape disperses during the propagation (distortion effect) members is described in terms of wave-mode dispersion The relations can be linearized, yielding a nondispersive behavior, characteristics and impulse responses Dissert Abstr but only for very small wave numbers Being the eigenvalues related to the wave numbers, the natural frequencies (all belonging to the dispersion curves) tend to congregate (clustenng effect) Gaps in the frequency range (stopping bands) for which no frequency N85-15772*# Smithsonian Astrophysical Observatory, Cambridge, corresponds to real wave number, do not allow propagation in Mass these bands (filtering effect) Author (ESA) THE INVESTIGATION OF TETHERED SATELLITE SYSTEM DYNAMICS Quarterly Report, 15 Aug. - 30 Nov. 1984 N85-14020# European Space Agency European Space E LORENZINI Nov 1984 90 p refs Research and Technology Center, ESTEC, Noordwijk (Contract NAS8-36160) (Netherlands) (NASA-CR-171278, NAS 1 26 171278, QPR-1) Avail NTIS HC STUDY OF STRUCTURE CONTROL DYNAMIC INTERACTION A05/MF A01 CSCL 22B FOR RADIO FREQUENCY ANTENNA CONTROL SYSTEMS Tethered satellite system (TSS) dynamics were studied The D MUZI In ESA Workshop on Mech Technol for Antennas p dynamic response of the TSS dunng the entire stationkeepmg 147-152 Sep 1984 refs phase for the first electrodynamic mission was investigated An Avail NTIS HC A09/MF A01 out of plane swing amplitude and the tether's bowing were Dynamic interaction between spacecraft flexible structural observed The dynamics of the slack tether was studied and elements and control systems was investigated for a computer code, SLACK2, was improved both in capabilities and telecommunication satellite configuration Nonlinear time computational speed Speed hazard related to tether breakage or simulations of N/S stationkeepmg maneuvers were performed to plasma contactor failure was examined Preliminary values of the assess the impact of antenna inertia and flexible modes on the potential difference after the failure and of the drop of the electnc mam body attitude control system Simulations were performed field along the tether axis have been computed The update of using the Dynamic and Control Analysis Package (DCAP), for the satellite rotational dynamics model is initiated E.A.K

26 05 STRUCTURAL DYNAMICS AND CONTROL

N85-18078# National Aerospace Lab, Tokyo (Japan) N85-19012*# Martin Manetta Aerospace, Denver, Colo VIBRATION ANALYSIS OF A MULTIPURPOSE PLATFORM OPERATIONAL FITNESS OF BOX TRUSS ANTENNAS IN T HANAWA, Y OHKAMI, E NAKAI, and T TADAKAWA Apr RESPONSE TO DYNAMIC SLEWING Final Report 1984 42 p refs In JAPANESE, ENGLISH summary E E BACHTELL, S S BETTADAPUR, W A SCHARTEL, and L (NAL-TR-803, ISSN-0389-4010) Avail NTIS HC A03/MF A01 A. KARANIAN Jan 1985 100 p Some results are presented of the vibration analysis for (Contract NAS1-17551) simplified models of a multipurpose geostationary platform For (NASA-CR-172470; NAS 1 26 172470; MCR-84-594) Avail the detailed analysis, the finite element method is widely used, NTIS HC A05/MF A01 CSCL 22B but in a preliminary analysis the method descnbed here is also A parametric study was performed to define slewing capability useful since it is computationally tractable and easy to handle of large satellites along with associated system changes or although there are constraints on the configuration complexity. A subsystem weight and complexity impacts The satellite mission model is descnbed for the proposed platform containing configuration and structural arrangement from the Earth six missions of communication and broadcasting Launch Observation Spacecraft (EOS) study was used as the baseline sequences and deployments of the platform, and mass and inertia spacecraft Varying slew rates, settling times, damping, maneuver properties of the constrtutent modules are bnefly explained The frequencies, and attitude hold times provided the data required to analysis procedure is presented together with the simplifing establish applicability to a wide range of potential missions The assumptions and the main results The analysis are performed key elements of the study are (1) determine the dynamic transient not only for the final platform of cross type and T-letter configuration response of the antenna system, (2) calculate the system errors but also for the mtenm stages of construction. The results are produced by the dynamic response, (3) determine if the antenna shown in figures with numencal tables Author has exceeded operational requirements at completion of the slew, and if so, (4) determine when the antenna has settled to the operational requirements The slew event is not considered N85-18360 Virginia Polytechnic Inst and State Univ, complete until the antenna is within operational limits Author Blacksburg IDENTIFICATION OF VIBRATION PARAMETERS OF FLEXIBLE N85-19014*# National Aeronautics and Space Administration STRUCTURES Ph.D. Thesis Marshall Space Flight Center, Huntsville, Ala S RAJARAM 1984 134 p ACTIVE CONTROL OF LARGE SPACE STRUCTURES: AN Avail Univ Microfilms Order No. DA8421888 INTRODUCTION AND OVERVIEW Several identification methods to determine the best estimates G B DOANE, III, D K TOLLISON, and H B WAITES Feb Of higher order strucutral models directly from on-orbit vibration 1985 11 p refs expenments are examined The methods presented are relatively (NASA-TM-86490, NAS 1 15 86490) Avail NTIS HC A02/MF immune to the presence of many low frequency modes with A01 CSCL 22B repeated or closely spaced natural frequencies, damping, and very An overview of the large space structure (LSS) control system high dimensionality. A time domain identification method using design problem is presented The LSS is defined as a class of transient response, a steady state response method, and mass system, and LSS modeling techniques are discussed. Model and stiffness parameters of a vibrating system from measured truncation, control system objectives, current control law design eigenvalues and eigenvectors were studied All the methods are techniques, and particular problem areas are discussed Author demonstrated via example problems Numerical results are presented to study the effects of several implementation issues N85-20368*# National Aeronautics and Space Administration Dissert Abstr Lewis Research Center, Cleveland, Ohio REPORT OF THE CONSTELLATIONS PANEL D J BENTS, G VONTIESENHAUSEN (NASA Marshall Space N85-18378*# National Aeronautics and Space Administration Flight Center), C A LUNDQUIST (Alabama Univ, Huntsville), P Marshall Space Flight Center, Huntsville, Ala SWAN (California Univ, Los Angeles), H L MAYER (Aerospace KEYNOTE ADDRESS Corp), M J MANGANO (JPL, California Inst of Tech , Pasadean), R S RYAN In Shock and Vibration Information Center The S BERGAMASUI (Padua Univ), F BEVILACQUA (Aentaha), F Shock and Vibration Bull 54, R 1 p 3-21 Jun 1984 refs WILLIAMS (Martin Manetta, New Orleans), G RUM (CNR, Italy) Avail SVIC. Code 5804, Naval Research Lab, Washington, D C et al In NASA Marshall Space Flight Center Appl of Tethers 20375 CSCL 20K in Space, Vol 2 16 p Mar 1985 Shock and vibration research relative to manned spacecraft is Avail NTIS HC A14/MF A01 CSCL 131 surveyed Past, present, and future research projects are discussed The purpose of a constellation is to provide a mode of Dynamic response, structural modeling, rotor dynamics, reliability, distributing space systems in a method that could be advantageous large space sttructures, and testing are among the topics and not eliminating the consolidation/aggregation advantages The discussed R J F applicability of stabilization concepts to vanous orbital conditions was defined B G

N85-18998*# National Aeronautics and Space Administration N85-20373*# National Aeronautics and Space Administration Marshall Space Flight Center, Huntsville, Ala Goddard Space Flight Center, Greenbelt, Md NASA-VCOSS DYNAMIC TEST FACILITY APPLICATION NUMBER 3: USING TETHERS FOR ATTITUDE H B WAITES, S M SELTZER (Control Dynamics Co), and G CONTROL B DOANE, III Feb 1985 21 p refs R M MULLER In NASA Marshall Space Flight Center Appl (NASA-TM-86491; NAS 1 1586491) Avail NTIS HC A02/MF of Tethers in Space, Vol 2 10 p Mar 1985 A01 CSCL 148 Avail NTIS HC A14/MF A01 CSCL 131 The Large Space Structure Ground Test Facility under Past application of the gravity gradient concept to satellite development at the NASA Marshall Space Flight Center in attitude control produced attitude stabilities of from 1 to 10 degrees Huntsville, Alabama is descnbed The Ground Test Facility was The satellite members were ngigly interconnected and any motion established initially to test experimentally the control system to be in one part of the satellite would cause motion in all members used on the Solar Array flight Expenment. The structural dynamics This experience has restricted gravity gradient stabilization to of the selected test article were investigated, including the fidelity applications that need attitude stability no better than 1 degree A of the associated mathematical model The facility must permit gravity gradient technique that combines the flexible tether with the investigation of structural dynamics phenomena and be able an active control that will allow control stability much better than to evaluate candidate attitude control and vibration suppression 1 degree is proposed This could give gravity gradient stabilization techniques B W much broader application In fact, for a large structure like a space

27 05 STRUCTURAL DYNAMICS AND CONTROL station, it may become the preferred method Two possible ways N85-21248*# National Aeronautics and Space Administration of demonstrating the techniques using the Tethered Satellite Marshall Space Flight Center, Huntsville, Ala System (TSS) tether to control the attitude of the shuttle are NASA/MSFC GROUND EXPERIMENT FOR LARGE SPACE proposed Then a possible space station tether configuration is STRUCTURE CONTROL VERIFICATION shown that could be used to control the initial station It is then H B WAITES, S M SELTZER (Control Dyamics Co), and D K shown how the technique can be extended to the control of space TOLLISON (Control Dynamics Co) Dec 1984 24 p refs stations of virtually any size G L C Previously announced in IAA as A85-19528 (NASA-TM-86496, NAS 1 15 86496) Avail NTIS HC A02/MF A01 CSCL 22B Marshall Space Flight Center has developed a facility in which closed loop control of Large Space Structures (LSS) can be demonstrated and verified The main objective of the facility is to verify LSS control system techniques so that on orbit performance can be ensured The facility consists of an LSS test article which N85-21235# Wnght State Univ, Dayton, Ohio is connected to a payload mounting system that provides control MODAL CONTROL OF STRUCTURAL SYSTEMS Final Report, torque commands It is attached to a base excitation system which Jun. - Sep. 1983 will simulate disturbances most likely to occur for Orbiter and D F MILLER and W R WELLS Wnght-Patterson AFB, Ohio DOD payloads A control computer will contain the calibration AFWAL Nov 1984 32 p software, the reference system, the alignment procedures, the (Contract F33615-83-C-3000) telemetry software, and the control algorithms The total system (AD-A149734, AFWAL-TR-84-3054) Avail NTIS HC A03/MF will be suspended in such a fashion that LSS test article has the A01 CSCL 13M characteristics common to all LSS Author (IAA) There is much interest in the practical control of large space structures such as space transportation systems and large communication satellites The control task is normally thought of in terms of maintaining specified shape configurations, onentation and alignment, vibration suppression and pointing accuracy, etc Because of their inherent flexibility, they are generally analyzed as distributed parameter systems which creates difficulties in the design and analysis of controllers for them Modal control N85-21249*# National Aeronautics and Space Administration techniques have been developed to bypass problems associated Marshall Space Flight Center, Huntsville, Ala with distributed parameter theory Modal control is built upon the DEFINITION OF GROUND TEST FOR LARGE SPACE notion that certain specified system modes can be controlled by STRUCTURE (LSS) CONTROL VERIFICATION appropriate design of the associated closed-loop eigenvalues This H B WAITES, G B DOANE, III (Control Dynaics Co), and D K reduces the number of sensors and actuators needed to effect TOLLISON (Control Dynamics Co) Nov 1984 36 p the control of the structure An undesirable phenomenon, referred (NASA-TM-86495, NAS 1 15 86495) Avail NTIS HC A03/MF to as observation and control spillover, can occur if the number A01 CSCL 22B of sensors and actuators used is small Spillover refers to the An overview for the definition of a ground test for the verification phenomenon in which energy intended to go solely into the of Large Space Structure (LSS) control is given The definition controlled modes leaks into the uncontrolled modes This report contains information on the description of the LSS ground discusses the control of flexible systems described by a generalized verification expenment, the project management scheme, the one-dimensional wave equation which relates the structure design, development, fabrication and checkout of the subsystems, displacement to the force distribution acting on the structure the systems engineering and integration, the hardware subsystems, Optimal control involving the minimization of a quadratic the software, and a summary which includes future LSS ground performance index representing control and modal energy content test plans Upon completion of these items, NASA/Marshall Space is considered Typically this control formulation leads to a state Flight Center will have an LSS ground test facility which will provide feedback algorithm GRA sufficient data on dynamics and control verification of LSS so that LSS flight system operations can be reasonably ensured Author

N85-21247 Communications Research Centre, Ottawa (Ontano) Space Technology and Applications Branch STABILITY ANALYSIS OF FLEXIBLE SPACERAFT WITH PID N85-21253# Control Dynamics Co, Huntsville, Ala CONTROLLER ACOSS 17 (ACTIVE CONTROL OF SPACE STRUCTURES) Final J DELAFONTAINE Nov 1984 59 p refs Technical Report, 1 Feb. 1982 - 31 Jan. 1984 (CRC-1372) Avail Issuing Activity S M SELTZER, H E WORLEY, J R GLAESE, M L BUTLER, A graphical method for the design and analysis of a flexible V L JONES, and D K TOLLISON Gnffiss AFB, N Y RADC spacecraft controller is presented It can handle as many modes Sep 1984 266 p as desired, in constrained or unconstrained form, modal separability (Contract F30602-82-C-0053, ARPA ORDER 3654, AF PROJ is not assumed and the method is exact when the spacecraft 3654) axes are uncoupled The definition of a system function, (AD-A150007, CDC-0330284TR-DA09-AC004, RADC-TR-84-186) independent of the controller parameters, simplifies the Avail NTIS HCA12/MF A01 CSCL 22B determination of the system stability boundanes It also allows the This is the Control Dynamics Company final technical report investigation of the modal separability assumption, resulting in a on extended analysis and evaluation of the Control Techniques of cntenon for its validity Stabilization through structural damping Large Space Structures The research effort was primarily aimed and flexible modes filtering is illustrated using graphs of the system at mathematical model development and control systems analysis function Closed-form approximations are derived in order to and design tool development Additional keywords, Spacecraft, complement the exact, numerical method Extensions to systems Structural mechanics, Expenmental design, Control theory, Stability, with loop delay and nonlinear elements are also included along Damping, Cost analysis, Line of sight, Computations, Flow charting, with applications to the LSAT-1 Roll axis Author Computer aided design GRA

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06 A85-13177# ENGINEERING ASPECT OF THE MICROWAVE IONOSPHERE NONLINEAR INTERACTION EXPERIMENT (MINIX) WITH A ELECTRONICS SOUNDING ROCKET M. NAGATOMO (Tokyo, University, Tokyo, Japan), N KAYA (Kobe Includes techniques for power and data distnbution, antenna RF University, Kobe, Japan), and H MATSUMOTO (Kyoto University, performance analysis, communications systems, and spacecraft Kyoto, Japan) International Astronautical Federation, International charging effects Astronautical Congress, 35th, Lausanne, Switzerland, Oct 7-13, 1984 9 p (IAF PAPER 84-289) A85-13040*# Jet Propulsion Lab, California Inst of Tech , One type of problem arising in connection with an evaluation Pasadena of the feasibility of the Solar Power Satellite (SPS) and the definition NASA'S MOBILE SATELLITE COMMUNICATIONS PROGRAM; of suitable SPS designs is related to environmental issues GROUND AND SPACE SEGMENT TECHNOLOGIES Questions exist, for instance, regarding the interaction between F NADERI, W J WEBER (California Institute of Technology, Jet microwave power and the upper atmosphere The present Propulsion Laboratory, Pasadena, CA), and G. H KNOUSE (NASA, investigation is concerned with the Microwave Ionosphere Washington, DC) International Astronautical Federation, Nonlinear Interaction Experiment (MINIX), which is a space plasma International Astronautical Congress, 35th, Lausanne, Switzerland, expenment originally devoted to the research of space plasma Oct. 7-13, 1984 13 p NASA-supported research refs physics MINIX is eventually to observe possible effects of a strong (IAF PAPER 84-84) microwave field in the tonosphenc environment The scientific This paper describes the Mobile Satellite Communications requirements of the MINIX are discussed, taking into account Program of the United States National Aeronautics and Space functional and experimental conditions Attention is also given to Administration (NASA) The program's objectives are to facilitate rocket characteristics, experimental design, the payload, the inflight the deployment of the first generation commercial mobile satellite expenment configuration, and details concerning the conduction by the private sector, and to technologically enable future of the experiment G R generations by developing advanced and high risk ground and space segment technologies These technologies are aimed at mitigating severe shortages of spectrum, orbital slot, and spacecraft A85-13224# EIRP which are expected to plague the high capacity mobile ATTITUDE CONTROL SYSTEM AND COMMUNICATIONS satellite systems of the future After a bnef introduction of the PAYLOAD FOR AN AMATEUR SOLAR SAIL SPACECRAFT concept of mobile satellite systems and their expected evolution, T WILLIAMS (Kingston Polytechnic, Kingston upon Thames, this paper outlines the cntical ground and space segment England) and P COLLINS (Imperial College of Science and technologies Next, the Mobile Satellite Experiment (MSAT-X) is Technology, London, England) International Astronautical descnbed MSAT-X is the framework through which NASA will Federation, International Astronautical Congress, 35th, Lausanne, develop advanced ground segment technologies An approach is Switzerland, Oct 7-13, 1984 13 p refs outlined for the development of conformal vehicle antennas, (IAF PAPER 84-363) spectrum and power-efficient speech codecs, and modulation This paper describes work performed in continuation of the techniques for use in the non-linear faded channels and efficient British Solar Sail Group project to produce a Phase A Design multiple access schemes Finally, the paper concludes with a Study for an earth-orbiting, solar sail spacecraft which might description of the current and planned NASA activities aimed at realistically be produced by an amateur group It is shown in this developing complex large multibeam spacecraft antennas needed paper that the possible disturbance torques acting on a such a for future generation mobile satellite systems Author spacecraft are different from those expenenced by more conventional vehicles, and that they can greatly outweigh the nominal control torques required for optimal steering Thus, these disturbances must be analyzed carefully as a preliminary to serious control system design This paper carnes out such an analysis giving bounds on each such disturbance The number of different types of solar pressure-based control actuators is then shown to be greater than is generally believed, and a particularly attractive set chosen for this spacecraft Finally, it is shown that it is feasible to provide a reliable radio link from a ground station to the spacecraft at the distance of the moon within the constraints of an amateur project Author

A85-13066# A85-13640# FACTORS AFFECTING PUSH-BROOM PERFORMANCES IN SAMPLED DATA CONTROL OF FLEXIBLE STRUCTURES FUTURE SPACE PLATFORMS USING CONSTANT GAIN VELOCITY FEEDBACK S VETRELLA and A MOCCIA (Napoli, Universita, Naples, Italy) N H MCCLAMROCH (Michigan, University. Ann Arbor, Ml) Journal International Astronautical Federation, International Astronautical of Guidance, Control, and Dynamics (ISSN 0731-5090), vol 7, Congress, 35th, Lausanne, Switzerland, Oct. 7-13, 1984 8 p Nov -Dec. 1984, p 747-750 Research supported by the University Research supported by the Consiglio Nazionale delle Ricerche of Michigan refs and Ministero delta Pubblica Istruzione refs (Contract F49620-82-C-0089) (IAF PAPER 84-116) A sampled data-controlled flexbile structure can be defined as This paper discusses a simulation computer program to evaluate a distnbuted parameter system, in which the structure input is the different aspects of a remote sensing platform, with particular output of an ideal zero order hold and the structure output is reference to a push-broom high resolution system The procedure sampled The present investigation is concerned with the finite takes into account the satellite orbital geometry and attitude, the dimensional model M x(two dots) + Kx=Bu(1)y=C x(dot) sensor geometnc and radiometnc charactenstics, the digital terrain (2) The relations include the structural displacement vector x, the model, the atmosphenc refraction and absorption and the solar force input vector u, and the velocity output vector y The mass illumination Each factor is descnbed with equations and examples matrix M and the structural stiffness matrix K are assumed in order to identify the principal constraints that affect push-broom symmetric and positive definite The input influence matrix B and performances in future high geometnc and radiometnc resolution the output influence matnx C are assumed to be dimensionless systems Author Attention is given to several results which can serve as guidelines

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for choice of feedback gains and sampling time to guarantee that A85-15812* Jet Propulsion Lab , California Inst of Tech , a sampled data-controlled structure is stable G R Pasadena NUCLEAR-ELECTRIC POWER IN SPACE A85-14430 V C. TRUSCELLO and H S DAVIS (California Institute of REPORT OF THE STUDENT WORKING GROUP TO THE PANEL Technology, Jet" Propulsion Laboratory, Pasadena, CA) IEEE ON SATELLITE COMMUNICATIONS Spectrum (ISSN 0018-9235), vol 21, Dec 1984, p 58-65 J HANWECK (Madison High School, Vienna, VA) IN EASCON Prospective missions requinng large power supplies that might '83, Proceedings of the Sixteenth Annual Electronics and be satisfied with space nuclear reactors (SNR) are discussed, Aerospace Conference and Exposition, Washington, DC, along with design concepts and problems and other potential September 19-21, 1983 . New York, Institute of Electrical and high-power space systems Having a minimum economic output Electronics Engineers, 1983, p 27-32 of 10 kWe, SNR seem well-suited as the power sources for DBS Conclusions drawn by a high school panel regarding applications systems, space-based ATC systems manned planetary missions, of space capabilities are reported Weather satellites should be an expanding Space Station, materials processing, and outer equipped with communications systems for automated severe planets missions SNR avoid the large area problems of solar cell weather and natural disaster warning systems An internationally arrays, short lifetimes of thermionic converters, and vibration and onented system of satellites for air and manne navigational data heat control in Stirling engines Design problems exist for SNR in is required, as are DBS television satellites beaming signals to the heat transfer and rejection systems, radioactive emissions and dwellings with low-cost antennas, and military systems employing degradation of reactor matenals, and size The latter is a function all available and some specialized systems Research is required of Shuttle payload constaints and raises the possibility of having to identify practical alternatives to solar cells for powering to load the fuel while in orbit The earliest operational date of spacecraft, frequency use must be made a finer discipline through SNRs is projected for the early 1990s, if progress is good in the digital systems, polarization studies to control atmospheric effects, current SP-100 program MSK and defining the HF range at which lonization would become a hazard The cost of individual earth stations must be reduced, A85-16081 while satellites must be funded by innovative means, e.g, common ANTENNA ENGINEERING HANDBOOK /2ND EDITION/ stock or through quasi-charitable donations Galaxies of R C JOHNSON, ED (Geogia Institute of Technology, Atlanta, intercommunicating satellites in GEO would permit larger scale GA) and H JASIK, ED (Eaton Corp, AIL Div, Deer Park, NY) missions to be flown, and manned space colonies in LEO, GEO New York, McGraw-Hill Book Company, 1984,1356 p No individual and on the moon would support all R and D activities, items are abstracted in this volume industrialization, and exploitation of interplanetary resources Essential principles, methods, and data for solving a wide range MSK of problems in antenna design and application are presented The basic concepts and fundamentals of antennas are reviewed, A85-15760 followed by a discussion of arrays of discrete elements Then all EFFECT OF PHASE FLUCTUATIONS IN AN INCIDENT BEAM primary types of antennas currently in use are considered, providing ON THE CHARACTERISTICS OF A RECTENNA SYSTEM [O concise descnptions of operating principles, design methods, and VLIIANII FLUKTUATSII FAZY V PADAIUSHCHEM LUCHE NA performance data Small antennas, microstnp antennas, KHARAKTERISTIKI REKTENNOI SISTEMY] frequency-scan antennas, conformal and low-profile arrays, G P BOIAKHCHIAN, V A VANKE, and S K LESOTA adaptive antennas, and phased arrays are covered The major Radiotekhnika (ISSN 0033-8486), Sept 1984, p 74-76 In applications of antennas and the design methods peculiar to those Russian refs applications are discussed in detail The employment of antennas The paper presents a theoretical study of the effects of the to meet the requirements of today's complex electronic systems phase fluctuations of a microwave beam over its cross section as is emphasized, including earth station antennas, satellite antennas, it is transmitted on a space-to-ground path on the characteristics seeker antennas, microwave-relay antennas, tracking antennas, of the rectenna system, particularly the efficiency and the width radiometer antennas, and ECM and ESM antennas Finally, of the radiation pattern The phase fluctuations are shown to have significant topics related to antenna engineering, such as a significant effect on the rectenna system when the radius of transmission lines and waveguides, radomes, microwave the spatial correlation of the field over the beam cross section is propagation, and impedance matching and broadbandmg, are less than 25 times the wavelength The results are pertinent to addressed Author the study of microwave power transmission in solar satellite power systems. L M A85-16641 EARTH'S MAGNETIC FIELD PERTURBATIONS AS THE A85-15800* Cleveland State Univ, Ohio POSSIBLE ENVIRONMENTAL IMPACT OF THE NEAR-OPTIMUM DESIGN OF GAAS-BASED CONCENTRATOR CONCEPTUALIZED SOLAR POWER SATELLITE SPACE SOLAR CELLS FOR 80 C OPERATION M C LEE (Regis College, Weston, MA) and S P KUO (New C GORADIA, M GHALLA-GORADIA (Cleveland State University, York, Polytechnic Institute, Farmmgdale, NY) Journal of Cleveland, OH), and H CURTIS (NASA, Lewis Research Center, Geophysical Research (ISSN 0148-0227), vol 89, Dec 1, 1984, Cleveland, OH) Applied Physics Communications (ISSN p 11043-11047 refs 0277-9374), vol 4, no 2-3, 1984, p 97-119 NASA-supported (Contract F19628-83-K-0024, NSF ATM-83-15322, research refs AF-AFOSR-83-0001) Using a detailed computer simulation model and reasonable (AD-A149120, AFGL-TR-84-0334) values of optical, geometncal and matenal parameters from current It is predicted that the earth's magnetic field can be significantly published literature, parameter optimization studies were performed perturbed locally by a microwave beam transmitted from the on two cell geometries, namely, the circular geometry for a conceptualized solar power satellite (SPS) at a frequency of 2 45 Cassegramian concentrator with 100 AMD, 80 C operation and GHz with incident power density of 230 W/per sq m at the center the rectangular geometry for a Venetian blind concentrator with of the beam The simultaneous excitation of earth's magnetic field 20 AMD, 80 C operation For each cell geometry, three cell fluctuations and ionospheric density irregulanties is caused by the configurations were considered p/n AIGaAs/GaAs, n/p thermal filamentation instability of microwaves with scale lengths AIGaAs/GaAs, and, n/p GaAs shallow home-junction The studies greater than a few hundred meters Earth's magnetic field show the possibility of designing GaAs-based space solar cells perturbations with magnitudes (a few tens of gammas) comparable with begmning-of-life efficiencies exceeding 22 percent at 20 to to those in magnetosphenc substorms can be expected Particle 100 AMD, 80 C and probable efficiency degradation of less than precipitation and airglow enhancement are the possible, 15 percent after a 70 percent reduction in diffusion length in each concomitant ionospheric effects associated with the cell region Author microwave-induced geomagnetic field fluctuations The present

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work adds earth's magnetic field perturbations as an additional contemporary energy storage and attitude control systems in many effect to those such as ionospheric density irregularities, plasma applications More recent technology advances in composite rotors, heating, etc, that should be assessed as the possible magnetic bearings, and power control electronics have tnggered environmental impacts of the conceptualized solar power satellite new optimism regarding the feasibility and merits of such a system proram Author The paper presents the results of a recent study whose focus was to define an advanced IPACS and to evaluate its merits for A85-18584* Hughes Aircraft Co., El Segundo, Calif the Space Station application A system and component design ENVIRONMENTALLY-INDUCED VOLTAGE LIMITATIONS IN concept is developed to establish the system performance LARGE SPACE POWER SYSTEMS capability A system level trade study, including life-cycle costing, N J. STEVENS (Hughes Aircraft Co, El Segundo, CA) (IEEE, is performed to define the merits of the system relative to two U S Defense Nuclear Agency, U S Department of Energy, and other candidate systems It is concluded that an advanced IPACS NASA, Annual Conference on Nuclear and Space Radiation Effects, concept is not only feasible, but offers substantial savings in mass, 21st, Colorado Spnngs, CO, July 23-25, 1984) IEEE Transactions and life-cycle cost Author on Nuclear Science (ISSN 0018-9499), vol NS-31, Dec 1984, p 1381-1386 refs A85-19713*# National Aeronautics and Space Administration (Contract NAS3-23869) Lewis Research Center, Cleveland, Ohio Large power systems proposed for future space missions imply THE EFFECT OF PLASMA ON SOLAR CELL ARRAY ARC higher operating voltage requirements which, in turn, will interact CHARACTERISTICS with the space plasma environment The effects of these D B SNYDER (NASA, Lewis Research Center, Cleveland, OH) interactions can only be inferred because of the limited data base and E TYREE (NASA, Lewis Research Center, Case Western of ground simulations, small test samples, and two space flight Reserve University, Cleveland, OH) Amencan Institute of expenments This report evaluates floating potentials for a 100 Aeronautics and Astronautics, Aerospace Sciences Meeting, 23rd, kW power system operating at 300, 500, 750, and 1000 volts in Reno, NV, Jan 14-17, 1985 10 p Previously announced in STAR relation to this data base Of primary concern is the possibility of asN85-11133 refs discharging to space The implications of such discharges were (AIAA PAPER 85-0384) studied at the 500 volt operational setting. It was found that The influence from the ambient plasma on the arc discharging can shut down the power system if the discharge characteristics of a negatively biased solar cell array was current exceeds the array short circuit current Otherwise, a power investigated The arc charactenstics examined were the peak oscillation can result that ranges from 2 to 20 percent, depending current during an arc, the decay time as the arc terminates, and upon the solar array area involved in the discharge Means of the charge lost dunng the arc These arc charactenstics were . reducing the effect are discussed Author examined in a nitrogen plasma with charge densities ranging from 15,000 to 45,000 cu cm Background gas pressures ranged from A8S-18608* National Aeronautics and Space Administration 8x1,000,000 to 6x100,000 torr Over these ranges of parameters Lewis Research Center, Cleveland, Ohio no significant effect on the arc charactenstics were seen Arc CHARACTERISTICS OF ARC CURRENTS ON A NEGATIVELY charactenstics were also examined for three gas species helium, BIASED SOLAR CELL ARRAY IN A PLASMA nitrogen and argon The helium arcs have higher peak currents D B SNYDER (NASA, Lewis Research Center, Cleveland, OH) and shorter decay times than nitrogen and argon arcs There are (IEEE, U S Defense Nuclear Agency, U S Department of Energy, slight differences in the arc charactenstics between nitrogen and and NASA, Annual Conference on Nuclear and Space Radiation argon. These differences may be caused by the differences in Effects. 21st, Colorado Spnngs, CO, July 23-25, 1984) IEEE mass of the respective species Also, evidence is presented for Transactions on Nuclear Science (ISSN 0018-9499), vol NS-31, an electron emission mechanism appearing as a precursor to solar Dec 1984, p 1584-1587 Previously announced in STAR as array arcs Occasionally the plasma generator could be turned N84-27824 refs off, and currents could still be detected in the vacuum system The time dependence of the emitted currents dunng arcing on When these currents are presented, arcs may occur Author solar cell arrays is being studied The arcs are charactenzed using three parameters the voltage change of the array dunng the arc (i e, the charge lost), the peak current dunng the arc, and the A85-21835# time constant descnbmg the arc current This paper reports the PRECISION OF MESH-TYPE REFLECTORS FOR LARGE dependence of these charactenstics on two array parameters, the SPACE-BORNE ANTENNAS interconnect bias voltage and the array capacitance to ground It R X MEYER (Aerospace Corp, El Segundo, CA) (Structures, was found that the voltage change of the array during an arc is Structural Dynamics and Matenals Conference, 23rd, New Orleans, nearly equal to the bias voltage The array capacitance, on the LA, May 10-12, 1982, Collection of Technical Papers Part 1, p other hand, influences both the peak current and the decay tme 60-65) Journal of Spacecraft and Rockets (ISSN 0022-4650), vol constant of the arc Both of these charactenstics increase with 22, Jan -Feb 1985, p 80-84 Previously cited in issue 13, p. 2029, increasing capacitance Author Accession no A82-30083 (Contract F04701-81-C-0082) A85-19695*# Rockwell International Corp , Downey, Calif. INTEGRATED POWER AND ATTITUDE CONTROL SYSTEMS A85-23651* Illinois Univ , Urbana FOR SPACE STATION SATELLITE COMMUNICATION ANTENNA TECHNOLOGY R. E. OGLEVIE (Rockwell International Corp, Space Station R MITTRA, ED (Illinois, University, Urbana, IL), W A IMBRIALE, Systems Drv, Downey, CA) and D. B EISENHAURE (Charles Stark ED (California Institute of Technology, Jet Propulsion Laboratory, Draper Laboratory, Inc, Cambndge, MA) Amencan Institute of Pasadena, CA), and E J MAANDERS, ED (Eindhoven, Techmsche Aeronautics and Astronautics, Aerospace Sciences Meeting, 23rd, Hogeschool, Eindhoven, Netherlands) Amsterdam, North-Holland, Reno, NV, Jan 14-17, 1985 13 p Research sponsored by the 1983, 667 p For individual items see A85-23652 to A85-23663 Rockwell International Corp and Charles Stark Draper Laboratory, A general overview of current technology in the field of Inc refs communication satellite antennas is presented. Among the topics (Contract NAS1-17633) discussed are the design of multiple beam systems, frequency (AIAA PAPER 85-0358) reuse, and polanzation control of antenna measurements Integrated Power and Attitude Control Systems (IPACS) studies Consideration is also given to- contour beam synthesis, dual shaped performed over a decade ago established the feasibility of reflector synthesis, beam shaping, and offset reflector design The simultaneously stonng electrical energy in wheels and utilizing the applications of the above technologies to present and future resulting momentum for spacecraft attitude control. It was shown generations of communications satellites is considered, with that such a system possessed many advantages over other emphasis given to such systems as the Intelsats, the Defense

31 06 ELECTRONICS

Satellite Communications System, (DSCS-III), Satellite Business A85-26685 System (SBS), and Comstar I H A PLAN FOR CONTROLLING ELECTROSTATIC DISCHARGES ON GEOSYNCHRONOUS SPACECRAFT K J DEGRAFFENREID and R C EVANS TRW, Inc , TRW Space and Technology Group, Redondo Beach, CA) IN International Symposium on Electromagnetic Compatibility, 25th, Arlington, VA, A85-23652 August 23-25, 1983, Symposium Record New York, Institute of THE SYSTEMS BACKGROUND FOR SATELLITE Electrical and Electronics Engineers, Inc, 1983, p 362-365 refs COMMUNICATION ANTENNAS Over the past decade, the awareness of electrostatic discharges J C ARNBAK (Eindhoven, Technische Hogeschool, Eindhoven, as a threat to geosynchronous satellite performance has increased Netherlands) IN Satellite communication antenna technology significantly Operational anomalies occurnng on various satellites Amsterdam, North-Holland, 1983, p 1-51 refs have been correlated with the energetic plasma induced The major elements of the operational environment of satellite disturbances of the geomagnetic substorm environment In the communication antennas are reviewed, including perturbations and plasma environment of a geomagnetic substorm, geosynchronous stationkeepmg in the geostationary orbit, antenna tracking on satellite elements may differentially charge and, subsequently, arc earth-satellite links, earth-terminal off-axis limitations, satellite link discharge A suitable electrostatic charge control program is budgets, multiple access and satellite antennas, and the considered along with computerized charging analysis techniques specification of satellite antennas Also given are definitions and Aspects regarding the charge control of conductive surfaces are formulas which are intended to provide general guidance and show discussed, taking into account multilayer blankets, and a graphite major constraints relevant at all stages of antenna engmeenng for fiber reinforced plastic Questions concerning the discharge control satellite systems Two main trends in satellite communication of dielectric surfaces are also explored, giving attention to second antenna technology are noted (1) an increasing impact of general surface mirrors and solar array design G R system requirements on the specific design and operational exploitation of antennas in satellite systems, and (2) more emphasis A85-28126* Hughes Aircraft Co , Los Angeles, Calif on adaptive, flexible, or multipurpose antenna systems B J AN INVESTIGATION DURING THE SYSTEM TEST PHASE OF THE GOES SPACECRAFT L A MALLETTE (Hughes Aircraft Co , Space and Communications Group, Los Angeles, CA) IN SOUTHEASTCON '83, Proceedings A85-25101 of the Region 3 Conference and Exhibit, Orlando, FL, April 11-13, SKY-HOOKS, FISH-WARMERS AND HUB-CAPS - MILESTONES 1983 New York, Institute of Electrical and Electronics Engineers, Inc, 1983, p 638-642 IN SATELLITE COMMUNICATIONS (Contract NAS5-24342) A W RUDGE (ERA Technology, Ltd , Leatherhead, Surrey, England) IEE Proceedings, Part F - Communications, Radar and Spurious RF oscillations were noted during the system test Signal Processing (ISSN 0143-7070), vol 132, pt F, no 1, Feb phase of the Geostationary Operational Environmental Satellite (GOES) A space qualified data collection platform report (DCPR) 1985, p 1-12 refs The present discussion is concerned with the origin of satellite transmitter was subsequently found to have a cracked load resistor in its output isolator The failure mechanism was caused by heat communications, its development and current status, and predictions regarding its future The feasibility of such a from the output power of a 20 watt transmitter being reflected communication system had been foreseen by Clarke (1945), who into the DCPR transmitter through a sneak path The reflection first recognized the peaceful potential of German rocketry, from a high VSWR at the rotary joint was not part of the normal combined with the use of the geostationary orbit, as a basis for a operation but was due to unusual circumstances The reliability of worldwide communication system After the launching of 'Sputnik', the load resistor under normal operation (low VSWR) over the life Clarke's concept of a 'sky-hook' was first implemented in 1964 of the satellite was determined to be high Author with the expenmental satellite Syncom The founding of the International Telecommunications Satellite Organization (Intelsat) N85-11016*# Auburn Umv, Ala Dept of Electrical occurred in the same year Attention is given to the various satellites Engineering of Intelsat with their increasing technological capabilities, the THE COMPUTER-COMMUNICATION LINK FOR THE satellite industry in North America, developments in the USSR, INNOVATIVE USE OF SPACE STATION Abstract Only the situation in the UK and in Western Europe, and advancements C C CARROLL In NASA Marshall Space Flight Center 2nd in spacecraft technology made by Japan, China, and the world at Symp on Space Industrialization p 52 Oct 1984 large Details of spacecraft technology are considered along with Avail NTISHCA19/MF A01 CSCL 17B ground stations G R The potential capability of the computer-communications system link of space station is related to innovative utilization for industrial applications Conceptual computer network architectures are presented and their respective accommodation of innovative industrial projects are discussed To achieve maximum system A85-25359* National Aeronautics and Space Administration availability for industrialization is a possible design goal, which Langley Research Center, Hampton, Va would place the mdustnal community in an interactive mode with WAVELENGTH DIVISION MULTIPLEXING FOR FUTURE SPACE facilities in space A worthy design goal would be to minimize the STATION DATA SYSTEMS computer-communication management function and thereby H D HENDRICKS and N D MURRAY (NASA, Langley Research optimize the system availability for mdustnal users Center, Hampton, VA) IN Fiber optics in local area networks, Quasi-autonomous modes and subnetworks are key design issues, Proceedings of the Meeting, San Diego, CA, August 25, 1983 since they would be the system elements directly effecting the Bellmgham, WA, SPIE - The International Society for Optical system performance for industrial use R S F Engmeenng (SPIE Proceedings Volume 434), 1983, p 41-49 refs N85-11017*# Turner Broadcasting System, Atlanta, Ga A future Space Station will require information network THE REAL WORLD: THE USER architectures and technologies that are evolvable, adaptive, high J KITCHELL In NASA Marshall Space Flight Center 2nd performing, and self-correcting and repairing One of the conceptual Symp on Space Industnalization p 53-59 Oct 1984 network configurations involves fiber optic data buses with Avail NTISHC A19/MFA01 CSCL 17B Wavelength Division Multiplexing (WDM) Discussion of this network Satellite communication is by far the most advanced of all concept, components being developed and results on a commercial applications of space technology The past, present, four-channel WDM star bus will be presented Author and some future possibilities for the field of public communications

32 06 ELECTRONICS are considered Some serious concerns that are becoming apparent N85-13892*# National Aeronautics and Space Administration to the user of this technology are examined. Among the specific Lewis Research Center, Cleveland, Ohio topics mentioned are digital television, electronic mail, cable DYNAMIC POWER SYSTEMS FOR POWER GENERATION television, and systems security R S F R E ENGLISH In its Space Power p 137-149 Apr 1984 refs Avail NTIS HC A14/MF A01 CSCL 10B N85-12299*# Martin Marietta Aerospace, Denver, Colo. The characteristics of dynamic power systems have POWER SUBSYSTEM AUTOMATION STUDY Final Report considerable potential value, especially for the space station The J C TIETZ, D SEWY, C PICKERING, and R. SAUERS Sep base of technology that makes these dynamic power systems 1984 207 p refs practical is reviewed The following types of power-generating (Contract NAS8-34938) systems are examined herein organic Rankme cycle, potassium (NASA-CR-171213, NAS 1 26 171213; MCR-84-596) Avail Rankine cycle, Brayton cycle, and Stirling cycle R S F. NTIS HC A10/MF A01 CSCL 09E The purpose of the phase 2 of the power subsystem automation N85-14006# TICRA ApS, Copenhagen (Denmark) study was to demonstrate the feasibility of using computer software ELECTRICAL CONSEQUENCES OF MECHANICAL ANTENNA to manage an aspect of the electrical power subsystem on a CHARACTERISTICS space station The state of the art in expert systems software K. PONTOPPIDAN In ESA Workshop on Mech Technol for was investigated in this study This effort resulted in the Antennas p 41-47 Sep 1984 refs demonstration of prototype expert system software for managing Avail NTIS HC A09/MF A01 one aspect of a simulated space station power subsystem B W Reflector antenna surface distortion errors that lead to a best fit paraboloid, and additional random and systematic errors were investigated It is demonstrated that the influence of each type of error is very different in magnitude as well as in the spatial N85-12933*# Bendix Corp, Teterboro, N J Guidance Systems distribution It is also shown that not only the peak gain but also Div the sidelobe requirement play a decisive role when the acceptable AUTONOMOUS MOMENTUM MANAGEMENT FOR SPACE surface accuracy is to be established Author (ESA) STATION, EXHIBIT A Final Report, 1 Oct. 1983 - 31 Aug. 1984 E HAHN 15 Oct 1984 70 p refs N85-14008# Dornier-Werke GmbH, Friednchshafen (West (Contract NAS8-35349) Germany) (NASA-CR-171256, NAS 1 26 171256) Avail. NTIS HC A04/MF TECHNOLOGY FOR THE ERS-1 SAR ANTENNA A01 CSCL 22B R WAGNER In ESA Workshop on Mech Technol for Antennas The report discusses momentum management for the COG p 59-66 Sep 1984 refs Planar Space Platform The external torques on the Space Station Avail NTIS HC A09/MF A01 are assumed to be gravity gradient and aerodynamic with both The metallization of CFRP waveguides, the Deployable Truss having bias and cyclic terms The integrals of the cyclic torques Structure (DTS) and verification in terrestrial environment of the are the cyclic momenti which will be stored in the momentum 10 x 1 m SAR antenna of ERS-1 (ESA satellite) are discussed Storage actuator Vanous techniques to counteract the bias torques Waveguide metallization was achieved indirectly with metallization and center the cyclic momentum were investigated including gravity of the mandrel prior to CFRP lay-up, and directly, by electroplating gradient desaturation by adjusting vehicle attitude, aerodynamic of manufactured CFRP components Both techniques proved desaturation using solar panels and radiators and the deployment unsatisfactory, but a surface treatment applied to the metal layer of flat plates at the end of long booms generating aerodynamic in the indirect technique improves adhesion strength by an order torques Author of magnitude, and enables the waveguides to meet requirements The DTS satisfies launch, deployment, and inflight specifications for a 5 panel/2 wing structure Ground tests include analytical N85-13881*# National Aeronautics and Space Administration, simulation of deployment with and without gravity effects, and a Washington, DC gravity compensation technique for tests Author (ESA) SPACE STATION POWER SYSTEM C R BARAONA In NASA Lewis Research Center Space N85-14010# Construcciones Aeronauticas S A, Madnd (Spain) Power p 7-14 Apr 1984 refs Space Div. Avail NTIS HC A14/MF A01 CASA TECHNOLOGICAL EFFORT IN THE FIELD OF The strategies, reasoning, and planning guidelines used in the ANTENNAS development of the United States Space Station Program are M A. LLORCA In ESA Workshop on Mech Technol for Antennas outlined The power required to support Space Station missions p 73-75 Sep 1984 and housekeeping loads is a key dnver in overall Space Station Avail NTIS HC A09/MF A01 design conversely, Space Station requirements dnve the power Shaped reflector and waveguide array antennas for ESA technology Vanous power system technology options are projects were developed The wind scatterometer antenna for discussed The mission analysis studies resulting in the required ERS-1 (ESA satellite) is descnbed This is a three beam concept Space Station capabilities are also discussed An example of Space consisting of a fixed antenna on top of the synthetic aperture Station functions and a concept to provide them is presented radar, and two deployable, but ngid, antennas situated at either The weight, area, payload and altitude requirements on draft and side of the payload Author (ESA) mass requirements are descnbed with a summary and status of key power systems technology requirements and issues R J F N85-14018# Rome Univ (Italy) IN-ORBIT PERFORMANCE OF INTELSAT V COMMUNICATIONS ANTENNAE DEPLOYMENT SYSTEMS N85-13890'# Boeing Aerospace Co, Seattle, Wash N LOMAS In ESA Workshop on Mech Technol for Antennas POTENTIAL OF FLYWHEELS FOR SPACECRAFT ENERGY p 133-139 Sep 1984 STORAGE Avail NTIS HC A09/MF A01 S GROSS In NASA. Lewis Research Center Space Power p The INTELSAT hinged antenna deployment system is descnbed, 101-113 Apr 1984 and use of real time telemetry from spacecraft sensors to evaluate Avail NTIS HC A14/MF A01 CSCL 10C the success of the deployments, and the actions taken to correct The use of flywheel systems for energy storage in spacecraft performance anomalies are discussed Two partial failures were is considered Energy density, efficiency, weight, voltage range, successfully diagnosed using the telemetry from nutaton life, and reliability of flywheel systems are discussed. R S F accelerometers and Sun and Earth sensors Both anomalies arose

33 06 ELECTRONICS from conditions where initial clearances in the mechanism were N85-20348*# National Aeronautics and Space Administration too small to accommodate the thermal distortions encountered in Marshall Space Flight Center, Huntsville, Ala orbit A large increase in the friction torque resulted, which was ELECTRODYNAMIC INTERACTIONS beyond the capacity of the spnngs to overcome until temperatures N H STONE In its Appl of Tethers in Space, Vol 1 17 p moderated Thermal distortion effects were accounted for in the Mar 1985 hinge design, the clearances were correctly adjusted at final Avail NTIS HC A13/MF A01 CSCL 22B assembly and revenfied by an inspection and test program, so It is apparent that the electrodynamic tether offers new potential INTELSAT 5 overcame deployment problems. Author (ESA) for unique scientific experiments which should enhance the understanding of space plasma physics and in particular certain classes of solar system plasma phenomena, and that these science N85-14022# Societe Nationale Industnelle Aerospatiale, Cannes studies will also address a number of key engineenng concerns (France) which may open up new power and thrust generation technology ARABSAT SPACECRAFT: RX AND TX ANTENNA that could be a significant factor in future space operations MECHANISMS Author C LONG and C VIDAL In ESA Workshop on Mech Technol for Antennas p 159-167 Sep 1984 Avail NTIS HC A09/MF A01 N85-20356*# National Aeronautics and Space Administration A receive antenna (Rx at 6 GHz) and transmit antenna (Tx at Marshall Space Flight Center, Huntsville, Ala 4 GHz) were developed for the Arabsat communication satellite SUMMARY PRESENTATION OF THE ELECTRODYNAMICS The Rx antenna has a single hinge line and during launch the INTERACTIONS PANEL reflector dish is restrained against the antiearth panel by two N H STONE In NASA Marshall Space Flight Center Appl of hold-down points Deployment is actuated by spnngs and regulated Tethers in Space, Vol 1 12 p Mar 1985 by a centrifugal regulator. The Rx antenna mechanisms consist of Avail NTIS HC A13/MF A01 CSCL 20N two motonzed rods, hinged on the structure, a dnvmg rod ensuring Technological and scientific uses of electrodynamic tethers in the required lateral stiffness to the mechanisms in deployed space are considered Areas of concern for such applications of configuration, a centnfugal regulator on the motonzed rod, two electrodynamic tethers are enumerated Thrust and power hold-down points ensured by two pyrotechnical separation nuts, generation using tethers are discussed R S F and a latch on each motonzed rod to block the reflector in the deployed configuration The position of the Tx antenna in stowed and deployed configuration requires double hinge lines A coupling N85-20363*# National Aeronautics and Space Administration rod conjugates the rotation of the double hinge line to allow Marshall Space Flight Center, Huntsville, Ala actuation on only one hinge line, and control deployment rate REPORT OF THE ELECTRODYNAMIC INTERACTIONS PANEL with only one centnfugal regulator Author (ESA) N H STONE, R S TAYLOR (Smithsonian Astrophysical Observatory), S BENFORD (NASA Lewis Research Center), J H BINSACK (MIT), M DOBROWOLNY (CNR, Italy), P FINNEGAN (NASA Lewis Research Center), M. D GROSSI (Smithsonian N85-19326*# Goodyear Aerospace Corp, Litchfield Park, Anz Astrophysical Observatory), M HUDSON (Martin Marietta, Denver), INTERLEAVED ARRAY ANTENNA TECHNOLOGY D INTRILIGATOR (Carmel Research Center), R KAMINSKAS DEVELOPMENT (TRW) et al In its Appl of Tethers in Space, Vol. 2 19 p 30 Jan 1985 55 p refs Mar 1985 (Contract NAS9-16430) Avail NTISHCA14/MF A01 CSCL 20N (NASA-CR-171845, NAS 1 26 171845, GERA-2702) Avail NTIS A wide range of opportunities is provided by the electrodynamic HC A04/MF A01 CSCL 09C tether to more fully understand the generation of waves in plasmas, This is the third phase of a program to establish an antenna the behavior of field aligned currents, the behavior of large concept for shuttle and free flying spacecraft earth resources body-space plasma interactions, and for process simulation, using experiments using Synthetic Aperture Radar The feasibility of a the electrodynamic tether to study processes and phenomena plated graphite epoxy waveguide for a space antenna was relevant to solar system and astrophysics plasma physics. The evaluated A quantity of flat panels and waveguides were electrodynamic tether offers a means of study and expenmentation developed, procured, and tested for electrical and mechanical in space which will provide a nch yield in new scientific results properties. In addition, processes for the assembly of a unique and will enhance the understanding of space plasma physics It waveguide array were investigated Finally, trades between various also has promising technological applications (e g, the generation configurations that would allow elevation (range) electronic of electncal power and thrust) which may be highly significant to scanning and that would minimize feed complexity for various RF future space operations Author bandwidths were made B W

N85-20553# Deutsche Forschungs- und Versuchsanstalt fuer M85-20244*# Hydraulic Research Textron, Irvine, Calif Systems Luft- und Raumfahrt, Cologne (West Germany) Engineenng Drv CONTROL OF LARGE COLLECTOR ARRAYS: THE SSPS COMPENSATOR DEVELOPMENT AND EXAMINATION OF EXPERIENCE PERFORMANCE AND ROBUSTNESS R CARMONA and J G MARTIN 1984 44 p refs 5 Oct. 1984 11 p Prepared for JPL, Pasadena, Calif. (Contract DE-AC04-76DR-00789) (Contract NAS7-918, JPL-956541) (DE85-001461, DOE/DR-00789/T4, SSPS-TR-4/84) Avail (NASA-CR-175470, JPL-9950-962, NAS 1 26175470, NTIS HC A03/MF A01 REPT-956541-EXTENSION-1) Avail NTIS HC A02/MF A01 Experience gained in the control of the distnbuted collector CSCL 09A fields at the IEA Small Solar Power Systems project may be of A compensator was synthesized to minimize the mean square value in the design of control systems for future large arrays The surface error of a wrap nb antenna Two separate cases were project expenence with analog and digital systems is discussed, considered, one in which the flexible nbs and mesh were given as are details on the improvements that were made and the lessons weight, thereby penalizing the actual error of the reflecting area, learned A priority item in this year's efforts on site is the evaluation and the other in which the antenna is considered rigid, thus of the potential for fully automatic operation, with a suitable control penalizing only the ngid body rotation The numencal results show algorithm, of a reliable collector array Preliminary results from that the flexible modes of the antenna have to be included in the dynamic models of the fields in terms of lumped and distnbuted performance cntenon to obtain a better performance G L C parameters are given Adaptive controls are discussed. DOE

34 07 ADVANCED MATERIALS

N85-21252# Lockheed Missiles and Space Co, Palo Alto, Calif A85-13246# SCATHA (SPACECRAFT CHARGING AT HIGH ALTITUDES) DESIGN PREPARATIONS FOR LARGE SPACE STRUCTURES PLASMA INTERACTION EXPERIMENT: SC-3 HIGH ENERGY H W BERGMANN (Deutsche Forschungs- und Versuchsanstalt PARTICLE SPECTROMETER; SC-8 ENERGETIC ION fuer Luft- und Raumfahrt, Instrtut fuer Strukturmechamk, Brunswick, COMPOSITION EXPERIMENT Rnal Report, 1 Nov. 1975 - 30 West Germany) International Astronautical Federation, Oct 1984 International Astronautical Congress, 35th, Lausanne, Switzerland, E G SHELLEY, R D. SHARP. R. W NIGHTINGALE, and J M Oct. 7-13, 1984 6 p. QUINN 30 Nov 1984 53 p (IAF PAPER 84-392) (Contract N00014-76-C-0444) Progress made on studies of fiber-resin systems response to (AD-A149728) Avail NTIS HC A04/MF A01 CSCL 22B long-duration exposure to space conditions, writing codes for large This report describes the results of the SC-3 (High Energy space structures (LSS)design and analysis, and companng code Particle Spectrometer) and SC-8 (Energetic Ion Composition predictions with realistic laboratory data on structures at DFVLR Experiment) instruments flown on the SCATHA (Spacecraft is summarized Carbon-fiber resin elements have been selected Charging at High Altitudes) satellite, launched in January 1979 as pnme LSS elements due to suitable strength, weights and into a near geosynchronous orbit The instruments measure thermal properties Therman cycling and electron bombardment electrons at energies of 005-50 MeV, protons of 1-100 MeV, tests run on a vanety of samples revealed reductions in the bond and mass composition of ions in the range E/q=01-32 keV/e strength between the fibers and the matrix, an effect most Both instruments continue to be fully operational at this time. pronounced with polyimide matenals Irradiation produced no Principal results of the High Energy Particle Spectrometer have marked structural changes except a reddening in color at the addressed radial profiles and energy spectra of energetic particles, surface It is thought that comprehensive predictive codes will be the role of energetic particles in the charging and discharging of needed to offset the impossibility of satisfactorily performing spacecraft dielectncs, the behavior of trapped electrons at flux laboratory tests on LSS models on earth The programs have levels near the Kennel-Petchek trapping limit, and the precipitation identified fiber-wound joints as suitable replacements for carbon of energetic electrons into the ionosphere The Energetic Ion fiber-metal interfaces, which were shown to deteriorate with thermal Composition Expenment has provided the first ion composition cycling M S K data with routine pitch angle coverage in the vicinity of geosynchronous orbit The advances resulting from this mstnjment can be grouped into four categories (1) plasma injection and transport, (2) detailed structure of near-geosynchronous plasma distributions, (3) interactions between hot plasmas and spacecraft, and (4) global understanding arising from the synthesis of individual results Additional keywords abstracts, literature surveys, electnc charge, space charge, particle flux, electron guns, ion guns Author (GRA) A85-13255# KEVLAR AND T300 FABRIC PREPREGS - THEIR MATERIAL PROPERTIES AND THEIR USE IN HIGH LOADED AREAS OF A SOLAR ARRAY W WEISS (Messerschmitt-Boelkow-Blohm GmbH, Munich, West Germany) and H RAPP (Muenchen, Techmsche Universitaet, Munich, West Germany) International Astronautical Federation, International Astronautical Congress, 35th, Lausanne, Switzerland, Oct 7-13, 1984 23 p refs (IAF PAPER 84-402) The mechanical properties of sandwich structures compnsing Kevlar and T300 (carbon) fabncs and 3/8 50560007 p Al-alloy honeycomb cores are investigated experimentally and applied to finite-element modeling and fabrication of concentric cylindrical 07 structures for the solar arrays of the Intelsat VI communications satellite The results are presented in photographs, drawings, ADVANCED MATERIALS diagrams, and graphs The measured strengths of the sandwiches are found to exceed the calculated values by 60 percent or more, Includes matrix composites, polyimide films, thermal control and the facing stiffness is unaffected by radiation T K coatings, bonding agents, antenna components, manufacturing techniques, and space environmental effects on matenals

A85-12395 EFFECTS OF RESIDUAL STRESSES IN POLYMER MATRIX COMPOSITES H T HAHN (Washington University, St. Louis, MO) Journal of the Astronautical Sciences (ISSN 0021-9142). vol 32, July-Sept A85-13257# 1984, p 253-267 refs THERMOELASTIC BEHAVIOUR OF SPACE STRUCTURES IN (Contract NSF MEA-81-10777) COMPOSITE MATERIALS Several conventional methods of elastic analysis are reviewed L B CREMA, R BARBONI, and A CASTELLANI (Roma. and the effects of residual stresses on polymer matnx composites Unrversita, Rome, Italy) International Astronautical Federation, are determined analytically It is found that residual stresses are International Astronautical Congress, 35th, Lausanne, Switzerland, caused by the expansional mismatch between the fibers and the Oct. 7-13, 1984. 13 p refs matrix The stresses manifest themselves in unusual thermal (IAF PAPER 84-404) expansion behavior, premature ply cracking, delammation, and the An evaluation of the mechanical and thermal behavior of Kevlar warping of unsymmetnc laminates It is suggested that by optimizing fabnc cured resin epoxy is presented The tensile, compressrve, the cure cycle and annealing the homogeneous matenals used in and flexural properties of the material are both theoretically and the construction of the composite, some reductons in residual expenmentaliy mvestgated The thermal expansion coefficient and stresses are possible IH the damping properties of the matenal are discussed C D

35 07 ADVANCED MATERIALS

A85-13258# composites, transportation applications of composites, types and INFLUENCE OF THE LAMINATION AND OF SOME properties of reinforced thermoplastics, manne composite ENVIRONMENTAL EFFECTS ON DAMPING CHARACTERISTICS structures manufacture, novel resin systems, and advancements OF ADVANCED COMPOSITES FOR SPACE STRUCTURES in molding processes O C M MARCHETTI (Roma, Universita, Rome, Italy), F MORGANTI, L MUCCIANTE, and A D NOVELLINO (Selenia SpA, Rome, A85-15638# Italy) International Astronautical Federation, International CONTINUOUS GRAPHITE/POLYSULFONE RP Astronautical Congress, 35th, Lausanne, Switzerland, Oct 7-13, THERMOFORMING FOR LARGE SPACE STRUCTURE 1984 26 p Sponsorship Consiglio Nazionale delle Ricerche CONSTRUCTION refs D E BECK (Goldsworthy Engmeenng, Inc, Torrance, CA) IN (Contract CNR-83,02713,07) Reinforced Plastics/Composites Institute, Annual Conference, 38th, (IAF PAPER 84-405) Houston, TX, February 7-11, 1983, Preprints New York, Society Experimental data are presented on the damping behavior of of the Plastics Industry, Inc, 1984, p 20-C-1 to 20-C-6 graphite/epoxy and Kevlar/epoxy composites extensively used in The composite beam cap forming systems (CBCFS) has been space structures Expenmental results are then compared with formulated as a technology demonstrator for large space structure the results of an analytical study, with account taken of the cutting construction Composite tnangular truss beams have been selected direction, lamination topology, fiber type, and laminate thickness as a major approach to the fulfillment of system requirements in A numencal method is developed in order to evaluate the modal virtue of their simplicity and efficiency The graphite-reinforced damping of structures starting from the unidirectional specific polysulfone composite material employed exhibits a near-zero damping capacity This method is an extension of a theory based thermal expansion coefficient in the + or - 250 F space on the dissipation energy V L environment In the CBCFS, a composite nbbon is first continuously formed, and then reshaped into a triangular beam cap The CBCFS A85-13500 apparatus weighs less than 200 Ibs O C MATERIAL SCIENCES IN SPACE [KOSMICHESKOE MATERIALOVEDENIE] A8S-15977 L L REGEL Itogi Nauki i Tekhniki, Serua Issledovanie STRUCTURES AND MATERIALS TECHNOLOGIES FOR Kosmicheskogo Prostranstva (ISSN 0202-0734), vol 21, 1984, 244 SPACECRAFT SYSTEMS AN OVERVIEW p In Russian refs R N GOUNDER (RCA, Astro-Electronics Div , Princeton, NJ) IN Current theoretical and experimental research related to material Technology vectors, Proceedings of the Twenty-ninth National sciences in space is reviewed. Topics discussed include theoretical SAMPE Symposium and Exhibition, Reno, NV, April 3-5, 1984 considerations concerning the growth of crystals under microgravity Covma, CA, Society for the Advancement of Material and Process conditions, the growth of semiconducting matenals from melts and Engmeenng, 1984, p 1-9 from the vapor phase in space, and the solidification of metals, The role of Structures and Materials disciplines in the alloys, composites and glasses in the reduced gravity environment development of spacecraft systems is reviewed A discussion of Attention is also given to crystal growth from aqueous solutions the spacecraft systems requirements for advanced structures and in microgravity, the apparatus and instrumentation used in matenals is presented Application of matenals, design, analysis material-science experiments in space, material processing and test technologies to satellite structures development are experiments using aircraft and rockets, and crystal growth and outlined by way of specific hardware examples This paper forms solidification under high gravity V L an introduction to the individual papers presented at the symposium on Spacecraft Structures and Materials Author A85-14163 INFLUENCE OF SIMULATED SPACE ENVIRONMENT ON THE A85-15980 BEHAVIOR OF CARBON-FIBER-REINFORCED PLASTICS WITH GRAPHITE EPOXY STRUCTURE OF THE SPACE TELESCOPE'S +, -45 PLY ORIENTATIONS. II OPTICAL TELESCOPE ASSEMBLY W HARTUNG and H W BERGMANN Composites Technology C T GOLDEN and E E SPEAR (Boeing Aerospace Co, Seattle, Review, vol 6, Fall 1984, p 126-133 WA) IN Technology vectors, Proceedings of the Twenty-ninth Attention is given to the influence of environmental exposure National SAMPE Symposium and Exhibition, Reno, NV, April 3-5, on the mechanical properties of +, -45 deg carbon fiber-reinforced 1984 Covma, CA, Society for the Advancement of Material and plastic (CFRP) laminates, especially with respect to tensile and Process Engmeenng, 1984, p 33-45 compressive strength, longitudinal direction stiffness, and High strength and stiffness, low weight, and a controlled transverse oscillation damping The effects of thermal cycling and coefficient of thermal expansion approaching zero present electron irradiation on the tested CFRP laminates were evaluated significant incentives for the use of graphite/epoxy composite by comparing the initial and residual mechanical properties of the optical equipment structures in space Attention is presently given specimens Emphasis is given to the maintenance of identical to the NASA Space Telescope's Metenng Truss Structure and test conditions and the determination of the extent of Focal Plane Structure Motions of 0 000048 inches over a 200-inch degradation O C long structure, and optical path alignments of 00018 sec within the 1200-lb graphite/epoxy Focal Plane Structure that will support A85-15626 6000 Ib of scientific instruments, have been demonstrated in the REINFORCED PLASTICS/COMPOSITES INSTITUTE, ANNUAL thermal environment that will be encountered in space O C CONFERENCE, 38TH, HOUSTON, TX, FEBRUARY 7-11, 1983, PREPRINTS A85-15990 New York, Society of the Plastics Industry, Inc, 1984, 847 p For EFFECTS OF SPACE ENVIRONMENTAL CONDITIONS ON individual items see A85-15627 to A85-15640 GRAPHITE EPOXY COMPOSITES Among the topics discussed are automotive applications of S SEEHRA, D BENTON, J ROSEN, and R GOUNDER (RCA, sheet molding compounds, the corrosion and creep rupture Astro Electronics Div, Pnnceton, NJ) IN Technology vectors, behavior of reinforced plastics, the characteristics and applications Proceedings of the Twenty-ninth National SAMPE Symposium and of glass and ceramic additives and fillers, the properties of Exhibition, Reno, NV, Apnl 3-5, 1984 Covma, CA, Society for the matnx/reinforcement interfaces, mdustnal materials evaluation and Advancement of Matenal and Process Engineering, 1984, p quality assurance practices, novel resins and processes for 157-168 pultrusion, oil field applications of reinforced plastics, and sheet Graphite-epoxy composites (metallized with varying amounts molding compound formulation and process control Also covered of vapor-deposited aluminum), thermal protection coating, and are economic planning in the reinforced plastics industry, composite sunshield matenals were exposed to simulated space storage tanks and pipes, aerospace applications of advanced environmental conditions The thermophysical, thermooptical, RF,

36 07 ADVANCED MATERIALS and mechanical properties were measured Radiation (300 million dependences of polymer erosion rates on atomic oxygen kinetic rads maximum) and thermal components of the environment were energy, flux, and fluence and on materials processing Comments simulated by thermal cycling between -175 C and + 50 C. Test on the impacts of reaction products are presented Author results indicate that most properties of the composite materials remained practically unchanged after exposure to the simulated A85-19771# radiation environment However, the solar absorptivity of the ATOMIC OXYGEN SURFACE INTERACTIONS - MECHANISTIC thermal protection coating and sunshield materials increased by a STUDY USING GROUND-BASED FACILITIES factor of two The mechanical properties of the graphite/epoxy J B CROSS and D A. CREMERS (Los Alamos National did not change except for a slight decrease in strength at low Laboratory, Los Alamos, NM) Amencan Institute of Aeronautics temperatures and a small increase in the coefficient of thermal and Astronautics, Aerospace Sciences Meeting, 23rd, Reno, NV, expansion Author Jan 14-17, 1985 18 p refs (AIAA PAPER 85-0473) A85-15993 The present investigation is concerned with the mechanism of ADVANCED ANALYSIS METHODS FOR SPACECRAFT oxygen atom etching of spacecraft surfaces, taking into account COMPOSITE STRUCTURES etching which occurs in low-earth orbit due to attack of C TRUNDLE, F H CHU, and D W GROSS (RCA, translationally hot (5 eV) and thermal (less than 0 5 eV) O-atoms Astro-Electronics Div, Pnnceton, NJ) IN Technology vectors. Attention is also given to a correlation of these results with the Proceedings of the Twenty-ninth National SAMPE Symposium and glow phenomenon observed on the Space Shuttle and other Exhibition, Reno, NV, Apnl 3-5, 1984 Covma, CA, Society for the satellites, and to a data base for the modeling of spacecraft in Advancement of Material and Process Engineering, 1984, p the 500 km altitude region The feasibility of producing 195-202 refs high-temperature (8000 K) atomic and molecular beams using the Structural analysis is an essential step in the development and Continuous Optical Discharge (COD) technique is demonstrated venfication of spacecraft composite structures The accuracy and Extrapolations of the results to a COD generated helium plasma adequacy of the analysis has a direct impact on the success of predict that a 5 eV O-atom source could be developed G R the design The prediction of the behavior of composite structures often requires special finite element formulation techniques that A85-21508 focus on the composite material characteristics at the lamina level EFFECT OF NEUTRON AND PROTON IRRADIATION ON SOME These techniques are significantly more complex than structural PROPERTIES OF KAPTON analysis for conventional matenals This paper discusses the V SHRINET, U K CHATURVEDI, S K AGRAWAL, V N RAI, analysis methods presently used at RCA Astro-Electronics for finite and A K NIGAM (Banaras Hindu University, Varanasi, India) IN element model generation, optimal design, vibration analysis, Polyinmdes Synthesis, characterization, and applications Volume thermal distortion analysis, and stress analysis of lightweight 1 New York, Plenum Press, 1984, p 555-571 Sponsorship composite structures for spacecraft applications Computer-aided Department of Atomic Energy of India refs engineering techniques which are a part of the integrated analysis (Contract DAE PROJECT 34/4/81-G) approach are also discussed Author Surface morphology, dielectric, and photoacoustic characteristics are studied for the case of 25-micron thick Kapton A85-16499 sheets subjected to irradiation by fast reactor neutrons and protons EXPERIMENTAL STUDY OF THE EFFECT OF THE TYPE OF A net enhancement of the dc dielectric constant of about 13 STRESS STATE ON PLASTIC STRAIN IN STRUCTURAL percent is noted after the maximum neutron dose, and is attributed MATERIALS AT LOW TEMPERATURES to the enhanced water absorptivity of the material due to G. S PISARENKO, A A LEBEDEV, and B I KOVALCHUK neutron-induced radiation damage SEM of the n- and (Akademiia Nauk Ukramskoi SSR, Institut Problem Prochnosti, Kiev, H(+)-irradiated Kapton surfaces respectively show a swollen, rough Ukrainian SSR) (International Astronautical Federation, surface and scattered blisters O C International Astronautical Congress, 34th, Budapest, Hungary, Oct 10-16,1983) Acta Astronautica (ISSN 0094-5765), vol 11, July-Aug A85-24672* Rome Air Development Center, Hanscom AFB, 1984, p 483-488 refs Mass The apparatus and theoretical models used at the Ukrainian DIELECTRIC MATERIAL IN THE SPACE ENVIRONMENT Institute for Problems of Strength to assess the complex A R FREDERICKSON, J A WALL (USAF, Rome Air Development load-carrying strengths of materials for rocket and space structures Center, Bedford, MA), D B COTTS (SRI International, Menlo Park, are descnbed Thin-wall tubular specimens are tested with axial CA), and F L BOUQUET (California Institute of Technology, Jet force, torque and internal pressure Hydrostatic buckling is applied Propulsion Laboratory, Pasadena, CA) SAMPE Journal (ISSN to membranes and plates, and biaxial tension is forced on 0091-1062), vol 21, Mar-Apr 1985, p 12-16 refs cross-shaped specimens. Temperatures from 100-1200 K can be The irradiation encountered in space environments causes high applied The specimens are monitored with extensometer strain insulation matenals to discharge, either through electrical gages All tests are performed under preprogrammed computer breakdown or surface voltage effect mechanisms Attention is control Numerical models have been defined for the plastic strain presently given to polymers which, serving as 'leaky' insulators, trajectories under loading and the relations between stresses and avoid this problem by means of conduction mechanisms that are strains for smooth surfaces on orthotropic media and in structurally acceptable in space applications The class of conductive polymers unstable matenals Sample ultimate strength data are provided encompasses polyvmylcarbazole, polyacrylonitnle, Kapton, and for austenitc steel and aluminum alloys M S K polythiazil A testing procedure useful in the qualification of such polymers is outlined O.C A85-19770# KINETICS OF OXYGEN INTERACTION WITH MATERIALS A85-24675 G S ARNOLD and D R PEPLINSKI (Aerospace Corp, Chemistry RADIATION EFFECTS IN MATERIALS - FIELD-ION and Physics Laboratory, El Segundo, CA) Amencan Institute of MICROSCOPE CHARACTERIZATIONS Aeronautics and Astronautics, Aerospace Sciences Meeting, 23rd, O T INAL (New Mexico Institute of Mining and Technology, Reno, NV, Jan 14-17, 1985 9 p. Research supported by the Socorro, NM) and W F. SOMMER (Los Alamos National Aerospace Corp refs Laboratory, Los Alamos, NM) SAMPE Journal (ISSN 0091-1062). (Contract F04701-«2-C-0083) vol 21, Mar-Apr 1985, p 42, 44-46, 48, 49, 95 refs (AIAA PAPER 85-0472) Atomic-level analyses of radiation effects in metals and alloys, An analysis of the currently available laboratory and flight data utilizing field ion microscopy (FIM) has shed much light into the on the kinetics of the oxidation of spacecraft matenals in low various irradiation-induced phenomena exhibited in the form of earth orbit is presented Subjects addressed in detail are the point defects, point defects clusters and voids of small sizes (less

37 07 MWANCEB MATERIALS

than 10 nm) The study presented summanzed FIM research done A85-30024 on crystalline as well as amorphous materials exposed to explosive INFLUENCE OF STARTING MATERIAL AND TECHNOLOGICAL shock, laser, and charged (proton) and uncharged (neutron) particle PROCESSES ON THE RADIATION RESISTANCE OF SILICON irradiation at room temperature Also included is an in situ study SOLAR CELLS FOR SPACE USE [ROLE DU MATERIAU DE of gaseous plasma-introduced defects on preimaged field emission DEPART ET DES PROCESSUS TECHNOLOGIQUES SUR LA end forms, to further emphasize the capability of this analysis TENUE AUX IRRADIATIONS DES PHOTOPILES SOLAIRES AU technique Author SILICIUM A USAGE SPATIAL] M LAGOUIN Toulouse III, Universite, Docteur (3e cycle) Thesis, 1984, 133 p In French refs A85-24703* National Aeronautics and Space Administration The degradation of Si solar-cell layers of thickness 200-480 Langley Research Center, Hampton, Va microns by 1 -MeV electron irradiation is investigated experimentally A REVIEW OF CONTAMINATION ISSUES ASSOCIATED WITH with a focus on the role of raw-material characteristics and AN ORBITING SPACE STATION EXTERNAL ENVIRONMENT processing parameters in the n/p-type cells typically used for A C SMITH (NASA, Langley Research Center, Hampton, VA) satellite solar panels The use of open-circuit, short-circuit, and Journal of Environmental Sciences (ISSN 0022-0906), vol 28, maximum-power electncal measurements to estimate the bulk Jan-Feb. 1985, p 52-55. refs minority-earner lifetime tau(V) is evaluated by comparison with direct Techniques for measunng, modeling, and limiting the effluent measurements, and the technique based on the time evolution of contamination of external spacecraft and instrument surfaces are short-circuit current is found to be significantly better than the reviewed, with an emphasis on their application to the Space other methods in tests on samples with B or Ga doping, resistivity Station The major factors addressed by contamination studies 1 or 10 ohm cm, and various levels of O and C impurities The are outlined, typical contamination sources are characterized, the defects responsible for the degradation of the cells are studied critical measurement parameters are defined (molecular column by means of both bulk-property measurements and deep-layer density, background spectral intensity from UV to IR, particle size transient spectroscopy (summarizing the results of Roux et al, and velocity distribution, molecular deposition on ambient and 1983), and the effects of different standard manufacturing steps cryogenic surfaces, molecular return flux for gaseous species, on tau(V) are explored Graphs, diagrams, and tables are paniculate deposition on surfaces, and optical-surface degradation), provided T K and measurement instrumentation is described Contamination limits for quiescent operation periods of the Space Station are proposed, including column density 10 to the 11 th/sq cm for H2O + CO2, 10 to the 13th/sq cm for O2 + N2, and 10 to the 10th/sq cm for other species, particle release no greater than N85-11047*# Corning Glass Works, N Y 15-micron particle/orbit/0 00001 sr FOV for a 1-m telescope, and INORGANIC COMPOSITES FOR SPACE APPLICATIONS surface deposition 4 pg/sq cm sec for 298-K surfaces and 10 J W MALMENDIER In NASA Marshall Space Flight Center pg/sq cm sec for 4-K surfaces T K 2nd Symp on Space Industrialization p 321-332 Oct 1984 Avail NTIS HC A19/MF A01 CSCL 11D The development of inorganic composite materials for space A85-25988* National Aeronautics and Space Administration applications is reviewed The composites do not contain any organic Langley Research Center, Hampton, Va materials, and therefore, are not subject to degradation by TOROID JOINING GUN ultraviolet radiation, volatilization of constituents, or embnttlement J D BUCKLEY, R L FOX, and R J SWAIM (NASA, Langley at low temperatures The composites consist of glass, Research Center, Hampton, VA) Society of Automotive Engineers, glass/ceramics or ceramic matrices, reinforced by refractory International Congress and Exposition, Detroit, Ml, Feb 25-Mar whiskers or fibers Such composites have the low thermal 1, 1985 13 p refs expansion, refractories, chemical stability and other desirable (SAE PAPER 850408) properties usually associated with the matrix materials The The Toroid Joining Gun is a low cost, self-contained, portable composites also have a degree of toughness which is extraordinary low powered (100-400 watts) thermoplastic welding system for refractory inorganic matenals MAC developed at Langley Research Center for joining plastic and composite parts using an induction heating technique The device developed for use in the fabrication of large space sructures (LSST Program) can be used in any atmosphere or in a vacuum Components can be joined in situ, whether on earth or on a N85-11239*# National Aeronautics and Space Administration space platform The expanded application of this welding gun is Marshall Space Flight Center, Huntsville, Ala in the joining of thermoplastic composites, thermosettmg AN EVALUATION OF GREASE TYPE BALL BEARING composites, metals, and combinations of these materials Its LUBRICANTS OPERATING IN VARIOUS ENVIRONMENTS Final low-power requirements, light weight, rapid response, low cost, Status Report portability, and effective joining make it a candidate for solving E L MCMURTREY Oct 1984 23 p refs many varied and unique bonding tasks Author (NASA-TM-86480, NAS 1 1586480, FSR-8) Avail NTIS HC A02/MFA01 CSCL11H Because many future spacecraft or space stations will require A85-29730* National Aeronautics and Space Administration mechanisms to operate for long penods of time in environments Ames Research Center, Moffett Field, Calif which are adverse to most beanng lubncants, a series of tests CATALYTIC SURFACE EFFECT ON CERAMIC COATINGS FOR has been completed to evaluate 38 grease type lubncants in R-4 AN AEROASSISTED ORBITAL TRANSFER VEHICLE size beanngs in five different environments for a 1 year period D A STEWARD and D B LEISER (NASA, Ames Research Center, Four repetitions of each test were made to provide statistical Moffett Field, CA) Ceramic Engineenng and Science Proceedings samples These tests were also used to select four lubncants for (ISSN 0196-6219), vol 5, July-Aug 1984, p 491-505 refs 5 year tests in selected environments with five repetitions of each Surface catalytic efficiencies of glassy coatings were determined test for statistical samples In this completed program, 172 test from a reaction boundary layer computation and arc-jet data The sets have been completed The three 5 year tests in (1) continuous catalytic efficiencies of the various coatings examined are operation and (2) start stop operation, with both in vacuum at discussed in terms of their reaction-rate constants These constants ambient temperatures, and (3) continuous vacuum operation at are a function of the wall temperature (1290 K to 2000 K) In 93 3 C have been completed In both the 1 year and 5 year addition, the advantage of a thermal protection system for a bent tests, the best results in all environments have been obtained biconic, aeroassisted orbital transfer vehicle with a low surface with a high viscosity index perfluoroalkylpolyether (PFPE) grease catalytic efficiency is discussed Author Author

38 07 ADVANCED MATERIALS

N85-14013# Deutsche Forschungs- und Versuchsanstalt fuer and matenals to attain the ultimate sensitivities inherent to that Lutt- und Raumfahrt, Brunswick (West Germany) Inst for Structural procedure Subsequent chemical analysis of the contaminant Mechanics sample by infrared and mass spectrometry identifies the INFLUENCE OF THERMAL CYCLING ON THE BEHAVIOR OF components, gives semiquantitative estimates of contaminant CFRP MATERIAL FOR SPACE STRUCTURES thickness, indicates possible sources of the nonvolatile residue W HARTUNG In ESA Workshop on Mech Technol for Antennas (NVR), and provides guidance for effective cleanup procedures p 97-101 Sep 1984 refs Author Avail. NTIS HC A09/MF A01 The effects of a simulated 10 yr service in geosynchronous N85-19137*# Martin Marietta Aerospace, Denver, Colo. orbit on the thermomechamcal properties of graphite/fiber EVALUATION AND PREDICTION OF LONG-TERM composite structures were tested Materials were exposed to 3500 ENVIRONMENTAL EFFECTS OF NONMETALLIC MATERIALS thermal cycles with a temperature range from minus 160 to +100 Final Report C The influence of microcrackmg increases mainly dunng the H. PAPAZIAN Jan 1985 29 p refs first 1000 thermal cycles Strength reduction corresponds to the (Contract NAS8-33578) amount of microcrackmg It is slight for epoxy-based laminates (NASA-CR-171353, NAS 1 26 171353, MCR-85-506) Avail (3% to 22%). Polyimide based matenal suffers strength reduction NTIS HC A03/MF A01 CSCL 11G of 40%. The percentage of stiffness degradation at the end of The properties of a number of nonmetalhc matenals were the test is nearly equal to that of strength A slight increase of evaluated experimentally in simulated space environments in order thermal expansion at the end of thermal cycling reflects increased to develop models for accelerated test methods useful for predicting influence of the matrix due to fiber matrix debondmg Poor such behavioral changes Graphite-epoxy composites were resistance of polyimide resin against thermal cycling is caused by exposed to thermal cycling Adhesive foam tapes were subjected the too small strain at failure combined with the high curing to a vacuum environment Metal-matnx composites were tested temperature, resulting in a higher prestress at operating for baseline data Predictive modeling designed to include strength temperatures. Author (ESA) and aging effects on composites, polymeric films, and metals under such space conditions (including the atomic oxygen environment) N85-14014# Rome Univ (Italy) Dipt Aerospaziale is discussed The Korel 8031-00 high strength adhesive foam tape THE DIMENSIONAL STABILITY OF ADVANCED COMPOSITE was shown to be supenor to the other two tested R S F ANTENNA REFLECTORS: ANALYTICAL AND TEST EVALUATION N85-19519*# Lockheed Missiles and Space Co, Sunnyvale, M MARCHETTI and F. MORGANTI (Selenia S p A , Rome) In Calif Space Systems Drv ESA Workshop on Mech. Technol for Antennas p 103-109 INVESTIGATION OF WELDED INTERCONNECTION OF LARGE Sep 1984 refs AREA WRAPAROUND CONTACTED SILICON SOLAR CELLS Avail NTIS HC A09/MF A01 Final Report The effects of thermal expansion coefficient of the D R LOTT Aug 1984 42 p Sponsored by NASA Lewis graphite-epoxy structure, thermal cycling which the structure Research Center Prepared for JPL, Pasadena, Calif undergoes at ground and in orbit, and moisture sorption on the (Contract JPL-956020) dimensional stability of a 4 m diameter reflector 20 to 30 GHz (NASA-CR-174438, JPL-9950-975, NAS 1 26 174438, spacecraft antenna were tested A finite element model to predict LMSC-D973421) Avail NTIS HC A03/MF A01 CSCL 10A thermal expansion coefficients (TEC) in sandwich panels was An investigation was conducted to evaluate the welding and developed Tests suggest that artificial thermal aging helps to temperature cycle testing of large area 59x59 wraparound silicon stabilize the TEC value of graphite-epoxy composites, solar cells utilizing printed circuit substrates with SSC-155 compensating ground environment effects, such as moisture, and interconnect copper metals and the LMSC Infrared Controlled weld reducing settling and creep effects m-orbit. Author (ESA) station An initial group of 5 welded modules containing Phase 2 developmental 59 x 59 cm cells were subjected to cyclical N85-14015# Construcciones Aeronauticas SA, Madnd (Spain) temperatures of + or 80 C at a rate of 120 cycles per day Space Div Anomalies were noted in the adhesion of the cell contact CASA ACTIVITIES IN ANTENNA TECHNOLOGY metallization, therefore, 5 additional modules were fabncated and M DECASTRONODAL In ESA Workshop on Mech Technol tested using available Phase I cells with demonstrated contact for Antennas p 111-116 Sep 1984 integrity Cycling of the later module type through 12,000 cycles Avail NTIS HC A09/MF A01 indicated the viability of this type of lightweight flexible array The technology required to manufacture molded solid reflectors concept This project demonstrated acceptable use of an alternate from composite matenals for spaceborne applications is outlined interconnect copper in combination with large area wraparound An 11 to 14 GHz circular polarization double offset reflector with cells and emphasized the necessity to implement weld pull as 23x31 m aperture was designed The reflector dish is a CFRP opposed to solder pull procedures at the cell vendors for cells covered aluminum honeycomb core sandwich, interfacing through that will be interconnected by welding B W 12 fixation points with the truss support structure The design is also used as a basis for Olympus TVB1 satellite reflectors Matenals N85-20019*# General Dynamics/Convair, San Diego, Calif selection and surface coatings for reflectors in the 100 to 300 DEVELOP AND DEMONSTRATE MANUFACTURING GHz range are discussed Author (ESA) PROCESSES FOR FABRICATING GRAPHITE FILAMENT REINFORCED POLYMIDE (GR/PI) COMPOSITE STRUCTURAL N85-17019*# National Aeronautics and Space Administration. ELEMENTS Final Report Goddard Space Flight Center, Greenbelt, Md V A CHASE and E S. HARRISON Feb 1985 235 p refs ANALYSIS OF NONVOLATILE RESIDUE (NVR) FROM (Contract NAS1-14784) SPACECRAFT SYSTEMS (NASA-CR-172497, NAS 1.26 172497) Avail NTIS HC A11/MF J A COLONY Jan 1985 12 p A01 CSCL11D (NASA-TM-86184; G-85F0284; NAS 1 1586184) Avail NTIS A study was conducted to assess the merits of using HC A02/MF A01 CSCL 07D graphite/polyimide, NR-150B2 resin, for structural applications on Organic contamination on cntacal spacecraft surfaces can cause advanced space launch vehicles The program was divided into electronic problems, senous attenuation of vanous optical signals, two phases' (1) Fabrication Process Development, and (2) thermal control changes, and adhesion problems. Such Demonstration Components The first phase of the program contaminants can be detected early by the controlled use of witness involved the selection of a graphite fiber, quality assurance of the mirrors, witness plates, wipe sampling, or direct solvent extraction NR-150B2 polyimide resin, and the quality assurance of the Each method requires careful control of vanables of technique graphite/polyimide prepreg In the second phase of the program,

39 07 ADVANCED MATERIALS

a limited number of components were fabricated before the N85-21188*# National Aeronautics and Space Administration NR-150B2 resin system was removed from the market by the Johnson (Lyndon B) Space Center, supplier, Du Pont The advancement of the NR-150B2 polyimide ORBITAL DEBRIS resin binder was found to vary significantly based on previous D J KESSLER, comp and S Y SU, comp (Lockheed-EMSCO, time and temperature history during the prepregging operation Houston, Tex) Mar 1985 453 p refs Proc of a Workshop Strength retention at 316C (600F) was found to be 50% that of held in Houston, Tex, 27-29 Jul 1982 room temperature strength However, the composite would retain (NASA-CP-2360, S-532, NAS 1 55 2360) Avail NTIS HC its initial strength after 200 hours exposure at 316C (600F) Basic A20/MF A01 CSCL 22A chemistry studies are required for determining NR-150B2 resin Earth orbital debris issues and recommended future activities binder quality assurance parameters Graphite fibers are available are discussed The workshop addressed the areas of environment that can withstand high temperature cure and postcure cycles definition, hazards to spacecraft, and space object management Author It concluded that orbital debris is a potential problem for future space operations However, before recommending any maior efforts to control the environment, more data are required The most significant required data are on the population of debris smaller than 4 cm in diameter New damage cntena are also required When these data are obtained, they can be combined with hypervelocity data to evaluate the hazards to future spacecraft N85-20128*# National Aeronautics and Space Administration After these hazards are understood, then techniques to control Langley Research Center, Hampton, Va the environment can be evaluated PROCESS FOR PREPARING ESSENTIALLY COLORLESS POLYIMIDE FILM CONTAINING PHENOXY-LINKED DIAMINES Patent Application N85-21195*# Aerospace Corp , El Segundo, Calif A K STCLAIR and T L STCLAIR, inventors (to NASA) 23 ASSESSMENT OF SATELLITE COLLISION HAZARDS BY Aug 1984 23 p SIMULATED SAMPLING IN SPACE (NASA-CASE-LAR-13353-1, NAS 1 71 LAR-13353-1, V A CHOBOTOV In NASA Lyndon B Johnson Space Center US-PATENT-APPL-SN-643524) Avail NTIS HC A02/MF A01 Orbital Debris p 84-101 Mar 1985 refs CSCL 11B Avail NTIS HC A20/MF A01 CSCL 22A A polyimide film that is approximately 90% transparent at 500 The origin and distribution of the tracked population of objects nm, useful for thermal protective coatings and solar cells, and the and implications for future missions were examined The distribution processes for preparing the same by thermal and chemical of the tracked population of objects as a function of altitude and conversion are disclosed An essential feature for achieving orbital inclination are studied Representative encounter parameters maximum optical transparency films requires utilizing recrystallized such as the number, relative velocity, and miss distance are and/or sublimated specific aromatic diammes and dianhydnde determined for circular mission orbits and are used to classify monomers and introducing phenoxy or thiophenyl separator regions of space according to the degree of collision hazard groupps and isomenc m,m'- or o,p'-onented diammes into the presented Implications for space shuttle and geosynchronous polymer molecular structure The incorporation of these groups in orbits are examined E A K the polymer structure serves to separate the chromaphoric centers and reduce the formation of inter-chain and mtra-cham charge N85-21199*# Southwestern Univ , Georgetown, Tex transfer complexes which normally cause absorptions in the PRELIMINARY DESIGN OF AN EARTH-BASED DEBRIS UV-visible range The films may be obtained by hand, brushing, DETECTION SYSTEM USING CURRENT TECHNOLOGY AND casting or spraying a layer of the polyamic acid solutions onto a EXISTING INSTALLATIONS surface and thermally converting the applied layer to the polyimide T H MORGAN In NASA Lyndon B Johnson Space Center In addition, the polyamic acid solution can be chemically converted Orbital Debris p 150-163 Mar 1985 to the polyimide, subsequently dissolved in an organic solvent, Avail NTIS HC A20/MF A01 CSCL 22A and applied as a polyimide film layer with the solvent therein Assessment of debns hazard requires the determination of thermally removed NASA debris down to mm sizes for near-Earth orbits and near-stationary points It is necessary to obtain reasonable orbits for a statistically significant sample of the debris population Several ground-based techniques for detection are available Radar detection was used to obtain information of existing debris population Another technique is optical detection The possibilities and application of optical detection with state-of-the-art instrumentation is studied N85-20371*# National Aeronautics and Space Administration Langley Research Center, Hampton, Va EAK PULTRUSION PROCESS FOR FABRICATION OF TETHERS (PRELIMINARY CONCEPTS) N85-21223*# National Aeronautics and Space Administration I O. MACCONOCHIE and M L WILSON In NASA Marshall Johnson (Lyndon B) Space Center, Space Flight Center Appl of Tethers in Space, Vol 2 15 p ENVIRONMENT DEFINITION, SMALL PARTICLES, DIAMETER Mar 1985 LESS THAN OR EQUAL TO 1 MM Avail NTISHCA14/MFA01 CSCL 22B In its Orbital Debns p 426-429 Mar 1985 Three composite materials were manufactured by the pultrusion Avail NTIS HC A20/MF A01 CSCL 22A process, coiled on 24 inch diameter spools for a period of two The collection of particles of diameters one millimeter and less months, uncoiled and evaluated for memory recall These matenals far outnumbers the larger particle distribution in orbit These small were pultruded to lengths of approximately 150 feet and cross particles cannot be tracked from ground based radar as can the section profiles were maintained at 0143 inch in thickness by larger debris, therefore, there is greater uncertainty in their 0 566 inch in width Mechanical properties were studied and results properties The population is growing from contributions due to compared The reinforcement matenal volume percent of each collisions of larger debns, explosions, and aluminum oxide particles was identical Of the three systems, the Kevlar reinforced composite from solid rocket motors The solid rocket motor contnbution is had the highest specific strength, the lowest flexural modulus, the prominent growth parameter, and the input from Space Shuttle and the lowest memory recall Further evaluations of matenals deployed upper stages will range between 50,000 and 100,000 and fabncation technology of pultrusion should be conducted to pounds per year The environment is important because of the address some problem areas encountered in this preliminary different design problems that will be posed to the engineer and concept Areas for further study are suggested M G scientist The emphasis shifts from catastrophe deign, probability

40 08 ASSEMBLY CONCEPTS versus exposure time, and tracking-avoidance, to a continuous the platform and on the transportation vehicles and placed in degradation problem Author service for routine, difficult (only partially programmable), or emergency (reaction time limited) tasks It is assumed that platform designs would assure that only one manipulator be required for a task The models account for adaptation of the arm motions to 08 the local environment, selection of the geometric and kmematical system charactenstics, characterization of the manipulator ASSEMBLY CONCEPTS dynamics, architecture and configuration, and different control modes with variable operator involvement Critical areas of further Includes automated manipulator techniques, EVA, robot assembly, research to realize a European manipulator system are teleoperators, and equipment installation delineated M S K A85-13229# A85-13001*# Massachusetts Inst. of Tech., Cambndge SATELLITE GRASPING MANIPULATOR SYSTEM NEUTRAL BUOYANCY EVALUATION OF TECHNOLOGIES FOR J J RUNAVOT, M MAURETTE, J M LOPEZ, L PETITJEAN, SPACE STATION EXTERNAL OPERATIONS and M L VILLA (Centre National d'Etudes Spatiales, Toulouse, D L AKIN, M L BOWDEN, and J. R SPOFFORD (MIT, Cambndge, France) International Astronautical Federation, International MA) International Astronautical Federation, International Astronautical Congress, 35th, Lausanne, Switzerland, Oct 7-13, Astronautical Congress, 35th, Lausanne, Switzerland, Oct 7-13, 1984 6 p. 1984 8 p refs (IAF PAPER 84-371) (Contract NAGW-21) Progress made on identification of design parameters on (IAF PAPER 84-38) missions for European spaceborne mampular systems are outlined In order to perform a complete systems analysis for almost The manipulator would be deployed after a chaser sequence to any large space program, it is vital to have a thorough close on a satellite After grappling, a period of time would be understanding of human capabilities in extravehicular activity (EVA) needed to damp the relative motion between the two spacecraft The present investigation is concerned with the most significant The manipulator was found to have 6 DOF, with control laws results from the MIT Space Systems Lab's neutral buoyancy tests being necessary to govern joint movement and trajectory in An evaluation of neutral buoyancy is considered along with the proximity operations A NASTRAN modal analysis is being tested structures, aspects of learning, productivity, time and motion performed to derive control law and hardware design parameters analysis, and assembly loads Attention is given to EVA assembly Gear train lubrication has become recognized as a cntical factor with a manned maneuvering unit, teleoperated structural assembly, Further studies are being pursued on the proximity, optical, and an integrated control station, a beam assembly teleoperator, and RF sensors A simulation laboratory has been established for space station proximity operations G R examining modeled dynamical situations M S K

A85-13017# A85-19466# A SPACE STATION EXPERIMENT ON LARGE ANTENNA SPACE STATION REMOTE MANIPULATOR REQUIREMENTS ASSEMBLY AND MEASUREMENT - A FOLLOW-ON STUDY DEFINITION Y OHKAMI, K MATSUMOTO (National Aerospace Laboratory, B A LOGAN, JR (Rockwell International Corp, Space Station Chofu, Tokyo, Japan), T IIDA, K OKAMOTO (Ministry of Posts Systems Div, Downey, CA) American Institute of Aeronautics and Telecommunications, Radio Research Laboratories, Koganei, and Astronautics, Aerospace Sciences Meeting, 23rd, Reno, NV, Tokyo, Japan), A KINPARA (Japan Broadcasting Corp, Technical Jan 14-17, 1985 4 p Research Laboratories, Tokyo, Japan), and I OHTOMO (Nippon (AIAA PAPER 85-0029) Telegraph and Telephone Public Corp, Yokosuka Electncal An essential element of the Space Station is the remote Communication Laboratory, Yokosuka, Kanagawa, Japan) manipulator It will be used for assembly of the Space Station International Astronautical Federation, International Astronautical from the modules brought up by the National Space Transportation Congress, 35th, Lausanne, Switzerland, Oct 7-13, 1984 9 p System (NSTS), for handling of payloads/expenments on the Space (IAF PAPER 84-58) Station, for grappling and berthing co-orbiting spacecraft (including Results are presented of a follow-on study of a space-station the orbiter), and for assembly of large space structures The experiment involving the assembly of a large antenna and the operational and assembly uses are examined to define the carrying out of a senes of measurements and operational tests A requirements that these uses impose on the Space Station remote 10-meter antenna reflector is assumed to be assembled from manipulator These requirements include degrees-of-freedom (such segments using manipulators operated by a crew inside the as translation of the mounting base), reach envelope, loads pressunzed module of the space station Vanous configurations capacity, stopping distance, translational and rotational rates, of the antenna reflector are evaluated to meet the requirements positioning accuracy, etc Finally, the capabilities of the orbiter imposed on such instalments as the microwave radiometer, remote manipulator system are compared with the requirements weather radar, and VLBI detector Particular consideration is given of the Space Station remote manipulator Author to offset/center-feed configurations, segmentation methods, surface control capabilities, compatibility with the STS cargo bay, A85-20400# and scalability to larger reflectors B J SYNERGY IN SPACE - MAN-ROBOT COOPERATION S WALTERS Mechanical Engmeenng (ISSN 0025-6501), vol A85-13227# 107, Jan. 1985, p 26-37 SERVICE MANIPULATOR SYSTEM FOR MAINTENANCE AND The forecast of U S national space strategy for the next 25 SERVICING OF FUTURE SPACE PLATFORMS years and beyond, as announced by President Reagan in October, J-L LACOMBE and T BLAIS (Matra, S.A, Vehzy-Villacoublay, 1983, is concerned with the permanent occupation of space by Yvelines, France) International Astronautical Federation, man In connection with plans for the implementation of such an International Astronautical Congress, 35th, Lausanne, Switzerland, occupation, NASA has considered the concept of a 'flotilla' with a Oct. 7-13,1984 11 p Research supported by the European Space manned base in the center, a utility core, a modular laboratory, Agency and Centre National d'Etudes Spatiales. refs and an orbital service station The presence of man and machines, (IAF PAPER 84-369) in particular computer-linked machines, is to provide possibilities Design features, performance parameters, and numerical for the continuous exploitation of space. Studies have identified models for manipulators (robot arm) which would be used in the automation, robotics, and machine intelligence systems (ARAMIS) maintenance and servicing of orbiting materials processing as an important contnbutor to the productivity of orbital factones platforms are descnbed The manipulators could be located on Attention is given to aspects of 'telepresence', plans for 1995

41 08 ASSEMBLY CONCEPTS

and beyond, the orbital maneuvering vehicle (OMV), OMV provides the deploy, latch and unlatch capabilities of the Remote applications, the support of materials-processing platforms, Manipulator System arm R J F telepresence technology, a stereo-optic .vision system, manipulator arms, end-effectors, communications, and long-term plans and N85-16964*# Spar Aerospace Ltd , Toronto (Ontano) goals G R AN OVERVIEW OF THE SPACE REMOTE MANIPULATOR SYSTEM N85-14492*# CAE Electronics Ltd, Montreal (Quebec) T. H USSHER and K H DOETACH In NASA Johnson Space SIX DEGREES OF FREEDOM CONTROL WITH EACH HAND? Center Space Shuttle Tech Conf, Pt 2 p 892-904 Jan 1985 Abstract Only refs M L KING In NASA Ames Research Center 20th Ann Conf Avail NTIS HC A23/MF A01 CSCL 22B on Manual Control, Vol 1 p 91 Sep 1984 An overview of the system requirements and performance of Avail NTIS HC A99/MF A01 CSCL 05H the Shuttle Remote Manipulator System (SRMS) is given Data on For some time man has made six degree of freedom inputs to some of the mechanical design considerations that were necessary a pair of dextrous manipulators using both hands simultaneously dunng the development program are presented The operational by the use of the master/slave concept The advent of the success of both the Orbiter and the SRMS dunng flights of Space microprocessor has the potential to make the master/slave concept Transportation System-2, -3, and -4 is ample evidence that the redundant by replacing the master with a mathematical model All SRMS performed as expected and as desired. While some minor spacecraft to date, including the space shuttle, that were flown in improvements were made in the follow-on production systems, six degrees of freedom were controlled by using both hands, the one of which was delivered and two of which are currently under left hand controlling translation and the nght rotation Almost construction, the system design did not change significantly Thus, inevitably the same pnnciple was applied to the CANADARM At information given is applicable to all the manipulator systems the instigation of NASA the development of a device whereby RJF both translation and rotation could be combined allowing full control with one hand was developed The development and testing of N85-19015*# National Aeronautics and Space Administration the device, and the extension of its application into spaceflight Langley Research Center, Hampton, Va control are described Also the concept of an adaptable workstation SWING-ARM BEAM ERECTOR (SABER) CONCEPT FOR SINGLE for multi-manipulator and spacecraft flight control is discussed ASTRONAUT ASSEMBLY OF SPACE STRUCTURE BG J J WATSON, W L HEARD, JR, and J K JENSEN (Kentron International, Inc) Mar 1985 32 p refs (NASA-TP-2379, L-15886, NAS 1602379) Avail NTIS HC N85-16178*# Stanford Univ, Calif A03/MF A01 CSCL 22B PRECISE CONTROL OF FLEXIBLE MANIPULATORS Final Results are presented of tests conducted to evaluate a mobile Report, Mar. 1983 - Jun. 1984 work station/assembly fixture concept that would mechanically R H CANNON, JR, T O BINDFORD, and E SCHMITZ Sep assist an astronaut in the on-orbit manual assembly of erectable 1984 53 p refs Ongmal contains color illustrations truss-beams The concept eliminates astronaut manual translation (Contract NAG 1-322) by use of a motorized work platform with foot restraints The (NASA-CR-174210, NAS 1 26-174210) Avail NTIS HC A04/MF tests involved assembly of a tetrahedral truss-beam by a test A01 CSCL 05H 'subject in simulated zero gravity (neutral bouyancy in water) A The design and experimental testing of end point position three-bay truss-beam was assembled from 30 aluminum struts controllers for a very flexible one link lightweight manipulator are with quick-attachment structural joints The results show that summanzed The latest upgraded version of the experimental set average on-orbit assembly rates of 2 1 struts per minute can be up, and the basic differences between conventional joint angle expected for struts of the size employed in these tests Author feedback and end point position feedback are described A general procedure for application of modern control methods to the problem N85-21666# Carnegie-Mellon Univ, Pittsburgh, Pa Lab for is outlined The relationship between weighting parameters and Autonomous Mobile Robots the bandwidth and control stiffness of the resulting end point A FUNCTIONAL VEHICLE FOR AUTONOMOUS MOBILE ROBOT position closed loop system is shown It is found that joint rate RESEARCH Interim Report angle feedback in addition to the primary end point position sensor G PODNAR, K DOWLING, and M BLACKWELL Apr 1984 is essential for adequate disturbance rejection capability of the 80 p Sponsored in part by the Office of Naval Research closed loop system The use of a low order multivanable (AD-A150052, CMU-RI-TR-84-28) Avail NTIS HC A05/MF A01 compensator design computer code, called Sandy is documented CSCL 14B \ A solution to the problem of control mode switching between Neptune is a tethered vehicle built for autonomous mobile robot position sensor sets is outlined The proof of concept for endpomt research Included are the design considerations, the resulting position feedback for a one link flexible manipulator was design, and details of the mechanical structure and electncal control demonstrated The bandwidth obtained with the experimental end system Detail is sufficient to enable replication or adaptation by point position controller is about twice as fast as the beam's first others A discussion of the performance with respect to the design natural cantilevered frequency, and comes within a factor of four considerations is also included GRA of the absolute physical speed limit imposed by the wave propagation time of the beam E A.K N85-22230*# Berry Coll, Mount Berry, Ga Dept of Physics EVALUATION OF OMV RANGING AND DOCKING SYSTEMS N85-16963*# National Aeronautics and Space Administration M W MCDONALD In Alabama Univ. Res Rept 1984 Johnson (Lyndon B) Space Center, NASA/ASEE Summer Faculty Fellowship Program THE SPACE SHUTTLE ORBITER REMOTE MANIPULATOR (NASA-CR-171317) 18p Jan 1985 refs POSITIONING MECHANISM Avail NTIS HC A99/MF £03 CSCL 22A J H HARDEE In its Space Shuttle Tech Conf, R 2 p The Orbital Maneuvering Vehicle (OMV) will serve as a 883-891 Jan 1985 shuttle-based or permanent space station-based vehicle designed Avail NTIS HC A23/MF A01 CSCL 22B to rendezvous and soft dock with various other free-flying space The major subassembhes of the Manipulator Positioning vehicles for purposes of inspection, support, and retneval This Mechanism (MPM) are descnbed and illustrated The Space Shuttle study is concerned pnmanly with the eventual need for the OMV Orbiter design provides that the MPM may be mounted on either to rendezvous and dock softly with the Edwin P Hubble Space left or nght sides of the payload bay, or both sides if two are Telescope (ST) Utilizing the available capabilities of the large flown This MPM is provided for the purpose of secunng the remote microwave anechoic chamber facility at Marshall Space Flight arm in stowed position dunng lift-off, boost, and landing It also Center for simulating docking target vehicle motions in a free-space 09 PROPULSION environment, a program is being devised for benchmark testing of A85-12926 rendezvous and docking sensor systems proposed for use on the THE STATE OF THE ART SOLAR SAIL AND THE OMV A testing regimen suitable for evaluating the accuracy and INTERSTELLAR PRECURSOR MISSION tracking agility in sensing range, range rate, and angle information G. L MATLOFF (Pratt Institute. Brooklyn, NY) British Interplanetary at close ranges (0 R 30m) has been developed G L C Society, Journal (Interstellar Studies) (ISSN 0007-084X), vol 37, Nov 1984, p 491-494 refs Current designs for interplanetary solar sailing, such as those of the World Space Foundation, could be modified to boost interstellar precursor probes on long-duration interstellar trajectories. In this paper, the utilization of the thinnest current Kapton sail for this application is examined A performance 09 envelope is generated using a modification of the previously published sail performance optimization program for optimistic and PROPULSION pessimistic sail thermal assumptions and payloads in the range of 10-100 kg Many configurations can boost interstellar medium probes capable of reaching Alpha Centaun in 7000-9000 years Includes propulsion concepts and designs utilizing solar sailing, Results derived from a three-dimensional interactive computer solar electric, ion, and low thrust chemical concepts graphics package are presented for thermal and stress effects on the sail-cable combination Author A85-12519# BIPROPELLANT PROPULSION IN THE NEW GENERATION OF SATELLITES AND UPPER STAGES: THE ROLE OF BPD DIFESA-SPAZIO IN THIS FIELD - MANUFACTURING FACILITIES AND TECHNOLOGY [LA PROPULSIONE A BIPROPELLENTE A85-13000# NELLA NUOVA GENERAZIONE Dl SATELLITI E UPPER DESIGN AND TECHNOLOGY TRENDS ON LARGE SOLAR STAGES: RUOLO DELLA BPD DIFESA-SPAZIO IN QUESTO ARRAYS FOR SPACE STATIONS CAMPO - IMPLANTISTICA E TECNOLOGIA] W WESTPHAL and J RATH (Telefunken AG, Wedel, West A. FABRIZI, G BAIOCCHI, M LIGUTTI, and A PETRIVELLI (BPD Germany) International Astro-nautical Federation, International Difesa-Spazio, Direzione Sviluppo e Ricerche, Colleferro, Italy) IN Astronautical Congress, 35th, Lausanne, Switzerland, Oct 7-13, International Scientific Conference on Space, 23rd, Rome, Italy, 1984 14 p March 24, 25, 1983, Proceedings. Rome, Rassegna Internazionale (IAF PAPER 84-37) Elettronica Nucleare ed Aerospaziale, 1984, p. 275-286 In Italian New design and technology requirements for large solar arrays The development of integrated storable-liquid-propellant operating in the environment of a space station are reviewed, propulsion systems (ISPS) for satellites and upper stages at BPD with particular attention given to blanket/solar cell assemblies, Difesa-Spazio is surveyed and illustrated with drawings, diagrams, structures and mechanisms, and special maintenance-related and a plan of the assembly plant The flexibility and performance devices It is shown that the overall configuration and system of ISPS are shown to make them well suited for LEO-GEO transfer concept are largely dictated by the operational environment of a missions, either as satellite propulsion or as upper stage for larger space station Both the indefinite service life of a space station payloads (for example in the weight-class gap between the STS and its growing power requirements call for a design that would PAM-A and IUS) The ISPSs developed for the ESA L-Sat and for incorporate the following features replaceability and add-on Italsat and proposed for an ESA STS-compatible upper propulsion capability made possible by a modular design of functional units, stage and an ESA large multipurpose platform (compnsmg one versatility of the system configuration, design testability by the ISPS, one service module, and three payload modules, to be Space Shuttle in a low earth orbit, and configuration control assembled in LEO with the STS manipulator arm after STS launch capability V L. and propelled to GEO by the ISPS) are characterized, and the assembly facility at Colleferro (including a class 30,000 and a class 100,000 cleanroom) is described T K

A85-12520# A85-13021# IRIS SPINNING STAGE - A PERIGEE STAGE FOR SATELLITES IN-ORBIT LASER REGENERATION OF THE RADIATION UP TO 900 KG TO BE LAUNCHED FROM THE SPACE SHUTTLE DAMAGED SOLAR ARRAYS WITH THE IRIS SYSTEM [IRIS SPINNING STAGE - UNO STADIO V POULEK (Ceskoslovenska Akademie Ved, Fyzikalni Ustav, Dl PERIGEO PER SATELLITI FINO A 900 KG DA LANCIARE Prague, Czechoslovakia) International Astronautical Federation, DALLO SPACE SHUTTLE CON IL SISTEMA IRIS] International Astronautical Congress, 35th, Lausanne, Switzerland, G. SOLPANELLI and G BALDI (BPD Difesa-Spazio, Direzione Oct 7-13, 1984 7 p refs Sviluppo e Ricerche, Colleferro, Italy) IN International Scientific (IAF PAPER 84-62) Conference on Space, 23rd, Rome, Italy, March 24, 25, 1983, Technological developments targeted at permitting laser Proceedings. Rome, Rassegna Internazionale Elettronica Nucleare annealing of space radiation-damaged solar cells on spin-stabilized ed Aerospaziale, 1984, p 287-299. In Italian satellites are outlined The concept is feasible because solar cell The design of the IRIS Spinning Stage (ISS), the propulsion defects can be removed by laser temperatures of 200-400 C, unit which with the reusable airborne support systems and the while the transfer of heat to the cell panel structure results in ground-support equipment comprises the IRIS GTO-miection structural temperatures below 100-200 C The structures are not system, is presented and illustrated with drawings The ISS includes damaged at temperatures under 200 C Tests with a 2 J/sq cm payload attachment and separation fittings, a thermal-control laser beam with a 1 msec pulse shone on Si solar cells revealed system, electronic systems (power supply, sequencer, and nutation no damage to soldered panel connections Future tests on cells control); telemetry (2K baud, 5-W, 22-23 GHz, with 80 analog irradiated in orbit are recommended If implemented, the technology and 48 digital channels), and an end-bummg-configuration would consist of a deployable laser-directing boom to guide the HTPB-1813 solid-fuel motor providing maximum total impulse 4 49 beam perpendicular to the satellite surface, tracing a spiral pattern MN sec with bum time 79 sec and propellant weight 1574 kg that eventually covers the entire surface A semiconductor laser The ISS is scheduled to achieve operational status by the end of would draw 10 V, which could be supplied directly from the panels 1986 TK without power conversion M S K.

43 09 PROPULSION

A85-13191# A85-16439*# National Aeronautics and Space Administration THE CHALLENGE OF ADVANCED SPACE TRANSPORTATION Lewis Research Center, Cleveland, Ohio AND PROPULSION SYSTEMS PERFORMANCE CAPABILITIES OF THE 12-CENTIMETER V R LARSON (Rockwell International Corp, Rocketdyne Div, XENON ION THRUSTER Canoga Park, CA) International Astronautical Federation, M MANTENIEKS and M SCHATZ (NASA, Lewis Research Center, International Astronautical Congress, 35th, Lausanne, Switzerland, Cleveland, OH) IN International Electric Propulsion Conference, Oct 7-13, 1984 32 p refs 17th, Tokyo, Japan, May 28-31, 1984, Proceedings Tokyo, Japan (IAF PAPER 84-310) Society for Aeronautical and Space Sciences, 1984, p 506-523 In connection with trends related to developments concerning Previously announced in STAR as N84-27825 refs space transportation, space missions, and the utilization of space, The 8- and 12-cm mercury ion thruster systems were developed challenges arise The present investigation is concerned with these primarily to provide N-S station keeping of satellites with masses challenges, taking into account aspects of system definition and up to about 1800 to 3600 kg respectively The on-orbit propulsion economic evaluation In an examination of the current situation, it requirements of recently proposed Large Space Systems (LSS) is found that for a reduction of space transportation costs it would are beyond the thrust capabilities of the baseline 8- and 12-cm be most beneficial to lower the cost for the boost (earth-to-LEO) thruster systems This paper presents a characterization of the phase A 50 percent reduction in this phase would reduce LEO performance capabilities of the 12-cm Xenon ion thruster to enable (low-earth-orbit) cost to the 500 to 750 U S $/lb range Space an evaluation of its application to LSS auxiliary propulsion missions are discussed, taking into account requirements, requirements With minor thruster modifications and simplifications projections of future flights, the replacement market (GEO the thrust was increased to 64 mN, a factor of six over the baseline satellites), competing technologies and future growth, and large 12-cm mercury thruster performance The thruster was operated space stations Attention is also given to propulsion conceps, over a range of specific impulse of about 2000 to 4000 seconds expendable and reusable LEO-to-GEO transfer vehicles, space and at total efficiencies up to 68 0 percent The operating levels transfer economics, and planetary and other scientific space reached in this study were found to be close to the operating missions G R limits of the thruster design in terms of perveance, grid breakdown voltage and thruster component temperatures such as those of the magnets and cathode baffle Author A85-13282*# National Aeronautics and Space Administration Johnson (Lyndon B) Space Center, TETHERED PROPELLANT RESUPPLY TECHNIQUE FOR SPACE STATIONS A85-16448# K. R KROLL (NASA, Johnson Space Center, Houston, TX) DESIGN AND BENEFITS OF PULSED MPD THRUSTER ORBIT International Astronautical Federation, International Astronautical TRANSFER VEHICLES Congress, 35th, Lausanne, Switzerland, Oct 7-13, 1984 8 p L K RUDOLPH (Martin Marietta Aerospace, Denver, CO) IN (IAF PAPER 84-442) International Electric Propulsion Conference, 17th, Tokyo, Japan, One of the primary functions of the space station is related to May 28-31, 1984, Proceedings Tokyo, Japan Society for the propellant resupply of orbital transfer vehicles, orbital Aeronautical and Space Sciences, 1984, p. 590-599 refs maneuvering vehicles, and satellites Difficulties arise in the case (Contract F04611-82-C-0049) of an acquisition of cryogenic propellants by means of a use of Two detailed orbit transfer vehicle (OTV) point designs have zero-gravity techniques The use of the 'tethered propellant been completed for pulsed self-field MPD thruster systems The resupply technique' is, therefore, considered A study is being first design is for a 200 kWe nuclear-powered reusable OTV capable conducted to determine the feasibility, design requirements, and of delivering a 20,000 kg payload to geosynchronous orbit (GEO) operational limitations of this technique Attention is given to The second design is for a 50 kWe solar-powered expendable aspects of gravity feed, transfer method selection, requirements OTV capable of delivering 5,000 kg to GEO These OTVs were related to the orbital transfer vehicle, hazard clearance, attitude compared to similar advanced LO2/LH2 chemical OTVs Although control, depot operations, end mass velocity, the microgravity both MPD thruster OTVs have lower launch masses and simpler laboratory, and concept evaluation activities G R mission operational requirements, overall life cycle cost estimates indicate that higher power levels or larger payloads are necessary for MPD thruster OTVs to be competitive Author A85-15874# SIMULATION OF REUSABLE CISLUNAR SPACE TRANSPORTATION SYSTEMS WITH SPECIAL CONSIDERATION OF CHEMICAL PROPULSION [SIMULATION A85-18671* Aerospace Corp, Los Angeles, Calif WIEDERVERWENDBARER RAUMTRANSPORTSYSTEME IM OPTIMAL LOW-THRUST, THREE-BURN ORBIT TRANSFERS CISLUNAREN RAUM UNTER BESONDERER WITH LARGE PLANE CHANGES BERUECKSICHTIGUNG CHEMISCHER ANTRIEBE] K P ZONDERVAN (Aerospace Corp, Performance Analysis Dept, R RESS Berlin, Techmsche Universitaet, Fachbereich Los Angeles, CA), L J WOOD (California Institute of Technology, Verkehrswesen, Dr-lng Dissertation, 1983, 188 p In German Jet Propulsion Laboratory, Navigation Systems Section, Pasadena, refs CA), and T K CAUGHEY (California Institute of Technology, The design of a multicomponent space transportation system Pasadena, CA) Journal of the Astronautical Sciences (ISSN to support such missions as nuclear-waste disposal, GEO 0021-9142), vol 32, Oct-Dec 1984, p 407-427 refs solar-power-satellite construction, and lunar mining or Optimal low-thrust, three-burn solutions have been obtained manufactunng is investigated by means of computer simulations for orbit transfers between a 28 5-degree inclined low earth orbit involving reusable chemically propelled spacecraft The simulation and a senes of 63 4-degree inclined circular orbits as well as a comprises mission, spacecraft, facilities, management, production, series of 63 4-degree inclined elliptical orbits with twelve hour and cost models and is based on currently available technologies periods Solutions have also been obtained for orbit transfers and current costs The main requirements for the system are supply between 97-degree inclined orbits and a 57-degree inclined low of a lunar station and transport of 100 Gg/yr or more from earth earth orbit Thrust to weight ratios as low as 0 02 were considered or moon to GEO, with a system life of about 60 yr, and it is A hybrid nonlinear programming method was used to obtain the found that they are best met by a two-stage 95 Gg ballistic solutions Analysis of the optimal steenng dunng various burns launcher, three types of shuttle vehicles, and space stations in reveals a natural division of the steering strategies into two GEO and lunar orbit to provide the shuttles with H2 and O2, categories based on whether a burn results in a change respectively Up to 730 launches and 1000 shuttle flights (on each predominantly in semi-major axis or orbit plane The similarity of route) per year at costs of $30-50/kg for earth-Leo, $100-150/kg these optimal steering strategies to previously obtained simple for earth GEO, anad $40-60/kg for moon-GEO predicted T K near-optimal steenng strategies is discussed Author

44 09 PROPULSION

A85-19561# A85-19715*# System Science and Software, San Diego, Calif SOLAR CONCENTRATOR FOR SPACE POWER GENERATION COMPUTER SIMULATION OF PLASMA ELECTRON J E LINDSAY and C S NERHEIM (Washington, University. COLLECTION BY PIX-II Seattle, WA) American Institute of Aeronautics and Astronautics, M J MANDELL, I KATZ, G A. JONGEWARD (System Science Aerospace Sciences Meeting, 23rd, Reno, NV, Jan 14-17, 1985 and Software, La Jolla, CA), and J C. ROCHE (NASA, Lewis 7 p refs Research Center, Cleveland, OH) American Institute of (AIAA PAPER 85-0164) Aeronautics and Astronautics, Aerospace Sciences Meeting, 23rd, A solar collector of Cassegramian type, designed to collect Reno, NV, Jan 14-17, 1985 9 p refs over 1000 kilowatts of solar energy, is presented When combined (Contract NAS3-23881) with energy storage, a dynamic energy conversion cycle, and a (AIAA PAPER 85-0386) liquid droplet radiator for heat rejection, the system has great A wake model was defined for the NASCAP/LEO finite element potential for space station applications. Wrapped nbs provide the model for the plasma interaction experiment (PIX-II) launched to supporting structure for the mirrors, and the reflective surface is study the interaction between high-voltage large solar arrays with to be alumimzed Kapton An opening at the base of the large the space plasma environment The cell surface model considers mirror provides the entrance to energy storage Located at this the individual cells, distances between interconnects, and the opening is a conic concentrator to enhance the energy gathering fraction of surface covered by interconnects Account is taken of capability of the system The component and total mass of a the electrostatic potential around the spacecraft, which travels at typical system is computed Computenzed ray tracing is used to 7500 mps, over five times the speed of thermal ions Ram ions examine the interaction between the structural and optical aspects are produced ahead of the array and the wake ion density is of the mirror system The aiming accuracy of the configuration is described with a geometric shadowing model The model correctly very sensitive to vibrations of the secondary mirror The effects of predicted the currents in high and low bias voltages when compared these on the focusing power of the mirrors is investigated, and to orbital data The panel snapover, however, was projected to the maximum allowable displacement is determined Author occur at 100 V and instead occurred at 300 V, which indicates that the snapover state is bistable Finally, a low potential was both predicted and measured in the wake M S K

A85-19660# THE LOW COST DEVELOPMENT, TEST, AND PRODUCTION A85-19744# OF A COMMERCIAL STS UPPER STAGE: TOS OPTIMAL ELECTRIC PROPULSION ORBIT TRANSFER T W WHITE, B E THOMPSON, and J R GRUBBS (Martin VEHICLE DESIGN AND OPERATIONAL EFFECTIVENESS Marietta Aerospace, Denver, CO) American Institute of L W MADDOX (USAF, Colorado Spnngs, CO), M M MEKARU, Aeronautics and Astronautics, Aerospace Sciences Meeting, 23rd, W C ELROD, and W E WIESEL (USAF, Institute of Technology, Reno, NV, Jan 14-17, 1985 8 p. Research supported by the Wnght-Patterson AFB, OH) American Institute of Aeronautics Orbital Sciences Corp. and Astronautics, Aerospace Sciences Meeting, 23rd, Reno, NV, (AIAA PAPER 85-0313) Jan 14-17, 1985 12 p refs The Space Transportation System (STS) has to compete for (AIAA PAPER 85-0431) commercial payload launches with a variety of expendable launch An analysis methodology for examining electnc propulsion vehicles (ELVs) Many of these payloads have to be placed into technologies for spacecraft and making compansons with other a final orbit which cannot be provided by the Shuttle Orbiter An propulsion systems is described Attention is focused on a reusable upper stage booster is, therefore, needed The Transfer Orbit Stage electnc orbit transfer vehicle (EOTV) with specific impulses (Isp) (TOS) is being developed to satisfy this need at a competitive of 1000-10,000 sec capable of moving large payloads to GEO user cost The requirements for the development and test program The technique involves design optimization for different electric for the TOS system are related to a 'minimum cost - minimum thruster technologies followed by a simulated fly-off among systems risk' approach In this context, the use of existing flight qualified with a 20 yr operational lifetime Optimization is earned out using 'off the shelf hardware is to be maximized Attention is given to the sequential unconstrained optimization technique, taking into a TDS system description, the development test objectives, and account the input power vs Isp and exhaust velocity relationship the TOS test program results G R and input power vs thrust Sample predictions are made for the EOTV, IDS, Centaur-G, and a reusable bipropeltant vehicle The EOTV is found to have the lowest life cycle cost/kg for payloads delivered to GEO M S K A85-19714# CIRCUIT TRANSIENTS DUE TO NEGATIVE BIAS ARCS ON A HIGH VOLTAGE SOLAR ARRAY IN LOW EARTH ORBIT R N METZ (Colby College, Waterville, ME) Amencan Institute A85-22444# of Aeronautics and Astronautics, Aerospace Sciences Meeting, FINITE MULTIPLE BURN ORBIT TRANSFER ERROR ANALYSIS 23rd, Reno, NV, Jan 14-17, 1985 7 p refs VIA COVARIANCE MATRIX (AIAA PAPER 85-0385) W YANG Chinese Society of Astronautics, Journal, no 4, 1984, Arcing to negabvely biased, exposed solar cell interconnects p 30-43 In Chinese, with abstract in English refs on solar arrays placed in plasma environments has been well The finite multiple bum method is used for the transfer from established in laboratory tests and inferred from space data Such Space Shuttle low earth orbit to the geostationary orbit with low arcing may cause damaging interference with the operation of accelerations In this case, the study of orbit transfer insertion electrical power systems in spacecraft planned to be driven with error becomes very complicated Generally speaking, an analytical high voltage solar arrays A simple analytical model has been method via covanance matrix is not suitable, and a semianalytical developed to estimate the effects of negative bias arcs on solar metod or digital method must be employed It is pointed out after array power system performance Solar cell characteristics, plasma detailed discussion that it is feasible for perigee bums to adopt a interactions and power system features are modeled approximately semianalytical method, and for apogee burn to adopt an analytical by a linear, lumped element transient circuit and the time domain method in order to save computation time. The paper descnbes equations are solved Exact numencal results for solar array the propagation matrices of perigee burns, apogee bum, and coast common-mode and load voltage transients are calculated for typical phase, and also provides a transfer matrix for orbit element error. conditions Acceptable load transients are found for a range of In addition, the flow chart and verification methods of the program arc current amplitudes and time constants Author are discussed in detail Finally, an example is given Author

45 09 PROPULSION

A85-23393*# Aerojet Techsystems Co, Sacramento, Calif among the number of stages and horizontal or vertical take-off INTEGRATABLE PROPULSION SYSTEMS FOR THE SPACE MSK STATION S D ROSENBERG, D C JUDD (Aerojet TechSystems Co, A85-24793# Sacramento, CA), and P W GARRISON (California Institute of NUCLEAR REACTORS FOR SPACE POWER Technology, Jet Propulsion Laboratory, Pasadena, CA) Journal D BUDEN Aerospace America (ISSN 0740-722X), vol 23, Feb of Propulsion and Power (ISSN 0748-4658), vol 1,Jan-Feb 1985, 1985, p 66-69 p 65-69 NASA-supported research Previously announced in STAR The growth in power demands for spacecraft, especially outer as N84-29933 refs planet missions, is dnvmg the development of space nuclear power Oxygen/hydrogen propulsion system options for space station systems Nuclear reactors could also be used to process lunar orbit maintenance and attitude control were developed and matenals to take advantage of order of magnitude lower fuel evaluated relative to monopropellant and storable bipropellant requirements to move construction components off the moon propulsion systems Space station propulsion requirements were instead of the earth Larger, more powerful broadcast satellites analyzed with reference to such considerations as station size, which lower the GEO station space demand could use nuclear altitude, power, crew size, and orbit transfer vehicle and orbital power, as could navigational systems, orbital transfer vehicles and maneuvering vehicle servicing requirements The evolutionary a manned Mars mission The SP-100 design is currently undergoing growth of oxygen/hydrogen bipropellant propulsion as an integral parametnc evaluation before engineenng studies begin Safety part of several interrelated space station functions, e g, life support, concerns are concentrated on preventing fissioning until the reactor power, and thermal management was considered Propellant is on-orbit and keeping the active or discarded reactor out of the resupply evolves from resupply based on transport of liquid oxygen atmosphere until the radioactivity has decayed to levels defined and liquid hydrogen to water The advantages of the operation of by international standards MSK the space station based on an oxygen/hydrogen economy are presented and discussed Author A85-25796 UNLIMITED POWER FOR OUR SPACE VEHICLES A85-23394*# Los Alamos Scientific Lab, N Mex L G CHIDESTER (Lockheed Missiles and Space Co, Inc, DESIGN OF A NUCLEAR ELECTRIC PROPULSION ORBITAL Sunnyvale, CA) Space Solar Power Review (ISSN 0191-9067), TRANSFER VEHICLE vol 4, no 3, 1983, p 211-228 D BUDEN (Los Alamos National Laboratory, Los Alamos, NM) Photovoltaic solar arrays which derive their energy from the and P W GARRISON (California Institute of Technology, Jet sun and provide the electrical power needed on long life space Propulsion Laboratory, Pasadena, CA) Journal of Propulsion vehicles are examined Present spacecraft solar arrays provide in and Power (ISSN 0748-4658), vol 1, Jan-Feb 1985, p 70-76 the range of 1-5 kW, however, lightweight flexible arrays with Previously cited in issue 17, p 2443, Accession no A84-37655 reduced cost and increased performance are being developed to refs provide serveral hundred kilowatts of power The state of the art of solar cell technology, Lockheed's development efforts on new solar arrays, and the upcoming NASA Solar Array Flight Experiment A85-23990 are described The experiment package includes a huge 4 x 32 m THE COST EFFECTIVENESS AND OPTIMAL PARAMETERS OF flexible solar array, a structure and mechanism for moving it out AN ELECTRIC ROCKET PROPULSION SYSTEM FOR AN of the shuttle cargo bay, and a complete data acquisition system INTERORBITAL TRANSPORT VEHICLE [EKONOMICHESKAIA to record operational data dunng ascent and on-orbit operations EFFEKTIVNOST' I OPTIMAL'NYE PARAMETRY Space Shuttle applications and three array concepts, developed ELEKTRORAKETNOI DVIGATEL'NOI USTANOVKI DLIA for space power sources in the 300 kW to 1 MW range, are MEZHORBITAL'NOGO TRANSPORTNOGO APPARATA] considered Examples of cost and efficiency improvements being D D SEVRUK, V K SHININ, and A F. SHTYRLIN Aviatsionnaia worked on include transparent arrays, multi-bandgap solar cells, Tekhnika (ISSN 0579-2975), no 3, 1984, p 65-69 In Russian thin-film solar cells, and improved concentrator systems Photos refs of the presently used solar arrays and drawings of the array The cost effectiveness of using an electnc propulsion system concepts are presented M D for an mterorbital transport vehicle for cargo delivery from a low near-earth orbit to a geostationary orbit is analyzed For given A85-25797 power plant parameters, charactenstic velocity, and initial mass of THE MAXIMUM EFFICIENCY OF AN ISOLATED SOLAR ENERGY the vehicle, the parameters of the electnc propulsion system are CONVERSION DEVICE IN SPACE optimized with respect to minimum cost per unit load It is shown C G ADLER and J W BYRD (East Carolina University, Greenville, that the use of an electric propulsion system can reduce the cost NC) Space Solar Power Review (ISSN 0191-9067), vol 4, no 3, of cargo delivery to a geostationary orbit by a factor of 1 5-3 2 in 1983, p 231, 232 companson with a liquid-propellant engine V L The conversion efficiency of radiant energy to work is considered Interest in energy-conversion devices isolated in space A85-24788*# National Aeronautics and Space Administration has prompted consideration of optimum location of these systems Langley Research Center, Hampton, Va to maximize the work extracted It is found that optimizing the ORBIT ON DEMAND - IN THIS CENTURY IF PUSHED extraction of work is better characterized by a global efficiency J A MARTIN (NASA, Langley Research Center, Space Systems defined in terms of the power extracted, the effective temperature Div, Hampton, VA) Aerospace Amenca (ISSN 0740-722X), vol of the sun, and the area of the receiver The global efficiency has 23, Feb 1985, p 46-48 a peak which occurs at about 1 5 sun radii from the center of the Performance requirements and design features of the next sun Author generation of manned launch vehicles are discussed The vehicles will launch within minutes of demand and will have a several-day A85-25828 turnaround time Launch and landing sites will have minimal ON THE POTENTIAL PERFORMANCE OF NON-NUCLEAR facilities Baseline requirements compose carnage and return of a INTERSTELLAR ARKS 5000 Ib, 7 ft diam, 15 ft long payload, a 160 n mi polar orbit, a G L MATLOFF (Pratt Institute, Brooklyn, NY) Bntish Interplanetary 200 fps on-orbit delt-V capability, provisions for two men for 24 Society, Journal (Interstellar Studies) (ISSN 0007-084X), vol 38, hr, an 1100 n mi cross range option, 500 flights/vehicle, land on March 1985, p 113-119 refs 10,000 ft runways, and be acceptable passing over populated Previous publications which have presented vanous aspects of areas Significant advances are needed in propulsion and fuel non-nuclear interstellar flight, are reviewed These papers have systems, lightweight durable structures and airbreathmg demonstrated the utility of optimized hyperthm or perforated solar acceleration engines Trade-offs have yet to be fully explored sails deployed behind occulters dunng close penhehon passes

46 09 PROPULSION

limited only by sail internal thermal constraints, multiple sail storage in wheels is an attractive concept for immediate technology missions, and electric propulsion dunng the pre-penhehon trajectory development and future Space Station application. B.W leg After accounting for the acceleration tolerance of the human occupants, trip times substantially less than 1000 years are possible for one-way missions to Alpha Centaun of payloads of 5 million kg or larger This paper extends this analysis and considers utilization of the Light Sail Windmill as a 'storage battery* and N85-13896*# TRW, Inc, Redondo Beach, Calif electnc propulsion for the early posl-penhelion trajectory leg of SPACE POWER MANAGEMENT AND DISTRIBUTION STATUS the mission The Light Sail Windmill's energy storage capability AND TRENDS will also be useful for on-board power dunng the long-interstellar G M REPPUCCI, J J BIESS, and L INOUYE In NASA Lewis cruise phase of the mission Appropriate combination of various Research Center Space Power p 205-218 Apr. 1984 refs propulsive techniques reveals that trip times of less than 800 Avail NTIS HC A14/MF A01 CSCL 10B years may ultimately be feasible Author An overview of space power management and distribution (PMAD) is provided which encompasses histoncal and current N85-12071*# Bartelle Columbus Labs, Ohio technology trends The PMAD components discussed include PRELIMINARY ANALYSIS OF SPACE MISSION APPLICATIONS power source control, energy storage control, and load power FOR ELECTROMAGNETIC LAUNCHERS Final Technical processing electronic equipment The status of distribution Report equipment comprised of rotary joints and power switchgear is L A. MILLER, E E RICE, R W EARHART, and R J CONLON evaluated based on power level trends in the public, military, and 30 Aug 1984 326 p refs commercial sectors. Component level technology thrusts, as driven (Contract NAS3-23354) by perceived system level trends, are compared to technology (NASA-CR-174067, MAS 1.26 174067) Avail NTIS HC A15/MF status of piece-parts such as power semiconductors, capacitors, A01 CSCL 22A and magnetics to determine critical bamers R S F The technical and economic feasibility of using electromagnetically launched EML payloads propelled from the Earth's surface to LEO, GEO, lunar orbit, or to interplanetary space was assessed Analyses of the designs of rail accelerators and coaxial magnetic accelerators show that each is capable of N85-16292*# Life Systems, Inc , Cleveland, Ohio. launching to space payloads of 800 KG or more A hybrid launcher ENGINEERING MODEL SYSTEM STUDY FOR A in which EML is used for the first 2 KM/sec followed by chemical REGENERATIVE FUEL CELL: STUDY REPORT rocket stages was also tested A cost estimates study shows that B J CHANG, F H SCHUBERT, A J KOVACH, and R A one to two EML launches per day are needed to break even, WYNVEEN Sep 1984 91 p refs compared to a four-stage rocket Development models are (Contract NAS3-21287) discussed for (1) Earth orbital missions, (2) lunar base supply (NASA-CR-174801, NAS 1 26 174801, LSI-TR-376-30) Avail mission, (3) solar system escape mission; (4) Earth escape NTIS HC A05/MF A01 CSCL 10A missions, (5) suborbital missions, (6) electromagnetic boost Key design issues of the regenerative fuel cell system concept missions, and (7) space-based missions Safety factors, were studied and a design definition of an alkaline electrolyte environmental impacts, and EML systems analysis are discussed based engineering model system or low Earth orbit missions was Alternate systems examined include electrothermal thrustors, an completed Definition of key design issues for a regenerative fuel EML rocket gun, an EML theta gun, and Soviet electromagnetic cell system include gaseous reactant storage, shared heat accelerators ARM exchangers and high pressure pumps A power flow diagram for the 75 kW initial space station and the impact of different N85-13371*# United Technologies Corp, South Windsor, Conn regenerative fuel cell modular sizes on the total 5 year to orbit Power Systems Dw weight and volume are determined System charactenstics, an REGENERATIVE FUEL CELL ENERGY STORAGE SYSTEM FOR isometnc drawing, component sizes and mass and energy balances A LOW EARTH ORBIT SPACE STATION are determined for the 10 kW engmeenng model system An open R E MARTIN, J. GAROW, and K B MICHAELS Aug 1984 loop regenerative fuel cell concept is considered for integration of 146 p refs the energy storage system with the life support system of the (Contract NAS3-22234) space station Technical problems and their solutions, pacing (NASA-CR-174802, NAS 1 26 174802, FCR-6128) Avail NTIS technologies and required developments and demonstrations for HC A07/MF A01 CSCL 10B the regenerative fuel cell system are defined E A K Results of a study to define the charactenstics of a regenerative fuel cell energy storage system for a large space station operating in low earth orbit (LEO) are presented The regenerative fuel cell system employs an alkaline electrolyte fuel cell with the option of employing either an alkaline or a solid polymer electrolyte N85-16302*# Lockheed Missiles and Space Co, Sunnyvale, electrolyzer R.S F Cahf DEMONSTRATION OF TRANSPARENT SOLAR ARRAY N85-13860'# Rockwell International Corp, Downey, Calif Shuttle MODULE DESIGN Final Report Integration and Satellite Systems Dw G J PACK Sep 1984 79 p Prepared for JPL PERSPECTIVES ON ENERGY STORAGE WHEELS FOR SPACE (Contract JPL-956608) STATION APPLICATION (NASA-CR-174257, NAS 1 26 174257, LMSC-D973437) Avail R E OGLEVIE In NASA Langley Research Center An NTIS HC A05/MF A01 CSCL 10A Assessment of Integrated Flywheel System Technol p 117-127 This report discusses the design, development, fabncation and Nov 1984 refs testing of IR transparent solar array modules. Three modules, Avail NTIS HC A18/MF A01 CSCL 108 consisting of a baseline design using back surface reflector cells, Several of the issues of the workshop are addressed from the and two modules using gndded back contact, IR transparent cells, perspective of a potential Space Station developer and energy were subjected to vacuum thermal balance testing to verify wheel user Systems' considerations are emphasized rather than analytical predictions of lower operating emperature and increased component technology The potential of energy storage wheel efficiency As a result of this test program, LMSC has verified (ESW) concept is discussed The current status of the technology that a significant degree of IR transparency can be designed into base is descnbed Justification for advanced technology a flexible solar array Test data correlates with both steady state development is also discussed The study concludes that energy and transient thermal analysis Author

47 09 PROPULSION

N85-16989*# National Aeronautics and Space Administration refrigeration at the LH2 tank A reversed Brayton cycle unit was Lewis Research Center, Cleveland, Ohio baselmed for the propellant processor It is concluded that (1) OTV PROPULSION ISSUES rehquefaction systems are not attractive for minimizing propellant Washington Apr 1984 296 p refs Conf held in Cleveland, boiloff, (2) open cycle systems may not be economically attractive 3-4 Apr 1984 for long term storage, (3) a number of refrigeration systems are (NASA-CP-2347, E-2171, NAS 1 552347) Avail NTIS HC available to assist in the long term storage of cryogenic propellents, A13/MF A01 CSCL 22B and (4) shields can significantly improve the performance of The statistical technology needs of aero-assist maneuvering, mechanical coolers R S F propulsion, and usage of cryogenic fluids were presented Industry panels discussed the servicing of reusable space based vehicles N85-17006*# National Aeronautics and Space Administration and propulsion-vehicle mteration Johnson (Lyndon B) Space Center, PROPELLANT TRANSFER: TETHERED DEPOT N85-16997*# National Aeronautics and Space Administration K KROLL In NASA Lewis Research Center OTV Propulsion Lewis Research Center, Cleveland, Ohio Issues p 191-206 Apr 1984 refs OTV PROPULSION TECNOLOGY PROGRAMMATIC Avail NTIS HC A13/MF A01 CSCL 211 OVERVIEW Spacebasing of orbital transfer vehicles at a space station L P COOPER In its OTV Propulsion Issues p 97-102 Apr requires a depot that safely and efficiently stores and transfers 1984 refs the resupply propellants In order to transfer propellants, a method Avail NTIS HC A13/MF A01 CSCL 22B effectively acquire only liquid and vent only gas must exist A An advanced orbit transfer vehicles (OTV) which will be an method that produces a low gravity to settle propellants would integral part of the national space transportation system to carry bypass these weaknesses, while allowing ground-like operations men and cargo between low Earth orbit and geosynchronous orbit This low gravity can be passively produced using gravity gradient will perform planetary transfers and deliver large acceleration limited techniques A satellite with a large length to diameter ratio, such space structures to high Earth orbits is reviewed The establishment as a depot attached to a space station with a tether, stabilizes of an advanced propulsion technology base for an OTV for the along on Earth radial because of an outward acceleration mid 1990's is outlined The program supports technology for three proportional to the distance from the satellite's center of gravity unique engine concepts Work is conducted to genenc technologies Analysis indicates that liquid can be setteled with relatively short which benefit all three concepts and specific technology which tether lengths The feasibility, design requirements, and operational benefits only one of the concepts Concept and technology limitations of a tethered refueling depot were investigated with definitions to identify propulsion innovations, and subcomponent special emphasis on slosh control R S F research to explore and validate their potential benefits are included E A K N85-17008*# National Aeronautics and Space Administration Lewis Research Center, Cleveland, Ohio N85-16999*# Aerojet Technical Systems Co, Sacramento, VEHICLE/ENGINE INTEGRATION Calif L P COOPER, T J VI NOPAL (Boeing Aerospace Co, Seattle), AEROJET ADVANCED ENGINE CONCEPT D E FLORENCE (General Electnc Corp, Fairfield, Conn), R W L SCHOENMAN In NASA Lewis Research Center OTV MICHEL (Aerojet TechSystems Co), J R BROWN (Pratt and Propulsion Issues p 113-125 Apr 1984 refs Whitney Aircraft, East Hartford, Conn), R P BERGERON Avail NTISHCA13/MF A01 CSCL 20H (Rockwell International Corp, Pittsburg), and V A WELDON In The future orbit transfer vehicle (OTV) requirements which its OTV Propulsion Issues p 229-245 Apr 1984 refs dictate the need for a highly versatile, highly reliable, reusable Avail NTISHC A13/MFA01 CSCL 22B propulsion module are discussed To attain maximum operational VEHICLE/ENGINE Integration Issues are explored for orbit economy, space-basing is essential This requires a reusable, transfer vehicles (OTV's) The impact of space basing and maintenance free engine The design features of this space based aeroassist on VEHICLE/ENGINE integration is discussed The engine are defined A new engine cycle and its advantages allow AOTV structure and thermal protection subsystem weights were all the maintenance goals to be attained Rubbing contact and scaled as the vehicle length and surface was changed It is interpropellant seals and purges are eliminated when GO2 is used concluded that for increased allowable payload lengths in a to drive the LO2 pump The TPA design has only one moving ground-based system, lower length-to-diameter (L/D) is as part The use of both GH2 and QO2 to drive the turbines lowers important as higher mixture ration (MR) in the range of mid L/D the turbine temperatures in addition lower GH2 temperatures and ATOV's Scenario validity, geometry constraints, throttle levels, pressures improve chamber cooling and longer life The use of reliability, and servicing are discussed in the context of engine GO2 as a turbine dnve fluid is addressed Space based engines design and engine/vehicle integration R.S F require an integrated control and health monitoring system to improve system reliability and eliminate all scheduled maintenance N85-17009*# Rockwell International Corp, Richardson, Tex. It is concluded that all OTV propulsion requirements can be fulfilled ORBITAL TRANSFER VEHICLE PROPULSION ISSUES with a single engine The technological developments required to R P BERGERON and V A WELDON In NASA Lewis Research demonstrate that engine are outlined E A K Center OTV propulsion Issues p 246-251 Apr 1984 refs Avail NTIS HC A13/MF A01 CSCL 22B N85-17004*# Jet Propulsion Lab, California Inst of Tech , The development of a reusable and space-based orbital transfer Pasadena vehicle (OTV) necessitates an integral approach toward structural ACTIVE COOLING REQUIREMENTS FOR PROPELLANT and propulsion subsystems design A single engine installation STORAGE necessitates moving the engine further aft and/or relocation of G A KLEIN In NASA Lewis Research Center OTV Propulsion the engine gimbal point to accommodate vehicle control Issues p 165-177 Apr 1984 refs requirements Penalties associated with gimbal point relocation Avail NTIS HC A13/MF A01 CSCL 211 without increasing stage length or modifying typical advanced Recent NASA and DOD mission models have indicated future engine concepts, as well as a method for minimizing such penalties, needs for orbital cryogenic storage and supply systems Two are presented for a single engine toroidal tank OTV configuration thermal control systems which show the greatest promise for Alternative integrated vehicle structure/engine concepts are also improving propellant storage life were evaluated One system was presented for multi-engine configurations Features of these an open cycle thermodynamic vent type with a refrigeration system potential concepts are given which indicate the need for substantial for partial hydrogen rehquefaction located at the LH2 tank and a additional study of feedlme gimbal alternatives before firmly vapor cooled shield for integrated and non-integrated tank designs establishing advanced engine design The issue of vehicle/engine to reduce boiloff The other was a closed system with direct integration is addressed in three areas interfaces (physical and

48 09 PROPULSION functional), installation requirements, and reliability apportionment N85-20002*# Rockwell International Corp, Downey, Calif Space (i e, number of engines required to assure mission completion). Transportation Systems Div RSF SPACE TRANSPORTATION SYSTEM (STS) PROPELLANT SCAVENGING SYSTEM STUDY. VOLUME 3: COST AND WORK BREAKDOWN STRUCTURE-DICTIONARY Final Report Jan 1985 43 p 3 Vol N85-19018# National Aerospace Lab, Tokyo (Japan) (Contract NAS9-16994) PARTIAL BLEED EXPANDER CYCLE FOR LOW THRUST (NASA-CR-171850-VOL-3, NAS 1 26.171850-VOL-3, LOX/LH2 ROCKET ENGINE DRL-T-1811-VOL-3.STS-84-0570-VOL-3) Avail NTIS HC Y. WAKAMATSU, A KANMNURI, and K TOKI (Inst. of Space A03/MF A01 CSCL 22B and Astronautical Science) Sep 1984 13 p refs Fundamentally, the volumes of the oxidizer and fuel propellant (NAL-TR-837T, ISSN-0389-4010) Avail NTIS HC A02/MF A01 scavenged from the orbiter and external tank determine the size The expander cycle or the coolant bleed cycle LOX/LH2 engine and weight of the scavenging system The optimization of system is considered suitable for use with the orbit transfer vehicle and dimensions and weights is stimulated by the requirement to the upper stage of a conventional rocket because of their simplicity minimize the use of partial length of the orbiter payload bay Thus, of engine system However, these engine cycles generally require the cost estimates begin with weights established for the optimum a thrust chamber with a high expansion area ratio in order to design Both the design, development, test, and evaluation and obtain a high performance and necessanly require a High Altitude theoretical first unit hardware production costs are estimated from Test Facility even in the initial phase of development A new parametric cost weight scaling relations for four subsystems. For engine cycle called the 'Partial Bleed Expander (PBE) cycle is cryogenic propellents, the widely differing characteristics of the proposed In the PBE cycle, only the turbopump of one propellent oxidizer and the fuel lead to two separate tank subsystems, in (usually LH2) is dnven in the expander cycle and a portion of fuel addition to the electrical and instrumentation subsystems is bled to dnve the turbopump of the other propellent (usually Hardwares costs also involve quantity, as an independent variable, LOX) The bled fuel may be utilized for dump cooling or film since the number of production scavenging systems is not firm cooling From the calculation of the PBE cycle, it was clear that For storable propellants, since the tankage volume of the oxidizer the PBE cycle can perform at a level close to that of the expander and fuel are equal, the hardware production costs for developing cycle with the bleeding rate resulting in minimum ISp loss B W these systems are lower than for cryogenic propellants Author

N85-20000*# Rockwell International Corp , Downey, Calif Space N85-20376*# Air Force Wnght Aeronautical Labs, Transportation Systems Div Wright-Patterson AFB, Ohio SPACE TRANSPORTATION SYSTEM (STS) PROPELLANT THE SATELLITE SAIL SCAVENGING SYSTEM STUDY. VOLUME 1: TECHNICAL J PEARSON In NASA Marshall Space Flight Center Appl of REPORT Final Report Tethers in Space, Vol 2 6 p Mar 1985 Jan 1985 293 p refs 3 Vol Avail NTIS HC A14/MF A01 CSCL 02B (Contract NAS9-16994) It is proposed to suspend an airfoil from the Space Shuttle by (NASA-CR-171848-VOL-1, NAS 1 26 171848-VOL-1, a long tether into the upper atmosphere to provide a horizontal DRL-T-1811-VOL-1, STS-84-0570-VOL-1) Avail NTIS HC force on the Shuttle, thereby changing its orbital plane most A13/MF A01 CSCL 22B efficiently The airfoil would need high-temperature skin and tether, The objectives are to define the most efficient and cost effective and remotely controlled flaps to adjust its angle of attack The methods for scavenging cryogenic and storable propellants and airfoil could also be used as a hypersonic facility to measure then define the requirements for these scavenging systems For aerodynamic characteristics at extreme altitudes and velocities cryogenic propellants, scavenging is the transfer of propellants This use would require a vertical lift force to counteract the drag from the Shuttle orbiter external tank (ET) and/or mam propulsion force and prevent the Shuttle orbit from decaying too rapidly during subsystems (MRS) propellant lines into storage tanks located in the aerodynamic measurements Author the orbiter payload bay for delivery to the user station by a space based transfer stage or the Space Transportation System (STS) by direct insertion For storable propellants, scavenging is the direct transfer from the orbital maneuvering subsystem (OMS) and/or N85-20862# Los Alamos Scientific Lab, N Mex Advanced tankage in the payload bay to users in LEO as well as users in Energy Conversions Systems the vicinity of the Space Station B G OPENING UP THE FUTURE IN SPACE WITH NUCLEAR POWER D BUDEN and J ANGELO, JR (Florida Inst of Technology, Melbourne) 1985 22 p refs Presented at the 2nd Symp on N85-20001*# Rockwell International Corp, Downey, Calif Space Space Nucl Power Systems, Albuquerque, N Mex Transportation Systems Div (Contract W-7405-ENG-36) SPACE TRANSPORTATION SYSTEM (STS) PROPELLANT (DE85-002411, LA-UR-84-3388, CONF-850103-2) Avail NTIS SCAVENGING SYSTEM STUDY. VOLUME 2: SUPPORTING HC A02/MF A01 RESEARCH AND TECHNOLOGY REPORT Final Report Man's extraterrestrial development is dependent on abundant Jan 1985 17 p 3 Vol power For example, space based manufacturing facilities are (Contract NAS9-16994) projected to have a power demand of 300 kWe by the end of (NASA-CR-171849-VOL-2, NAS 1 26.171849-VOL-2, this century, and several megawatts in the early part of next DRL-T-1811-VOL-2, STS-85-0570-VOL-2) Avail NTIS HC millenium The development of the lunar resource base will result A02/MF A01 CSCL 22B in power needs ranging from an initial 100 kW(e) to many The technology effort required for the development of a megawatts Human visits to Mars could be achieved using a propellant scavenging system is identified For a cryogenic multimegawatt nuclear electnc propulsion system or high thrust propellant system, the development tests identified are for a nuclear rockets Detailed exploration of the solar system will also cryogenic capillary acquisition system for zero-g feedout capability be greatly enhanced by the availability of large nuclear electnc and for definition of existng Space Transformation System (STS) propulsion systems All of these activities will require substantial performance capabilities. For a storable propellant system, the increases in space power - hundreds of kilowatts to many development tests identified are for three major components megawatts The use of nuclear energy to support humanity's required in the system a propellant pump, a helium compressor, expansion into space is explained and applications are given and a zero leakage fluid disconnect Author DOE

49 09 PROPULSION

W85-21231*# National Aeronautics and Space Administration designed to be installed in a pressunzed room within a freely Lewis Research Center, Cleveland, Ohio falling generation-travel starship, an interplanetary spacecraft, or ADVANCED RESEARCH AND TECHNOLOGY PROGRAMS FOR an orbiting space colony The growth chamber system will provide ADVANCED HIGH-PRESSURE OXYGEN-HYDROGEN ROCKET fresh vegetables and oxygen replenishment for the occupants of PROPULSION the vehicle or colony In this system, the growing plants are potted S J MARSIK and S F MOREA (NASA Marshall Space Flight in sealed boxes that protect the roots from light and supply the Center) 1985 14 p refs Proposed for presentation at the roots with a sustaining aerosol of water and nutnents The leaves 1985 JANNAF Propulsion Meeting, San Diego, Calif, 9-12 Apr and stems of the plants extend outside of the boxes where they 1985 are exposed to fluorescent light Both the physical configuration (NASA-TM-86969, E-2495, NAS 1 1586969) Avail NTIS HC and the biological attributes of the system are presented for the A02/MF A01 CSCL 20H guidance of the reader Author A research and technology program for advanced high pressure, oxygen-hydrogen rocket propulsion technology is presently being A85-12979# pursued by the National Aeronautics and Space Administration COST EFFECTIVE LAUNCH TECHNOLOGY FOR (NASA) to establish the basic discipline technologies, develop the COMMUNICATIONS SATELLITES analytical tools, and establish the data base necessary for an T C TAYLOR (Taylor and Associates, Inc, Wnghtwood, CA) and orderly evolution of the staged combustion reusable rocket engine A OVERMAN International Astronautical Federation, International The need for the program is based on the premise that the USA Astronautical Congress, 35th, Lausanne, Switzerland, Oct 7-13, will depend on the Shuttle and its derivative versions as its pnncipal 1984 10 p refs Earth-to-orbit transportation system for the next 20 to 30 yr The (IAF PAPER 84-04) program is focused in three pnncipal areas of enhancement (1) The present investigation is concerned with the possibility to life extension, (2) performance, and (3) operations and diagnosis reduce the costs for placing satellites in orbit by making use of Within the technological disciplines the efforts include an 'Air Launch' system It is pointed out that the launching of rotordynamics, structural dynamics, fluid and gas dynamics, rockets to orbit from aircraft in flight has been done successfully matenals fatigue/fracture/life, turbomachinery fluid mechanics, It is suggested to modify the existing technology for the purpose ignition/combustion processes, of launching communications satellites and other payloads to orbit manufactunng/producibihty/nondestructive evaluation methods and Thus, the Air Launch Concept combines aircraft and missile matenals development/evaluation An overview of the Advanced technologies to produce a method of transport to orbit A heavy High Pressure Oxygen-Hydrogen Rocket Propulsion Technology lift cargo aircraft is employed to fly a rocket and the satellite Program Structure and Working Groups objectives are presented payload to a specific location at the service ceiling of the aircraft with highlights of several significant achievements Author Attention is given to aspects of cost reduction, commercial and technical benefits, the anticipated market, and technical details GR

A85-12981# LAY-OUT OF A RE-USABLE RE-ENTRY VEHICLE REQUIRED GENERAL IN A FUTURE EUROPEAN LOW EARTH ORBIT SCENARIO H T UEBELHACK (Dormer System GmbH, Fnednchshafen, West Includes either state-of-the-art or advanced technology which may Germany) and J FAVE (ONERA, Chatillon-sous-Bagneux, apply to Large Space Systems and does not fit within the previous Hauts-de-Seine, France) International Astronautical Federation, categones Publications of conferences, seminars, and workshops International Astronautical Congress, 35th, Lausanne, Switzerland, are covered in this area Oct 7-13, 1984 6 p (IAF PAPER 84-06) The design concept of a reusable unmanned A85-10261*# Tel-Aviv Umv (Israel) semiballistic-reentry spacecraft to provide raw matenals and return A CASE FOR GOHRERfl - GEOSYNCHRONOUS ORBIT HIGH processed matenals from a European automated space production RESOLUTION EARTH MONITORING facility in LEO is presented and illustrated with drawings, diagrams, J. OTTERMAN (Tel Aviv University, Tel Aviv, Israel), V V graphs, and tables of parameters A typical mission scenario SALOMONSON, D ATLAS, W SHENK, M S MAXWELL (NASA, includes Ariane launch, rendezvous and docking for sample Goddard Space Flight Center, Greenbelt, MD), and D E PITTS exchange, center-of-mass tnmmmg by adjustment of the load after (NASA, Johnson Space Center, Houston, TX) IN International dedockmg, updating of mertial systems, deorbiting to a ballistic Symposium on Remote Sensing of Environment, 17th, Ann Arbor, arc by means of four 400-N thrusters, atmospheric flight from Ml, May 9-13, 1983, Proceedings Volume 3 Ann Arbor, Ml, 100-km altitude at path angle 4 deg, lift/drag ratio 02, and Environmental Research Institute of Michigan, 1984, p maximum deceleration 5 g, and final deceleration and landing using 1125-1135 refs three-stage drogue and mam-parachutes, an air-bag system, and Although the constant viewing geometry of the geostationary landing gears T K orbit simplifies quantitative monitonng of study areas, the high satellite altitude, in conjunction with the need for high spatial A85-12994# resolution, leads to large and complex sensors and spacecraft SPACE STATION RELATED INVESTIGATIONS IN EUROPE State-of-the-art linear array detectors and a telescope of 1 m W WIENSS (ERNO Raumfahrttechmk GmbH, Bremen, West diameter and 10 m focal length can meet the requirements in Germany) and E VALLERAIN (Aentalia S p A , Turin, Italy) question, which include a scan rate of the ground of at least 25 International Astronautical Federation, International Astronautical km/sec, the ability to cover a 150 X 150-km scene every several Congress, 35th, Lausanne, Switzerland, Oct 7-13, 1984 29 p. minutes, and an instantaneous field of view of 50 m in the visible (IAF PAPER 84-28) portion of the spectrum and 1000 m in the IR O C Studies pertaining to the definition of Europe's role in the Space Station program are descnbed, with consideration given to such A85-12927 elements as pressunzed modules as laboratones for matenals SPACE GREENHOUSE DESIGN processing and life sciences, unpressunzed elements, and service N E LEGGETT and J A FIELDER Bntish Interplanetary Society, vehicles for on-orbit maintenance and repair activities Candidate Journal (Interstellar Studies) (ISSN 0007-084X), vol 37, Nov 1984, elements were selected against such criteria as clean interfaces, p 495-498 the satisfaction of European user needs, new technology items, This paper presents a design of a plant growth chamber system and European financial capabilities, and their technical and for a zero gravity environment This growth chamber system is programmatic implications were examined Different scenarios were

50 10 GENERAL considered, ranging from a fully Space-Station-dependent case to A85-13259# a completely autonomous, free-flying man-tendable configuration SPACE AS MOTIVATIONAL PROPULSION Recommendations on a collaboration between Europe and the L W DAVID (National Space Institute, Washington, DC) United States are presented B.J International Astronautical Federation, International Astronautical Congress, 35th, Lausanne, Switzerland, Oct. 7-13, 1984 12 p refs A85-13114*# National Aeronautics and Space Administration, (IAF PAPER 84-407) Washington, D.C Several student activities for motivating continued intellectual ASSESSMENT OF MEDICAL RISK IN SPACE FLIGHT efforts directed at space-related fields are descnbed The long A NICOGOSSIAN. P RAMBAUT. and S POOL (NASA, duration exposure facility, deployed from the Orbiter in 1984 and Washington, DC) International Astronairbcal Federation, due to be retneved in 1985, contained bags containing a total of International Astronautical Congress, 35th, Lausanne, Switzerland, 9 million tomato seeds shielded from radiation to varying degrees Oct. 7-13, 1984 5 p refs The seeds will be distributed to students from grades 5 to university (IAF PAPER 84-189) level for expenmentation An amateur space telescope is being Among the various manned space missions expected dunng constructed by 700 participants in 15 countries under the guidance the next 10 years are flights of up to 6 months duration in low of university faculty and optics engineers Test components will earth orbit as well as short excursions to geosynchronous orbit. be flown in Getaway Special cannisters and then used in the Research activities are described which cover the full spectrum of flight hardware Reception of images from the 175 Ib telescope physiological and psychological problems presented by such flights will be possible anywhere on the planet for $400-500 worth of as well as by ongoing Shuttle flights This paper includes a summary equipment The Solar Mesosphere Explorer is monitored by of the major technical thrusts needed for habitation in space It university students interfacing with NASA tracking network NASA concludes that there is a high probability of developing has initiated a Young Astronauts program to encourage interest in countermeasures that will alleviate the neurophysiological and space and participation in science projects and math Finally, cardiovascular effects encountered dunng Shuttle flights and that discussions are underway between NASA and an entrepreneur to the resolution of musculoskeletal, psychological and radiobiological devise a module that will permit dozens of tounsts to fly on a 3 problems will also prove possible Author day mission at the same time at a cost of $2-3 million per seat MSK A85-13141# A85-13276*# National Aeronautics and Space Administration, TOS AND AMS - AMERICA'S NEW CAPABILITIES IN SPACE Washington, DC TRANSPORTATION APPLICATIONS OF SPACE TETHERS D W THOMPSON (Orbital Sciences Corp, Vienna, VA) I BEKEY (NASA, Office of Space Flight, Washington, DC) International Astronautical Federation, International Astronautical Congress, 35th, Lausanne, Switzerland, Oct 7-13, 1984 11 p International Astronautical Federation, International Astronautical (IAF PAPER 84-220) Congress, 35th, Lausanne, Switzerland, Oct 7-13, 1984 10 p The arrangements with NASA in the form of Memorandums of (IAF PAPER 84-436) The dynamics of orbiting tethered bodies are reviewed and Understanding and contracts with a private company to produce a line of transfer orbit stages (TOS) apogee and maneuvenng several practical aphcations are examined Two tethered masses in orbit will seek a local vertical orientation and a stable equilibrium, stages (AMS) are descnbed, along with the hardware features TOS/AMS will provide GEO and other high orbit boosts from LEO with energy transferred to the 'upper' object The tether tensions are provided by accelerations as low a 0 0004 g, permitting long The company subcontracts the hardare development to aerospace tethers an relatively large masses at the ends The Shuttle can firms already building hardware for the Shuttle Financing of the expenses has been done through limited partnerships TOS is send a payload into a transfer orbit by placing it at the upper end of the tether, unreeling the tether, then releasing the tether and intended for payloads with masses between those handled by the PAM and Centaur boost motors Design features include reaction thereby imparting the excess energy to the satellite while the Orbiter thrusters, laser-gyroscope avionics, solid propellents, and a falls to a lower pengee A 10 ton payload could be unreeled on a gimballed nozzle The AMS uses hypergohc fuels and is actually 148 km tether, released to a 12 n mi apogee, and the Orbiter a modified MX missile fourth stage A joint TOS/AMS configuration would be in full deorbit Similarly, the Orbiter can tether down to is suitable for boosting planetary missions from LEO Details of deorbit form the Space Station, boosting the Station to a higher the airborne and grounds support systems of the two boosters orbit. The station can then unreel a large satellite, release it to a are provided M S K higher orbit, thereby returning to the stations ongmal orbit Unreeling a wire 10 km from the Space station and having the wire cut the earth's magnetic field lines, then closing the contact between the A85-13148# upward and lower ends of the wire, can, with modifications, either AN ECONOMIC ANALYSIS OF HUMANS AND MACHINES FOR provide power or thrust without propellents for the Station SPACE CONSTRUCTION MSK. D G STUART (MIT, Cambndge, MA) International Astronautical Federation, International Astronautical Congress, 35th, Lausanne, A85-14426 Switzerland, Oct 7-13, 1984 17 p EASCON '83; PROCEEDINGS OF THE SIXTEENTH ANNUAL (IAF PAPER 84-232) ELECTRONICS AND AEROSPACE CONFERENCE AND Cost-dnving factors associated with the personnel/teleoperators EXPOSITION, WASHINGTON, DC, SEPTEMBER 19-21, 1983 necessary for the construction of large space structures are Conference and Exposition sponsored by IEEE, Amencan Satellite outlined The structures would be in a 260 km LEO Construction Co, BDM Corp, et al New York, Institute of Electrical and workers would be humans in pressunzed suits, humans in EVA Electronics Engineers, 1983, 508 p For individual items see and teleoperators working from a Shuttle base, and free-flying A85-14427 to A85-14469 teleoperators A line-item cost input was used, based on historical Numerous topics pertinent to earth and space-based segments data, to perform the calculations, which included all ground-support of space remote sensing, computer/software systems, military costs Attention was focused on a baseline mission to construct a command, control and communications, data processing, and 725 m diam microwave radiometer for earth remote sensing The telecommunications technologies are discussed Attention is given strongest cost driver was the productivity of the human construction to potential Space Station configurations and uses, NASA advanced crew, followed by launch costs and the learning curve satellite communications technology development, systems for Teleoperators were projected to be 1/3-4/5 as productive as surveillance-detection from space and earth, and artificial humans Further research is, however, needed to more finely hone intelligence software tools Fail safe/fault tolerant electronic the predictions of the capabilities of teleoperators M S K systems are descnbed, as are survivable communications,

51 10 GENERAL distributed data bases and data base management systems, and slightly higher than in 1979 However, little attention has been a standard local area network for military operations Consideration paid to proposals regarding large space platforms and recoverable is also devoted to hardware for powering DBS transmitters and launchers Now the Future Prospects Group representing the multi-beam antennas for communications satellites M S K industrial interest in Eurospace has been set up, and the progress of this group is discussed Attention is given to the level of Europe's A85-15509# space activities in a worldwide context, the mean annual value of A RECTILINEAR GUIDANCE STRATEGY FOR SHORT ORBITAL governmental and commercial markets accessible to the European TRANSFERS space industry, developments in the communication market, the S A STERN (Colorado, University, Boulder, Martin Marietta Anane market, the development of a new generation of launchers Aerospace, Denver, CO) Journal of Spacecraft and Rockets for 1992, and the space industrialization market G R (ISSN 0022-4650), vol 21, Nov-Dec 1984, p 542-545 Research supported by the Martm-Manetta Aerospace refs The solutions to Clohessy-Wiltshire equations of motion have been approximated for short transfer times For such transfers, A85-16305 these solutions describe decoupled rectilinear trajectories that are AN UNMANNED PLATFORM AS AN INITIAL CAPABILITY IN easy to implement The bounds over which this rectilinear SPACE approximation holds are explored Separate normalized error T J SHESKIN (Cleveland State University, Cleveland, OH) British functions then are derived for both in-plane and out-of-plane motion Interplanetary Society, Journal (Space Technology) (ISSN From these error functions transfer time limits are denved Further 0007-084X), vol 37, Dec 1984, p 555-558 refs it is shown that in-plane motion diverges from straight-line paths An automated, unmanned space platform is proposed as a much more rapidly than out-of-plane motion Rectilinear guidance lower risk, lower cost alternative to a permanently manned space strategies are of importance to terminal rendezvous and station Many operations on a space platform are performed by extravehicular as well as satellite servicing operations Author telepresence controlled from the ground A space platform is supported by 20-day visits by the Space Shuttle every two months A85-15976 Mission requirements for a space station are analyzed Advantages TECHNOLOGY VECTORS; PROCEEDINGS OF THE and limitations of a space platform are identified A space platform TWENTY-NINTH NATIONAL SAMPE SYMPOSIUM AND is shown to be capable of performing almost all of the missions EXHIBITION, RENO, NV, APRIL 3-5, 1984 intended for a space station, at a lower cost, although some Symposium and Exhibition sponsored by the Society for the missions will be completed more slowly Author Advancement of Matenal and Process Engineenng Covma, CA, Society for the Advancement of Material and Process Engineering (Science of Advanced Materials and Process Engineering Series A85-16881 Volume 29), 1984, 1615 p. For individual items see A85-15977 to THE GERMAN REMOTE SENSING PROGRAM [DAS DEUTSCHE A85-16000, A85-16002, A85-16003, A85-16006 to A85-16009, ERDERKUNDUNGSPROGRAM] A85-16011, A85-16013 to A85-16015, A85-16017 to A85-16070 H STRUB (Bundesmmisterium fuer Forschung und Technologie, Among the topics discussed are structures and materials Unterabteilung Luftfahrt und Weltraum, Bonn, West Germany) technologies for spacecraft systems, room temperature-cure Zeitschrrft fuer Flugwissenschaften und Weltraumforschung (ISSN structural adhesives, computer-controlled filament winding, 0342-068X), vol 8, Sept-Oct 1984, p 293-296 In German thermomechamcal criteria for the selection of encapsulation A short survey gives the objectives and present state of the materials, the behavior of woven graphite/epoxy composite at very national program, which is part of the German Space Program high strain rates, spacecraft structure damping, the finite element The program involves close international cooperation within ESA analysis of joints involving graphite/epoxy tubes and metallic and with NASA Discussion of future planning of projects and fittings, materials properties data base computerization, the elastic research fields shows the advantages of cooperation between stiffness of biaxial and tnaxial woven fabric composites, and classical type satellites and elements of the future space station damage accumulation and fracture initiation in composite laminates A national basis for earth observation is an additional requirement Also discussed are the compatibility of resin properties with high for the future and will be best secured by further extension to the strength carbon fibers, a systematic approach to the development German Remote Sensing Data Center at DFVLR Author of resins for damage-tolerant composites, adhesive-bonded noise suppression structures for aircraft, continuous systems for the production of hot melt adhesives, creep behavior in kevlar/epoxy composites, braided fabric properties and applications, UV-curmg A85-17573* National Aeronautics and Space Administration, resin systems for electronics, composite springs, martensitic Washington, D C transformations and the shape-memory effect, fine-grained THE NASA MLA PROGRAM superplastic matenals, polyphenylene sulfide-based composites, K J ANDO (NASA, Washington, DC) IN 1983 International thick-wall kevlar/epoxy pressure vessels, thermoplastic composite Geoscience and Remote Sensing Symposium (IGARSS '83), San matrices with improved solvent resistance, electrically conducting Francisco, CA, August 31-September 2, 1983, Digest Volume 2 composites, composite applications in sporting goods, metal New York, Institute of Electrical and Electronics Engineers, Inc, moisture bamers for composites, and cost-effective tape-laying 1983, 6 p refs techniques O C The NASA Multispectral Linear Array (MLA) program is structured to provide for the evolutionary development of advanced A85-16302 sensor concepts, technologies, and scientific basis for future remote FUTURE PROSPECTS IN SPACE ENVISAGED BY A FORUM sensing missions Program elements include the development of OF EUROPEAN SPACE COMPANIES multispectral visible and shortwave infrared (SWIR) detector arrays, M TOUSSAINT (Eurospace, Pans, France) (European Space optics and on-board signal processing technologies, sensor design Symposium, 18th, London, England, June 8, 9, 1983) Bntish studies, and supporting research The research consists of Interplanetary Society, Journal (Space Technology) (ISSN advanced airborne sensor development with data acquisitions, field 0007-084X), vol 37, Dec 1984, p 537-540 measurements, and supporting science studies At the present In June 1980, Eurospace, the Association of the European time, two instrument concepts, including an imaging spectrometer, space industry, presented a paper based on a set of proposals are in development as payloads for a senes of Shuttle remote for a European long term space program A study of this paper sensing research flights beginning as early as 1987 Progressively shows that the effort devoted by Europe to space activities was more advanced capability instruments suitable for extended decreasing The current situation (1983) is compared with the duration Shuttle, free flyer, and space platform missions in the situation three years earlier It is found that the ESA budget is 1990's are also being studied Author

52 10 GENERAL

A85-19795*# National Aeronautics and Space Administration, agencies and their strict limitation by NASA (to the laboratory Washington, 0 C module that became Spacelab) during the first half of 1972 are SPACELAB HITCHHIKER, A QUICK REACTION CARRIER recounted, the provisions of the final decision of December 1972, E. F JAMES, J. E. MOVE, and R L LOHMAN (NASA, Washington, are summarized (including commitment to Spacelab, creation of DC) American Institute of Aeronautics and Astronautics, ESA, development of the L III launcher, and rationalization of the Aerospace Sciences Meeting, 23rd, Reno, NV, Jan 14-17, 1985 satellite programs), and the resulting agreement with NASA is 8P characterized The implications of this history for the present (AIAA PAPER 85-0504) discussion of ESA participation in the Space Station are indicated It is pointed out that NASA is developing a new way to get in the form of open questions T K payloads into orbit in a short time and at a low cost. The 'Spacelab Hitchhiker' is the carrier program which will accomplish this objective The Spacelab Hitchhiker earner is a Shuttle payload A85-24654 The primary application of the considered program will be related THE POTENTIAL OF SOLAR POWER SATELLITES FOR to science and technology payloads Attention is given to the DEVELOPING COUNTRIES Hitchhiker concept, details regarding the Hrtchhiker-G and N JASENTULIYANA and R A LUDWIG (United Nations, Outer Hitchhiker-M, aspects of integration and operations, Orbiter Space Affairs Div, New York, NY) Space Solar Power Review resources and STS interfaces, the conduction of Hitchhiker flights (ISSN 0191-9067), vol 4, 1983, p 291-300 refs as 'flights of opportunity', questions of payload selection, and The basic political, economic and technical aspects of a solar organizational interfaces G R. power satellite system (SPS) for the Third Wortd are bnefly discussed It is shown that the development of a SPS system A85-21826*# National Aeronautics and Space Administration could contribute significantly to economic growth in developing Langley Research Center, Hampton, Va countries by reducing the costs of energy to a level commensurate A SURVEY OF AEROASSISTEO ORBIT TRANSFER with the rest of the world Attention is given to the INTELSAT G D WALBERG (NASA, Langley Research Center, Hampton, program as a model of a satellite system which serves the VA) Journal of Spacecraft and Rockets (ISSN 0022-4650), vol economic interests of the Third World without compromising the 22, Jan-Feb 1985, p 3-18 Previously cited in issue 20, p 3158, economic interests of the more developed nations I H Accession no A82-40291 refs

A85-21831*# National Aeronautics and Space Administration Langley Research Center, Hampton, Va A85-24787# CHEMICAL NONEQUILIBRIUM EFFECTS ON FLOWFIELDS FOR WHEN SPACECRAFT GET CHARGED UP, THEY HAVE MINDS AEROASSISTED ORBITAL TRANSFER VEHICLES OF THEIR OWN J L SHINN and J. J JONES (NASA, Langley Research Center, E J LERNER Aerospace America (ISSN 0740-722X), vol 23, Space Systems Div, Hampton, VA) Journal of Spacecraft and Feb 1985, p 38, 40, 42, 83 Rockets (ISSN 0022-4650), vol. 22, Jan-Feb 1985, p 54-59 The problems and solutions pursued in development of a flight Previously cited in issue 05, p 602, Accession no. A83-17913 model discharge system (FMDS) for eliminating the arcing that refs occurs in satellites are described The charges anse from particle bombardment and the lack of sufficient conductive particles in the space environment Potentials up to 10 kV build up between A85-22S76 insulated conductors and eventually arc discharge and can upset DEPLOYABLE OPTICAL SYSTEMS; PROCEEDINGS OF THE or destroy on-board electronic systems After detecting the charge MEETING, LOS ANGELES, CA, JANUARY 18, 19, 1983 build-up the FMDS generates a plasma to conduct the charge to J S FENDER, ED (USAF, Weapons Laboratory, Kirtland AFB, space or the spacecraft exterior The device carries on on-board NM) Meeting sponsored by SPIE - The International Society for template data base for comparisons with normal charging events Optical Engmeenng Bellingham, WA, SPIE - The International to permit functional charging events to continue Difficulties are Society for Optical Engmeenng (SPIE Proceedings Volume 383), still being encountered in producing plasma quickly enough to 1983, 105 p For individual items see A85-22577 to A85-22587 prevent discharges M.S K Among the topics discussed are deployable reflector configurations, the alignment and phasing of deployable telescopes, reflector antenna structure design concepts, a point spread function for a segmented mirror system, the use of a multiple order radial A85-24790*# National Aeronautics and Space Administration. grating shearing interferometer for mirror segment alignment, the Langley Research Center, Hampton, Va design of an extended retroreflector that is insensitive to tube ORBIT-ON-DEMAND VEHICLES - MISSION POSSIBLE, BUT bend, and novel techniques for the fusion bonding and replication ONE-DAY TURNAROUND? of large glass reflectors Also discussed are holographic figure T A TALAY, W. D. MORRIS (NASA, Langley Research Center, sensing for large primary mirrors, active vibration control for lasers Hampton, VA), and R W LEMESSURIER (Kentron International, and spacecraft, the results of recent structural control research at Inc, Hampton, VA) Aerospace Amenca (ISSN 0740-722X), vol the U S Air Force's Office of Scientific Research, active control 23, Feb 1985, p 54-57 technology development at NASA, and structural control research The next generation launch-on-demand manned orbital vehicles and experiments at NASA O C will ideally be able to perform plane change maneuvers for rendezvous Plane-changes of, eg, 11 deg, will require a 3000 A85-23824# fps on-orbit maneuver velocity Any plane-change capabilities LOOKING BACK ON THE PAST - THE DECISION OF EUROPE beyond 800 fps rapidly increase the necessary vehicle weight TO PARTICIPATE IN THE POST-APOLLO PROGRAM [RETOUR Sensitivity studies of the payload weight/vehicle weight, the SUR LE PASSE - LA DECISION DE L'EUROPE DE PARTICIPER presence or absence of air-breathing engines, high acceleration, AU PROGRAMME POST-APOLLO] etc, indicated that advances are required in the payload stowage R FRAYSSE (ESA, Bureau de Coordination et de Controle des pallet, thermal protection system, fault detection electronics, Projets, Pans, France) ESA Bulletin (ISSN 0376-4265), no 40, line-replaceable units, and accessibility to realize one-day Nov. 1984, p 61-65 In French turnaround The spacecraft would also need autonomous systems The process by which the European space community agreed checks and launch from minimum support sites reached by air on its participation in the NASA post-Apollo program is examined ferry A honzontal take-off, two-stage subsonic launch vehicle so in a historical review covering the penod 1970-1973 The ambitious far offers the lowest weight, maximum flexibility and minimum goals and unreahstically low cost estimates of the originally planned support combination of all configurations under consideration. program are outlined, the preliminary proposals of the European MSK

53 10 GENERAL

A85-24794# Topics examined include the successful operation of ANS (despite SOLAR CELLS FOR TOMORROW'S SPACECRAFT the fact that it did not attain its planned circular orbit), the scientific P A ILES and K S LING (Applied Solar Energy Corp, City of accomplishments of the US-UK-Netherlands IRAS program, Industry, CA) Aerospace Amenca (ISSN 0740-722X), vol 23, potential social benefits of space projects (remote-sensing Feb 1985, p 70-72, 77 information, improved search and rescue capability, manufactunng, Solar cells and arrays for providing power to spacecraft are and telecommunications), and the political consequences of the undergoing several developmental changes in various directions decision to participate actively in space development For the future, The main inpetus is for better efficiencies and longer life, larger full cooperation in ESA plans (scientific missions, continued surface areas, lower weight and larger arrays Back surface communications and remote-sensing development, a new reflectors and field technologies are being studied, along with generation of Anane launchers, and the Columbus contnbution to wraparound contacts, modified back surfaces, thinner cells (50-100 the NASA Space Station), active support on a national level, and microns), surface texturing and AR coatings The cells are still national projects of a commercial and/or scientific nature are sliced from ingots and contacts and other appurtenances are added recommended T K by vapor deposition Tnals with concentrator arrays and GaAs cells are planned to obtain higher efficiencies and better radiation A85-27973 hardening GaAs cells can be grown epitaxially but require greater ASTRONOMERS, CONGRESS, AND THE LARGE SPACE surface preparations than Si cells Finally, the manufactunng TELESCOPE infrastructure for GaAs cells has yet to be established M S K P A HANLE (National Air and Space Museum, Washington, DC) Sky and Telescope (ISSN 0037-6604), vol 69, April 1985, p A85-26369# 300-305 INTELSAT'S TWENTIETH ANNIVERSARY - TWO DECADES OF The Hubble Space Telescope (HST) project was initiated near INNOVATION IN GLOBAL COMMUNICATIONS the end of the Apollo program and immediately encountered fiscal R R COLINO (International Telecommunications Satellite contraints Planned as a long-term facility, the HST had to be Organization, Washington, DC) ITU Telecommunication Journal continually justified to the public, astronomers and Congress from (ISSN 0497-137X), vol 52, Jan 1985, p 22-31 1973 onward Budgetary restraints caused design reductions which It is pointed out that the world's global satellite communications for a while threatened the practicality of the HST and changed it revolution began with a study conducted by Clarke (1945), who from a pressunzed, manned unit to an automatic mode, provided a detailed description of a network of three teleoperated, intermittently visited spacecraft It is noted that geosynchronous communications satellites However, Clarke had numerous exaggerations were made of both the power of the considered a need for manned space stations, because of HST for scientific research and the total support of the astronomical maintenance requirements related to the use of radio tubes This community dunng promotion of the HST program, although the difficulty regarding the implementation of Clarke's concept was HST is the most powerful visual wavelength telescope ever to be eliminated by the invention of the transistor Following the launch built due to its unique operating environment NASA's consistent of Sputnik in 1957, and the launch of the world's first and steadily more detailed definitions of the design features and communications satellite in 1958, the use of satellites for effective missions of the HST proved to be a decisive factor in repeated international satellite communications was considered by the World requests for information by funding committees who were Administrative Radio Conference in 1959, and the International deliberating in the presence of severe fiscal difficulties M S K Telecommunications Satellite Organization (Intelsat) was established in 1964 Attention is given to Intelsat's N85-10789*# National Aeronautics and Space Administration accomplishments, patterns of innovation in connection with the Langley Research Center, Hampton, Va growth in Intelsat traffic and technological advances, and future HUMAN RESPONSE TO VIBROACOUSTIC ENVIRONMENTS OF developments regarding Intelsat over the next 20 years G R SPACE VEHICLES K F WILLSHIRE Oct 1984 37 p refs Presented at the A85-26385# 108th Meeting of the Acoust Soc of Am , Minneapolis, 8-12 Oct FLIGHT OPERATION CONSIDERATIONS FOR AN 1984 AERO-BRAKED OTV (NASA-TM-86316, MAS 1 15 86316) Avail NTIS HC A03/MF W H WILLCOCKSON (Martin Marietta Aerospace, Denver, CO) A01 CSCL 05H Amencan Institute of Aeronautics and Astronautics, Aerospace To insure efficient utilization of the system, space station design Sciences Meeting, 23rd, Reno, NV, Jan 14-17, 1985 12 p and operations will require special habitability considerations for (AIAA PAPER 85-0220) the occupants and crew because of the relatively long duration A description of design features and flight-operation principles missions Of particular concern is the environment in which the of ground-based and space-based orbit transfer vehicles (OTV), personnel will live and work, and how it affects both the scheduled for operation by the early 1990's, is presented The performance and comfort of the occupants Current criteria do ground-based cryogenic stage has a four-propellant tank not consider possible effects of reduced gravity, long duration, configuration mounted atop a single 15,000-lb thrust engine, a and confinement Preliminary to developing space station 6,500-lb dry weight, and 51,000-lb liquid fuel capacity The vibroacoustic habitability criteria, the adequacy of cntena for other space-based system is similar in its general features to the space vehicles has been reviewed In this paper, responses to ground-based system, but has a dry weight of 11,000 Ibs and a the noise and vibration environments of both Skylab and Shuttle 94,000-lb capacity for COX/hydrogen fuel Consecutive phases of are discussed Some astronauts have reported sleep interference, the passive-payload delivery to a geosynchronous orbit via aft communication interference, distraction, and general annoyance cargo earner are detailed, including the boost phase, navigation, as noise related complaints In addition, information from the aeroentry, deployment, and recovery It is noted that a considerable Russian Salyut missions, as well as similar based situations (e g, efficiency increase can be achieved through the aeroentry LT submannes), is reviewed Author

A85-26770# N85-11023*# Microgravity Research Associates, Inc, Coral TEN YEARS AFTER THE LAUNCH OF ANS - LOOKING BACK Gables, Fla IN PERSPECTIVE [10 JAAR NA DE ANS LANCERING • PRODUCING GALLIUM ARSENIDE CRYSTALS IN SPACE TERUGBLIK EN PERSPEKTIEF] R L RANDOLPH In NASA Marshall Space Flight Center 2nd P F J LINSSEN (Nederlands Instituut voor Vhegtuigontwikkeling Symp on Space Industrialization p 82-86 Oct 1984 en Ruimtevaart, Delft, Netherlands) Ruimtevaart, vol 33, Aug -Oct Avail NTIS HC A19/MF A01 CSCL 20B 1984, p 123-129 In Dutch The production of high quality crystals in space is a promising Netherlands space activities since the launch of the first national near-term application of microgravity processing. Gallium arsenide satellite ANS in 1974 are surveyed, and future plans are discussed is the selected matenal for initial commercial production because

54 10 GENERAL

of its inherent superior electronic properties, wide range of market N85-11057*# Booz-Allen and Hamilton, Inc., Arlington, Va. applications, and broad base of on-going device development effort DOING BUSINESS IN SPACE: HOW TO GET THERE FROM Plausible product prices can absorb the high cost of space HERE transportation for the initial flights provided by the Space P W WOOD and P. M STARK In NASA. Marshall Space Transportation System. The next step for bulk crystal growth, Flight Center 2nd Symp on Space Industrialization p 371-382 beyond the STS, is planned to come later with the use of free Oct 1984 flyers or a space station, where real benefits are foreseen The Avail NTIS HC A19/MF A01 CSCL 05A use of these vehicles, together with refinement and increasing A step by step process is described through which an existing automation of space-based crystal growth factories, will bnng down enterprise or an entrepreneurial venture can initiate and carry out costs and will support growing demands for high quality GaAs a new space venture. Throughout this process the business and and other specialty electronic and electro-optical crystals grown technical aspects must be advanced in parallel with each other in space Author Each depends on the other for its continued success, and companies may be unable to complete the venture if one or the other is neglected The existing NASA programs and the expenence of early trailblazers provide sufficient examples and opportunities N85-11032*# European Space Agency, Pans (France) Space for other firms to undertake new ventures with confidence With Transportation Systems the introduction of NASA's Commercial Space Policy, both the EUROPEAN RETRIEVABLE CARRIER (EURECA) AND opportunities and the ease with which ventures can be earned EVOLUTIONARY SPACE CARRIER FOR MICROGRAVITY, out should increase significantly MAC EARTH OBSERVATION AND TECHNOLOGY DEMONSTRATION N85-12075*# General Research Corp , McLean, Va R MORY and G SEIBERT In NASA Marshall Space Flight PROCEEDINGS OF A WORKSHOP ON APPLICATIONS OF Center 2nd Symp on Space Industrialization p 147-168 Oct TETHERS IN SPACE, EXECUTIVE SUMMARY Final Report 1984 1 Dec 1983 70 p Proc held in Williamsburg, Va, 15-17 Jun Avail NTIS HC A19/MF A01 CSCL 22B 1983 3 Vol The Spacelab relatively short stay-time in orbit has led to (Contract NAS8-35403) consideration of the European Retrievable Carrier (EURECA) (NASA-CR-171195, NAS 1 26171195) Avail NTIS HC A04/MF concept as a reusable earner The EURECA concept is a free-flying A01 CSCL 22B earner of expenments which is launched and recovered by the The objectives were to identify potential applications for tethers space shuttle It is commensurate with the size of payloads that in space, develop a first order assessment of the feasibility and can be economically developed in Europe and combines the benefits of tether applications, recommend future actions necessary advantages of Spacelab (high mass and power capability, recovery) to enable tether applications, including required technology with those of a free flyer (extended operating time in a non-polluted advancements, and stimulate industry and government planners environment) The launch of the first EURECA mission is scheduled to consider the unique properties of tethers in designs for future for October 1987 The Eureca spacecraft will be deployed from missions B G the Shuttle cargo bay in orbit, will operate in a free-flying mode for about six months, and will then be retneved, together with its N85-12076*# General Research Corp , McLean, Va payloads, returned to Earth by the Space Shuttle and prepared PROCEEDINGS OF A WORKSHOP ON THE APPLICATIONS OF for the next mission The first mission of EURECA is dedicated to TETHERS IN SPACE, VOLUME 1 Final Report research in the fields of life sciences and matenal sciences The 1 Dec 1983 294 p Proc held in Williamsburg, Va, 15-17 Jun experimental hardware of the first mission consist of a variety of 1983 3 Vol processm chambers for crystal growth and equipment for biological (Contract NAS8-35403) investigations viz plant growth and protein crystallization, and there (NASA-CR-171196, NAS 126171196) Avail NTIS HC A13/MF is the possibility to perform expenments in the field of exobiology A01 CSCL 22B MG Project overview, tether deployment, satellite system descnption, tether fundamentals, science applications, electrodynamic interactions, transportation, artificial gravity, and N85-11056*# TRW Space Technology Labs, Redondo Beach, constellations, were descnbed B G Calif SATELLITE SERVICING: A BUSINESS OPPORTUNITY? N85-12077*# General Research Corp, McLean, Va Abstract Only PROCEEDINGS OF A WORKSHOP ON APPLICATIONS OF R E WONG and E H MEDLER In NASA. Marshall Space TETHERS IN SPACE, VOLUME 2 Final Report Flight Center 2nd Symp on Space Industnahzation p 370 Oct 1 Dec 1983 315 p refs Proc held in Williamsburg, Va, 1984 15-17 Jun 1983 3 Vol Avail NTIS HC A19/MF A01 CSCL 05A (Contract NAS8-35403) The possibilities of satellite servicing as a business opportunity (NASA-CR-171197, NAS 126171197) Avail NTIS HC A14/MF are examined The service rate which a user must be charged to A01 CSCL 22B yield a reasonable return is derived and then compared against The panel conclusions for each of the following panels (science the market's willingness to pay that rate Steps taken to provide applications, electrodynamic interactions, transportation the basis from which the service rate could be derived include applications, artificial gravity, constellations, and technology and (1) constructing a hypothetical on orbit servicing business offering test) are given B G both on orbit and associated ground services, (2) estimating the total on orbit service business potential by analyzing mission models N85-12921*# Martin Marietta Corp, Bethesda, Md to the year 2000, and (3) setting up ground rules to bound the SELECTED TETHER APPLICATIONS IN SPACE: AN ANALYSIS conduct of the business Using this basic information service OF FIVE SELECTED CONCEPTS Final Report demand (business volume) cost to set up the business, costs for 31 Jul 1984 206 p operation and maintenance tax rates and desired rate of return (Contract NAS8-35499) are estimated to determine the user charge Sensitivity of the (NASA-CR-171222, NAS 1 26 171222) Avail NTIS HC A10/MF service rate to various parameters are also assessed The time A01 CSCL 22B span for the business venture runs from 1986 through 2000 with Ground rules and assumptions, operations, orbit service to 1991 provided via the orbiter and by a space station considerations/dynamics, tether system design and dynamics, beyond 1991 This point analysis shows about five years of negative functional requirements, hardware concepts, and safety factors cash flow, with steady profits thereafter are examined for five scenanos tethered effected separation of

55 10 GENERAL an Earth bound shuttle from the space station, tether effected N85-16993*# National Aeronautics and Space Administration orbit boost of a spacecraft (AXAF) into its operational orbit from Langley Research Center, Hampton, Va the shuttle, an operational science/technology platform tether PERFORMANCE ASSESSMENT OF AERO-ASSISTED ORBITAL deployed from space station, a tether mediated rendezvous TRANSFER VEHICLES involving an OMV tether deployed from space station to rendezvous R W POWELL, T A TALAY, A W WILHITE, J J REHDER, N with an aerobraked OTV returning to geosynchronous orbit from a H WHITE, J C NAFTEL, H W STONE, J P ARRINGTON, and payload delivery mission, and an electrodynamic tether used in a R S MCCANDLESS In NASA Lewis Research Center OTV dual motor/generator mode to serve as the primary energy storage Propulsion Issues p 41-56 Apr 1984 refs facility for space station ARM Avail NTISHC A13/MFA01 CSCL 22B Aero-assisted orbital transfer vehicles are analyzed The aerodynamic charactenstics over the flight profile and three- and N85-13473*# McDonnell-Douglas Astronautics Co, Huntington six-degree-of-freedom performance analyses were determined The Beach, Calif important results, to date, are (1) the aerodynamic preliminary THE HUMAN ROLE IN SPACE. VOLUME 1: EXECUTIVE analysis system, an interactive computer program, used to predict SUMMARY Final Report the aerodynamics (performance, stability, and control) for these Oct 1984 27 p 3 Vol vehicles, (2) the performance capability, e g, maximum inclination (Contract NAS8-35611) change, maximum heating rate, and maximum sensed acceleration, (NASA-CR-171223, NAS 1 26 171223, MDC-H1295-VOL-1, can be determined using continuum aerodynamics only, (3) DR-4-VOL-1) Avail NTIS HC A03/MF A01 CSCL 05H guidance schemes can be developed that allow for errors in The role and degree of direct involvement of humans required atmospheric density prediction, mispredicted tnm angle of attack, in future space missions were investigated Criteria for allocating and off-nominal atmospheric interface conditions, even for vehicles functional activities between humans and machines were with a low lift-to-drag ratio, and (4) multiple pass trajectories can established The technology requirements, economics, and benefits be used to reduce the maximum heating rate B G of the human presence in space were investigated R S F N85-16998*# National Aeronautics and Space Administration N85-13847*# National Aeronautics and Space Administration Marshall Space Flight Center, Huntsville, Ala Marshall Space Flight Center, Huntsville, Ala DRIVES AND BENEFITS OVERVIEW GROUND TEST EXPERIMENT FOR LARGE SPACE S D MCINTYRE In NASA Lewis Research Center OTV STRUCTURES, APPENDIX I Propulsion Issues p 103-112 Apr. 1984 refs D K TOLLISON (Control Dynamics Co) and H B WAITES In Avail NTISHCA13/MF A01 CSCL 22B Control Dyn Co Definition of Ground Test for Verification of The major technology issues for an advanced orbital transfer Large Space Struct Control 4 p Nov 1984 vehicles (OTV) engine to be used in conjunction with a space Avail NTIS HC A08/MF A01 CSCL 22B based, reusable orbit transfer vehicle are discussed The results Marshall Space Flight Center has developed a Large Space of the space station studies as they relate to the OTV and the Structure (LSS) ground test verification experiment facility having ground rules and guidelines for a reusable OTV vehicle study are adequate fidelity and flexibility to accommodate the demands of reviewed The technology drives and benefit categories such as LSS control theory testing The first experiment is in the subsystem mission versatility, increased reliability or reduced cost are verification and integration phase This test employs the presented The technology drivers and the associated benefits ASTROMAST, a lightweight S glass composite deployable beam are covered with regard to relative significance and impact on the structure, as the test article and is cited to prove out centralized ongoing OTV engine technology program It is recommended that and distributed sensor control strategies Author because of the broad range of mission requirements and the long term potential cost benefits a new engine is needed for the space N85-13880*# National Aeronautics and Space Administration based reusable OTV E A K Lewis Research Center, Cleveland, Ohio SPACE POWER N85-17010*# Martin Marietta Aerospace, Bethesda, Md Washington Apr 1984 322 p refs Workshop held in SPACE BASED OTV SERVICING Cleveland, 10-12 Apr 1984 J G MCALLISTER In NASA Lewis Research Center OTV (NASA-CP-2352, E-2305, NAS 1 55 2352) Avail NTIS HC Propulsion Issues p 255-272 Apr 1984 refs Sponsored in A14/MF A01 CSCL 22B part by Pratt and Whitney Aircraft Appropriate directions for the applied research and technology Avail NTISHC A13/MFA01 CSCL 22A programs that will develop space power systems for U S future Space based servicing of an orbit transfer vehicle (OTV) was space missions beyond 1995 are explored Spacecraft power previously outlined in sufficient detail to arrive at OTV and support supplies, space stations, space power reactors, solar arrays, system servicing requirements Needed space station facilities and thermoelectric generators, energy storage, and communication their functional requirements were identified The impact of logistics satellites are among the topics discussed and space serviceable design on the OTV design is detailed herein RL10 denvative rocket engine inspection task times are N85-16981*# Wyle Labs, Inc, El Segundo, Calif enumerated RSF COMMERCE LAB: MISSION ANALYSIS AND PAYLOAD INTEGRATION STUDY Interim Progress Report N85-17551*# Houston Univ, Tex Dept of Mechanical 6 Dec 1984 91 p Engmeenng (Contract NAS8-36109) CHARACTERIZATION OF HEAT TRANSFER IN NUTRIENT (NASA-CR-171272, NAS 126171272) Avail NTIS HC A05/MF MATERIALS Final Report, 30 Apr. 1971 - 31 Dec. 1984 A01 CSCL 22A L C WITTE 7 Jan 1985 6 p The needs of an aggressive commercial microgravity program (Contract NAS2-11676) are identified, space missions are defined, and infrastructural issues (NASA-CR-171841, NAS 1 26 171841) Avail NTIS HC A02/MF are identified and analyzed A commercial laboratory, commerce A01 CSCL 06H lab, is conceived to be one or more an array of earners which The processing and storage of foodstuffs in zero-g environments would fly aboard the space shuttle and accommodate microgravity such as in Skylab and the space shuttle were investigated science experiment payloads Commerce lab is seen as a logical Particular attention was given to the efficient heating of foodstuffs transition between currently planned space shuttle missions and The thermophysical properties of vanous foods were cataloged future microgravity missions centered around the space station and critiqued The low temperature storage of biological samples RSF as well as foodstuffs during shuttle flights was studied Research

56 10 GENERAL and development requirements related to food preparation and N85-20360*# National Aeronautics and Space Administration storage on the space station are discussed. R S F Langley Research Center, Hampton, Va SUMMARY PRESENTATION OF THE TECHNOLOGY AND TEST PANEL N85-20174# Joint Publications Research Service, Arlington, Va P SIEMERS In NASA Marshall Space Flight Center Appl of WEST EUROPE REPORT: SCIENCE AND TECHNOLOGY Tethers in Space, Vol 1 11 p Mar 1985 19 Feb 1985 141 p refs Transl into ENGLISH from various Avail NTISHCA13/MF A01 CSCL 22A Chinese articles Tether related technology issues were investigated along with (JPRS-WST-85-008) Aval NTIS HC A07/MF A01 potential applications Several of the applications do not derive News items, abstracts, and scientific reports on aspects of necessarily from nor are they related to a technology issue Tether science and technology including advanced materials, aerospace designs must concern itself with length requirements (whether the engmeenng, civil aviation, computers, factory automation, tether is to be flexible or stiff) and what the environmental impact microelectronics, and scientific and industrial policy is on the particular material that is proposed for the tether As far as tether manufactunng techniques, a lot of technology related N85-20339*# National Aeronautics and Space Administration work is required to develop cost effective manfactunng capabilities Marshall Space Flight Center, Huntsville, Ala for the future tether There are techniques that are used on the APPLICATIONS OF TETHERS IN SPACE, VOLUME 1 ground now However, after some of the proposed applications A. C CRON, comp (General Research Corp, McLean, Va) are determined to be feasible, it may be that the best way to Washington Mar 1985 283 p refs Workshop held in manufacture the tether is to pretend the satellite is a spider and Wilhamsburg, Va ,15-17 Jun 1983 2 Vol allow it to spin its own web in space The technology required to (Contract NAS8-35403) developed tapered tethers was considered Definition of the taper, (NASA-CP-2364, M-475, NAS 1 55 2364) Avail NTIS HC where the center of that taper should be, and the taper's relation A13/MF A01 CSCL 131 to the end masses are all of concern R S F The tethered satellite system is described including tether fundamentals Applications of very long tethers in space to a broad N85-20361*# National Aeronautics and Space Administration spectrum of future space missions are explored Topics covered Marshall Space Flight Center, Huntsville, Ala include science, transportation, constellations, artificial gravity, APPLICATIONS OF TETHERS IN SPACE, VOLUME 2 technology and test, and electrodynamic interactions A C CRON, comp (General Research Corp, McLean, Va) Recommendations to NASA are included Washington Mar 1985 319 p refs Workshop held in Wilhamsburg, Va ,15-17 Jun 1983 2 Vol (Contract NAS8-35403) N85-20345*# National Aeronautics and Space Administration (NASA-CP-2365, M-476, NAS 1 55 2365) Avail NTIS HC Marshall Space Flight Center, Huntsville, Ala A14/MF A01 CSCL 131 TETHER FUNDAMENTALS Topics discussed include tethered satellites, tether deployment, C RUPP In its Appl of Tethers in Space, Vol 1 15 p Mar satellite systems, science applications, electrodynamic interactions, 1985 transportation applications, artificial gravity, constellations, and Avail NTISHCA13/MF A01 CSCL 131 technology and testing Forces on tethered satellites, tether tension as a function of the effective mass, and parameters of candidate tether materials N85-20364*# Aentalia S p A , Torino (Italy) are examined Illustrations show stabilization control law, tethered REPORT OF THE TRANSPORTATION PANEL satellite deployment and retrieval, angular momentum, electnc E. VALLERANI, M W HUNTER (Lockheed Missiles and Space motor effect reboost, a very long tether phenomenon, shuttle Co), P M BAINUM (Howard Umv), V J MODI (British Columbia tethered satellite effects on the orbiter; artificial gravity, tethered Univ), K A FAYMON (NASA Lewis Research Center), B CHANG satellite rendezvous docking relative velocity, and scaling up from (Space Communication Company), S LEWIS (NASA Johnson the shuttle/TSS Limitations of the tethered satellite system and Space Center), J YGLESIAS (NASA Johnson Space Center), L of tether properties as well as cost/benefits trades for future EDWARDS (NASA, Washington), R J ADORNATO (Grumman applications are considered A R H Aerospace) et al In NASA Marshall Space Flight Center Appl of Tethers in Space, Vol 2 56 p Mar 1985 Avail NTIS HC A14/MF A01 CSCL 22A N85-20353*# National Aeronautics and Space Administration Tether applications for space transportation are covered (1) Langley Research Center, Hampton, Va payload boast, (2) upper stage boost, (3) E T deboost, (4) shuttle TECHNOLOGY AND TEST deboost, (5) shuttle docking , (6) payload and OTV boost, (7) P SIEMERS In NASA Marshall Space Flight Center Appl of OTV payload boost, (8) lunar assist and eccentricity change, (9) Tethers in Space, Vol 1 5 p Mar 1985 aeromaneuvenng by remote sail or kite, (10) electrodynamic Avail NTIS HC A13/MF A01 CSCL 131 deceleration, and (11) lunar and planetary applications The first The status of tether-related technology is discussed together seven transfer momentum between two masses at the tether tips, with the program that should be initiated to develop the technology and the remaining for use tethers for controlled interaction with required by the tethered satellite system Successful tethering the environment B G dunng the Gemini program is mentioned Technology areas which appear to have application to tethered systems are identified, including electrodynamics, atmosphencs, and N85-20370*# National Aeronautics and Space Administration aerothermodynamics R S F Langley Research Center, Hampton, Va REPORT OF THE TECHNOLOGY AND TEST PANEL P SIEMERS, S GRAFF (JPL, California Inst of Tech , Pasadena), N85-20359'# Martin Marietta Corp, Denver, Colo H COMPTON, R J DUCKETT, C BUONJIOLNO (CNR, Italy), G. SUMMARY PRESENTATION OF THE CONSTELLATIONS WOOD, D R TENNEY, D D LANG (NASA Johnson Space PANEL Center), K. SUTTON (Analytical Mechanics Associates), P F. WILLIAMS In NASA Marshall Space Flight Center Appl of FLANAGAN et al In NASA Marshall Space Flight Center Appl Tethers in Space, Vol 1 11 p Mar 1985 of Tethers in Space, Vol 2 27 p Mar 1985 Avail NTISHCA13/MF A01 CSCL 22A Avail NTIS HC A14/MF A01 CSCL 131 Tethered multiple spacecraft configurations are discussed The state of technology relative to the Tethered Satellite System relative to low Earth orbit, geosynchronous Earth orbit, and one, (TSS) was reviewed The technology areas which could benefit two, or three dimensional configurations Attitude control, pointing, from the TSS were defined To support TSS design studies it is and stabilization of such tethered systems are addressed R S F necessary to develop tether dynamic model computer codes for

57 10 GENERAL definition of mission and tether requirements Present major codes that the radar and lidar systems offer the greatest versatility and are very elaborate, expensive to run, and not very user friendly accuracy since they control the direction, intensity and duration of An additional technology concern was related to the manufacturing the energy incident on the target object The performance of the of tethers The development of complex tethers passive optical system is determined by the capability of the (nonconductmg-taper/double taper long 100 km, detector and by the baseline separation of the telescopes, which conductmg-embedded conduction, , fiber optics, and requires the use of an on-orbit deployment mechanism The passive superconducting) and their applications to space stations requires optical concept provides the largest total event rae, and includes the development of manufacturing capabilities for both Earth-based significant detections of particle sizes greater than 10 cm to allow as well as space-based systems B G correlation with ground based observations of the larger particles The event rate tor the radar system is relatively constant with N85-20372*# National Aeronautics and Space Administration particle while the lidar system is slightly biased toward the smaller Langley Research Center, Hampton, Va sizes These event rate differences result from a combination of INSTRUMENTATION FOR APPLICATION NUMBER 1: MASS the debris flux size distribution and the vanation of sensitive SPECTROMETRIC ANALYSIS OF THE BOUNDARY LAYER detection area with particle size for the three concepts E A K ASSOCIATED WITH THE TETHERED SATELLITE G M WOOD In NASA Marshall Space Flight Center Appl of N85-21213*# Texas Univ, Austin. Dept of Aerospace and Tethers in Space, Vol 2 18 p Mar 1985 refs Engineenng Mechanics Avail NTIS HC A14/MF A01 CSCL 22B THE LONG TERM BEHAVIOUR OF EARTH ORBITS AND THE Knowledge about the boundary layer associated with high IMPLICATIONS FOR DEBRIS CONTROL enthalpy flow fields has mostly been denved from measurements A C MUELLER In NASA Lyndon B Johnson Space Center of physical properties To further this understanding, the chemistry Orbital Debris p 332-348 Mar 1985 refs of the gaseous layer must be studied as well This requires that Avail NTIS HC A20/MF A01 CSCL 03C instrumentation and measurement methods be developed that can GEO orbits with inclinations which remain less than 45 degrees analyze the gases while having a minimal effect on the flow field are very stable Although the inclination of the orbital plane may and composition Because of its sensitivity and ability to identity vary as much as 15 degrees over a period of about 50 years, the species, the mass spectrometer is the most promising instrument orbit altitude will always remain within a few hundred kilometers for this application, although other spectroscopic methods are being of geosynchronous altitude, GEO orbits with inclinations greater evaluated as well There are, however, several non-trivial problems than 45 degrees exhibit remarkable instabilities ir the eccentricity that must be solved in order to apply the mass spectrometer, due to gravitational resonance Over a period of a century the including the obtaining of a representative sample from near the eccentricity can reach such a large value that reentry is a possibility model surface These problems are being addressed in a research The combined effects of the Sun, Moon, and oblate Earth play a program to develop qualitative and quantitative measurement significant role in determining the lifetime of a GEO transfer orbit methods to examine the gas chemistry in several large hot-gas Depending on the initial onentation of the orbital plane with respect blowdown facilities, and to study the aerodynamics of the boundary to the Sun and Moon, lifetimes may vary from under 6 months to layer associated with models in these facilities and in instrumented over several hundred years Transfer orbits with inclinations over hypersonic vehicles These methods can also be applied to the 45 degrees show strong instabilities in the perigee altitude resulting tethered satellite, which will provide a unique opportunity to obtain in generally short lifetimes of less than a few years All transfer aerothermodynamic data that is unaltered by effects from the test orbits can be designed to decay within one year if the initial perigee facility M G altitude is less than 231 km However, there are restrictions on orbit plane placement and time of year of launch Author N85-21197*# Air Force Satellite Control Facility, Sunnyvale, Calif GEOSYNCHRONOUS SATELLITE COLLISION AVOIDANCE N85-21214*# National Aeronautics and Space Administration Abstract Only Goddard Space Flight Center, Greenbelt, Md W FRASER In NASA Lyndon B Johnson Space Center Orbital DEBRIS IN THE GEOSTATIONARY ORBIT RING, THE ENDLESS Debns p 133 Mar 1985 SHOOTING GALLERY: THE NECESSITY FOR A DISPOSAL Avail NTIS HC A20/MF A01 CSCL 22A POLICY The increases in the number of satellite systems, the growing D H SUDDETH In NASA Lyndon B Johnson Space Center dependency on these systems, and the potentially hazardous Orbital Debris p 349-364 Mar. 1985 conjunctions in space, dictates careful management of satellite Avail NTIS HC A20/MF A01 CSCL 03C positions The potential for satellite collision increases as more NASA is considenng establishing a policy for the limitation of objects are placed in orbit At geosynchronous altitudes active the physical crowding of the geostationary orbit. The proposed satellites maintain fixed longitudinal station-keeping control while policy is intended to address the following issues (1) deal only inactive satellites and debris generally drift around the globe or with geostationary altitudes, (2) illustrate the unique value and oscillate about two geopotential stable points Portions of the total usefulness of the geostationary orbit nng, (3) describe the orbital objects in geosynchronous orbit are tracked by ground stations dynamics as simply as possible, (4) describe the current spacecraft while a significant number of additional pieces of space debns and debns situation, (5) briefly review current industry and agency regularly pass through geosynchronous orbit altitudes The policies, (6) project future trends of physical crowding with the probability of an operational satellite colliding with another satellite present nonpolicy, (7) propose solutions that can be implemented or a piece of space debns will increase in the number of space in the near future, and (8) use previous work as much as objects, their sizes, and on-orbit lifetimes E A K desirable G L C

N85-21198*# General Electnc Co , Fairfield, Conn N85-21215*# National Aeronautics and Space Administration, IN SITU ORBITAL DEBRIS EXPERIMENT CONCEPTS Washington, D C S. L NESTE In NASA Lyndon B Johnson Space Center THE INTERNATIONAL ENVIRONMENT UNISPACE '82 AND THE Orbital Debns p 134-149 Mar 1985 refs ITU: A RELATIONSHIP BETWEEN ORBIT-SPECTRUM Avail NTIS HC A20/MF A01 CSCL 22A RESOURCE ALLOCATION AND ORBITAL DEBRIS Implementation of the radar, lidar and passive optical remote D OLMSTEAD In NASA Lyndon B Johnson Space Center sensing concepts for measuring space debns from an Earth orbiting Orbital Debns p 372-378 Mar 1985 platform was investigated Each system was compared for their Avail NTIS HC A20/MF A01 CSCL 05D requirements on the host platform, their performance relative to The 1985 Space WARC will examine and potentially modify the space debns measurement program and the estimated cost the current geostationary orbit spectrum resource allocation of developing each concept into a flight instrument It is found methodology Discussions in this international political environment

58 10 GENERAL could likely associate the geostationary orbital debns issue with the politicized issue of orbit spectrum allocation. G L C

N85-21414'# National Academy of Sciences - National Research Council, Washington, D C Commission on Engineering and Technical Systems. COMPUTER INTEGRATION OF ENGINEERING DESIGN AND PRODUCTION: A NATIONAL OPPORTUNITY Final Report Oct. 1984 73 p (Contract NASW-3811) (NASA-CR-175483, NAS 1 26 175483, PB85-128429) Avail NTIS HC A04/MF A01 CSCL 13H The National Aeronautics and Space Administration (NASA), as a purchaser of a variety of manufactured products, including complex space vehicles and systems, clearly has a stake in the advantages of computer-integrated manufacturing (CIM). Two major NASA objectives are to launch a Manned Space Station by 1992 with a budget of $8 billion, and to be a leader in the development and application of productivity-enhancing technology At the request of NASA, a National Research Council committee visited five companies that have been leaders in using CIM Based on these case studies, technical, organizational, and financial issues that influence computer integration are described, guidelines for its implementation in industry are offered, and the use of CIM to manage the space station program is recommended GRA

N85-21659*# General Research Corp , McLean, Va APPLICATIONS OF TETHERS IN SPACE Executive Summary A C CRON 1985 69 p Workshop held in Williamsburg, Va, 15-17 Jun 1983 (Contract NAS8-35408) (NASA-CP-2366, NAS 1 55 2366) Avail NTIS HC A04/MF A01 CSCL22A The proceedings of the first workshop on applications of tethers in space are summanzed The workshop gathered personalities from industry, academic institutions and government to discuss the relatively new area of applied technology of very long tethers in space to a broad spectrum of future space missions A large number of tethered concepts and configurations was presented covenng electrodynamic interaction tethers, tethered transportation through angular momentum exchange, tethered constellations, low gravity utilization, applicable technology, and tethered test facilities. Specific recommendations were made to NASA in each area Author

N85-22234*# Tennessee Technological Univ., Cookeville Dept of Civil Engmeenng. DEBRIS IMPACT ON EARTH-ORBITING SPACECRAFT D G SMITH In Alabama Umv Res. Rept 1984 NASA/ASEE Summer Faculty Fellowship Program (NASA-CR-171317) 15p Jan 1985 refs Avail NTIS HC A99/MF E03 CSCL 22A The accumulation of Earth-orbiting space debris leads to important new design considerations Some 5,000 orbiting objects, many of them explosion fragments, are currently being tracked and future collision of these objects with each other is predicted These collisions will occur at high velocities Each collision will be explosive, ejecting thousands, of new orbiting objects, in turn increasing the frequency of future collisions The debns population may thus become self-regeneratrve, and the future flux of orbiting debns will exceed that of meteoroids As a result, a large space structure in Earth-orbit for several years has a significant probability of impact by debns objects As a design problem, debns impact is significantly different from meteoroid impact. Protection against such large objects may require structural measures The consideration of debns impact in the design of large, Earth-orbiting spacecraft is recommended E.A.K

59 SUBJECT INDEX

TECHNOLOGY FOR LARGE SPACE SYSTEMS / A Bibliography (Supplement 13) MARCH 1986

Typical Subject Index Listing

1 SUBJECT HEADING ADHESIVES Assessment of satellite collision hazards by simulated I Evaluation and prediction of long-term environmental sampling in space p 40 N85-211951 effects of nonmetallic materials Natural environment design criteria for the Space Station | (NASA-CR-171353J p 39 N85-19I37 definition and preliminary design AEROASSIST [NASA-TM-86498] p9 N85-21232) Determination of atmospheric density using a AEROSPACE INDUSTRY CHECKOUT space-launched projectile Bipropellant propulsion in the new generation of I i— Definition ol ground test lor large Space Structure (LSS) [AIAA PAPER 854)327) p2 A85-20866 satellites and upper stages The role of BPD Difesa-Spazto | control verification A survey of aeroassisted orbit transfer in this field - Manufacturing facilities and technology [NASA-TM-88495] D 28 N8S-21249 p 53 A85-21826 p43 A85-12519| Chemical nonequihbnum effects on flowfields for AEROSPACE MEDICINE aeroassisted orbital transfer vehicles p 53 A8S-2183I T Assessment of medical risk in space flight OTV Propulsion Issues [IAF PAPER 84-189] p51 A85-13114 | [NASA-CP-2347] p 48 N85-16989 NASA OAST perspective p5 N85-16990 AEROSPACE SCIENCES F Performance assessment of aero-assisted orbital Space as motivational propulsion — Shuttle Orbiter I NASA related projects as educational tools TITLE REPORT PAGE transfer vehicles P 56 N85-16993 NUMBER NUMBER ACCESSION [IAF PAPER 84-407] p 51 A85-13259 NUMBER AEROBRAKINQ Trajectory analysis of radiative heating for planetary CRC handbook of space technology Status and missions with aerobraking of spacecraft Projections p3 A85-28275 p 14 A85-21829 AEROSPACE SYSTEMS The subject heading is a key to the subject content Flight operation considerations for an aero-braked EASCON '83, Proceedings of the Sixteenth Annual OTV Electronics and Aerospace Conference and Exposition, of the document The title is used to provide a Washington, DC, September 19-21, 1983 description of the subject matter When the title is (AIAA PAPER 854)220] p 54 A85-26385 Design study of an integrated aerobraking orbital transfer p 51 A85-14426 CRC handbook of space technology Status and insufficiently descriptive of the document content, vehicle Projections p3 A85-28275 the title extension is added, separated from the title [NASA-TM-58264] p9 N85-21262 Conceptual design for scaled truss antenna flight AERODYNAMIC CHARACTERISTICS by three hyphens The (NASA or AIM) accession expenment Determination of atmospheric density using a number and the page number are included in each [NASA-TM-85804] p4 N85-12932 space-launched projectile AEROSPACE TECHNOLOGY TRANSFER entry to assist the user in locating the abstract in [AIAA PAPER 854)327] p2 A85-20866 Commercialization of space - Incentives, impediments Performance assessment of aero-assisted orbital the abstract section If applicable, a report number and alternatives p3 A85-27375 transfer vehicles P 56 N85-16993 is also included as an aid in identifying the AEROSPACEPLANES AERODYNAMIC FORCES Orbit on demand - In this century if pushed document Under any one subject heading, the Autonomous momentum management for the CDG accession numbers are arranged in sequence with planar Space Station p46 A85-24788 Orbit-on-demand vehicles - Mission possible, but [AIAA PAPER 85-0031 ] p 21 A85-19468 the AIAA accession numbers appeanng first one-day turnaround? p 53 A85-24790 AERODYNAMIC HEATING Chemical nonequilibnum effects on flowfields for AEROTHERMODYNAMICS Experimental and predicted heating distributions for aeroassisted orbital transfer vehicles p53 A85-21831 biconics at incidence in air at Mach 10 Experimental and predicted heating distributions for [NASA-TP-2334] p 14 N85-12313 biconics at incidence in air at Mach 10 AIR LAUNCHING [NASA-TP-2334J p 14 N85-12313 Cost effective launch technology for communications AERODYNAMIC STABILITY satellites ACCELERATION (PHYSICS) Effect of aerodynamic moment on the regime of the [IAF PAPER 84-04) p 50 A85-12979 Tether fundamentals p 57 N85-20345 gravity gradient stabilization of the Salyut-6 - Soyuz orbital system p 23 A85-28488 AIRCRAFT ANTENNAS ACCURACY Antenna engineenng handbook /2nd edition/ AERODYNAMICS Research on large, highly accurate, inflatable p30 A85-16081 reflectors Autonomous momentum management for space station AIRCRAFT STRUCTURES [AD-A145080] P11 N85-10099 Measurement of the mertial constants of a ngid or flexible [NASA-CR-174065] p 24 N85-12931 Modal control of structural systems structure of arbitrary share through a vibration test AEROMANEUVERING [AD-A149734] P2B N85-21235 [NASA-TM-77557] p 24 N85-11381 Report of the Transportation Panel ACTIVE CONTROL AIRCRAFT WAKES p57 N85-20364 High precision active nutation control of a momentum Spectral charactenstics of radar echoes from AEROSPACE ENGINEERING biased spacecraft with flexible appendages aircraft-dispensed chaff p 23 A85-26606 Generalized transform methods based finite element P20 A85-18337 AIRFOILS methodology - Thermal/structural dynamic applications Active vibration control for lasers and spacecraft The Satellite sail p49 N85-20376 (AIAA PAPER 85-0155] p 14 A85-19553 P 21 A85-22S84 ALGEBRA Reduction method for thermal analysis of complex Active control technology development at NASA Formex configuration processing in structural aerospace structures P22 A85-22S86 engineenng — Book p 14 A85-20916 [NASA-TP-2373] p 15 N85-16066 ACTUATORS ALGORITHMS West Europe report Science and technology Comparing attitude control effectiveness for actuators [JPHS-WST-65-008) p 57 N85-20174 Modal control of structural systems on two bodies of a SOL body model of a flexible spacecraft [AD-A149734] p 28 N85-21235 AEROSPACE ENVIRONMENTS with that for actuators restricted to a single body ALLOYS Environmental effects on the dynamics and control of P 17 A85-11086 an orbiting large flexible antenna system Experimental study of the effect of the type of stress An analytical investigation of shape control of large [IAF PAPER 84-358) p 18 A85-13220 state on plastic strain in structural matenals at low space structures by applied temperatures Effects of space environmental conditions on graphite temperatures p37 A85-16499 ANTENNA ARRAYS P 14 A8S-2S14S epoxy composites p36 A85-15990 Autonomous momentum management tor space station, Interleaved array antenna technology development exhibit A Dielectric material in the space environment p37 A85-24672 [NASA-CR-17184S] p34 N85-19326 [NASA.CR.171256J p 33 N85-12933 ANTENNA COMPONENTS A review of contamination issues associated with an Precast) control of flexible manipulators Development of advanced composite tubular structures orbiting Space Station external environment [NASA-CH-174210] p 42 N85-t6178 for antenna reflector p 10 A85-24817 p 38 A85-24703 ADAPTATION Space frame design, development and optimization of Safyut Mission Report p3 A85-25700 Environmental interactions working group report antenna platform structure for a mobile 3D radar ADAPTIVE CONTROL pS N85-13908 p8 A85-24908 Some applications of direct adaptive control to large Evaluation and prediction of long-term environmental Deployable folded antenna apparatus structural systems p 19 A85-13636 effects of nonmetallic materials (AD-D011503) p12 N85-21495 Adaptive modal control of structural dynamic systems (NASA-Cfl-171353] P 39 N85-19137 ANTENNA DESIGN using recursive lattice Blare p 23 A8S-26435 Instrumentation for Application Number 1 Mass Deployable reflector antennas - Mechanical design of Precise control ol flexible manipulator) spectrometnc analysis of the boundary layer associated the reflective surface [NASA-CH.174210] p42 N85-16178 with the tethered satellite p 58 N85-20372 [IAF PAPER 84-393) p6 A85-13247

A-1 ANTENNAS SUBJECT INDEX

Antenna engineering handbook /2nd edition/ Dynamics of the Orbiter based construction of structural BIOASTRONAUTICS p30 A85-16081 components Assessment of medical nsk in space flight Precision of mesh-type reflectors for large space-borne [IAF PAPER 84-359] p 18 A85-13221 [IAF PAPER 84-189] p 51 A85-13114 antennas p 31 A85-21835 Stability of the stationary motions of a tethered system BIOPROCESSING Design concepts for reflector antenna structures of two bodies in orbit under the effect of gravitational and Second Symposium on Space Industrialization — space p7 A85-22579 aerodynamic forces p 20 A85-15254 commercialization Satellite communication antenna technology High precision active nutation control of a momentum [NASA-CP-2313] p4 N85-11011 p 31 A85-23651 biased spacecraft with flexible appendages BODY KINEMATICS The systems background for satellite communication p20 A85-18337 Recursive Langrangian dynamics of flexible manipulator antennas p 32 A85-23652 Equations of motion governing the deployment of a arms p20 A85-15745 BOOMS (EQUIPMENT) Survey of deployable antenna concepts flexible linkage from a spacecraft p 10 A85-23663 [AIAA PAPER 85-0023] p 20 A85-19462 Torsional vibration of booms with open cross section Conceptual design for scaled truss antenna flight caused by unidirectional radiant heating ASTRONOMICAL NETHERLANDS SATELLITE expenment p22 A85-26350 Ten years after the launch of ANS - Looking back in [NASA-TM-85804] p4 N85-12932 BOUNDARY LAYERS perspective p 54 A85-26770 Workshop on Mechanical Technology for Antennas — Instrumentation for Application Number 1 Mass conferences, satellite antennas ASTRONOMICAL TELESCOPES spectrometnc analysis of the boundary layer associated [ESA-SP-225] p11 N85-13999 A modular approach to developing a large deployable with the tethered satellite p 58 N85-20372 Antenna mechanical technologies within ESA reflector p7 A85-22685 BRAYTON CYCLE p11 N85-14000 Space - The future of mankind p 3 A85-25697 Dynamic power systems for power generation High performance deployable antenna structures Astronomers, Congress, and the Large Space p33 N85-13892 p11 N85-14001 Telescope p 54 A85-27973 Active cooling requirements for propellant storage Offset unfuriable antenna concepts p5 N8S-14002 ASTROPHYSICS p48 N85-17004 Electrical consequences of mechanical antenna Report of the Electrodynamic Interactions Panel BUCKLING charactenstics p 33 N85-14006 p 34 N85-20353 Minimum weight design of truss structures with Structural aspects of SAR antenna for Japanese Earth ATMOSPHERIC DENSITY geometric nonlinear behavior p 10 A85-18694 Resources Satellite 1 p 12 N85-14007 Determination of atmosphenc density using a Technology for the ERS-1 SAR antenna space-launched projectile p 33 N85-14008 [AIAA PAPER 85-0327] p2 A85-20866 Mechanical/thermal design of a polarization sensitive ATMOSPHERIC ENTRY reflector — communication satellites p 15 N85-14009 CAMERAS A survey of aeroasststed orbit transfer Preliminary design of an Earth-based debns detection CASA technological effort in the field of antennas — p53 A85-21826 satellite radar antennas p 33 N85-14010 system using current technology and existing Trajectory analysis of radiative heating for planetary BAe antenna hardware technology for current satellite installations p40 N85-21199 missions with aerobraking of spacecraft CANADIAN SPACE PROGRAM projects p9 N85-14011 p 14 A85-21829 Technology and performances of structural thermal Some results of the MSAT phase B studies and their ATMOSPHERIC PHYSICS impact on system design mechanical equipment used for antenna of TV SAT-TDF Science Applications, part 1 p 5 N85-20346 1 program p 15 N85-14012 [IAF PAPER 84-89] p 1 A85-13045 ATTITUDE CONTROL CANTILEVER BEAMS CASA activities in antenna technology — satellite Comparing attitude control effectiveness for actuators antennas p39 N85-14015 Optimal design of a passive vibration absorber for a on two bodies of a six body model of a flexible spacecraft ARABSAT spacecraft Rx and Tx antenna truss beam p 19 ASS-13638 with that for actuators restncted to a single body mechanisms p34 N85-14022 CAPACITANCE p17 A85-11086 Compensator development and examination of Charactenstics of arc currents on a negatively biased Developing sensitivity coefficients for a state vanable solar cell array in a plasma p31 A85-18608 performance and robustness model of a flexible spacecraft with modular attitude [NASA-CR-175470] p 34 N85-20244 CAPILLARY FLOW control p 17 A85-11087 Capillary Pump Loop (CPL) heat pipe development ANTENNAS Dynamical modelling of a gravity-loaded rectangular Antenna engineering handbook /2nd edition/ status report plate as a test configuration for attitude control of large p30 A85-16081 [NASA-CR-175273] p 16 N85-17323 space structures CARBON FIBER REINFORCED PLASTICS Conceptual design for scaled truss antenna flight [IAF PAPER 84-391] p 18 A85-13245 expenment Influence of simulated space environment on the A signed switching time bang-bang attitude control law [NASA-TM-85804] p4 N85-12932 behavior of carbon-fiber-reinforced plastics with +, -45 for fine pointing of flexible spacecraft p 19 A85-13893 Reduction method for thermal analysis of complex ply onentations II p36 A85-14163 Autonomous momentum management for the CDG aerospace structures Continuous graphite/polysulfone RP thermofomnmg for planar Space Station [NASA-TP-2373] p 15 N85-16066 large space structure construction p36 A85-15638 [AIAA PAPER 854)031 ] p 21 A85-19468 APOGEE BOOST MOTORS Development of advanced composite tubular structures Integrated Power and Attitude Control Systems for TOS and AMS - Amenca's new capabilities in space for antenna reflector p 10 A85-24817 Space Station transportation -- Transfer Orbit Stages and Apogee and Influence of thermal cycling on the behavior of CFRP [AIAA PAPER 85-0358] p 31 A85-19695 Maneuvering Stages matenal for space structures p39 N85-14013 Integratable propulsion systems for the Space Station [IAF PAPER 84-220] p 51 A85-13141 CARRIER TRANSPORT (SOLID STATE) p46 A85-23393 ARABSAT Influence of starting matenal and technological Modular design attitude control system ARABSAT spacecraft Rx and Tx antenna processes on the radiation resistance of silicon solar cells [NASA-CR-171182] p 24 N85-10098 mechanisms p 34 N85-14022 for space use — French thesis p 38 A85-30024 An Assessment of Integrated Flywheel System ARC DISCHARGES CASSEGRAIN OPTICS Technology Charactenstics of arc currents on a negatively biased Solar concentrator for space power generation [NASA-CP-2346] p 26 N85-13850 solar cell array in a plasma p 31 A85-18608 [AIAA PAPER 854)164] p 45 A85-19561 Perspectives on energy storage wheels for space station ARCHITECTURE (COMPUTERS) CATALYSIS application p47 N85-13860 The computer-communication link for the innovative use Catalytic surface effect on ceramic coatings for an Hemispherical antenna pointing mechanism — satellite of Space Station p32 N85-11016 aeroassisted orbital transfer vehicle p 38 A85-29730 antennas p 26 N85-14021 ARTIFICIAL GRAVITY CERAMIC COATINGS Summary presentation of the Constellations Panel Proceedings of a Workshop on Applications of Tethers Catalytic surface effect on ceramic coatings for an p57 N85-20359 in Space, Volume 2 aeroassisted orbital transfer vehicle p 38 A85-29730 Report of the Constellations Panel p27 N85-20368 [NASA-CR-171197] p55 N85-12077 CERAMICS AUTOMATIC CONTROL Inorganic composites for space applications ARTIFICIAL INTELLIGENCE Office of Technology Assessment p4 N85-10872 Office of Technology Assessment p4 N85-10872 p38 N85-11047 Control of large collector arrays The SSPS CHAFF A functional vehicle for autonomous mobile robot expenence Spectral charactenstics of radar echoes from research [DE85-001461] p 34 N85-20553 aircraft-dispensed chaff p 23 A85-26606 [AD-A150052] p 42 N85-21666 CHANNELS (DATA TRANSMISSION) ARTIFICIAL SATELLITES Wavelength division multiplexing for future Space Station Stability of a nng of connected satellites B data systems p 32 A85-25359 [IAF PAPER 84-342] p 18 A85-13206 BALANCING CHARGED PARTICLES Sky-nooks, fish-warmers and hub-caps - Milestones in SCATHA (spacecraft charging at high altitudes) plasma LOG balancing and reduced LOG compensation of satellite communications — technological development interaction expenment SC-3 high energy particle p32 A85-25101 symmetric passive systems — Linear Quadrate Gaussian p23 A85-27238 spectrometer; SC-8 energetic ion composition The long term behaviour of Earth orbits and the BALL BEARINGS expenment implications for debns control p 58 N85-21213 An evaluation of grease type ball beanng lubncants [AD-A149728] p 35 N85-21252 ASSEMBLIES operating in vanous environments CHECKOUT SMP A solid modeling program [NASA-TM-86480] p 38 N85-11239 Definition of ground test for Large Space Structure (LSS) [NASA-CR-172473] p8 N85-11570 BEAMS (SUPPORTS) control verification ASSEMBLING Swing-arm beam erector (SABER) concept for single [NASA-TM-86495] p 28 N85-21249 Ground test article for deployable space structure astronaut assembly of space structure CHEMICAL ANALYSIS systems [NASA-TP-2379] p 42 N85-19015 Inorganic composites for space applications [NASA-CR-171301] p9 N85-19011 BENDING p38 N85-11047 ASTRODYNAMICS Modelling and identification of the structural properties Analysis of Nonvolatile Residue (NVR) from spacecraft Dynamic isolation of a spacecraft science platform via of an astromast systems momentum compensation p 17 A85-11082 [CRC-1374] p 12 N85-18352 [NASA-TM-86184] p 39 N85-17019

A-2 SUBJECTINDEX CONTROL SIMULATION

CHEMICAL EQUILIBRIUM COMPLEX SYSTEMS CONCENTRATORS Chemical nonequilibnum effects on flowtields for Principal component analysis of flexible systems - Near-optimum design of GaAs-based concentrator aeroasststsd orbital transfer vehicles p 53 ABS-21B31 Open-loop case p7 A85-16648 space solar cells for 80 C operation p30 A85-15800 CHEMICAL PROPULSION A methodology for organizing performance requirements CONDUCTIVE HEAT TRANSFER Simulation of reusable crslunar space transportation for complex dynamical systems p 3 A85-25117 Heat conduction problems in large space structure systems with special consideration of chemical propulsion COMPOSITE MATERIALS [IAF PAPER 84-400] p 13 A85-13253 — German thesis p 44 A85-15874 Thermoelastic behaviour of space structures in CONFERENCES CIVIL AVIATION composite materials EASCON '83, Proceedings of the Sixteenth Annual West Europe report. Science and technology [IAF PAPER 84-404] p 35 AB5-13257 Electronics and Aerospace Conference and Exposition, [JPRS-WST-85-008] p57 N85-20174 Influence of the lamination and of some environmental Washington, DC, September 19-21, 1983 CLEAN ENERGY effects on damping characteristics of advanced p51 A85-14426 composites for space structures The potential of solar power satellites for developing Reinforced Plastics/Composites Institute, Annual [IAF PAPER 84-405] p 38 A85-13258 countries p 53 A85-24654 Conference, 38th, Houston, TX, February 7-11, 1983, COMPOSITE STRUCTURES COHERENT RADAR Preprints p 36 A85-15626 Advanced analysis methods for spacecraft composite Spectral characteristics of radar echoes from structures p 37 A85-15993 Technology vectors, Proceedings of the Twenty-ninth aircraft-dispensed chaff p 23 AB5-26606 National SAMPE Symposium and Exhibition, Reno, NV, COMPRESSIVE STRENGTH Apnl 3-5, 1984 p52 A85-15976 COLLISIONS Influence of simulated space environment on the Orbital Debris behavior of carbon-fiber-reinforced plastics with +. -45 International space programmes and policies [NASA-CP-2360] p 40 N85-21188 ply orientations II p 36 A85-14163 p2 A85-20507 Assessment of satellite collision hazards by simulated COMPUTER AIDED DESIGN Deployable optical systems. Proceedings of the Meeting, sampling in space p 40 N85-21195 Impacts of life support system on space station design Los Angeles, CA, January 18, 19, 1983 Geosynchronous satellite collision avoidance [IAF PAPER 84-166] p6 A85-13100 p 53 A85-22576 p58 N85-21197 Satellite grasping manipulator system Satellite communication antenna technology Preliminary design of an Earth-based debns detection [IAF PAPER 84-371] p 41 A85-13229 p 31 A85-23651 system using current technology and existing Advanced analysis methods for spacecraft composite International FEM-Congress, Baden-Baden, West installations p40 N85-21199 structures p 37 A85-15993 Germany, November 14. 15. 1983, Proceedings Debns impact on Earth-orbiting spacecraft Modular computer system cuts spacecraft simulation p8 A85-26675 p 59 N85-22234 costs p 10 A85-18435 Office of Technology Assessment p 4 N85-10872 Mass properties analysts and control of advanced space COMMAND AND CONTROL Second Symposium on Space Industnalrzation — space structures through computerized integration with design EASCON '83, Proceedings of the Sixteenth Annual commercialization and structural analysts Electronics and Aerospace Conference and Exposition, [NASA-CP-2313] p4 N85-11011 [SAWE PAPER 1527] p 13 A85-18812 Washington, DC, September 19-21, 1983 Proceedings of a Workshop on Applications of Tethers Computer aided design of multiple input/output control p 51 A85-14426 in Space, Executive Summary systems for multibody flexible Space Station [NASA-CR-171195] p 55 N85-12075 COMMERCIAL SPACECRAFT [AIAA PAPER 85-0223] p7 A85-19600 Proceedings of a Workshop on the Applications of The low cost development test, and production of a Formex configuration processing in structural Tethers in Space, Volume 1 commercial STS upper stage TOS engineenng — Book p 14 A85-20916 [AIAA PAPER 85-0313] p 45 A85-19660 [NASA-CR-171196] p 55 N85-12076 International FEM-Congress, Baden-Baden, West Proceedings of a Workshop on Applications of Tethers The communication-satellite market to the year 2000 Germany, November 14. 15, 1983, Proceedings in Space, Volume 2 p3 A85-26771 p8 A85-26675 [NASA-CR-171197] p55 N85-12077 Commercialization of space - Incentives, impediments Conceptual design for scaled truss antenna flight An Assessment of Integrated Flywheel System and alternatives p 3 A85-27375 expenment Technology COMMUNICATION [NASA-TM-85804] p4 N85-12932 [NASA-CP-2346] p 26 N85-13850 Second Symposium on Space Industnalrzation — space ACOSS 17 (Active Control of Space Structures) Space Power commercialization [AD-A150007] p28 N85-21253 [NASA-CP-2352] p56 N85-13880 [NASA-CP-2313] p4 N85-11011 Computer integration of engineenng design and Workshop on Mechanical Technology for Antennas — The real world The user p32 N85-11017 production A national opportunity conferences, satellite antennas COMMUNICATION NETWORKS [NASA-CR-175483] p 59 N85-21414 [ESA-SP-225] p11 N85-13999 Some results of the MSAT phase B studies and their COMPUTER AIDED MANUFACTURING OTV Propulsion Issues impact on system design Computer integration of engineenng design and [NASA-CP-2347] p 48 N85-16989 [IAF PAPER 84-89] p1 A85-13045 production A national opportunity Applications of Tethers in Space, volume 1 Wavelength division multiplexing for future Space Station [NASA-CR-175483] p 59 N85-21414 [NASA-CP-2364] p 57 N85-20339 data systems p 32 A85-25359 COMPUTER NETWORKS Applications of Tethers in Space, volume 2 Intelsat's twentieth anniversary - Two decades of The computer-communication link for the innovative use [NASA-CP-2365] p 57 N85-20361 innovation in global communications p 54 A85-26369 of Space Station p32 N85-11016 Orbital Debns COMMUNICATION SATELLITES COMPUTER PROGRAMMING [NASA-CP-2360] p40 N85-21188 Cost effective launch technology for communications Power subsystem automation study CONGRESSIONAL REPORTS satellites [NASA-CR-171213] p 33 N85-12299 National Aeronautics and Space Administration [IAF PAPER 84-04] p 50 A85-12979 COMPUTER PROGRAMS p4 N85-10871 Mass optimisation of telecommunications satellites Spacecraft systems engineenng and geometry Office of Technology Assessment p 4 N85-10872 [IAF PAPER 84-230] p 13 A85-13146 modelling - The ESABASE-MATVIEW approach Commercial space launches Robust attitude control of a large communication satellite p8 A85-27696 [S-REPT-98-656] p6 N85-21225 with flexible solar arrays IAC user manual CONICAL BODIES [IAF PAPER 84-ST-06] p 19 A85-13293 [NASA-CR-175300] p8 N85-10677 Expenmental and predicted heating distributions for Report of the student working group to the panel on SMP A solid modeling program biconics at incidence in air at Mach 10 satellite communications — Space Applications Board [NASA-CR-172473] p8 N85-11570 [NASA-TP-2334] p 14 N85-12313 Crestwood 1982 Summer Study p30 A85-14430 A user's guide to the Flexible Spacecraft Dynamics and CONICAL SCANNING Satellite communication antenna technology Control Program Spectral characteristics of radar echoes from p 31 A85-23651 [NASA-TM-87389] p 24 N85-12586 aircraft-dispensed chaff p23 A85-26606 The systems background for satellite communication Performance assessment of aero-assisted orbital CONSTELLATIONS antennas p 32 A85-23652 transfer vehicles p56 N85-16993 Proceedings of a Workshop on Applications of Tethers Sky-hooks, fish-warmers and hub-caps - Milestones in COMPUTER SYSTEMS DESIGN in Space, Executive Summary satellite communications — technological development EASCON '83, Proceedings of the Sixteenth Annual [NASA-CR-171195] p 55 N85-12075 p32 A85-25101 Electronics and Aerospace Conference and Exposition, Proceedings of a Workshop on Applications of Tethers The communicatiorvsatellite market to the year 2000 Washington. DC, September 19-21, 1983 in Space, Volume 2 p3 A85-26771 p 51 A85-14426 [NASA-CR-171197] p 55 N85-12077 Development and application of new technologies in The computer-communication link for the innovative use CONTINUITY (MATHEMATICS) ESA's Olympus programme p 3 A85-2769S of Space Station p 32 N85-11016 Shear deformation plate continua of large Offset unfurtable antenna concepts p 5 N85-14002 COMPUTERIZED SIMULATION double-layered space structures p 8 N85-10391 Technology and performances of structural thermal Factors affecting push-broom performances in future CONTRACT MANAGEMENT mechanical equipment used for antenna of TV SAT-TOF space platforms Ground test article for deployable space structure 1 program p 15 N85-14012 [IAF PAPER 84-116] p 29 ASS-13066 systems Commercial space Europe should have independent [NASA-CR-171301] p9 N85-19011 Simulation of reusable ctslunar space transportation strategy pS N85-19205 CONTROL systems with special consideration of chemical propulsion The international environment UNISPACE '82 and the — German thesis p 44 A85-15874 Active control of large space structures An introduction ITU A relationship between orbit-spectrum resource and overview Computer simulation of plasma electron collection by allocation and orbital debns p 58 N85-21215 [NASA-TM-86490] p 27 N85-19014 PIX-II — solar array-space plasma interaction COMMUNICATIONS TECHNOLOGY SATELLITE CONTROL CONFIGURED VEHICLES [AIAA PAPER 85-0386] p 45 A85-19715 Damping synthesis for a spacecraft using substructure Some applications of direct adaptive control to large and component data A user's guide to the Flexible Spacecraft Dynamics and structural systems p 19 A85-13636 [CRC-1365] p24 N85-12082 Control Program CONTROL SIMULATION COMPENSATORS [NASA-TM-87389] p 24 N85-12586 Comparing attitude control effectiveness for actuators Compensator development and examination of Level of effort p25 N85-13839 on two bodies of a six body model of a flexible spacecraft performance and robustness Elimination of uncontrollable rigid body mode, appendix with that for actuators restricted to a single body [ NASA-CR-175470] p 34 N85-20244 C p25 N85-13842 p 17 A85-11086

A-3 CONTROL STICKS SUBJECT INDEX

Developing sensitivity coefficients for a state variable COST EFFECTIVENESS Design consideration of space construction facility model of a flexible spacecraft with modular attitude Cost effective launch technology for communications [IAF PAPER 84-26] p6 A85-12992 control P 17 A85-11087 satellites Impacts of life support system on space station design Elimination of uncontrollable ngid body mode, appendix [IAF PAPER 84-04] p 50 A85-12979 (IAF PAPER 84-166] p6 A85-13100 C p25 N85-13842 Some design concepts for Intelsat VII Optimal design of a passive vibration absorber for a CONTROL STICKS p7 A85-15496 truss beam p 19 A85-13638 Level of effort p25 N85-13839 The cost effectiveness and optimal parameters of an Near-optimum design of GaAs-based concentrator CONTROL SYSTEMS DESIGN electric rocket propulsion system for an mterorbital space solar cells for 80 C operation p 30 A85-15800 Alleviation of observation spillover in continuous transport vehicle p 46 A85-23990 Thermal storage analysis for large manned space platforms structures P 17 A85-12434 COUNTER-ROTATING WHEELS Satellite grasping manipulator system Perspectives on energy storage wheels for space station [AIAA PAPER 85-0066] p 14 A85-19493 Precision of mesh-type reflectors for large space-borne [ IAF PAPER 84-371 ] p 41 A85-13229 application p47 N85-13860 antennas p31 A85-21835 Number and placement of control system components CRANES Spacecraft systems engmeenng and geometry considering possible failures — for large space Variable geometry truss and its application to deployable structures p 19 A85-13634 truss and space crane arm modelling - The ESABASE-MATVIEW approach p8 A85-27696 Sampled data control of flexible structures using [IAF PAPER 84-394] p 10 A85-13248 constant gain velocity feedback p29 A85-13640 CROSS POLARIZATION Stability analysis of flexible spaceraft with PIO Modal decoupling conditions for distributed control of Mechanical/thermal design of a polarization sensitive controller [CRC-1372] p 28 N85-21247 flexible structures p 19 A85-13641 reflector — communication satellites p 15 N85-14009 DEVELOPING NATIONS Optimal simultaneous structural and control design of CRYOGENIC COOLING Space exploitation - Spacelab an easy approach for maneuvenng flexible spacecraft p 7 A8S-18338 Active cooling requirements for propellant storage Closed form optimal control solutions for continuous p48 N85-17004 developing countries Prospectrves and suggestions by Aentalia p 1 A85-12502 linear elastic systems — with applications to flexible CRYOGENIC EQUIPMENT appendage satellite and rotational manipulator arm Passive Orbital Disconnect Strut (POOS 3) structural test The potential of solar power satellites for developing controls p20 A85-18672 program countnes p 53 A85-24654 Active vibration control for lasers and spacecraft [NASA-CR-177325] p 16 N85-17020 DIELECTRICS p 21 A85-22584 CRYOGENIC FLUID STORAGE Dielectric matenal in the space environment Active control technology development at NASA Passive Orbital Disconnect Strut (POOS 3) structural test p37 A85-24672 p22 A8S-22S86 program DIFFERENTIAL GEOMETRY Structural control research and experiments at [NASA-CR-177325] p 16 N85-17020 Precision of mesh-type reflectors for large space-borne NASA/LaRC p 22 A85-22587 antennas p 31 A85-21835 CRYOGENIC FLUIDS Level of effort p 25 N85-13839 OTV Propulsion Issues DIGITAL COMMAND SYSTEMS Oral presentation of first year final report, appendix A [NASA-CP-2347] p48 N85-16989 Speed test results and hardware/software study of computational speed problem, appendix D p 25 N85-13840 CRYSTAL GROWTH NASA-VCOSS dynamic test facility Matenal sciences in space p 36 A85-13500 p25 N85-13843 [NASA-TM-86491 ] p 27 N85-18998 CYCLES DIGITAL FILTERS Compensator development and examination of Investigation of welded interconnection of large area Adaptive modal control of structural dynamic systems using recursive lattice filters p 23 A85-26435 performance and robustness wraparound contacted silicon solar cells [NASA-CR-175470] p 34 N85-20244 [NASA-CR-174438] p 39 N85-19519 DISTRIBUTED PARAMETER SYSTEMS Modal decoupling conditions for distributed control of CONTROL THEORY CYCLIC LOADS Autonomous momentum management for space flexible structures p 19 A85-13641 Some applications of direct adaptive control to large Qualitative results for distributed systems with discrete structural systems P 19 A85-13636 station [NASA-CR-174065] p 24 N85-12931 damping and stiffness with application to control Pnncipal component analysis of flexible systems - [AD-A145525] p 24 N85-11382 Open-loop case p7 A85-16648 CYLINDRICAL ANTENNAS Precision of mesh-type reflectors for large space-borne DRAG Poles and transmission zeros of flexible spacecraft Report of the Constellations Panel p 27 N85-20368 antennas p 31 A85-21835 control systems p 22 A85-26433 DYNAMIC CONTROL Definition of ground test for venfication of large space Closed-form solutions for feedback control with terminal structure control constraints p20 A85-18331 [NASA-CR-171208] p9 N85-13838 Qualitative results for distnbuted systems with discrete Definition of ground test for Large Space Structure (LSS) DAMPING damping and stiffness with application to control control venfication, appendix G p 25 N85-1384S Influence of the lamination and of some environmental [AD-A145525] p 24 N85-11382 Review of technical papers, appendix H / effects on damping charactenstics of advanced Experiments in control of flexible structures with p25 N85-13846 composites for space structures uncertain parameters p 24 N85-13837 Ground test expenment for large space structures, [IAF PAPER 84-405] p 36 A85-13258 Review of technical papers, appendix H appendix I p 56 N85-13847 Damping synthesis for a spacecraft using substructure p25 N85-13846 and component data Dynamics and controls working group summary Precise control of flexible manipulators p26 N85-13854 [NASA-CR-174210] p 42 N85-16178 [CRC-1365] p24 N85-12082 Identification of vibration parameters of flexible DYNAMIC MODELS Ground test expenment for large space structures structures p 27 N85-18360 Dynamical modelling of a gravity-loaded rectangular [NASA-TM-86489] p9 N85-19013 Stability analysis of flexible spaceraft with PID plate as a test configuration for attitude control of large CONTROLLABILITY controller space structures Environmental effects on the dynamics and control of [CRC-1372] p28 N85-21247 [IAF PAPER 84-391] p 18 A85-13245 an orbiting large flexible antenna system DATA PROCESSING The development of a frequency method for the [IAF PAPER 84-358] p 18 A85-13220 Speed test results and hardware/software study of mathematical modeling of the motion of an elastic space A functional vehicle for autonomous mobile robot computational speed problem, appendix D vehicle p20 A85-17054 research p 25 N85-13843 DYNAMIC MODULUS OF ELASTICITY [AD-A150052] p 42 N85-21666 DATA SAMPLING Elastic dispersion effects on dynamics and control of CONTROLLERS Sampled data control of flexible structures using large modular antennas — spacecraft antennas Level of effort p 25 N85-13839 constant gain velocity feedback p 29 A85-13640 p26 N85-14019 Speed test results and hardware/software study of DECOUPLING DYNAMIC RESPONSE computational speed problem, appendix 0 Modal decoupling conditions for distributed control of The investigation of tethered satellite system p25 N85-13843 flexible structures p 19 A85-13641 dynamics CONVERGENCE DEFECTS [NASA-CR-171278] p 26 N85-15772 Qualitative results for distributed systems with discrete Effects of member imperfections on the behavior of Modelling and identification of the structural properties damping and stillness with application to control space trusses p 11 N85-11363 of an astromast [AD-A145525] p 24 N85-11382 DEGREES OF FREEDOM [CRC-1374] p12 N85-18352 Keynote address p27 N85-18378 CONVOLUTION INTEGRALS Autonomous momentum management for space Operational fitness of box truss antennas in response Closed form optimal control solutions for continuous station [NASA-CR-174065] p 24 N85-12931 to dynamic slewing linear elastic systems — with applications to flexible [NASA-CR-172470] p 27 N85-19012 appendage satellite and rotational manipulator arm DELAMINATING DYNAMIC STRUCTURAL ANALYSIS controls p20 A85-18672 Effects of residual stresses in polymer matnx composites p 35 A85-12395 The improvement of free-mode methods in component COOLING SYSTEMS DEPLOYMENT mode synthesis techniques and its accuracies Heat rejection working group synopsis Equations of motion governing the deployment of a p 17 A85-12442 p15 N85-13906 flexible linkage from a spacecraft Application of modal synthesis concepts to spacecraft COSMONAUTS [AIAA PAPER 85-0023] p 20 A85-19462 design venfication p 17 A85-12455 Salyut Mission Report p3 A85-25700 Survey of deployable antenna concepts Environmental effects on the dynamics and control of COST ANALYSIS p 10 A85-23663 an orbiting large flexible antenna system Economics of permanent polar platforms (PPP) for global In-orbit performance of INTELSAT V communications [IAF PAPER 84-358] p 18 A85-13220 monitonng antennae deployment systems p33 N85-14018 Large space structures ground and flight progress [IAF PAPER 84-226] p2 A85-13144 ARABSAT spacecraft Rx and Tx antenna [IAF PAPER 84-388] p 13 A85-13243 Space Transportatiom System (STS) propellant mechanisms p34 N85-14022 Dynamic charactenstics of a space reflector support scavenging system study Volume 3 Cost and work DESIGN ANALYSIS structure p 22 A85-24949 breakdown structure-dictionary Application of modal synthesis concepts to spacecraft Multicntical optimization of a large space structure [NASA-CR-171850-VOL-3] p 49 N85-20002 design venfication p 17 A85-12455 p11 A85-28489

A-4 SUBJECTINDEX EUROPEAN SPACE PROGRAMS

(AC user manual ELECTRIC PROPULSION Dynamics and controls working group summary [NASA-CR-175300) p8 N85-10677 Performance capabilities of the 12-centimeter Xenon ion p26 N85-13854 Elastic dispersion effects on dynamics and control of thruster p 44 A85-16439 Perspectives on energy storage wheels for space station large modular antennas — spacecraft antennas Optimal electric propulsion orbit transfer vehicle design application p47 N85-13860 p26 N85-14019 and operational effectiveness Potential of flywheels for spacecraft energy storage Study of structure control dynamic interaction for radio [AIAA PAPER 85-0431] P 45 A85-19744 p33 N85-13890 frequency antenna control systems — satellite antennas The cost effectiveness and optimal parameters of an Space power management and distribution status and p26 N85-14020 electric rocket propulsion system for an mterorbital trends p 47 N85-13896 Keynote address P 27 N85-18378 transport vehicle p46 A85-23990 Engmeenng model system study for a regenerative fuel DYNAMICAL SYSTEMS ELECTRIC WELDING cell Study report Toroid Joining Gun — thermoplastic welding system A methodology for organizing performance requirements [NASA-CR-174801] p 47 N85-16292 for complex dynamical systems p 3 A85-25117 using induction heating ENERGY TECHNOLOGY [SAE PAPER 850408] p 38 AB5-25988 The potential of solar power satellites for developing ELECTRICAL ENGINEERING countries p 53 A85-24654 Antenna engineering handbook /2nd edition/ ENGINE DESIGN p30 A85-16081 Vehicle/engine integration — oibrt transfer vehicles EARTH OBSERVATIONS (FROM SPACE) ELECTRICAL INSULATION p48 N85-17008 A case for Gohrem - Geosynchronous orbit high Dielectric material in the space environment Orbital transfer vehicle propulsion issues resolution earth monrtonng p 50 A85-10261 p37 A85-24672 p48 N85-17009 Architecture and implementation of an in-orbt ELECTRODYNAMICS ENGINEERING MANAGEMENT infrastructure Proceedings of a Workshop on the Applications of A methodology for organizing performance requirements [IAF PAPER 84-29] p6 A85-12995 Tethers in Space, Volume 1 for complex dynamical systems p 3 A85-25117 Economics of permanent polar platforms (PPP) for global [NASA-CR-171196] p 55 N85-12076 ENVIRONMENTAL MONITORING monrtonng Proceedings of a Workshop on Applications of Tethers A case for Gohrem - Geosynchronous orbit high [IAF PAPER 84-226] p2 A85-13144 in Space, Volume 2 resolution earth monrtonng p 50 A85-10261 Salyut Mission Report p3 A85-25700 [NASA-CR-171197] p 55 N85-12077 Economics of permanent polar platforms (PPP) for global EARTH ORBITS The investigation of tethered satellite system monitoring OTV propulsion tecnology programmatic overview dynamics [IAF PAPER 84-226] p2 A85-13144 p 48 N85-16997 [NASA-CR-171278] p 26 N85-15772 ENVIRONMENTAL TESTS Report of the Constellations Panel p27 N85-20368 Science Applications, part 1 p 5 N85-20346 Influence of the lamination and of some environmental Oebns in the geostationary orbit ring, the endless Electrodynamic interactions p 34 N85-20348 effects on damping charactenstics of advanced shooting gallery The necessity for a disposal policy Summary presentation of the Electrodynamics composites for space structures p58 N85-21214 Interactions Panel P34 N85-20356 [IAF PAPER 84-405] p 36 A85-13258 Environment definition, small particles, diameter less Applications of Tethers in Space, volume 2 EOSS than or equal to 1 MM p 40 N85-21223 [NASA-CP-2365] p 57 N85-20361 In situ orbital debns expenment concepts EARTHQUAKES Report of the Electrodynamic Interactions Panel p58 N85-21198 The Shock and Vibration Digest, volume 16, no 11 p 34 N85-20363 EQUATIONS OF MOTION [AD-A148466] p 16 N85-17382 Report of the Transportation Panel Equations of motion governing the deployment of a ECONOMIC ANALYSIS p57 N85-20364 flexible linkage from a spacecraft Satellite servicing A business opportunity? Report of the Technology and Test Panel [AIAA PAPER 85-0023] p 20 A85-19462 p55 N85-11056 p57 N85-20370 Damping synthesis for a spacecraft using substructure Doing business in space How to get there from here ELECTROEPITAXY and component data p55 N85-11057 Producing gallium arsenide crystals in space [CRC-1365] p24 N85-12082 ECONOMIC FACTORS p54 N85-11023 EQUIVALENCE Second Symposium on Space Industrialization — space ELECTROLYSIS Shear deformation plate continua of large commercialization Engmeenng model system study for a regenerative fuel double-layered space structures p 8 N85-10391 [NASA-CP-2313] p4 N85-11011 cell Study report ERROR ANALYSIS Satellite servicing A business opportunity? [NASA-CR-174801] p 47 N85-16292 Finite multiple burn orbit transfer error analysis via pSS N85-11056 ELECTROLYTIC CELLS covanance matrix p 45 A85-22444 EDUCATION Engmeenng model system study for a regenerative fuel ERS-1 (ESA SATELLITE) Space as motivational propulsion — Shuttle Orbiter cell Study report Technology for the ERS-1 SAR antenna related pro|ects as educational tools [NASA-CR-174801] p 47 N85-16292 p33 N85-14008 [IAF PAPER 84-407] p 51 A85-13259 ELECTROMAGNETIC INTERACTIONS ESA SATELLITES IAC user manual Applications of Tethers in Space, volume 2 Bipropellant propulsion in the new generation of [NASA-CR-175300] p8 N85-10677 [NASA-CP-2365] p 57 N85-20361 satellites and upper stages The role of BPD Difesa-Spazio EDUCATIONAL TELEVISION Report of the Electrodynamic Interactons Panel in this field - Manufactunng facilities and technology Report of the student working group to the panel on p34 N85-20363 p43 A85-12519 satellite communications — Space Applications Board ELECTROMAGNETIC PROPULSION Development and application of new technologies in Crestwood 1982 Summer Study p 30 A85-14430 Preliminary analysis of space mission applications for ESA's Olympus programme p 3 A85-27695 EIGENVALUES electromagnetic launchers ETCHING Modal control of structural systems [NASA-CR-174067] p 47 N85-12071 Atomic oxygen surface interactions - Mechanistic study [AD-A149734] p 28 N85-21235 ELECTRON BOMBARDMENT using ground-based facilities ELASTIC DAMPING Performance capabilities of the 12-centimeter Xenon ion [AIAA PAPER 85-0473] p 37 A85-19771 Flexural vibration of gravity-stabilized, structurally thmster p 44 A85-16439 EULER-LAGRANGE EQUATION damped, large flexible satellites p22 A85-26434 ELECTRON IRRADIATION Recursive Langrangian dynamics of flexible manipulator ELASTIC SYSTEMS Influence of starting material and technological arms p 20 ASS-15745 Closed form optimal control solutions for continuous processes on the radiation resistance of silicon solar cells EURECA (ESA) linear elastic systems — with applications to flexible for space use — French thesis p 38 AB5-30024 European removable earner (Eureca) and evolutionary appendage satellite and rotational manipulator arm Evaluation and prediction of long-term environmental space carrier for microgravity, Earth observation and controls p 20 A85-18672 effects of nonmetallic matenals technology demonstration pSS N85-11032 ELASTIC WAVES [NASA-CR-171353] p 39 N85-19137 EUROPEAN SPACE AGENCY Elastic waves propagation in bounded periodic ELECTRONIC EQUIPMENT Orientation and trends in European technology — space structures — for modeling large space structures Space power management and distribution status and programs [IAF PAPER 84-395] p 19 A85-13249 trends P47 N85-13896 [IAF PAPER 84-377] p2 A85-13233 ELASTODYNAMICS ELECTROSTATIC CHARGE Europe in space 1985-2000 p3 A85-26011 Application of modal synthesis concepts to spacecraft A plan lor controlling electrostatic discharges on Commercial space Europe should have independent design verification p 17 A85-12455 geosynchronous spacecraft p 32 A85-26685 strategy p5 N85-19205 ELECTRIC ARCS ELECTROSTATICS EUROPEAN SPACE PROGRAMS Circuit transients due to negative bias arcs on a high Research on large, highly accurate, inflatable Lay-out of a re-usable re-entry vehicle required in a future voltage solar array in low earth orbit reflectors European low earth orbit scenano [AIAA PAPER 85-0385] p 45 A85-19714 [AD-A145080] pit N85-10099 [IAF PAPER 84-06] pSO A85-12981 ELECTRIC CONTROL ENERGY CONSERVATION Space station related investigations in Europe Displacement control of flexible structures using Efficient inclination control for geostationary satellites [IAF PAPER 84-28] p 50 A85-12994 electrohydmulic servo-actuators p23 A85-29144 [AIAA PAPER 85-0216] p 21 A85-19595 Utilization and economics of a European low earth orbit ELECTRIC DISCHARGES ENERGY CONVERSION EFFICIENCY Space Platform A plan for controlling electrostatic discharges on Solar concentrator for space power generation [IAF PAPER 84-57] p 1 A85-13016 geosynchronous spacecraft p 32 A85-26685 [AIAA PAPER 85-0164] p 45 A85-19561 Satellite grasping manipulator system ELECTRIC POTENTIAL The maximum efficiency of an isolated solar energy [IAF PAPER 84-371] p 41 A85-13229 Potential of flywheels for spacecraft energy storage conversion device in space p 46 AB5-25797 Future prospects in space envisaged by a forum of p33 N85-13890 ENERGY STORAGE European space companies p 52 A85-16302 ELECTRIC POWER SUPPLIES Regenerative fuel cell energy storage system for a low The German remote sensing program Power subsystem automation study Earth orbit space station p52 A85-16881 [NASA-CR-171213] p 33 N85-12299 [NASA-CR-174802] p 47 N85-13371 Looking back on the past - The decision of Europe to ELECTRIC POWER TRANSMISSION An Assessment of Integrated Flywheel System participate in the post-Apollo program Power subsystem automation study Technology p53 A85-23824 [NASA-CR-171213] p 33 N85-12299 [NASA-CP-2346] p 26 N85-13850 Europe in space 1985-2000 p3 A85-26011

A-5 EXOBIOLOGY SUBJECT INDEX

Ten years after the launch of ANS - Looking back in NASA/MSFC ground expenment for large space Optimal simultaneous structural and control design of perspective p54 A85-26770 structure control verification maneuvering flexible spacecraft p 7 A85-18338 European retnevable earner (Eureca) and evolutionary [NASA-TM-86496] p 28 N85-21248 Equations of motion governing the deployment of a space carrier for microgravrty, Earth observation and FIBER OPTICS flexible linkage from a spacecraft technology demonstration p55 N85-11032 West Europe report Science and technology [AIAA PAPER 85-0023] p 20 A85-19462 Antenna mechanical technologies within ESA [JPRS-WST-85-008] p 57 N85-20174 On dynamical formulations of a tethered satellite system p11 N85-14000 Report of the Technology and Test Panel with mass transport EXOBIOLOGY p57 N85-20370 [AIAA PAPER 85-0117] p 21 A85-19529 Space greenhouse design p 50 A85-12927 Computer aided design of multiple input/output control FIBER REINFORCED COMPOSITES systems for multbody flexible Space Station Assessment of medical nsk in space flight Inflatable space-ngidized structures - Recent [AIAA PAPER 85-0223] p7 A85-19600 [IAF PAPER 84-189] P 51 A85-13114 developments of the matenal technology Active vibration control for lasers and spacecraft EXPANDABLE STRUCTURES [IAF PAPER 84-384] p 10 A85-13240 Inflatable space-ngidized structures - Recent p 21 A85-22584 Design preparations for large space structures developments of the matenal technology Poles and transmission zeros of flexible spacecraft [IAF PAPER 84-392] p 35 A85-13246 [IAF PAPER 84-384] P 10 A85-13240 control systems p 22 A85-26433 EXPENDABLE STAGES (SPACECRAFT) Reinforced Plastics/Composites Institute, Annual Flexural vibration of gravity-stabilized, structurally Commercial space launches Conference, 38th, Houston. TX, February 7-11, 1983, damped, large flexible satellites p 22 A85-26434 [S-REPT-98-656] p6 N85-21225 Preprints p 36 ASS-15626 Multicntical optimization of a large space structure EXPERIMENT DESIGN Inorganic composites for space applications p 11 A85-28489 Definition of ground test for verification of large space p38 N85-11047 Modular design attitude control system structure control FINANCIAL MANAGEMENT [NASA-CR-171182] p 24 N85-10098 [NASA-CR-171208] p9 N85-13838 Satellite servicing A business opportunity? Qualitative results for distributed systems with discrete Ground test experiment for large space structures, p55 N85-11056 damping and stiffness with application to control appendix I P 56 NB5-13847 FINITE ELEMENT METHOD [AD-A145525] p 24 N85-11382 EXPERT SYSTEMS Continuum modelling of damping in large space A user's guide to the Flexible Spacecraft Dynamics and Power subsystem automation study structures p 18 A85-12478 Control Program [NASA-CR-171213] P 33 N85-12299 Advanced analysis methods for spacecraft composite [NASA-TM-87389] p 24 N85-12586 EXTERNAL STORES structures p37 A85-15993 FLIGHT CHARACTERISTICS External tank aft cargo earner p 8 N85-11050 Generalized transform methods based finite element On dynamical formulations of a tethered satellite system EXTERNAL SURFACE CURRENTS methodology - Thermal/structural dynamic applications with mass transport When spacecraft get charged up, they have minds of [AIAA PAPER 85-0155] p 14 A85-19553 [AIAA PAPER 85-0117] p 21 A85-19529 their own p53 A85-24787 International FEM-Congress, Baden-Baden, West Determination of atmospheric density using a EXTERNAL TANKS Germany, November 14,15,1983, Proceedings space-launched projectile External tank aft cargo earner p 8 N85-11050 p8 A85-26675 [AIAA PAPER 85-0327] p2 A85-20866 EXTRATERRESTRIAL ENVIRONMENTS FLEXIBLE BODIES FLIGHT TESTS Natural environment design cntena for the Space Station The strongest structures with macrostrffness NASA-VCOSS dynamic test facility definition and preliminary design constraints p 10 A85-12933 [NASA-TM-86491] p 27 N85-18998 [NASA-TM-86498] p9 N85-21232 An optimal shape control of a large flexible radiator in EXTRAVEHICULAR ACTIVITY space FLUID DYNAMICS Advanced research and technology programs for Neutral buoyancy evaluation of technologies for space [IAF PAPER 84-64] p 18 A85-13023 advanced high-pressure oxygen-hydrogen rocket station external operations — EVA weightlessness Modal decoupling conditions for distnbuted control of propulsion simulation flexible structures p 19 A85-13641 [NASA-TM-86969] p 50 N85-21231 [IAF PAPER 84-38] P 41 A85-13001 Recursive Langrangian dynamics of flexible manipulator An economic analysis of humans and machines for arms p 20 A85-15745 FLUID MECHANICS space construction Principal component analysis of flexible systems - Advanced research and technology programs for [IAF PAPER 84-232] P 51 A85-13148 Open-loop case p7 A85-16648 advanced high-pressure oxygen-hydrogen rocket The human role in space Volume 1 Executive Closed form optimal control solutions for continuous propulsion summary linear elastic systems — with applications to flexible [NASA-TM-86969] p 50 N85-21231 [NASA-CR-171223] P 56 N85-13473 appendage satellite and rotational manipulator arm FLUX DENSITY EXTRAVEHICULAR MOBILITY UNITS controls p 20 A85-18672 Potential of flywheels for spacecraft energy storage Swing-arm beam erector (SABER) concept for single Displacement control of flexible structures using p33 N85-13890 astronaut assembly of space structure electrohydraulic servo-actuators p 23 A85-29144 FLYWHEELS [NASA-TP-2379] p 42 N85-19015 Measurement of the mertial constants of a ngid or flexible An Assessment of Integrated Flywheel System structure of arbitrary share through a vibration test Technology [NASA-TM-77557] p 24 N85-11381 [NASA-CP-2346] p 26 N85-13850 Expenments in control of flexible structures with Dynamics and controls working group summary uncertain parameters p24 N85-13837 p26 N85-13854 FABRICATION Precise control of flexible manipulators Develop and demonstrate manufacturing processes for Potential of flywheels for spacecraft energy storage [NASA-CR-174210] p42 N85-16178 fabncating graphite filament reinforced polymide (Gr/PI) p33 N85-13890 Identification of vibration parameters of flexible FOLDING STRUCTURES composite structural elements structures p27 N85-18360 [NASA-CR-172497] p 39 N85-20019 Large-diameter astromast development FLEXIBLE SPACECRAFT Pultrusion process for fabrication of tethers (preliminary [NASA-CR-171201] p11 N85-12200 The decentralized control of large flexible space concepts) p40 N85-20371 High performance deployable antenna structures structures p 17 A85-10071 p11 N85-14001 FEDERAL BUDGETS Comparing attitude control effectiveness for actuators National Aeronautics and Space Administration on two bodies of a six body model of a flexible spacecraft Development of a foldlme concept for automatic p4 N85-10871 with that for actuators restricted to a single body refolding of a flexible blanket (folding analysis) — FEEDBACK p17 A85-11086 spacebome solar generators Qualitative results for distributed systems with discrete Developing sensitivity coefficients for a state variable [ESA-CR(P)-1933] p 12 N85-17428 damping and stiffness with application to control model of a flexible spacecraft with modular attitude Deployable folded antenna apparatus [AD-A145525] P 24 N85-11382 control p 17 A85-11087 [AD-D011503] p12 N85-21495 FEEDBACK CONTROL Environmental effects on the dynamics and control of Variable geometry truss concept Sampled data control of flexible structures using an orbiting large flexible antenna system [REPT-614] p12 N85-21697 constant gain velocity feedback p29 A85-13640 [IAF PAPER 84-358] p 18 A85-13220 FOOD Closed-form solutions for feedback control with terminal Dynamical modelling of a gravity-loaded rectangular Characterization of heat transfer in nutnent materials constraints p20 A85-18331 plate as a test configuration for attitude control of large — space flight feeding NASA/MSFC ground experiment for Large Space space structures [NASA-CR-171841] p56 N85-17551 Structure control verification [IAF PAPER 84-391] p 18 A85-13245 FRAMES [AIAA PAPER 85-0115] p 21 A85-19528 Robust attitude control of a large communication satellite Continuum modelling of damping in large space LOG balancing and reduced LOG compensation of with flexible solar arrays structures p 18 A85-12478 symmetric passive systems — Linear Quadratic [IAF PAPER 84-ST-06] p 19 A85-13293 Space frame design, development and optimization of Gaussian p 23 A85-27238 Sampled data control of flexible structures using antenna platform structure for a mobile 3D radar Displacement control of flexible structures using constant gain velocity feedback p 29 ASS-13640 p8 A85-24908 A signed switching time bang-bang attitude control law electrohydraulic servo-actuators P 23 A85-29144 FREE FALL for fine pointing of flexible spacecraft p 19 ASS-13893 Experiments in control of flexible structures with Expenmental measurements of matenal damping in free Stability of the stationary motions of a tethered system uncertain parameters p24 N85-13837 fall with tunable excitation p20 A85-18692 of two bodies in orbit under the effect of gravitational and Precise control of flexible manipulators aerodynamic forces p20 A85-15254 FREE VIBRATION [NASA-CR-174210] p 42 N85-16178 The development of a frequency method for the The improvement of free-mode methods in component Tethered satellite system project overview mathematical modeling of the motion of an elastic space mode synthesis techniques and its accuracies p5 N85-20341 vehicle p20 A85-17054 p 17 A85-12442 Modal control of structural systems Closed-form solutions for feedback control with terminal FREQUENCY REUSE [AD-A149734] p 28 N85-21235 constraints p 20 A85-18331 Mechanical/thermal design of a polarization sensitive Stability analysts of flexible spaceraft with PID High precision active nutation control of a momentum reflector — communication satellites p 15 N85-14009 controller biased spacecraft with flexible appendages FURLABLE ANTENNAS [CRC-1372] p28 N85-21247 p20 A85-18337 Offset unfuriable antenna concepts p5 N85-14002

A-6 SUBJECTINDEX INFLATABLE STRUCTURES

The dimensional stability of advanced composite HEAT STORAGE antenna reflectors Analytical and test evaluation — Thermal storage analysis for large manned space GALLIUM ARSENIDES satellite antennas p39 N85-14014 platforms Near-optimum design of GaAs-based concentrator Passive Orbital Disconnect Strut (PODS 3) structural test [AIAA PAPER 854X366) p 14 A85-19493 space solar cells for 80 C operation p30 A85-15800 program HEAT TRANSFER Producing gallium arsenide crystals in space (NASA-CR-177325) p 16 N85-17020 Generalized transform methods based finite element p54 N85-11023 Evaluation and prediction of long-term environmental methodology - Thermal/structural dynamic applications GAS COHPOSmON effects of nonmetalfic materials [AIAA PAPER 85-0155] p 14 A85-19553 Instrumentation lor Application Number 1 Mass [NASA-CR-171353] p 39 N85-19137 Expenmental and predicted heating distnbutions for Interleaved array antenna technology development spectrometnc analysis of the boundary layer associated btcontcs at incidence in air at Mach 10 [NASA-CR-17184S] p 34 N85-19326 with the tethered satellite p 58 N85-20372 [NASA-TP-2334] p 14 N85-12313 GRAPHITE-POLYIMIDE COMPOSITES GAS DYNAMICS Capillary Pump Loop (CPL) heat pipe development Develop and demonstrate manufacturing processes for status report Advanced research and technology programs for fabricating graphite filament reinforced porynude (Gr/PI) advanced high-pressure oxygen-hydrogen rocket [NASA-CR-175273] p 16 N85-17323 composite structural elements propulsion Characterization of heat transfer in nutnent materials [NASA-CR-172497] p 39 N85-20019 — space flight feeding [NASA-TM-86969] p SO N85-21231 GRAVITATIONAL EFFECTS GAS EXPANSION Autonomous momentum management for the CDG [NASA-CR-171641] p 56 N85-17551 Partial bleed expander cycle for low thrust LOX/LH2 planar Space Station HIGH RESOLUTION rocket engine [AIAA PAPER 85-0031 ] p 21 A85-19468 A case for Gohrem - Geosynchronous orbit high (NAL-TR-837T) p 49 N85-19018 GRAVITY GRADIENT SATELLITES resolution earth moratonng p 50 ASS-10261 GEODYNAHICS Tethered propellant resupply technique for space HINGES Science Applications, part 2 p6 N85-20347 stations In-orbit performance of INTELSAT V communications GEOMETRY [IAF PAPER 84-442] p 44 A85-13282 antennae deployment systems p33 N85-14016 SMP- A solid modeling program Effect of aerodynamic moment on the regime of the HISTORIES [NASA-CR-172473] p8 N8S-11570 gravity gradient stabilization of the Salyut-6 - Soyuz orbital The future of space flight p2 A85-16109 GEOPOTENTIAL system p23 A85-28488 Looking back on the past - The decision ol Europe to Science Applications, part 2 p6 N8S-20347 The dynamics of the attitude control and stabilization participate in the post-Apollo program GEOSYNCHRONOUS ORBITS systems of spacecraft with a controlled gravity gradient p53 A65-23824 A case for Gohrem - Geosynchronous orbit high stabilizer p 23 A85-28903 Ten years after the launch of ANS - Looking back in resolution earth monitoring p 50 ASS-10261 Application Number 3 Using tethers for attitude perspective p 54 A85-26770 control p27 N85-20373 Efficient inclination control for geostationary satellites HUBBLE SPACE TELESCOPE [AIAA PAPER 85-0216] p 21 A85-19595 GREASES Graphite epoxy structure ol the Space Telescope's An evaluation of grease type ball beanng lubricants optical telescope assembly p 36 A85-15980 Finite multiple burn orbit transfer error analysis via operating in various environments Astronomers, Congress, and the Large Space covanance matrix p 45 A85-22444 [NASA-TM-86480] p 38 N85-11239 Telescope p54 A85-27973 Right operation considerations for an aero-braked GREENHOUSES OTV Space greenhouse design p 50 A85-12927 HUMAN FACTORS ENGINEERING [AIAA PAPER 85-0220] p 54 A85-26385 GROUND SUPPORT SYSTEMS An economic analysis of humans and machines for A plan for controlling electrostatic discharges on NASA-VCOSS dynamic test facility space construction geosynchronous spacecraft p 32 A85-26685 [NASA-TM-86491] p 27 N85-18998 [IAF PAPER 84-232] p 51 A85-13148 OTV propulsion tecnology programmatic overview GROUND TESTS Human response to vibroacoustic environments of p 48 N85-16997 NASA/MSFC ground experiment for Large Space space vehicles Efficient structures for geosynchronous spacecraft solar Structure control verification [NASA-TM-86316] p 54 N85-10789 arrays [AIAA PAPER 85-0115] p 21 A85-19528 HYDRAULIC CONTROL [NASA-CR-174448] p 12 N85-19004 Definition of ground test for verification of large space Displacement control of flexible structures using Assessment of satellite collision hazards by simulated structure control electrohydraulic servo-actuators p23 A65-29144 sampling in space p 40 N85-21195 [NASA-CR-171208] p9 N85-13838 HYDROGEN OXYGEN ENGINES Geosynchronous satellite collision avoidance Level of effort p25 N85-13839 Integratable propulsion systems lor the Space Station p58 N85-21197 Oral presentation of first year final report, appendix A p46 A85-23393 The long term behaviour of Earth orbits and the p25 N85-13840 Advanced research and technology programs for implications for debns control p 58 N85-21213 Simplified planar model of ground test verification advanced high-pressure oxygen-hydrogen rocket Debns in the geostationary orbit ring, the endless structure, appendix B p 25 N85-13841 propulsion shooting gallery The necessity for a disposal policy Definition of ground test for Large Space Structure (LSS) [NASA-TM-86969] p 50 N85-21231 p58 N85-21214 control verification, appendix G p25 N85-13845 HYPERSONIC FLOW The international environment UNISPACE '82 and the Ground test expenment for large space structures, Expenmental and predicted heating distributions for ITU A relationship between orbit-spectrum resource appendix I p 56 N85-13847 biconics at incidence in air at Mach 10 allocation and orbital debns p 58 N85-21215 NASA-VCOSS dynamic test facility [NASA-TP-2334] p 14 N85-12313 SCATHA (spacecraft charging at high altitudes) plasma [NASA-TM-86491] p 27 N85-18998 Instrumentation lor Application Number 1 Mass interaction expenment SC-3 high energy particle Ground test expenment for large space structures spectrometnc analysis of the boundary layer associated spectrometer, SC-8 energetic ion composition [NASA-TM-86489] p9 N85-19013 with the tethered satellite p58 N85-20372 expenment NASA/MSFC ground expenment for large space HYPERVELOCITY IMPACT [AD-A149728] p 35 N85-21252 structure control verification Orbital Debns GIMBALS [NASA-TM-86496] p 28 N85-21248 [NASA-CP-2360] p40 N85-21188 Orbital transfer vehicle propulsion issues Definition of ground test for Large Space Structure (LSS) Debns impact on Earth-orbiting spacecraft p48 N85-I7009 control venfication p59 N85-22234 GLASS [NASA-TM-86495] p 28 N85-21249 HYPERVELOCITY LAUNCHERS Inorganic composites for space applications Preliminary analysis of space mission applications for p38 N85-11047 electromagnetic launchers GLASS COATINGS H [NASA-CR-174067] p 47 N85-12071 Catalytic surface effect on ceramic coatings for an HYPERVELOCITY PROJECTILES aeroassisted orbital transfer vehicle p 38 A85-29730 HABrrABILITY Determination of atmosphenc density using a GOES SATELLITES Human response to vibroacoustic environments of space-launched projectile An investigation during the system test phase of the space vehicles [AIAA PAPER 85-0327] p 2 A85-20866 GOES spacecraft p32 A85-28126 [NASA-TM-86316] p 54 N85-10789 GOVERNMENT PROCUREMENT HANDBOOKS Astronomers, Congress, and the Large Space Antenna engmeenng handbook /2nd edition/ I Telescope p54 A85-27973 p30 A85-16081 GOVERNMENT/INDUSTRY RELATIONS IMPACT DAMAGE HARDENING (MATERIALS) Orbital Debns Commercialization of space - Incentives, impediments Inflatable space-ngidized structures - Recent and alternatives p 3 A85-27375 [NASA-CP-2360] p40 N85-21188 developments of the material technology Second Symposium on Space Industrialization — space Geosynchronous satellite collision avoidance [IAF PAPER 64-384] p 10 A85-13240 commercialization p58 N85-21197 [NASA-CP-2313] p4 NB5-11011 HARMONIC OSCILLATORS In situ orbital debns expenment concepts Concept for a commercial space station laboratory Principal component analysis ol flexible systems - p58 N85-21198 Open-loop case p7 A85-16648 p4 N85-11035 INCIDENT RADIATION Doing business in space How to get there from here HAZARDS Effect of phase fluctuations in an incident beam on the p55 N85-11057 Preliminary design ol an Earth-based debns detection charactenstics of a rectenna system p30 A85-15760 GOVERNMENTS system using current technology and existing INERTIA International cooperation and competition in space installations p40 N85-21199 Measurement ol the inertia! constants ol a ngid or flexible (GPO-38-001] p4 N85-11911 HEAT PIPES structure of arbitrary share through a vibration test GRAPHrTE-EPOXY COMPOSITES Space station thermal control - An interview with Robert [NASA-TM-77557] p 24 N85-11381 Graphite epoxy structure of the Space Telescope's Haslett p 13 A85-18321 INFLATABLE STRUCTURES optical telescope assembly p 36 A85-15980 Capillary Pump Loop (CPL) heat pipe development Inflatable space-ngidized structures - Recent Effects of space environmental conditions on graphite status report developments of the material technology epoxy composites p 36 A85-15990 [NASA-CR-175273] p 16 N85-17323 [IAF PAPER 84-384] p 10 ASS-13240

A-7 INFRARED SPECTRA SUBJECTINDEX

Research on large, highly accurate, inflatable An unmanned platform as an initial capability in space reflectors p52 A85-16305 [AD-A145080] p11 N85-10099 JAPANESE SPACECRAFT Environmentally-induced voltage limitations in large Large spacebome antenna reflectors using inflatable Structural aspects of SAR antenna for Japanese Earth space power systems p31 A85-18584 space ngidized structures p 12 N85-14004 Resources Satellite 1 p 12 N85-14007 Mass properties analysis and control of advanced space INFRARED SPECTRA JOINTS (ANATOMY) structures through computenzed integration with design Demonstration of transparent solar array module Recursive Langrangian dynamics of flexible manipulator and structural analysis design arms p20 A85-15745 [SAWE PAPER 1527] p 13 A85-18812 [NASA-CR-174257] p 47 N85-16302 Thermal storage analysis for large manned space platforms INFRARED SPECTROSCOPY [AIAA PAPER 854066] p 14 A85-19493 Analysis of Nonvolatile Residue (NVR) from spacecraft NASA/MSFC ground experiment for Large Space systems Structure control venfication [NASA-TM-86184] p 39 N85-17019 KAPTON (TRADEMARK) [AIAA PAPER 85-0115] p 21 A85-19528 Effect of neutron and proton irradiation on some INFRARED TELESCOPES Computer aided design of multiple input/output control properties of Kapton p 37 A85-21508 Construction of large precision reflectors using the Aft systems for multibody flexible Space Station Cargo Garner KEVLAR (TRADEMARK) [AIAA PAPER 85-0223] p7 A85-19600 [IAF PAPER 84-389] p2 A85-13244 Kevlar and T300 fabric prepregs - Their material Analytical and experimental research in large space Design concepts for reflector antenna structures properties and their use in high loaded areas of a solar structures control p7 A85-22579 array [AIAA PAPER 85-0356] p 21 A85-19693 INSULATORS [IAF PAPER 84-402] p 35 A85-13255 Geometrically nonlinear analysis of space frames by an Dielectric matenal in the space environment Thermoelastic behaviour of space structures in incremental iterative technique p 14 A85-19895 p 37 A85-24672 composite materials Precision of mesh-type reflectors for large space-borne INTEGRATED ENERGY SYSTEMS [IAF PAPER 84-404] p 35 A85-13257 antennas p31 A85-21835 An Assessment of Integrated Flywheel System Deployable optical systems, Proceedings of the Meeting, Technology Los Angeles, CA, January 18, 19, 1983 [NASA-CP-2346] p 26 N85-13850 p53 A85-22576 INTELSAT SATELLITES Deployable reflector configurations — for space Some design concepts for Intelsat VII LAMINATES telescope p2 A85-22577 p7 A85-15496 Effects of residual stresses in polymer matrix Active vibration control for lasers and spacecraft Intelsat's twentieth anniversary - Two decades of composites p 35 A85-12395 p 21 A85-22584 innovation in global communications p 54 A85-26369 Influence of the lamination and of some environmental Structural control research and experiments at effects on damping charactenstics of advanced NASA/LaRC p 22 A85-22587 INTERNATIONAL COOPERATION composites for space structures A modular approach to developing a large deployable Space exploitation - Spacelab an easy approach for I IAF PAPER 84-405] p 36 A85-13258 reflector p7 A85-22685 developing countries Prospectives and suggestions by Dynamic charactenstics of a space reflector support Aentalia p 1 A85-12502 Influence of simulated space environment on the behavior of carbon-fiber-reinforced plastics with +, -45 structure p 22 A85-24949 Space station related investigations in Europe ply orientations II p 36 A85-14163 An analytical investigation of shape control of large [IAF PAPER 84-28] p SO A85-12994 Develop and demonstrate manufacturing processes for space structures by applied temperatures '" international space programmes and policies fabncating graphite filament reinforced polymide (Gr/PI) p 14 A85-25145 ' " p2 A85-20507 composite structural elements Poles and transmission zeros of flexible spacecraft Looking back on the past - The decision of Europe to [NASA-CR-172497] p 39 N85-20019 control systems p 22 A85-26433 participate m the post-Apollo program LARGE SPACE STRUCTURES Flexural vibration of gravity-stabilized, structurally p 53 A85-23824 The decentralized control of large flexible space damped, large flexible satellites p 22 A85-26434 Commercialization of space - Incentives, impediments structures p 17 A85-10071 Adaptive modal control of structural dynamic systems and alternatives p 3 A85-27375 Continuum modelling of damping in large space using recursive lattice filters p 23 A85-26435 International cooperation and competition in space structures p 18 A85-12478 LOG balancing and reduced LOG compensation of [GPO-38-001] p4 N85-11911 Neutral buoyancy evaluation of technologies for space symmetnc passive systems — Linear Quadratic TSS Satellite overview p5 N85-20343 station external operations — EVA weightlessness Gaussian p 23 A85-27238 Multicntical optimization of a large space structure INTERORBITAL TRAJECTORIES simulation p11 A65-2B489 The cost effectiveness and optimal parameters of an [IAF PAPER 84-38] p 41 A85-13001 Shear deformation plate contmua of large electric rocket propulsion system for an interorbital A space station experiment on large antenna assembly double-layered space structures p 8 N85-10391 transport vehicle p 46 A85-23990 and measurement - A follow-on study [IAF PAPER 84-58] p 41 A85-13017 IAC user manual INTERPLANETARY SPACE [NASA-CR-175300] p8 N85-10677 The maximum efficiency of an isolated solar energy An optimal shape control of a large flexible radiator in space Effects of member imperfections on the behavior of conversion device in space p 46 A85-25797 [IAF PAPER 84-64] p 18 A85-13023 space trusses p11 N85-11363 INTERSTELLAR SPACECRAFT An economic analysis of humans and machines for Qualitative results for distributed systems with discrete On the potential performance of non-nuclear interstellar space construction damping and stiffness with application to control arks p46 A85-25828 [IAF PAPER 84-232] p 51 A85-13148 [AD-A145525] p 24 N85-11382 INTERSTELLAR TRAVEL Environmental effects on the dynamics and control of Definition of technology development missions for early The state of the art solar sail and the interstellar an orbiting large flexible antenna system space stations Large space structures precursor mission p 43 A85-12926 [IAF PAPER 84-358] p 18 A85-13220 [NASA-CR-171209] p4 N85-12084 On the potential performance of non-nuclear interstellar Large space structures ground and flight progress Conceptual design for scaled truss antenna flight arks p46 A85-25828 [IAF PAPER 84-388] p 13 A85-13243 expenment INTRAVEHICULAR ACTIVITY Construction of large precision reflectors using the Aft [NASA-TM-85804] p4 N85-12932 Cargo Garner The human role in space Volume 1 Executive Expenments in control of flexible structures with summary [IAF PAPER 84-389] p2 A85-13244 uncertain parameters p24 N85-13837 [NASA-CR-171223] p 56 N85-13473 Dynamical modelling of a gravity-loaded rectangular Definition of ground test for venfication of large space plate as a test configuration for attitude control of large ION ENGINES structure control space structures performance capabilities of the 12-centimeter Xenon ion [NASA-CR-171208] p9 N85-13838 thruster p 44 ASS-16439 [IAF PAPER 84-391] p 18 A85-13245 Design preparations for large space structures Level of effort p 25 NB5-13839 Optimal electnc propulsion orbit transfer vehicle design [IAF PAPER 84-392] p 35 A85-13246 Oral presentation of first year final report, appendix A and operational effectiveness Variable geometry truss and its application to deployable p25 N85-13840 [AIM PAPER 85-0431] p 45 A85-19744 truss and space crane arm Simplified planar model of ground test verification ION MICROSCOPES [IAF PAPER 84-394] p 10 A85-13248 structure, appendix B p 25 N85-13841 Radiation effects in materials - Field-ton microscope Elastic waves propagation in bounded penodic Speed test results and hardware/software study of characterizations p 37 A85-24675 structures — for modeling large space structures computational speed problem, appendix D IONOSPHERIC SOUNDING [IAF PAPER 84-395] p 19 A85-13249 p25 N85-13843 Engineering aspect of the Microwave Ionosphere Heat conduction problems in large space structure Section 1 Method of determining mode shapes and Nonlinear Interaction Experiment (MINIX) with a sounding [IAF PAPER 84-400] p 13 A85-13253 natural frequencies of the NASA unmodified test structure rocket Robust attitude control of a large communication satellite Section 2 Continuous beam closed from solution to the [IAF PAPER 84-289] p 29 A85-13177 with flexible solar arrays NASA-LSS astromast torsional vibration, appendix E IRIS SATELLITES [IAF PAPER 84-ST-06] p 19 A85-13293 p 25 N85-13844 IBIS Spinning Stage - A pengee stage for satellites up Number and placement of control system components Definition of ground test for Large Space Structure (LSS) to 900 kg to be launched from the Space Shuttle with considering possible failures — for large space control venfication, appendix G p 25 N85-13845 structures p 19 A85-13634 the IRIS system P43 A85-12520 Review of technical papers, appendix H Some applications of direct adaptive control to large p25 N85-13846 ITALIAN SPACE PROGRAM structural systems p 19 A85-13636 Space exploitation - Spacelab an easy approach for Sampled data control of flexible structures using Ground test expenment for large space structures, developing countries Prospectives and suggestions by constant gain velocity feedback p29 A85-13640 appendix I p56 N85-13847 Aentalia p 1 A85-12502 A rectilinear guidance strategy for short orbital Environmental interactions working group report ITERATIVE SOLUTION transfers p 52 A85-15509 p5 N85-13908 Geometrically nonlinear analysis of space frames by an Continuous graphrte/porysulfone RP thermoforming for Disturbance propagation in structural networks, control incremental iterative technique p 14 A85-19895 large space structure construction p 36 A85-15638 of large space structures p 26 N85-14856

A-8 SUBJECT INDEX MECHANICAL ENGINEERING

Space Station truss structures and construction LIQUID PHASE EPITAXY MANNED MANEUVERING UNITS considerations Producing gallium arsenide crystals in space Neutral buoyancy evaluation of technologies for space [NASA-TM-86338] p 15 N85-15796 p54 N85-11023 station external operations — EVA weightlessness Capillary Pump Loop (CPL) heat pipe development LIQUID PROPELLANT ROCKET ENGINES simulation status report Bipropellant propulsion in the new generation of [IAF PAPER 84-38] p 41 A85-13001 [ N ASA-CR-175273] p 16 N85-17323 satellites and upper stages' The role of BPO Difesa-Spazio MANNED ORBITAL LABORATORIES The Shock and Vibration Digest, volume 16, no 11 in this field - Manufacturing facilities and technology Space station related investigations in Europe (AD-A148466] p 16 N85-17382 p43 A85-12519 [IAF PAPER 84-28] p 50 ASS-12994 Partial bleed expander cycle for low thrust LOX/LH2 Modelling and identification of the structural properties MANNED ORBITAL RESEARCH LABORATORIES of an astromast rocket engine Concept for a commercial space station laboratory [CRC-1374] p 12 N85-18352 [NAL-TR-B37T] p 49 N85-19018 p4 N85-11035 LIQUID ROCKET PROPELLANTS NASA-VCOSS dynamic test facility MANNED SPACE FLIGHT Space Transportation System (STS) propellant [NASA-TM-86491] p 27 N85-189S8 Space as motivational propulsion — Shuttle Orfaiter scavenging system study Volume 1 Technical report Operational fitness of box truss antennas in response related protects as educational tools [NASA-CR-171848-VOL-1] p 49 N85-20000 [IAF PAPER 84-407] p 51 A85-13259 to dynamic slewing LIQUID SLOSHING MANNED SPACECRAFT [NASA-CR-172470] p 27 N85-19012 Propellant transfer Tethered depot Space station/space platform system design Ground test expenment for large space structures p48 N85-17006 considerations p7 A85-14429 [NASA-TM-86489] p9 N85-19013 LOADS (FORCES) Active control of large space structures An introduction Tether fundamentals p 57 N85-20345 Orbit on demand - In this century if pushed and overview LONG DURATION SPACE FLIGHT p46 A85-24788 [NASA-TM-86490] p 27 N85-19014 Assessment of medical risk in space flight Orbit-on-demand vehicles - Mission possible, but Swing-arm beam erector (SABER) concept for single [IAF PAPER 84-189] p 51 A85-13114 one-day turnaround? p 53 A85-24790 astronaut assembly of space structure On the potential performance of non-nuclear interstellar Dynamics and controls working group summary [NASA-TP-2379] p 42 N85-1901S arks p 46 A85-25828 p 26 N85-13854 Develop and demonstrate manufacturing processes for LONG TERM EFFECTS Keynote address p 27 N85-18378 fabricating graphite filament reinforced polymtde (Gr/PI) Evaluation and prediction of long-term environmental MANUFACTURING composite structural elements effects of nonmetallic matenals Develop and demonstrate manufacturing processes for [MASA-CR-172497] p 39 N85-20019 [NASA-CR-171353] p 39 N85-19137 fabncating graphite filament reinforced polymide (Gr/PI) Compensator development and examination of LONGERONS composite structural elements performance and robustness Section 1 Method of determining mode shapes and [NASA-CR-172497] p 39 N85-20019 [NASA-CR-175470] p 34 N85-20244 natural frequencies of the NASA unmodified test structure Report of the Technology and Test Panel Modal control of structural systems Section 2 Continuous beam closed from solution to the p57 N85-20370 [AD-A149734] p 28 N85-21235 NASA-LSS astromast torsional vibration, appendix E Computer integration of engineenng design and NASA/MSFC ground expenment for large space p25 N85-13844 production A national opportunity structure control verification Modelling and identification of the structural properties [NASA-CR-175483] p 59 N85-2lfl4 [NASA-TM-86496] p 28 N85-21248 of an astromast MARKET RESEARCH Definition of ground test for Large Space Structure (LSS) [CRC-1374] p12 N85-18352 The communication-satellite market to the year 2000 control verification Efficient structures for geosynchronous spacecraft solar p3 A85-26771 [NASA-TM-86495] p 28 N85-21249 arrays MARKETING ACOSS 17 (Active Control of Space Structures) [NASA-CR-174448] p 12 N85-19004 Future prospects in space envisaged by a forum of [AD-A150007] p28 N85-21253 LOW ALTITUDE European space companies p 52 ASS-16302 Variable geometry truss concept Lay-out of a re-usable re-entry vehicle required in a future MASS DISTRIBUTION [REPT-614] p 12 N85-21697 European low earth orbit scenario Measurement of the mertial constants of a ngid or flexible LASER ANNEALING [IAF PAPER 84-06] p 50 A85-12981 structure of arbitrary share through a vibration test In-orbit laser regeneration of the radiation damaged solar LOW GRAVITY MANUFACTURING [NASA-TM-77557] p 24 N85-11381 arrays Material sciences in space p36 A85-13500 MASS SPECTROSCOPY [IAF PAPER 84-62] p 43 A85-13021 LOW TEMPERATURE TESTS Instrumentation for Application Number 1 Mass LAUNCH VEHICLES Experimental study of the effect of the type of stress spectrometnc analysis of the boundary layer associated Cost effective launch technology for communications state on plastic strain in structural materials at low with the tethered satellite p 58 N85-20372 satellites temperatures p 37 A85-16499 MASS TRANSFER [IAF PAPER 84-04] p SO A85-12979 An evaluation of grease type ball bearing lubncants On dynamical formulations of a tethered satellite system Second Symposium on Space Industrialization — space operating in various environments with mass transport commercialization [NASA-TM-86480] p 38 N85-11239 [AIAA PAPER 85-0117] p 21 A85-19529 [NASA-CP-2313] p4 N85-11011 LOW THRUST PROPULSION MATERIALS SCIENCE Commercial space launches Optimal low-thrust, three-bum orbit transfers with large Matenal sciences in space p 36 A85-13500 [S-REPT-98-656] p6 N85-21225 plane changes p 44 A85-18671 Technology vectors, Proceedings of the Twenty-ninth LAW (JURISPRUDENCE) Partial bleed expander cycle for low thrust LOX/LH2 National SAMPE Symposium and Exhibition, Reno, NV, Second Symposium on Space Industrialization — space rocket engine Apnl 3-5, 1984 p 52 A85-15976 commercialization [NAL-TR-837T] p 49 N85-19018 MATERIALS TESTS [NASA-CP-2313] p4 N85-11011 LUBRICANTS Design preparations for large space structures LICENSING An evaluation of grease type ball beanng lubricants [IAF PAPER 84-392] p 35 A85-13246 Commercial space launches operating in various environments Expenmental measurements of matenal damping in free [S-REPT-98-656] p6 N85-21225 [NASA-TM-66480] p 38 N85-11239 fall with tunable excitation p20 A85-18692 LIFE (DURABILITY) Radiation effects in matenals - Fieldnon microscope Potential of flywheels for spacecraft energy storage characterizations p 37 A85-24675 p33 N85-13890 M MATHEMATICAL MODELS LIFE SUPPORT SYSTEMS Spacecraft systems engineenng and geometry Impacts of life support system on space station design MAGNETIC DISTURBANCES modelling - The ESABASE-MATVIEW approach [IAF PAPER 84-166] p6 A85-13100 Earth's magnetic field perturbations as the possible p8 A85-27696 environmental impact of the conceptualized solar power LINEAR EQUATIONS Modular design attitude control system Modular design attitude control system satellite [NASA-CR-171182] p24 N85-10098 [NASA-CR-171182] p24 N85-10098 [AD-A149120] p30 A85-16641 Satellite servicing A business opportunity? LINEAR SYSTEMS MAGNETOHYDRODYNAMIC STABILITY p55 N85-11056 Closed form optimal control solutions for continuous Electrodynamic interactions p 34 N85-20348 Damping synthesis for a spacecraft using substructure linear elastic systems — with applications to flexible MAGNETOPLASMADYNAMICS and component data appendage satellite and rotational manipulator arm Design and benefits of pulsed MPO thruster orbit transfer [CRC-1365] p24 N85-12082 controls p 20 A85-18672 vehicles p 44 A85-16448 Compensator development and examination of Qualitative results for distnbuted systems with discrete MAGSAT SATELLITES performance and robustness damping and stiffness with application to control Science Applications, part 2 p 6 N85-20347 [NASA-CR-175470] p 34 N85-20244 [AD-A145525] p 24 N85-11382 MAN MACHINE SYSTEMS ACOSS 17 (Active Control of Space Structures) LIQUEFACTION Synergy in space - Man-robot cooperation [AD-A150007] p28 N85-21253 p 41 A85-20400 Active cooling requirements for propellent storage MATRICES (MATHEMATICS) p48 N85-17004 The human role in space Volume 1 Executive Finite multiple burn orbit transfer error analysis via summary LIQUID COOLING covanance matrix p 45 A85-22444 The liquid droplet radiator - an ultralightweight heat [NASA-CR-171223] p 56 N85-13473 MEASURING INSTRUMENTS refection system for efficient energy conversion in space Sa degrees of freedom control with each hand? Number and placement of control system components p 15 N85-13900 p42 N85-14492 considenng possible failures — for large space LIQUID HYDROGEN MANAGEMENT ANALYSIS structures p 19 A85-13634 Partial bleed expander cycle for low thrust LOX/LH2 Doing business in space How to get there from here MECHANICAL DEVICES rocket engine p55 N85-11057 Swing-arm beam erector (SABER) concept for single [NAL-TR-837T] p 49 N85-19018 MANIPULATORS astronaut assembly of space structure LIQUID OXYGEN Recursive Langrangian dynamics of flexible manipulator [NASA-TP-2379] p 42 N85-19015 Partial bleed expander cycle for low thrust LOX/LH2 arms p20 A85-15745 MECHANICAL ENGINEERING rocket engine Precise control of flexible manipulators BAe antenna hardware technology for current satellite [NAL-TR-837T] p 49 N85-19018 [NASA-CR-174210] p 42 N85-16178 protects p9 N85-14011

A-9 MECHANICAL PROPERTIES SUBJECTINDEX

Hemispherical antenna pointing mechanism — satellite MODULES antennas p26 N85-14021 Demonstration of transparent solar array module MECHANICAL PROPERTIES design OBSERVABILITY (SYSTEMS) Kevlar and T300 fabnc prepregs • Their material [NASA-CR-174257] p 47 N85-16302 Alleviation of observation spillover in continuous properties and their use in high loaded areas of a solar MOMENTUM structures p 17 A85-12434 array High precision active nutation control of a momentum Number and placement of control system components [IAF PAPER 84-402] p 35 A85-13255 biased spacecraft with flexible appendages considenng possible failures — for large space Thermoelastic behaviour of space structures in p20 A85-18337 structures p 19 A85-13634 composite matenals Autonomous momentum management for the COG OFF-ON CONTROL [IAF PAPER 84-404] p35 A85-13257 planar Space Station A signed switching time bang-bang attitude control law Report of the Technology and Test Panel [AIAA PAPER 85-0031 ] p 21 A85-19468 for fine pointing of flexible spacecraft p 19 A85-13893 p57 N85-20370 ONBOARD DATA PROCESSING Autonomous momentum management for space station, Wavelength division multiplexing for future Space Station METAL FILMS exhibit A data systems p32 A85-25359 Research on large, highly accurate, inflatable [NASA-CR-171256] p 33 N85-12933 OPERATING COSTS reflectors MSAT Utilization and economics of a European low earth orbit [AD-A145080] p11 N85-10099 Some results of the MSAT phase B studies and their Space Platform METAL MATRIX COMPOSITES impact on system design [IAF PAPER 84-57] p 1 A85-13016 Evaluation and prediction of long-term environmental [IAF PAPER 84-89] p 1 A85-13045 OPERATOR PERFORMANCE effects of nonmetallic matenals MULTIMISSION MODULAR SPACECRAFT Six degrees of freedom control with each hand? [NASA-CR-171353] p 39 N85-19137 Satellite module design p9 N85-20344 p42 N85-14492 METALLOGRAPHY MULTISPECTRAL LINEAR ARRAYS OPTICAL COMMUNICATION Radiation effects in matenals - Field-ion microscope The NASA MLA program — Multispectral Linear Array Wavelength division multiplexing for future Space Station characterizations p 37 A85-24675 p52 A85-17573 METEOROID PROTECTION data systems p 32 A85-25359 Parametric analysts SOC meteoroid and debns OPTICAL MEASUREMENT protection p 16 N85-21209 N Preliminary design of an Earth-based debns detection MICROCOMPUTERS system using current technology and existing A functional vehicle for autonomous mobile robot NASA PROGRAMS installations p40 N85-21199 research NASA's mobile satellite communications program, OPTICAL RADAR [AD-A150052] p 42 N85-21666 ground and space segment technologies In situ orbital debns expenment concepts MICROELECTRONICS [IAF PAPER 84-84] p 29 A85-13040 p58 N85-21198 West Europe report Science and technology TOS and AMS - America's new capabilities in space OPTICAL REFLECTION [JPRS-WST-85-008] p 57 N85-20174 transportation — Transfer Orbit Stages and Apogee and Space environment simulation to test satellite thermal MICROSCOPY Maneuvering Stages control coatings, volume 1 Radiation effects in matenals - Field-ion microscope [IAF PAPER 84-220] p 51 A85-13141 [CERT-4128-VOL-1] p 16 N85-17012 characterizations p 37 A85-24675 Space as motivational propulsion — Shuttle Orbiter Space environment simulation to test satellite thermal MICROWAVE ANTENNAS related projects as educational tools control coatings Volume 2 Annex 1 Satellite communication antenna technology [IAF PAPER 84-407] p 51 A85-13259 [ESA-CR(P)-1870-VOL-2] p 16 N85-17013 p 31 A85-23651 The future of space flight p2 A85-16109 Space environment simulation to test satellite thermal MICROWAVE EMISSION The NASA MLA program — Multispectral Linear Array control coatings Volume 2 Annexes 2, 3, 4 Effect of phase fluctuations in an incident beam on the p52 A85-17573 [ESA-CR(P)-1870-VOL-3] p 16 N85-17014 characteristics of a rectenna system p 30 A85-15760 NASA/MSFC ground experiment for Large Space OPTIMAL CONTROL MICROWAVE RADIOMETERS Structure control venficabon An optimal shape control of a large flexible radiator in An economic analysis of humans and machines for [AIAA PAPER 85-0115] p 21 A85-19528 space space construction Active control technology development at NASA [IAF PAPER 84-64] p 18 A85-13023 [IAF PAPER 84-232] p 51 A85-13148 p22 A85-22586 Optimal simultaneous structural and control design of MICROWAVE SENSORS Looking back on the past - The decision of Europe to maneuvenng flexible spacecraft p7 A85-18338 Evaluation of OMV ranging and docking systems participate in the post-Apollo program Optimal low-thrust, three-bum orbit transfers with large p42 N85-22230 p53 A85-23824 plane changes p44 ASS-18671 MICROWAVE SOUNDING Astronomers, Congress, and the Large Space Closed form optimal control solutions for continuous Engineering aspect of the Microwave Ionosphere Telescope p 54 A85-27973 linear elastic systems — with applications to flexible Nonlinear Interaction Expenment (MINIX) with a sounding National Aeronautics and Space Administration appendage satellite and rotational manipulator arm rocket p4 N85-10871 controls p 20 A85-18672 [IAF PAPER 84-289] p 29 A85-13177 Proceedings of a Workshop on Applications of Tethers OPTIMIZATION MICROWAVE TRANSMISSION in Space, Executive Summary The strongest structures with macrostiffness Earth's magnetic field perturbations as the possible [NASA-CR-171195] p 55 N85-12075 constraints p 10 A85-12933 environmental impact of the conceptualized solar power Proceedings of a Workshop on the Applications of Reduction method for thermal analysis of complex satellite Tethers in Space, Volume 1 aerospace structures [AO-A149120] p30 A85-16641 [NASA-CR-171196] p55 N85-12076 [NASA-TP-2373] p 15 N85-16066 MISSION PLANNING NASA/MSFC ground expenment for large space ORBIT CALCULATION The state of the art solar sail and the interstellar structure control venfication A rectilinear guidance strategy for short orbital precursor mission p43 A85-12926 [NASA-TM-86496] p 28 N85-21248 transfers p52 A85-15509 Space station related investigations in Europe NEUTRON IRRADIATION ORBIT DECAY [IAF PAPER 84-28] p 50 A85-12994 Effect of neutron and proton irradiation on some Orbital Debns Orientation and trends in European technology — space properties of Kapton p 37 A85-21508 [NASA-CP-2360] p40 N85-21188 programs NOISE INTENSITY The long term behaviour of Earth orbits and the [IAF PAPER 84-377] p2 A85-13233 Human response to vnbroacoustic environments of implications for debns control p58 N85-21213 The future of space flight p 2 A85-16109 space vehicles ORBIT SPECTRUM UTILIZATION Orbrt-on-demand vehicles - Mission possible, but [NASA-TM-86316] p 54 N85-10789 The international environment UNISPACE '82 and the one-day turnaround? p 53 A85-24790 NONDESTRUCTIVE TESTS ITU A relationship between orbit-spectrum resource Proceedings of a Workshop on Applications of Tethers Develop and demonstrate manufacturing processes for allocation and orbital debns p58 N85-21215 in Space, Executive Summary fabncating graphite filament reinforced polymide (Gr/PI) ORBIT TRANSFER VEHICLES [NASA-CR-171195] p 55 N85-12075 composite structural elements Bipropellant propulsion in the new generation of The human role in space Volume 1 Executive [NASA-CR-172497] p 39 N85-20019 satellites and upper stages The role of BPD Difesa-Spazio summary NONLINEAR EQUATIONS in this field - Manufactunng facilities and technology [NASA-CR-171223] p 56 N85-13473 Geometrically nonlinear analysis of space frames by an p43 A85-12519 Missions/planning panel p4 N85-13886 incremental iterative technique p 14 A85-19895 IRIS Spinning Stage - A pengee stage for satellites up Commerce Lab Mission analysis and payload NONLINEAR PROGRAMMING to 900 kg to be launched from the Space Shuttle with integration study Optimal low-thrust, three-bum orbit transfers with large the IRIS system p43 A85-12520 [NASA-CR-171272] p 56 N85-16981 plane changes p 44 A85-18671 Utilization and economics of a European low earth orbit Satellite module design p 9 N85-20344 NUCLEAR ELECTRIC PROPULSION Space Platform MOBILE COMMUNICATION SYSTEMS Nuclear-electric power in space p30 A85-15812 [IAF PAPER 84-57] p 1 A85-13016 NASA's mobile satellite communications program, Design of a nuclear electnc propulsion orbital transfer TOS and AMS - Amenca's new capabilities in space ground and space segment technologies vehicle p46 A85-23394 transportation — Transfer Orbit Stages and Apogee and [IAF PAPER 84-84] p 29 A85-13040 Nuclear reactors for space power p 46 A85-24793 Maneuvenng Stages Space frame design, development and optimization of NUMERICAL ANALYSIS [IAF PAPER 84-220] p 51 A85-13141 antenna platform structure for a mobile 3D radar Formex configuration processing in structural Design and benefits of pulsed MPDthruster orbit transfer p8 A85-24908 engmeenng — Book p 14 A85-20916 vehicles p44 A85-16448 MODAL RESPONSE NUTATION Optimal low-thrust, three-bum orbit transfers with large Application of modal synthesis concepts to spacecraft High precision active nutation control of a momentum plane changes p 44 A85-18671 design verification p 17 A85-12455 biased spacecraft with flexible appendages The low cost development, test, and production of a Modal decoupling conditions for distributed control of p20 A85-18337 commercial STS upper stage TOS flexible structures p 19 A85-13641 NUTRIENTS [AIAA PAPER 85-0313] p 45 A85-19660 MODELS Characterization of heat transfer in nutrient matenals Optimal electnc propulsion orbit transfer vehicle design SMP A solid modeling program — space flight feeding and operational effectiveness [NASA-CR-172473] p8 N85-11570 [NASA-CR-171841] p 56 N85-17551 [AIAA PAPER 85-0431 ] p 45 A85-19744

A-10 SUBJECTINDEX PLASMA JETS

Chemical nonequilibnum effects on flowfields for Space based OTV servicing p56 N85-17010 PARTICLE FLUX DENSITY aeroassisted orbital transfer vehicles p53 A85-21831 Applications of Tethers in Space, volume 1 SCATHA (spacecraft charging at high altitudes) plasma Hrate multiple burn orbit transfer error analysis via [NASA-CP-2384] p 57 N85-20339 interaction expenment SC-3 high energy particle covanance malm p 45 A85-22444 Orbital Debns spectrometer; SC-8 energetic ion composition Design of a nuclear electric propulsion orbital transfer [NASA-CP-2360] p40 N85-211B8 expenment [AD-A149728] p 35 N85-21252 vehicle p46 A85-23394 ORBITAL SPACE STATIONS The cost effectiveness and optimal parameters of an Space station related investigations in Europe PARTICLE SIZE DISTRIBUTION electric rocket propulsion system for an mlerorbrtal [IAF PAPER 84-28] p 50 A85-12994 Environment definition, small panicles, diameter less than or equal to 1 MM p 40 N85-21223 transport vehicle P 46 A85-23990 Neutral buoyancy evaluation of technologies for space PAYLOAD CONTROL Flight operation considerations for an aero-braked station external operations — EVA weightlessness Optimal design of a passive vibration absorber for a OTV simulation tniss beam p 19 A85-13638 [AIAA PAPER 85-0220] p 54 A85-26385 [IAF PAPER 84-38] p 41 A85-13001 Catalyse surface effect on ceramic coatings for an PAYLOAD DELIVERY (STS) Tethered propellant resuppty technique for space aeroassisted orbital transfer vehicle p 38 A85-29730 Spacelab Hitchhiker, a quick reaction earner stations OTV Propulsion Issues [AIAA PAPER 854)504] p 53 A85-19795 [IAF PAPER 84-442] p 44 A85-13282 [NASA-CP-2347] p 48 N85-16989 Right operation considerations for an aero-braked NASA OAST perspective p5 N85-16990 Solar concentrator for space power generation OTV Performance assessment of aero-assisted orbital [AIAA PAPER 85-0164] p 45 A85-19561 [AIAA PAPER 85-0220] p 54 A85-26385 transfer vehicles P 56 N85-16993 Integrated Power and Attitude Control Systems for Selected tether applications in space- An analysis of OTV propulsion tecnology programmatic overview Space Station five selected concepts p48 N85-16997 [AIAA PAPER 854)358] p 31 A85-19695 [NASA-CR-171222] p 55 N85-12921 Onves and benefits overview p 56 N85-16998 Synergy in space - Man-robot cooperation PAYLOAD DEPLOYMENT ft RETRIEVAL SYSTEM Aeroiet advanced engine concept p 48 N85-16999 p 41 A85-20400 Tethered satellite system project overview Active cooling requirements for propellent storage Integratable propulsion systems for the Space Station p5 N85-20341 p48 N85-17004 p46 A85-23393 Report of the Transportation Panel Propellant transfer Tethered depot A review of contamination issues associated with an p57 N85-20364 p48 N85-17006 orbiting Space Station external environment PAYLOAD INTEGRATION Vehicle/engine integration — orbit transfer vehicles p 38 A85-24703 Commerce Lab Mission analysis and payload p48 N85-17008 Definition of technology development missions for early integration study [NASA-CR-171272] p 56 N85-16981 Orbital transfer vehicle propulsion issues space stations Large space structures p48 N85-17009 [NASA-CR-171209] p4 N85-12084 PAYLOAD MASS RATIO Space based OTV servicing p 56 N85-17010 Mass optimisation of telecommunications satellites Engineering model system study for a regenerative fuel Orbital Debns [IAF PAPER 84-230] p 13 A85-13146 cell Study report [NASA-CP-2360] P 40 N85-21188 PERFORMANCE TESTS [NASA-CR-174801] p47 N85-16292 Environment definition, small particles, diameter less Performance capabilities of the 12-centimeter Xenon ion than or equal to 1 MM p40 N85-21223 Drives and benefits overview p 56 N85-16998 thruster p 44 A85-16439 Design study of an integrated aerobrakmg orbital transfer Parametric analysis SCO meteoroid and debns An investigation dunng the system test phase of the vehicle protection p 16 N85-21209 GOES spacecraft p32 A85-28126 [NASA-TM-58264] p9 N8S-21282 Natural environment design cntena for the Space Station Demonstration of transparent solar array module ORBITAL ASSEMBLY definition and preliminary design design Design consideration of space construction facility [NASA-TM-86498] p9 N85-21232 [NASA-CR-174257] p 47 N85-16302 [IAF PAPER 84-26] p6 A85-12992 Computer integration of engineering design and PERIGEES A space station expenment on large antenna assembly production A national opportunity Chemical nonequilibnum effects on flowfields for and measurement - A follow-on study [NASA-CR-175483] p 59 N85-21414 aeroassisted orbital transfer vehicles p53 A85-21831 [IAF PAPER 84-58] p 41 A85-13017 Debns impact on Earth-orbiting spacecraft The long term behaviour of Earth orbits and the Dynamics of the Obiter based construction of structural p59 N85-22234 implications for debns control p 58 N85-21213 PHASE DEVIATION components ORBITAL WORKERS Effect of phase fluctuations in an incident beam on the [IAF PAPER 84-359] p 18 ASS-13221 Neutral buoyancy evaluation of technologies for space charactenstics of a rectenna system p 30 A85-15760 Construction of large precision reflectors using the Aft station external operations — EVA weightlessness PHOTOVOLTAIC CELLS Cargo Camer simulation Unlimited power for our space vehicles [IAF PAPER 84-389] p2 A85-13244 [IAF PAPER 84-38] p 41 A85-13001 A modular approach to developing a large deployable p 46 A85-25796 reflector p7 A85-22685 ORGANIC MATERIALS PHYTOTRONS Kinetics of oxygen interaction with matenals Swing-arm beam erector (SABER) concept for single Space greenhouse design p 50 A85-12927 [AIAA PAPER 85-0472] p 37 A85-19770 astronaut assembly of space structure PIPES (TUBES) [NASA-TP-2379] p 42 N85-19015 OSCILLATIONS Development of advanced composite tubular structures ORBITAL ELEMENTS An investigation dunng the system test phase of the for antenna reflector p 10 A85-24817 Finite multiple burn orbit transfer error analysis via GOES spacecraft p 32 A85-28126 PLANAR STRUCTURES covanance matrix p 45 A85-22444 OXIDATION Autonomous momentum management for space ORBITAL LAUNCHING Kinetics of oxygen interaction with matenals station IRIS Spinning Stage - A pongee stage for satellites up [AIAA PAPER 85-0472] p 37 A85-19770 [NASA-CR-174065] p 24 N85-12931 to 900 kg to be launched from the Space Shuttle with OXYGEN ATOMS PLANETARY ORBITS the IRIS system p43 A85-12520 Atomic oxygen surface interactions - Mechanistic study A survey of aeroassisted orbit transfer Determination of atmospheric density using a using ground-based facilities p53 A85-21826 space-launched projectile [AIAA PAPER 85-0473] p 37 A85-19771 PLANTS (BOTANY) [AIAA PAPER 85-0327] p2 A85-20866 Space greenhouse design p50 A85-12927 ORBITAL LIFETIME PLASMA DIAGNOSTICS The long term behaviour of Earth orbits and the Electrodynamic interactions p 34 N85-20348 implications for debns control p58 N85-21213 Applications of Tethers in Space, volume 2 ORBITAL MANEUVERING VEHICLES PANEL FLUTTER [NASA-CP-2365] p 57 N85-20361 TOS and AMS - America's new capabilities in space Application of damping to spacecraft structures PLASMA DYNAMICS transportation — Transfer Orbit Stages and Apogee and p20 A85-15992 A plan for controlling electrostatic discharges on Maneuvenng Stages PARABOLIC REFLECTORS geosynchronous spacecraft p 32 A85-26685 [IAF PAPER 84-220] P 51 A85-13141 Precision of mesh-type reflectors for large space-borne PLASMA INTERACTION EXPERIMENT Evaluation of OMV ranging and docking systems antennas p 31 A85-21B35 Computer simulation of plasma electron collection by p42 N85-22230 PIX-II — solar array-space plasma interaction ORBITAL MANEUVERS Analytical thermal formulations for antenna dishes — [AIAA PAPER 854)386] p 45 A85-19715 satellite antennas p 15 N85-14017 A survey of aeroassisted orbit transfer SCATHA (spacecraft charging at high altitudes) plasma p53 A85-21826 PARAMETER IDENTIFICATION interaction expenment SC-3 high energy particle ORBITAL MECHANICS Adaptive modal control of structural dynamic systems spectrometer; SC-8 energetic ion composition Orbital Debns using recursive lattice filters p 23 A85-26435 expenment [NASA-CP-2360] P 40 N85-21188 Identification of vibration parameters of flexible [AD-A149728] p 35 N85-21252 The long term behaviour of Earth orbits and the structures p27 N85-18360 PLASMA INTERACTIONS Charactenstics of arc currents on a negatively biased implicatiorB for debns control p58 N85-21213 PARAMETERIZATION solar cell array in a plasma p 31 A85-18608 Debns in the geostationary orbit ring, the endless Qualitative results for distributed systems with discrete The effect of plasma on solar cell array arc shooting gallery- The necessity for a disposal policy damping and stiffness with application to control characteristics pSB N85-21214 [AD-A145525] p 24 N85-11382 ORBITAL SERVICING [AIAA PAPER 85-0384] p 31 A85-19713 Utilization of a teleoperated service vehicle for PARKING ORBITS Circuit transients due to negative bias arcs on a high spacecraft servicing The international environment UNISPACE '82 and the voltage solar array in low earth orbit [IAF PAPER 84-48] pi A85-13009 ITU A relationship between orbit-spectrum resource [AIAA PAPER 85-0385] p 45 A85-19714 In-orbrt laser regeneration of the radiation damaged solar allocation and orbital debns p 58 N85-21215 PLASMA JETS arrays PARTIAL DIFFERENTIAL EQUATIONS The effect of plasma on solar cell array arc [IAF PAPER 84-62] P 43 A85-13021 Qualitative results for distributed systems with discrete charactenstics OTV propulsion tecnology programmatic overview damping and stiffness with application to control [AIAA PAPER 854)384] p 31 A85-19713 p48 N85-16997 [AD-A145525] p 24 N85-11382 Electrodynamic interactions p 34 N85-20348

A-11 PLASMA PHYSICS SUBJECT INDEX

PLASMA PHYSICS PROJECT PLANNING RADIATION EFFECTS Science Applications, part 1 p S N85-20346 Europe in space 1985-2000 p 3 A85-26011 Dielectric matenal in the space environment Summary presentation of the Electrodynamics PROPELLANT STORAGE P37 A85-24672 Interactions Panel p 34 N85-20356 Active cooling requirements for propellant storage Radiation effects in matenals - Field-ion microscope PLASMA-ELECTROMAGNETIC INTERACTION p48 N85-17004 characterizations p 37 A85-24675 Engineering aspect of the Microwave Ionosphere PROPELLANT TRANSFER Environmental interactions working group report Nonlinear Interaction Experiment (MINIX) with a sounding Tethered propellant resupply technique for space p5 N85-13908 rocket stations RADIATION TOLERANCE [IAF PAPER 84-289] p 29 A85-13177 [IAF PAPER 84-442] p 44 A85-13282 Influence of starting matenal and technological PLASTIC DEFORMATION Propellant transfer Tethered depot processes on the radiation resistance of silicon solar cells Experimental study of the effect of the type of stress for space use — French thesis p 38 A85-30024 p48 N85-17006 state on plastic strain in structural materials at low RADIATIVE HEAT TRANSFER Space Transportation System (STS) propellant temperatures p37 ASS- 16499 Trajectory analysis of radiative heating for planetary scavenging system study Volume 1 Technical report Shear deformation plate contmua of large missions with aerobrakmg of spacecraft [NASA-CR-171848-VOL-1] p 49 N85-20000 double-layered space structures p8 N85-10391 p 14 A85-21829 PLATES (STRUCTURAL MEMBERS) Space Transportation System (STS) propellant RADIATORS Shear deformation plate continue of large scavenging system study Volume 2 Supporting research An optimal shape control of a large flexible radiator in double-layered space structures p8 N85-10391 and technology report space PLATES (TECTONICS) [NASA-CR-171849-VOL-2] p 49 N85-20001 [IAF PAPER 84-64] p 18 A85-13023 Science Applications, part 2 p 6 N85-20347 Space Transportatjom System (STS) propellant RADIO TRANSMITTERS PLATFORMS scavenging system study Volume 3 Cost and work An investigation dunng the system test phase of the Space frame design, development and optimization of breakdown structure-dictionary GOES spacecraft p 32 A85-28126 antenna platform structure for a mobile 3D radar [NASA-CR-171850-VOL-3] p 49 N85-20002 RAILGUN ACCELERATORS p 8 A85-24908 PROPULSION SYSTEM CONFIGURATIONS Preliminary analysis of space mission applications for POINTING CONTROL SYSTEMS The challenge of advanced space transportation and electromagnetic launchers A signed switching time bang-bang attitude control law propulsion systems (NASA-CR-174067] p 47 N85-12071 for fine pointing of flexible spacecraft p 19 A85-13893 [IAF PAPER 84-310] p 44 A85-13191 RANKINE CYCLE Precise control of flexible manipulators Design and benefits of pulsed MPD thruster orbit transfer Dynamic power systems for power generation [NASA-CR-174210] p 42 N85-16178 vehicles p 44 A85-16448 p33 N85-13892 Summary presentation of the Constellations Panel Design of a nuclear electric propulsion orbital transfer REACTION KINETICS p57 N85-20359 vehicle p 46 A85-23394 Kinetics of oxygen interaction with matenals Modal control of structural systems OTV Propulsion Issues [AIAA PAPER 85-0472] p 37 A85-19770 [AD-A149734] p 28 N85-2123S [NASA-CP-2347] p 48 N85-16989 RECTANGULAR PLATES POLAR ORBITS Dynamical modelling of a gravity-loaded rectangular Economics of permanent polar platforms (PPP) for global PROPULSION SYSTEM PERFORMANCE The cost effectiveness and optimal parameters of an plate as a test configuration for attitude control of large monitoring space structures [IAF PAPER 84-226] p2 A85-13144 electric rocket propulsion system for an mterorbital transport vehicle p 46 A85-23990 [IAF PAPER 84-391] p 18 A85-13245 POLICIES RECTENNAS Second Symposium on Space Industrialization — space NASA OAST perspective p5 N85-16990 Effect of phase fluctuations in an incident beam on the commercialization Aerojet advanced engine concept p 48 N85-16999 charactenstics of a rectenna system p30 A85-15760 [NASA-CP-2313] p4 N85-11011 PROTECTIVE COATINGS Debns \n Ihe geostationary orbrt ring, the endless Atomic oxygen surface mtetaclions - Mechanistic study RECURSIVE FUNCTIONS shooting gallery The necessity for a disposal policy using ground-based facilities Recursive Langrangian dynamics of flexible manipulator p 58 N85-21214 [AIAA PAPER 85-0473] p 37 A85-19771 arms p20 A85-15745 POLITICS Process for prepanng essentially colorless polyimide film REDUCED GRAVITY International cooperation and competition in space containing phenoxy-lmked diammes Second Symposium on Space Industrialization — space [GPO-38-001] p4 N85-11911 [NASA-CASE-LAR-13353-1] p 40 N85-20128 commercialization [NASA-CP-2313] p4 N85-11011 POLYIMIDES PROTON IRRADIATION Process for preparing essentially colorless polyimide film Effect of neutron and proton irradiation on some Producing gallium arsenide crystals m space containing phenoxy-lmked diammes properties of Kapton p 37 A85-21508 P54 N85-11023 [NASA-CASE-UAR-13353-1] p 40 N85-20128 PROTOTYPES Large-diameter astromast development POLYMER CHEMISTRY Spacecraft systems engmeenng and geometry [NASA-CR-171201] p11 N85-12200 Kinetics of oxygen interaction with matenals modelling - The ESABASE-MATVIEW approach REDUNDANT COMPONENTS [AIAA PAPER 85-0472] p 37 A85-19770 p8 A85-27696 The strongest structures with macrostiffness POLYMER MATRIX COMPOSITES PULTRUSION constraints p 10 A85-12933 Effects of residual stresses in polymer matrix Pultrusion process for fabncation of tethers (preliminary REENTRY VEHICLES composites p 35 A85-12395 concepts) p 40 N85-20371 Lay-out of a re-usable re-entry vehicle required in a future POLYMERIC FILMS PUSHBROOM SENSOR MODES European low earth orbit scenario Evaluation and prediction of long-term environmental Factors affecting push-broom performances in future [IAF PAPER 84-06] p 50 A85-12981 effects of nonmetallic matenals space platforms REFLECTING TELESCOPES [NASA-CR-171353] p 39 N85-19137 [IAF PAPER 84-116] p 29 A85-13066 Survey of deployable antenna concepts Process for preparing essentially colorless polyimide film The NASA MLA program — Multispectral Linear Array p 10 A85-23663 containing phenoxy-lmked diammes p52 A85-17573 [NASA-CASE-LAR-13353-1] p 40 N85-20128 REFLECTORS PORTABLE EQUIPMENT Construction of large precision reflectors using the Aft Toroid Joining Gun — thermoplastic welding system Cargo earner using induction heating [IAF PAPER 84-389] p2 A85-13244 [SAE PAPER 850408] p 38 A85-25988 RADAR Deployable reflector antennas - Mechanical design of POSITION (LOCATION) In situ orbital debns expenment concepts the reflective surface [IAF PAPER 84-393] p6 A85-13247 Displacement control of flexible structures using p58 N85-21198 electrohydraulic servo-actuators p23 A85-29144 RADAR ANTENNAS Deployable reflector configurations — for space POSITIONING DEVICES (MACHINERY) Structural aspects of SAR antenna for Japanese Earth telescope p2 A85-22577 The space shuttle orbiter remote manipulator positioning Resources Satellite 1 p 12 N85-14007 Design concepts for reflector antenna structures mechanism p 42 N85-16963 Technology for the ERS-1 SAR antenna p7 A85-22579 POWER CONDITIONING p33 N85-14008 A modular approach to developing a large deployable An Assessment of Integrated Flywheel System CASA technological effort in the field of antennas — reflector p7 A85-22685 Technology satellite radar antennas p33 N85-14010 Development of advanced composite tubular structures [NASA-CP-2346] p 26 N85-13850 RADAR ECHOES for antenna reflector p 10 A85-24817 POWER SUPPLY CIRCUITS Spectral charactenstics of radar echoes from Dynamic charactenstics of a space reflector support Circuit transients due to negative bias arcs on a high aircraft-dispensed chaff p 23 A85-26606 structure p 22 A85-24949 voltage solar array in low earth orbit RADAR REFLECTORS Research on large, highly accurate, inflatable [AIAA PAPER 85-0385] p 45 A85-19714 CASA activities in antenna technology — satellite reflectors PREFUGHT ANALYSIS antennas p39 N85-14015 [AD-A145080] p11 N85-10099 Oral presentation of first year final report, appendix A RADIANT COOLING p25 N85-13840 Space station thermal control - An interview with Robert REFUELING PREPREGS Haslett p 13 A85-18321 Propellant transfer Tethered depot Kevlar and T300 fabric prepregs - Their material RADIANT HEATING P48 N85-17006 properties and their use in high loaded areas of a solar Torsional vibration of booms with open cross section REGENERATIVE FUEL CELLS array caused by unidirectional radiant heating Integratable propulsion systems for the Space Station [IAF PAPER 84-402] p 35 A85-13255 p 22 A8S-26350 p 46 A85-23393 RWIATION DAMAGE Regenerative 1ue> cett energy storage system tot & tow large space structure construction p 36 A85-15638 In-orfait laser regeneration of the radiation damaged solar Earth orbit space station PROJECT MANAGEMENT arrays [NASA-CR-174802] p 47 N85-13371 Computer integration of engineering design and [IAF PAPER 84-62] p 43 A85-13021 Engmeenng model system study for a regenerative fuel production A national opportunity Effect of neutron and proton irradiation on some cell Study report [NASA-CR-175483] p 59 N85-21414 properties of Kapton p 37 A85-21508 [NASA-CR-174801] P47 N85-16292

A-12 SUBJECTINDEX SATELLITE ROTATION

REINFORCED PLASTICS ROBUSTNESS (MATHEMATICS) Mechanical/thermal design of a polarization sensitive Reinforced Plastics/Composites Insbtute, Annual Robust attitude control of a large communication satellite reflector — communication satellites p 15 N85-14009 Conference, 38th, Houston, TX, February 7-11, 1983, with flexible solar arrays CASA technological effort in the field of antennas — c- Preprints p36 A85-15626 [IAF PAPER 84-ST-06] p 19 A85-13293 satellite radar antennas p33 N85-14010 ^RELIABILITY ROCKET ENGINE DESIGN BAe antenna hardware technology for current satellite C-' Potential of flywheels for spacecraft energy storage IRIS Spinning Stage - A perigee stage for satellites up projects p9 N85-14011 p33 N85-138SO to 900 kg to be launched from the Space Shuttle with Technology and performances of structural thermal [REMOTE MANIPULATOR SYSTEM the IRIS system p43 AS5-12520 mechanical equipment used for antenna of TV SAT-TDF Service manipulator system for maintenance and Optimal electric propulsion orbit transfer vehicle design 1 program p 15 N85-14012 ~_ servicing of future space platforms and operational effectiveness The dimensional stability of advanced composite : [IAF PAPER 84-369] p 41 A85-13227 [AIAA PAPER 85-0431] p 45 A85-19744 ' antenna reflectors Analytical and test evaluation — Satellite grasping manipulator system ROCKET ENGINES satellite antennas p39 N85-14014 [IAF PAPER 84-371] p 41 A8S-13229 The cost effectiveness and optimal parameters of an CASA activities in antenna technology — satellite electric rocket propulsion system for an mterortaital '"- Space Station remote manipulator requirements antennas p39 N85-14015 transport vehicle p 46 A85-23990 definition Structural design and thermal stability of TELE-X Drives and benefits overview p 56 N85-16998 r [AIAA PAPER 85-0029] p41 A85-19466 antenna tower p 15 N85-14016 ROCKET SOUNDING Analytical thermal formulations for antenna dishes — Sot degrees of freedom control with each hand? Engineering aspect of the Microwave Ionosphere satellite antennas p 15 N85-14017 p42 N85-14492 Nonlinear Interaction Experiment (MINIX) with a sounding In-ortxt performance of INTELSAT V communications , The space shuttle ortaiter remote manipulator positioning rocket antennae deployment systems p33 N85-14018 " mechanism p42 N85-16963 [IAF PAPER 84-289] p 29 A85-13177 Study of structure control dynamic interaction for radio An overview of the space remote manipulator system RODS frequency antenna control systems — satellite antennas - p42 N85-16964 Stability of the rotation of a body suspended by means p26 N85-14020 REMOTE SENSING of a system of rods connected in senes Hemispherical antenna pointing mechanism — satellite An economic analysis of humans and machines for p23 A85-28906 antennas p 26 N85-14021 space construction ROOT-MEAN-SQUARE ERRORS ARABSAT spacecraft Rx and Tx antenna [IAF PAPER 84-232] p 51 A85-13148 Precision of mesh-type reflectors for large space-borne mechanisms p 34 N85-14022 The German remote sensing program antennas p 31 A85-21835 Operational fitness of box truss antennas in response p52 A8S-16881 ROTARY STABILITY to dynamic slewing The NASA MLA program — Muluspectral Linear Array Stability of the rotation of a body suspended by means [NASA-CR-172470] p 27 N85-19012 p52 A85-17573 of a system of rods connected in senes SATELLITE ATMOSPHERES p23 A85-28906 Second Symposium on Space Industnalrzation — space Trajectory analysis of radiative heating for planetary ROTATING BODIES commercialization missions with aerobraking of spacecraft Stability of the rotation of a body suspended by means [NASA-CP-2313] p4 N85-11011 p 14 A85-21829 of a system of rods connected in senes SATELLITE ATTITUDE CONTROL In situ orbital detans experiment concepts p23 A85-28906 Attitude control system and communications payload for pS8 N85-21198 ROTATION an amateur solar sail spacecraft REMOTE SENSORS Recursive Langrangian dynamics of flexible manipulator [IAF PAPER 84-363] p 29 A85-13224 Factors affecting push-broom performances in future arms p20 A85-15745 Robust attitude control of a large communication satellite space platforms with flexible solar arrays [IAF PAPER 84-116] p 29 A85-13066 [IAF PAPER 84-ST-06] p 19 A85-13293 RESEARCH AND DEVELOPMENT Efficient inclination control for geostationary satellites Environmentally-induced voltage limitations in large [AIAA PAPER 85-0216] p 21 A85-19595 S GLASS space power systems p 31 A8S-18584 The dynamics of the attitude control and stabilization Passive Orbital Disconnect Strut (PODS 3) structural test Structural control research at AFOSR systems of spacecraft with a controlled gravity gradient program p 21 A85-22585 stabilizer p 23 AB5-28903 [NASA-CR-177325] p 16 N85-17020 Active control technology development at NASA Study of structure control dynamic interaction for radio SAFETY MANAGEMENT p22 A85-22586 frequency antenna control systems — satellite antennas Geosynchronous satellite collision avoidance Development of advanced composite tubular structures p26 N85-14020 p58 N85-21197 for antenna reflector p 10 A8S-24817 Application Number 3 Using tethers for attitude SAILS Development and application of new technologies in control p 27 N85-20373 The Satellite sail p49 N85-20376 ESA's Olympus programme p 3 A85-27695 SATELLITE CONFIGURATIONS RESIDUAL STRESS SALYUT SPACE STATION TSS Satellite overview p 5 N85-20343 Effects of residual stresses in polymer matrix Salyut Mission Report p3 A85-25700 Satellite module design p 9 N85-20344 Effect of aerodynamic moment on the regime of the composites p 35 A85-12395 SATELLITE CONTROL gravity gradient stabilization of the Safyut-6 - Soyuz orbital RESIDUES Analytical and experimental research in large space system p 23 A85-28488 Analysis of Nonvolatile Residue (NVR) from spacecraft structures control systems SANDWICH STRUCTURES [AIAA PAPER 85-0356] p 21 A85-19693 [NASA-TM-86184] p 39 N85-17019 Kevlar and T300 fabric prepregs - Their material Definition of ground test for Large Space Structure (LSS) RESONANT FREQUENCIES properties and their use in high loaded areas of a solar control venfication Evaluation of efficiently computed exact vibration array [NASA-TM-86495] p 28 N85-21249 [IAF PAPER 84-402] p 35 A85-13255 characteristics of space platforms assembled from stayed SATELLITE DESIGN columns p 13 A85-12884 SATELLITE ANTENNAS Some design concepts for Intelsat VII RESOURCE ALLOCATION A space station expenment on large antenna assembly p7 A85-15496 The international environment UNISPACE '82 and the and measurement - A follow-on study Structures and matenals technologies for spacecraft ITU A relationship between orbit-spectrum resource [IAF PAPER 84-58] p 41 A85-13017 systems An overview p 36 A85-15977 allocation and orbital debns p 58 N85-21215 An optimal shape control of a large flexible radiator in The systems background for satellite communication REUSABLE ROCKET ENGINES space antennas p 32 A85-23652 [IAF PAPER 84-64] p 18 A85-13023 Aeroiet advanced engine concept p 48 N85-16999 Development and application of new technologies in Environmental effects on the dynamics and control of REUSABLE SPACECRAFT ESA's Olympus programme p 3 A85-27695 an orbiting large flexible antenna system Lay-out of a re-usable re-entry vehicle required in a future SATELLITE GROUND SUPPORT [IAF PAPER 84-358] p 18 A85-13220 European low earth orbit scenario NASA's mobile satellite communications program, [IAF PAPER 84-06] p 50 A85-12981 Antenna engineering handbook /2nd edition/ ground and space segment technologies Drives and benefits overview p56 N85-16998 p30 A85-16081 [IAF PAPER 84-84] p 29 A85-13040 Advanced research and technology programs for Satellite communication antenna technology SATELLITE IMAGERY advanced high-pressure oxygen-hydrogen rocket p 31 A85-23651 Factors affecting push-broom performances in future propulsion The systems background for satellite communication space platforms [NASA-TM-86969] p 50 N85-21231 antennas p 32 A85-23652 [IAF PAPER 84-116] p29 A85-13066 RIGID STRUCTURES Sky-hooks, fish-warmers and hub-caps - Milestones in SATELLITE INSTRUMENTS Measurement of the inertial constants of a rigid or flexible satellite communications — technological development Instrumentation for Application Number 1 Mass structure of arbitrary share through a vibration test p32 A85-25101 spectrometnc analysis of the boundary layer associated [NASA-TM-77557] p 24 N85-11381 Workshop on Mechanical Technology for Antennas — with the tethered satellite p 58 N85-20372 Elimination of uncontrollable rtgid body mode, appendix conferences, satellite antennas SATELLITE OBSERVATION C p25 N85-13842 [ESA-SP-225] p11 N85-13999 A case for Gohrern - Geosynchronous orbit high ROBOTICS Antenna mechanical technologies within ESA resolution earth monitoring p 50 A85-10261 Service manipulator system for maintenance and p11 N85-14000 SATELLITE POWER TRANSMISSION (TO EARTH) servicing of future space platforms Effect of phase fluctuations in an incident beam on the High performance employable antenna structures [IAF PAPER 84-369] p 41 A85-13227 charactenstics of a rectenna system p30 ASS-15760 pit N85-14001 ROBOTS Earth's magnetic field perturbations as the possible Offset unfuriable antenna concepts p5 N85-14002 Synergy in space - Man-robot cooperation environmental impact of the conceptualized solar power p41 A85-20400 Electrical consequences of mechanical antenna satellite Precise control of flexible manipulators characteristics p 33 N85-14006 [AD-A149120] p30 A85-16641 [NASA-CR-174210] p42 N85-16178 Structural aspects of SAR antenna for Japanese Earth SATELLITE ROTATION A functional vehicle for autonomous mobile robot Resources Satellite 1 p 12 N85-14007 Effect of aerodynamic moment on the regime of the research Technology for the ERS-1 SAR antenna gravity gradient stabilization of the Satyut-6 - Soyuz orbital [AD-A150052] p 42 N85-21666 p33 N85-14008 system p 23 A85-28488

A-13 SATELLITE SOLAR ENERGY CONVERSION SUBJECTINDEX

SATELLITE SOLAR ENERGY CONVERSION Investigation of welded interconnection of large area SOLAR POWER SATELLITES Influence of starting material and technological wraparound contacted silicon solar cells Engineering aspect of the Microwave Ionosphere processes on the radiation resistance of silicon solar cells [NASA-CR-174438] p 39 N85-19519 Nonlinear Interaction Expenment (MINIX) with a sounding for space use — French thesis p 38 A85-30024 SIMULATION rocket SATELLITE TELEVISION Compensator development and examination of [IAF PAPER 84-289] p 29 A85-13177 Report of the student working group to the panel on performance and robustness Earth's magnetic field perturbations as the possible satellite communications — Space Applicatioons Board [NASA-CR-175470] p 34 N85-20244 environmental impact of the conceptualized solar power Crestwood 1982 Summer Study p 30 A85-14430 SLEWING satellite Technology and performances of structural thermal Operational fitness of box truss antennas in response [AD-A149120] p30 A85-16641 mechanical equipment used for antenna of TV SAT-TDF to dynamic slewing The potential of solar power satellites for developing 1 program p 15 N85-14012 [NASA-CR-172470] p 27 N85-19012 countnes p 53 A85-24654 The maximum efficiency of an isolated solar energy SATELLITE TEMPERATURE SOLAR ARRAYS conversion device in space p 46 A85-25797 Space environment simulation to test satellite thermal Design and technology trends on large solar arrays for SOLAR SAILS control coatings, volume 1 space stations The state of the art solar sail and the interstellar [CERT-4128-VOL-1] p 16 N85-17012 [IAF PAPER 84-37] p 43 A85-13000 Space environment simulation to test satellite thermal precursor mission p 43 A85-12926 In-orbit laser regeneration of the radiation damaged solar control coatings Volume 2 Annex 1 Attitude control system and communications payload for arrays [ESA-CR(P)-1670-VOL-2] p 16 N85-17013 an amateur solar sail spacecraft [IAF PAPER 84-62] p 43 A85-13021 Space environment simulation to test satellite thermal [IAF PAPER 84-363] p 29 A85-13224 control coatings Volume 2 Annexes 2, 3, 4 Kevlar and T300 fabric prepregs - Their matenal On the potential performance of non-nuclear interstellar [ESA-CR(P)-1870-VOL-3] p 16 N85-17014 properties and their use in high loaded areas of a solar arks p46 A85-25828 SATELLITE TRACKING array SOUND WAVES Orbital Debns [IAF PAPER 84-402] p 35 A85-13255 Human response to vibroacoustic environments of [NASA-CP-2360] p 40 N85-21188 Robust attitude control of a large communication satellite space vehicles Geosynchronous satellite collision avoidance with flexible solar arrays [NASA-TM-86316] p 54 N85-10789 p58 N85-21197 [IAF PAPER 84-ST-06] p 19 A85-13293 SOYUZ SPACECRAFT SATELLITE TRANSMISSION Characteristics of arc currents on a negatively biased Effect of aerodynamic moment on the regime of the An investigation dunng the system test phase of the solar cell array in a plasma p 31 ASS-18608 gravity gradient stabilization of the Salyut-6 - Soyuz orbital GOES spacecraft p 32 A85-28126 Integrated Power and Attitude Control Systems for system p 23 A85-28488 SCATHA SATELLITE Space Station SPACE BASES SCATHA (spacecraft charging at high altitudes) plasma [AIAA PAPER 85-0358] p 31 A85-19695 Aerojet advanced engine concept p48 N85-16999 interaction experiment SC-3 high energy particle Circuit transients due to negative bias arcs on a high Opening up the future in space with nuclear power spectrometer; SC-8 energetic ion composition voltage solar array in low earth orbit [DE85-002411] p 49 N85-20862 expenment [AIAA PAPER 854)385) p 45 A85-19714 SPACE COLONIES [AD-A149728] p 35 N85-21252 Computer simulation of plasma electron collection by Space greenhouse design p50 A85-12927 SCAVENGING PIX-II — solar array-space plasma interaction SPACE COMMERCIALIZATION Space Transportation System (STS) propellant [AIAA PAPER 85-0386] p 45 A85-19715 Space exploitation - Spacelab an easy approach for scavenging system study Volume 1 Technical report Unlimited power for our space vehicles developing countnes Prospectwes and suggestions by [NASA-CR-171848-VOL-1] p 49 N85-20000 p46 A85-25796 Aentalia p 1 A85-12502 Space Transportation System (STS) propellant Autonomous momentum management for space Space - The future of mankind p 3 A85-25697 scavenging system study Volume 2 Supporting research station The communication-satellite market to the year 2000 and technology report [NASA-CR-174065] p 24 N85-12931 p3 A85-26771 [NASA-CR-171849-VOL-2] p 49 N85-20001 Autonomous momentum management for space station, Commercialization of space - Incentives, impediments Space TransportatJoin System (STS) propellant exhibit A and alternatives p3 A85-27375 scavenging system study Volume 3 Cost and work [NASA-CR-171256] p 33 N85-12933 Second Symposium on Space Industrialization — space breakdown structure-dictionary Demonstration of transparent solar array module commercialization [NASA-CR-171850-VOL-3] p 49 N85-20002 design [NASA-CP-2313] p4 N85-11011 SEISMIC WAVES [NASA-CR-174257] p 47 N85-16302 Doing business in space How to get there from here The Shock and Vibration Digest, volume 16, no 11 Efficient structures for geosynchronous spacecraft solar p55 N85-11057 [AD-A148466] p16 N85-17382 arrays International cooperation and competition in space SERVICE LIFE [NASA-CR-174448] p 12 N85-19004 [GPO-38-001] p4 N85-11911 Perspectives on energy storage wheels for space station Report of the Electrodynamic Interactions Panel Commerce Lab Mission analysis and payload application p 47 N85-13860 p34 N85-20363 integration study [NASA-CR-171272] p 56 N85-16981 SERVICE MODULES Control of large collector arrays The SSPS Commercial space Europe should have independent Utilization of a teleoperated service vehicle for expenence strategy p5 NB5-19205 spacecraft servicing [DE85-001461] p 34 N85-20553 Commercial space launches [IAF PAPER 84-48] p 1 A85-13009 SOLAR BLANKETS [S-REPT-98-656] p6 N85-2122S SERVOCONTROL Development of a foldlme concept for automatic SPACE DEBRIS The decentralized control of large flexible space refolding of a flexible blanket (folding analysis) — Orbital Debns structures p 17 A85-10071 spacebome solar generators [ESA-CR(P)-1933] p 12 N85-17428 [NASA-CP-2360] p 40 N85-21188 Displacement control of flexible structures using SOLAR CELLS Assessment of satellite collision hazards by simulated electrohydraulic servo-actuators p23 A85-29144 Near-optimum design of GaAs-based concentrator sampling in space p40 N85-21195 SHAPE CONTROL space solar cells for 80 C operation p 30 A85-15800 Geosynchronous satellite collision avoidance An optimal shape control of a large flexible radiator in Charactenstjcs of arc currents on a negatively biased p58 N85-21197 space solar cell array in a plasma p31 ASM 8608 In situ orbital debns expenment concepts [IAF PAPER 84-64] p 18 A85-13023 The effect of plasma on solar cell array arc p58 N85-21198 An analytical investigation of shape control of large charactenstcs Preliminary design of an Earth-based debns detection space structures by applied temperatures [AIAA PAPER 85-0384] p 31 A85-19713 system using current technology and existing p14 A85-25145 Solar cells for tomorrow's spacecraft installations p40 N85-21199 SHEAR p54 A85-24794 Parametnc analysts SOC meteoroid and debns Shear deformation plate continue of large Unlimited power for our space vehicles protection p 16 N85-21209 double-layered space structures p8 N85-10391 p46 A85-25796 The international environment UNISPACE '82 and the SHOCK HEATING Influence of starting matenal and technological ITU A relationship between orbit-spectrum resource Generalized transform methods based finite element processes on the radiation resistance of silicon solar cells allocation and orbital debns p58 N85-21215 methodology - Thermal/structural dynamic applications for space use — French thesis p 38 A85-30024 Environment definition, small particles, diameter less [AIAA PAPER 85-0155] p 14 A85-19553 Investigation of welded interconnection of large area than or equal to 1 MM p 40 N85-21223 SHOCK RESISTANCE wraparound contacted silicon solar cells Debns impact on Earth-orbiting spacecraft The Shock and Vibration Digest, volume 16, no 11 [NASA-CR-174438] p 39 N85-19519 p59 N85-22234 [AD-A148466] p 16 N85-17382 SOLAR COLLECTORS SPACE ENVIRONMENT SIMULATION SHOCK SIMULATORS Solar concentrator for space power generation Neutral buoyancy evaluation of technologies for space The Shock and Vibration Digest, volume 16, no 11 [AIAA PAPER 85-0164] p 45 A85-19561 station external operations — EVA weightlessness [AD-A148466] p 16 N85-17382 Control of large collector arrays The SSPS simulation expenence SHOCK SPECTRA [IAF PAPER 84-38] p 41 A85-13001 [DE85-001461] p34 N85-20553 The Shock and Vibration Digest, volume 16, no 11 Influence of simulated space environment on the SOLAR ENERGY CONVERSION [AD-A148466] p16 N85-17382 behavior of carbon-fiber-remforced plastics with +, -45 Unlimited power for our space vehicles ply onentations II p 36 A85-14163 SHOCK WAVES p 46 A85-25796 Keynote address p 27 N85-18378 The maximum efficiency of an isolated solar energy Effects of space environmental conditions on graphite SIGNAL DISTORTION conversion device in space p 46 A85-25797 epoxy composites p 36 A85-15990 Electncal consequences of mechanical antenna The liquid droplet radiator - an ultralightweight heat Space environment simulation to test satellite thermal charactenstes p33 N85-14006 rejection system for efficient energy conversion in space control coatings, volume 1 SILICON p 15 N85-13900 [CERT-4128-VOL-1] p 16 N85-17012 Influence of starting material and technological SOLAR GENERATORS Space environment simulation to test satellite thermal processes on the radiation resistance of silicon solar cells Environmentally-induced voltage limitations in large control coatings Volume 2 Annex 1 for space use — French thesis p 38 A85-30024 space power systems p 31 A85-18584 [ESA-CR(P)-1870-VOL-2] p 16 N85-17013

A-14 SUBJECTINDEX SPACE STATIONS

Space environment simulation to test satellite thermal SPACE OBSERVATIONS (FROM EARTH) Evaluation of OMV ranging and docking systems control coatings Volume 2. Annexes 2,3,4 Preliminary design of an Earth-based debns detection p42 N85-22230 [ESA-CR(P>1870-VOL-3) p 16 N85-17014 system using current technology and existing SPACE SHUTTLE MISSIONS SPACE ERECT ABLE STRUCTURES mstallatxjns p40 N85-21199 Spacelab Hitchhiker, a quick reaction earner Dynamics of the Orbrter based construction of structural SPACE PLASMAS [AIAA PAPER 85X1504] p 53 A85-19795 components Computer simulation of plasma electron collection by SPACE SHUTTLE ORBITERS [IAF PAPER 84-359] p 18 A85-13221 PIX-II — solar array-space plasma interaction Utilization of a teleoperated service vehicle for Inflatable space-ngxfized structures - Recent [AIAA PAPER 85-0386] p 45 A85-19715 spacecraft servicing developments of the material technology Science Applications, part 1 p 5 N85-20346 [IAF PAPER 84-48] p 1 ASS-13009 [IAF PAPER 84-384] p 10 A85-13240 SPACE PLATFORMS Optimal design of a passive vibration absorber for a Dynamic isolation of a spacecraft science platform via Variable geometry truss and its application to deptoyable truss beam p 19 A85-13638 momentum compensation p 17 A85-11082 truss and space crane arm Flight operation considerations for an aero-braked Comparing attitude control effectiveness for actuators [LAP PAPER 84-394) p 10 ASS-13248 OTV on two bodies of a six body model of a flexible spacecraft [AIAA PAPER 85-0220] p 54 A85-26385 Equations of motion governing the deployment of a with that for actuators restricted to a single body flexible linkage from a spacecraft p17 A85-11086 Selected tether applications in space An analysis of [AIAA PAPER 85-0023] p 20 A85-19462 Evaluation of efficiently computed exact vibration five selected concepts A modular approach to developing a large deptoyable characteristics of space platforms assembled from stayed [NASA-CH-171222] p 55 N85-12921 reflector p7 A85-22685 columns p13 A85-12884 SPACE SHUTTLE PAYLOADS Definition of technology development missions for early Architecture and implementation of an morbit IRIS Spinning Stage - A perigee stage for satellites up space stations Large space structures infrastructure to 900 kg to be launched from the Space Shuttle with [NASA-CR-171209] p4 N85-12084 [IAF PAPER 84-29] p6 A85-12995 the IRIS system p43 A85-12520 Large-diameter astromast development Utilization and economics of a European low earth orbit Construction of large precision reflectors using the Aft [NASA-CR-171201] pll N85-12200 Space Platform Cargo Garner Large spacebome antenna reflectors using inflatable [IAF PAPER 84-57] p1 A85-13016 [IAF PAPER 84-389] p2 A85-13244 space ngidized structures p 12 N85-14004 Factors affecting push-broom performances in future Applications of space tethers Development of a foldlme concept for automatic space platforms [IAF PAPER 84-436] p 51 A85-13276 refolding of a flexible blanket (folding analysts) — [IAF PAPER 84-116] P29 A85-13066 The NASA MLA program — Multispectral Linear Array spacebome solar generators Economics of permanent polar platforms (PPP) for global p52 A85-17573 [ESA-CR(P)-1933] p12 N85-17428 morutonng Spacelab Hitchhiker, a quick reaction earner [IAF PAPER 84-226] p2 A85-13144 Ground test article for deployable space structure [AIAA PAPER 85*504] p 53 A85-19795 Dynamics of the Orbrter based construction of structural systems Finite multiple bum orbit transfer error analysis via components [NASA-CR-171301] p9 N85-19011 covanance matrix p 45 A85-22444 [IAF PAPER 84-359] p 18 A85-13221 Variable geometry truss concept Service manipulator system for maintenance and A modular approach to developing a large deployable [REPT-614] p 12 N85-21697 servicing of future space platforms reflector p7 A85-22685 SPACE EXPLORATION [IAF PAPER 84-369] p 41 A85-13227 European retrievable earner (Eureca) and evolutionary Space - The future of mankind p 3 A85-25697 Space station/space platform system design space earner for microgravity, Earth observation and International cooperation and competition in space considerations p7 A85-14429 technology demonstration p55 N85-11032 [GPO-3B-001] p4 N85-11911 Report of the student working group to the panel on External tank aft cargo earner p 8 N85-11050 Opening up the future in space with nuclear power satellite communications — Space Applicatioons Board Proceedings of a Workshop on the Applications of [DE85-002411] p49 N85-20862 Crestwood 1982 Summer Study p 30 A85-14430 Tethers in Space, Volume 1 SPACE FLIGHT An unmanned platform as an initial capability in space [NASA-CR-171196] p 55 N85-12076 The future of space flight p 2 A85-16109 p52 A85-16305 Proceedings of a Workshop on Applications of Tethers The human role in space Volume 1 Executive Autonomous momentum management for the CDG in Space, Volume 2 summary planar Space Station [NASA-CR-171197] p 55 N85-12077 [NASA-CR-171223J p 56 N85-13473 [AIAA PAPER 85-0031] p 21 A85-19468 Commerce Lab Mission analysis and payload SPACE FLIGHT FEEDING Thermal storage analysis for large manned space integration study Characterization of heat transfer in nutrient matenals platforms [NASA-CR-171272] p 56 N85-16981 — space flight feeding [AIAA PAPER 85*066] p 14 A85-19493 Commercial space Europe should have independent [NASA-CR-171841] p 56 N85-17551 Dynamic charactenstics of a space reflector support strategy p5 N85-19205 structure p 22 A85-24949 Space Transportation System (STS) propellent SPACE INDUSTRIALIZATION Modular expenmental platform for science and scavenging system study Volume 1 Technical report Space exploitation - Spacelab an easy approach for applications p11 N85-11031 [NASA-CR-171848-VOL-1] p 49 N85-20000 developing countries Prospectn/es and suggestions by Selected tether applications in space An analysis of Tether fundamentals p 57 N85-20345 Aentalia p 1 A85-12502 five selected concepts Science Applications, part 1 p 5 N85-20346 Design consideration of space construction facility [NASA-CR-171222] p 55 N85-12921 SPACE SHUTTLES [IAF PAPER 84-26] p6 ASS-12992 Autonomous momentum management for space Orbit-on-demand vehicles - Mission possible, but Synergy in space - Man-robot cooperation station one-day turnaround? p 53 A85-24790 p 41 A85-20400 [NASA-CR-174065] p 24 N85-12931 International cooperation and competition in space Second Symposium on Space Industrialization — space Autonomous momentum management for space station, [GPO-38-001] p4 N85-11911 commercialization exhibit A Six degrees of freedom control with each hand? [NASA-CP-2313] p4 N85-11011 [NASA-CR-t71256] p 33 N85-12933 p 42 N85-14492 SPACE LABORATORIES SPACE POWER REACTORS Reduction method lor thermal analysis of complex Commerce Lab Mission analysts and payload Nudear-electnc power in space p 30 A85-15812 aerospace structures integration study Design of a nuclear electric propulsion orbital transfer [NASA-TP-2373] p 15 N85-16066 [NASA-CR-171272] p 56 N85-16981 vehicle p 46 A85-23394 The space shuttle orbiter remote manipulator positioning SPACE LAW Nuclear reactors for space power p 46 A85-24793 mechanism p42 N85-16963 Commercialization of space • Incentives, impediments The liquid droplet radiator - an ultralightweight heat An overview of the space remote manipulator system and alternatives p 3 A85-27375 rejection system for efficient energy conversion in space p42 N85-16964 SPACE MAINTENANCE p 15 N85-13900 Tethered satellite system project overview Service manipulator system for maintenance and Opening up the future in space with nuclear power p 5 N85-20341 servicing of future space platforms [DE85-002411] p49 N85-20862 The Satellite sail p49 N85-20376 [IAF PAPER 84-369] p 41 A85-13227 SPACE PROCESSING Environment definition, small particles, diameter less SPACE MANUFACTURING Lay-out of a re-usable re-entry vehicle required in a future than or equal to 1 MM p40 N85-21223 Dynamics of the Orbiter based construction of structural European low earth orbit scenario Advanced research and technology programs for components [IAF PAPER 84-06] p 50 A85-12981 advanced high-pressure oxygen-hydrogen rocket [IAF PAPER 84-359] p 18 A85-13221 Architecture and implementation of an in-orbit propulsion SPACE MISSIONS infrastructure [NASA-TM-86969] p 50 N85-21231 Nuclear-electric power in space p30 ASS-15812 [IAF PAPER 84-29] p6 A85-12995 SPACE STATIONS Salyut Mission Report p 3 A85-25700 Material sciences in space p 36 ASS-13500 Design consideration of space construction facility Preliminary analysts of space mission applications for Second Symposium on Space Industrialization — space [IAF PAPER 84-26] p6 ASS-12992 electromagnetic launchers commercialization Design and technology trends on large solar arrays for [NASA-CR-174067] p 47 N85-12071 [NASA-CP-2313] p4 N85-11011 space stations Definition of technology development missions for early Producing gallium arsenide crystals in space [IAF PAPER 84-37] p 43 ASS-13000 space stations Large space structures p54 N85-11023 A space station expenment on large antenna assembly [NASA-CR-171209] p4 N85-12084 SPACE PROGRAMS and measurement - A follow-on study The investigation of tethered satellite system Onentaoon and trends in European technology — space [IAF PAPER 84-58] p 41 A85-13017 dynamics programs Impacts of life support system on space station design [NASA-CR-171278] p 26 N85-15772 [IAF PAPER 84-377] p2 A85-13233 [IAF PAPER 84-166] p6 A85-13100 Tethered satellite system project overview The future of space flight p 2 A85-1S109 EASCON '83. Proceedings of the Sixteenth Annual p 5 N85-20341 International space programmes and policies Electronics and Aerospace Conference and Exposition, Summary presentation of the Electrodynamics p2 A85-20507 Washington, DC. September 19-21.1983 Interactions Panel p 34 N85-20356 SPACE RENDEZVOUS p 51 A85-14426 Summary presentation of the technology and test Satellite grasping manipulator system Space station/space platform system design panel p57 NB5-20360 [IAF PAPER 84-371 ] p 41 A85-13229 considerations p7 A85-14429

A-15 SPACE SURVEILLANCE SUBJECT INDEX

Report of the student working group to the panel on Simulation of reusable cislunar space transportation Summary presentation of the Constellations Panel satellite communications — Space Applications Board systems with special consideration of chemical propulsion p 57 N85-20359 Crestwood 1982 Summer Study p 30 ASS-14430 — German thesis p44 A85-15874 Report of the Constellations Panel p 27 N85-20368 Space station thermal control - An interview with Robert The low cost development, test, and production of a Modal control of structural systems Haslett p13 A85-18321 commercial STS upper stage TOS [AD-A149734] p 28 N85-21235 Space Station remote manipulator requirements [AIAA PAPER 85-0313] p 45 A85-19660 SPACECRAFT CONSTRUCTION MATERIALS definition National Aeronautics and Space Administration _ Inflatable space-ngidized structures - Recent [AIAA PAPER 85-0029] p 41 A85-19466 p4 N85-10871 developments of the matenal technology [IAF PAPER 84-384] p 10 A85-13240 Computer aided design of multiple input/output control External tank aft cargo earner p8 N85-11050 systems for multibody flexible Space Station Design preparations for large space structures Selected tether applications in space An analysis of [AIAA PAPER 85-0223] p7 A85-19600 [IAF PAPER 84-392] p 35 A85-13246 five selected concepts Analytical and experimental research in large space Kevlar and T300 fabric prepregs - Their material [NASA-CR-171222] p 55 N85-12921 structures control properties and their use in high loaded areas of a solar [AIAA PAPER 85-0356] p 21 A85-19693 Space Transportation System (STS) propellent array Wavelength division multiplexing for future Space Station scavenging system study Volume 1 Technical report [IAF PAPER 84-402] p 35 A85-13255 data systems p32 A85-25359 [NASA-CR-171848-VOL-1] p 49 N85-20000 Thermoelastic behaviour of space structures in Space - The future of mankind p 3 A85-25697 Space Transportation System (STS) propellant composite matenals Human response to vibroacoustic environments of scavenging system study Volume 2 Supporting research [IAF PAPER 84-404] p 35 A85-13257 space vehicles and technology report Influence of the lamination and of some environmental [NASA-TM-86316] p 54 N85-10789 [NASA-CR-171849-VOL-2] p 49 N85-20001 effects on damping charactenstics of advanced Office of Technology Assessment p 4 N85-10872 Space Transportatioin System (STS) propellant composites for space structures Second Symposium on Space Industrialization — space scavenging system study Volume 3 Cost and work [IAF PAPER 84-405] p 36 A85-13258 commercialization breakdown structure-dictionary Structures and matenals technologies for spacecraft [NASA-CP-2313] p4 N85-11011 [NASA-CR-171850-VOL-3] p 49 N85-20002 systems An overview p36 A85-15977 The computer-communication link for the innovative use Applications of Tethers in Space, volume 2 Graphite epoxy structure of the Space Telescope's of Space Station p32 N85-11016 [NASA-CP-2365] p 57 N85-20361 optical telescope assembly p36 A85-15980 An evaluation of grease type ball bearing lubricants SPACEBORNE ASTRONOMY Effects of space environmental conditions on graphite operating in various environments Astronomers, Congress, and the Large Space epoxy composites p 36 ASS-15990 [NASA-TM-86480] p 38 N85-11239 Telescope p 54 A85-27973 Experimental measurements of matenal damping in free SMP A solid modeling program SPACEBORNE EXPERIMENTS fall with tunable excitation p20 A85-18692 [NASA-CR-172473] p8 N85-11570 A space station expenment on large antenna assembly Kinetics of oxygen interaction with matenals International cooperation and competition in space and measurement - A follow-on study [AIAA PAPER 85-0472] p 37 A85-19770 [GPO-38-001] p4 N85-11911 [IAF PAPER 84-58] p 41 A85-13017 Atomic oxygen surface interactions - Mechanistic study Power subsystem automation study Space as motivational propulsion — Shuttle Orbiter using ground-based facilities [NASA-CR-171213] p 33 N85-12299 related projects as educational tools [AIAA PAPER 85-0473] p 37 A85-19771 Selected tether applications in space An analysis of [IAF PAPER 84-407] p 51 A85-13259 Effect of neutron and proton irradiation on some five selected concepts Material sciences in space p 36 A85-13500 properties of Kapton p37 A85-21508 [NASA-CR-171222] p 55 N85-12921 European retnevable earner (Eureca) and evolutionary Catalytic surface effect on ceramic coatings for an Autonomous momentum management for space station, space earner for microgravity. Earth observation and aeroassisted orbital transfer vehicle p 38 A85-29730 exhibit A technology demonstration p 55 N85-11032 Space Station truss structures and construction [NASA-CR-171256] p 33 N85-12933 SPACEBORNE LASERS considerations Regenerative fuel cell energy storage system for a low Active vibration control for lasers and spacecraft [NASA-TM-86338] p 15 N85-15796 Earth orbit space station p 21 A85-22584 SPACECRAFT CONTAMINATION [NASA-CR-174802] p 47 N85-13371 SPACEBORNE TELESCOPES A review of contamination issues associated with an Perspectives on energy storage wheels for space station Construction of large precision reflectors using the Aft orbiting Space Station external environment application p47 N85-13860 Cargo Gamer p38 A85-24703 Space Power [IAF PAPER 84-389] p2 A85-13244 Space environment simulation to test satellite thermal [NASA-CP-2352] p 56 N85-13880 Deployable optical systems, Proceedings of the Meeting, control coatings, volume 1 Space station power system p33 N85-13881 Los Angeles, CA, January 18.19, 1983 [CERT-4128-VOL-1] p 16 N85-17012 Thermal management technology status p53 A85-22576 Space environment simulation to test satellite thermal p 14 N85-13895 Deployable reflector configurations — for space control coatings Volume 2 Annex 1 Space Station truss structures and construction telescope p2 A85-22577 [ESA-CR(P)-1870-VOL-2] p 16 N85-17013 considerations Design concepts for reflector antenna structures Space environment simulation to test satellite thermal [NASA-TM-86338] p 15 N85-15796 p 7 A85-22579 control coatings Volume 2 Annexes 2, 3, 4 NASA OAST perspective p5 N85-16990 Survey of deployable antenna concepts [ESA-CR(P)-1870-VOL-3] p 16 N85-17014 Active cooling requirements for propellant storage p 10 A85-23663 Analysis of Nonvolatile Residue (NVR) from spacecraft p48 N85-17004 SPACECRAFT ANTENNAS systems Characterization of heat transfer in nutnent matenals Large spaceborne antenna reflectors using inflatable [NASA-TM-86184] p 39 N85-17019 — space flight feeding space ngidized structures p 12 N85-14004 SPACECRAFT CONTROL [NASA-CR-171841] p 56 N85-17551 Elastic dispersion effects on dynamics and control of The decentralized control of large flexible space large modular antennas -- spacecraft antennas structures p 17 A85-10071 Commercial space Europe should have independent Comparing attitude control effectiveness for actuators strategy p 5 N85-19205 p26 N85-14019 Interleaved array antenna technology development on two bodies of a six body model of a flexible spacecraft West Europe report Science and technology [NASA-CR-171845] p 34 N85-19326 with that for actuators restncted to a single body [JPRS-WST-85-008] p 57 N85-20174 SPACECRAFT CABIN ATMOSPHERES p 17 A85-11086 Applications of Tethers in Space, volume 1 Human response to vibroacoustic environments of Developing sensitivity coefficients for a state vanable [NASA-CP-2364] p 57 N85-20339 space vehicles model of a flexible spacecraft with modular attitude Environment definition, small particles, diameter less [NASA-TM-86316] p 54 N85-10789 control p17 A85-11087 than or equal to 1 MM p 40 N85-21223 SPACECRAFT CHARGING A signed switching time bang-bang attitude control law Advanced research and technology programs for When spacecraft get charged up, they have minds of for fine pointing of flexible spacecraft p 19 A85-13893 advanced high-pressure oxygen-hydrogen rocket their own p 53 A85-24787 Closed-form solutions for feedback control with terminal propulsion A plan for controlling electrostatic discharges on constraints p 20 A85-18331 [NASA-TM-66969] p 50 N85-21231 geosynchronous spacecraft p 32 A85-26685 High precision active nutation control of a momentum SPACE SURVEILLANCE SPACECRAFT COMMUNICATION biased spacecraft with flexible appendages EASCON '83, Proceedings of the Sixteenth Annual Attitude control system and communications payload for p20 A85-18337 Electronics and Aerospace Conference and Exposition, an amateur solar sail spacecraft Computer aided design of multiple input/output control Washington, DC, September 19-21,1983 [IAF PAPER 84-363] p 29 A85-13224 systems for multibody flexible Space Station p51 A85-14426 Sky-hooks, fish-warmers and hub-caps - Milestones in [AIAA PAPER 85-0223] p7 A85-19600 SPACE TRANSPORTATION satellite communications — technological development Analytical and expenmental research in large space TOS and AMS - America's new capabilities in space p 32 A85-25101 structures control transportation — Transfer Orbit Stages and Apogee and Intelsat's twentieth anniversary - Two decades of [AIAA PAPER 85-0356] p 21 A85-19693 Maneuvenng Stages innovation in global communications p 54 A85-26369 Deployable optical systems. Proceedings of the Meeting, [IAF PAPER 84-220] p 51 A85-13141 The real world The user p 32 N85-11017 Los Angeles, CA, January 18, 19, 1983 p53 A85-22576 The challenge of advanced space transportation and SPACECRAFT COMPONENTS Active vibration control for lasers and spacecraft propulsion systems Damping synthesis for a spacecraft using substructure p 21 A85-22584 [IAF PAPER 84-310] p 44 A85-13191 and component data [CRC-1365] p24 N85-12082 Structural control research at AFOSR Orbit on demand - In this century if pushed Analysis of Nonvolatile Residue (NVR) from spacecraft p 21 A85-22585 p46 A85-24788 systems Active control technology development at NASA Applications of Tethers in Space, volume 1 [NASA-TM-66184] p 39 N85-17019 p22 A85-22586 [NASA-CP-2364] p 57 N85-20339 SPACECRAFT CONFIGURATIONS Structural control research and expenments at Report of the Transportation Panel Economics of permanent polar platforms (PPP) for global NASA/LaRC p 22 A85-22587 p 57 N85-20364 monitonng Integratable propulsion systems for the Space Station SPACE TRANSPORTATION SYSTEM [IAF PAPER 84-226] p2 A85-13144 p 46 A85-23393 Large space structures ground and flight progress Vehicle/engine integration — orbit transfer vehicles Poles and transmission zeros of flexible spacecraft [IAF PAPER 84-388] p 13 A85-13243 p48 N85-17008 control systems p 22 A85-26433

A-16 SUBJECTINDEX SPACECRAFT TRAJECTORIES

Adaptive modal control of structural dynamic systems Characterization of heat transfer in nutrient materials Engineenng model system study for a regenerative fuel using recursive lattice filters p 23 AB5-2643S — space flight feeding cell Study report A user's guide to the Flexible Spacecraft Dynamics and [NASA-CR-171841) p 56 N85-17551 [NASA-CR-174801] p 47 N85-16292 Control Program SPACECRAFT EQUIPMENT Opening up the future in space with nuclear power [NASA-TM-87389] p 24 N85-12586 Space Station remote manipulator requirements [DE85-002411J p49 N85-20862 Disturbance propagation in structural networks, control definition SPACECRAFT PROPULSION of large space structures p 26 N85-14856 [AIAA PAPER 85-0029] p 41 ASS-19466 Brpropellant propulsion in the new generation of Summary presentation of the Constellations Panel SPACECRAFT INSTRUMENTS satellites and upper stages- The role of BPD Drfesa-Spazn p57 N85-20359 The NASA MLA program — Mutepectral Linear Array in this field - Manufacturing facilities and technology Trie Satellite sad p 49 N85-20376 p52 A85-17573 p43 ASS-12519 Stability analysis of flexible spaceraft with PID SPACECRAFT LAUNCHING The challenge of advanced space transportation and controller Cost effective launch technology for communications propulsion systems satellites [CRC-1372] p28 N85-21247 [IAF PAPER 84-310] p 44 A85-13191 SPACECRAFT DESIGN [IAF PAPER 84-04] p50 A85-12979 Design and benefits of pulsed MPD thruster orbit transfer SPACECRAFT MAINTENANCE Dynamic isolation of a spacecraft science platform via vehicles • p 44 ASS-16448 momentum compensation p 17 ASS-11082 Satellite servicing A business opportunity? Optimal electric propulsion orbit transfer vehicle design Application of modal synthesis concepts to spacecraft p55 N85-11056 design verification p 17 A85-12455 Space based OTV servicing p 56 N85-17010 and operational effectiveness [AIAA PAPER 85-0431] p 45 A85-19744 Lay-out of a re-usable re-entry vehicle required in a future SPACECRAFT MANEUVERS European low earth orbit scenario Closed-form solutions for feedback control with terminal Integratable propulsion systems for the Space Station [IAF PAPER 84-06] p 50 AB5-12981 constraints p 20 ASS-18331 p46 A85-23393 Design consideration of space construction facility Optimal simultaneous structural and control design of Design of a nuclear electric propulsion orbital transfer [IAF PAPER 84-26] p 6 A85-12992 maneuvenng flexible spacecraft p7 ASS-18338 vehicle p 46 A85-23394 Impacts of life support system on space station design SPACECRAFT MODELS Nuclear reactors for space power p 46 A85-24793 [IAF PAPER 84-166] p6 A85-13100 Developing sensitivity coefficients for a state variable On the potential performance of non-nuclear interstellar TOS and AMS - America's new capabilities in space model of a flexible spacecraft with modular attitude arks p 46 A85-25828 transportation — Transfer Orbit Stages and Apogee and control p17 A85-11087 OTV propulsion tecnology programmatic overview Maneuvering Stages SPACECRAFT MODULES p48 N85-16997 Modular expenmental platform for science and [IAF PAPER 84-220] p 51 A85-13141 Drives and benefits overview p56 N85-16998 Variable geometry truss and its application to deployable applications p11 N85-11031 truss and space crane arm SPACECRAFT MOTION Vehicle/engine integration — orbit transfer vehicles [IAF PAPER 84-394] p 10 A85-13248 Stability of the stationary motions of a tethered system p48 N85-17008 Space station/space platform system design of two bodies in orbit under the effect of gravitational and Orbital transfer vehicle propulsion issues considerations p7 A85-14429 aerodynamic forces p20 A85-15254 p48 N85-17009 Optimal simultaneous structural and control design of The development of a frequency method for the Design study of an integrated aerobraking orbital transfer maneuvering flexible spacecraft p7 A85-18338 mathematical modeling of the motion of an elastic space vehicle Modular computer system cuts spacecraft simulation vehicle p20 A85-17054 [NASA-TM-58264] p9 N85-21262 costs p 10 A85-18435 Equations of motion governing the deployment of a SPACECRAFT RADIATORS The low cost development, test and production of a flexible linkage from a spacecraft Space station thermal control - An interview with Robert commercial STS upper stage TOS [AIAA PAPER 85-0023] p 20 AS5-19462 Haslett p 13 A85-18321 [AIAA PAPER 85-0313] p 45 A85-19660 A user's guide to the Flexible Spacecraft Dynamics and Thermal storage analysis for large manned space Integrated Power and Attitude Control Systems for Control Program platforms Space Station [NASA-TM-87389] p 24 N85-12586 [AIAA PAPER 85-0066) p 14 A85-19493 [AIAA PAPER 85-0358] p 31 ASS-19695 SPACECRAFT ORBITS The liquid droplet radiator - an ultralightweight heat Optimal electric propulsion orbit transfer vehicle design Integratable propulsion systems for the Space Station reiection system for efficient energy conversion in space and operational effectiveness p46 A85-23393 p 15 N85-13900 [AIAA PAPER 85-0431 ] p 45 A85-19744 Summary presentation of the Constellations Panel Heat reiection working group synopsis p 57 N85-20359 Design of a nuclear electric propulsion orbital transfer p 15 N85-13906 vehicle p 46 A85-23394 Assessment of satellite collision hazards by simulated SPACECRAFT SHIELDING Orbit on demand - In this century if pushed sampling in space p 40 N85-21195 Parametric analysis SOC meteoroid and debns p46 A85-24788 SPACECRAFT PERFORMANCE protection p 16 N85-21209 Spacecraft systems engineering and geometry Chemical nonequilibnum effects on flowfields for modelling - The ESABASE-MATVIEW approach aeroassisted orbital transfer vehicles p53 A85-21831 SPACECRAFT STABILITY p8 A85-27696 SPACECRAFT POWER SUPPLIES Stability of the stationary motions of a tethered system Multicrrtical optimization of a large space structure Design and technology trends on large solar arrays for of two bodies in orbit under the effect of gravitational and p 11 A85-28489 space stations aerodynamic forces p 20 A85-15254 Modular expenmental platform for science and [IAF PAPER 84-37] p 43 A85-13000 Flexural vibration of gravity-stabilized, structurally applications pit N85-11031 Environmentally-induced voltage limitations in large damped, large flexible satellites p 22 A85-26434 External tank aft cargo earner p8 N85-11050 space power systems p31 A85-18584 Effect of aerodynamic moment on the regime of the SMP A solid modeling program Solar concentrator for space power generation gravity gradient stabilization of the Salyut-6 - Soyuz orbital [NASA-CR-172473] p8 N85-11570 [AIAA PAPER 85-0164] p 45 A85-19561 system p 23 A85-28488 Space power management and distribution status and Integrated Power and Attitude Control Systems for Multicntical optimization of a large space structure trends p47 N85-13896 Space Station p 11 A85-28489 Orbital transfer vehicle propulsion issues [AIAA PAPER 854)358] p 31 A85-19695 The dynamics of the attitude control and stabilization p48 N85-17009 Circuit transients due to negative bias arcs on a high systems of spacecraft with a controlled gravity gradient Space based OTV servicing p 56 N85-17010 voltage solar array in low earth orbit stabilizer p23 A85-28903 Vibration analysis of a multipurpose platform [AIAA PAPER 85-0385] p 45 A85-19714 Summary presentation of the Constellations Panel [NAL-TR-603] p 27 N85-18078 Nuclear reactors for space power p 46 A85-24793 p57 N85-20359 Efficient structures for geosynchronous spacecraft solar Solar cells for tomorrow's spacecraft Application Number 3 Using tethers for attitude arrays p 54 A85-24794 control p27 N85-20373 [NASA-CR-174448] p 12 N85-19004 SPACECRAFT STRUCTURES Sky-hooks, fish-warmers and hub-caps - Milestones in Design study of an integrated aerobraking orbital transfer Application of damping to spacecraft structures satellite communications — technological development vehicle p20 A85-15992 p32 A85-25101 [NASA-TM-58264] p9 N85-21262 Advanced analysis methods for spacecraft composite Deployable folded antenna apparatus Unlimited power for our space vehicles structures p 37 A85-15993 [AD-D011503] p 12 N85-21495 p46 A85-25796 Formex configuration processing in structural Debns impact on Earth-orbiting spacecraft The maximum efficiency of an isolated solar energy engmeenng — Book p 14 ASS-20916 p59 N85-22234 conversion device in space p 46 A85-25797 Deployable optical systems, Proceedings of the Meeting, SPACECRAFT DOCKING Space Power Los Angeles, CA, January 18, 19, 1983 Evaluation of OMV ranging and docking systems [NASA-CP-2352] p 56 N85-13880 p53 A85-22576 p42 N85-22230 Space station power system p 33 N85-13881 Structural control research at AFOSR SPACECRAFT ENVIRONMENTS Missions/planning panel p 4 N85-13886 p 21 A85-22585 Thermal analytical model of btdimenstonal and Potential of flywheels for spacecraft energy storage Torsional vibration of booms with open cross section unidimensional structural elements in a space p33 N85-13890 caused by unidirectional radiant heating environment p22 A85-26350 Dynamic power systems for power generation [IAF PAPER 84-399] p 13 A85-13252 Measurement of the inertia! constants of a rigid or flexible p33 N85-13892 Dielectric material in the space environment structure of arbitrary share through a vibration test p37 A85-24672 Space power management and distribution status and [NASA-TM-77557] p 24 N85-11381 Human response to vibroacoustic environments of trends p47 N85-13896 Influence of thermal cycling on the behavior of CFRP space vehicles The liquid droplet radiator - an ultralrghtweight heat material for space structures p 39 N85-14013 [NASA-TM-86316] p 54 N85-10789 rejection system for efficient energy conversion in space ACOSS 17 (Active Control of Space Structures) An evaluation of grease type ball beanng lubricants p 15 N85-13900 [AD-A150007] p28 N85-21253 operating in various environments Heat reiection working group synopsis SPACECRAFT TRAJECTORIES [NASA-TM-86480] p 38 N8S-11239 p 15 N85-13906 Trajectory analysis of radiative heating for planetary Thermal management technology status Environmental interactions working group report missions with aerobraking of spacecraft p 14 N85-13895 p5 N85-13908 p 14 A85-21829

A-17 SPACELAB SUBJECT INDEX

SPACELAB STRINGS Elastic waves propagation in bounded penodic Space exploitation - Spacelab an easy approach for Stability of the rotation of a body suspended by means structures — for modeling large space structures developing countnes Prospectves and suggestions by of a system of rods connected in senes [IAF PAPER 84-395] p 19 A85-13249 Aentalia p 1 A85-12502 p23 A85-28906 Active vibration control for lasers and spacecraft Spacelab Hitchhiker, a quick reaction earner STRUCTURAL ANALYSIS p 21 A85-22584 [AIAA PAPER 85-0504] p 53 A85-19795 Thermal analytical model of bidimensional and Flexural vibration of gravity-stabilized, structurally SPACELAB PAYLOADS unidimensional structural elements in a space damped, large flexible satellites p 22 A85-26434 Space station related investigations in Europe environment LOG balancing and reduced LOG compensation of [IAF PAPER 84-28] p 50 A85-12994 [IAF PAPER 84-399] p 13 A85-13252 symmetric passive systems — Linear Quadratic SPACETENNAS Advanced analysis methods for spacecraft composite Gaussian p23 A85-27238 Deployable optical systems, Proceedings of the Meeting, structures p37 A85-15993 Definition of ground test for Large Space Structure (LSS) control verification, appendix G p 25 N85-13845 Los Angeles, CA, January 18,19,1983 Mass properties analysis and control of advanced space The Shock and Vibration Digest, volume 16, no 11 p53 A85-22576 structures through computerized integration with design [AD-A148466] p 16 N85-17382 Design concepts for reflector antenna structures and structural analysis Modelling and identification of the structural properties p7 A85-22579 [SAWE PAPER 1527] p 13 A85-18812 Survey of deployable antenna concepts " of an astromast Generalized transform methods based finite element p 10 A85-23663 [CRC-1374] p 12 N85-18352 methodology - Thermal/structural dynamic applications Keynote address p27 N85-18378 SPECTRAL METHODS [AIAA PAPER 85-0155] p 14 A85-19553 Spectral characteristics of radar echoes from STRUCTURAL WEIGHT Geometrically nonlinear analysis of space frames by an aircraft-dispensed chaff p 23 A85-26606 Minimum weight design of truss structures with incremental iterative technique p 14 A85-19895 SPECTROMETERS geometnc nonlinear behavior p 10 ASS-18694 Analytical thermal formulations for antenna dishes — SCATHA (spacecraft charging at high altitudes) plasma STRUTS satellite antennas p 15 N85-14017 interaction expenment SC-3 high energy particle Passive Orbital Disconnect Strut (PODS 3) structural test spectrometer; SC-8 energetic ion composition Reduction method for thermal analysis of complex program expenment aerospace structures [NASA-CR-177325] p 16 N85-17020 [AD-A149728] p 35 N85-21252 [NASA-TP-2373] p 15 N85-16066 SUBSTRATES Investigation of welded interconnection of large area SPECULAR REFLECTION Vibration analysis of a multipurpose platform wraparound contacted silicon solar cells Deployable reflector antennas - Mechanical design of [NAL-TR-803] p 27 N85-18078 [NASA-CR-174438] p 39 N85-19519 the reflective surface STRUCTURAL DESIGN SUBSTRUCTURES [IAF PAPER 84-393] p6 A85-13247 Design preparations for large space structures [IAF PAPER 84-392] p 35 A85-13246 Damping synthesis for a spacecraft using substructure SPINNING SOLID UPPER STAGE and component data Some applications of direct adaptive control to large IRIS Spinning Stage - A pengee stage for satellites up [CRC-1365] p24 N85-12082 structural systems p 19 A85-13636 to 900 kg to be launched from the Space Shuttle with SUPERCONDUCTORS the IRIS system p 43 A85-12520 Graphite epoxy structure of the Space Telescope's Report of the Technology and Test Panel STABILITY optical telescope assembly p36 A85-15980 p 57 N85-20370 Inorganic composites for space applications Deployable optical systems, Proceedings of the Meeting, SUPERHIGH FREQUENCIES p38 N85-11047 Los Angeles, CA. January 18. 19, 1983 Electncal consequences of mechanical antenna Qualitative results for distributed systems with discrete p53 A85-22576 charactenstics p 33 N85-14006 damping and stiffness with application to control Structural control research at AFOSR SURFACE GEOMETRY [AD-A145525] p 24 N85-11382 p 21 A85-22585 Deployable reflector antennas - Mechanical design of STABILIZATION Space frame design, development and optimization of the reflective surface Stability analysis of flexible spaceraft with PID antenna platform structure for a mobile 3D radar [IAF PAPER 84-393] p6 A85-13247 controller p8 A65-24908 SURFACE REACTIONS [CRC-1372] p28 N85-21247 Structural design and thermal stability of TELE-X Atomic oxygen surface interactions - Mechanistic study STABILIZED PLATFORMS antenna tower p15 N85-14016 using ground-based facilities Dynamic isolation of a spacecraft science platform via Space Station truss structures and construction [AIAA PAPER 85-0473] p 37 A85-19771 momentum compensation p 17 A85-11082 considerations SURVEYS STATE VECTORS [NASA-TM-86338] p 15 N85-15796 Survey of deployable antenna concepts Principal component analysis of flexible systems - Passive Orbital Disconnect Strut (PODS 3) structural test p10 A85-23663 Open-loop case p7 A85-16648 program SUSPENDING (HANGING) Stability of the rotation of a body suspended by means STATIONKEEPING [NASA-CR-177325] p 16 N85-17020 of a system of rods connected in senes The investigation of tethered satellite system STRUCTURAL DESIGN CRITERIA p23 A8S-28906 dynamics The strongest structures with macrostiffness [NASA-CR-171278] p 26 N85-15772 constraints p 10 A85-12933 SYNCHRONOUS PLATFORMS Vibration analysis of a multipurpose platform STEADY STATE Structures and matenals technologies for spacecraft systems An overview p36 A85-15977 [NAL-TR-803] p 27 N85-18078 Identification of vibration parameters of flexible Optimal simultaneous structural and control design of SYNCHRONOUS SATELLITES structures p 27 N85-18360 maneuvenng flexible spacecraft p7 ASS-18338 A case for Gohrem - Geosynchronous orbit high STIFFNESS Minimum weight design of truss structures with resolution earth monitonng pSO A85-10261 The strongest structures with macrostiffness geometnc nonlinear behavior p 10 A85-18694 Mass optimisation of telecommunications satellites constraints p 10 A85-12933 Large-diameter astromast development [IAF PAPER 84-230] p 13 A85-13146 Modelling and identification of the structural properties [NASA-CR-171201] p11 N85-12200 of an astromast Efficient inclination control for geostationary satellites Space Transportatioin System (STS) propellant [AIAA PAPER 85-0216] p 21 A85-19595 [CRC-1374] p 12 N85-18352 scavenging system study Volume 3 Cost and work A plan for controlling electrostatic discharges on STIFFNESS MATRIX breakdown structure-dictionary geosynchronous spacecraft p 32 A85-26685 Evaluation of efficiently computed exact vibration [NASA-CR-171850-VOL-3] p 49 N85-20002 Debris in the geostationary orbit ring, the endless characteristics of space platforms assembled from stayed STRUCTURAL ENGINEERING shooting gallery The necessity for a disposal policy columns p 13 A85-12884 Formex configuration processing in structural p58 N85-21214 STIRLING CYCLE engmeenng — Book p 14 A85-20916 Nuclear-electric power in space p30 A85-15812 STRUCTURAL MEMBERS SYNTHETIC APERTURE RADAR Structural aspects of SAR antenna for Japanese Earth Dynamic power systems for power generation Development of advanced composite tubular structures Resources Satellite 1 p 12 N85-14007 p 33 N85-13892 for antenna reflector p 10 A85-24817 Technology for the ERS-1 SAR antenna STORABLE PROPELLANTS Research on large, highly accurate, inflatable p 33 N85-14008 Space Transportation System (STS) propellent reflectors scavenging system study Volume 1 Technical report [AD-A145080] p11 N85-10099 Interleaved array antenna technology development [NASA-CR-171848-VOL-1] p 49 N85-20000 STRUCTURAL RELIABILITY [NASA-CR-171845] p 34 N85-19326 Space Transportation System (STS) propellant Structural control research and experiments at SYSTEM FAILURES scavenging system study Volume 2 Supporting research NASA/LaRC p 22 A85-22587 Number and placement of control system components and technology report STRUCTURAL STABILITY considenng possible failures — for large space [NASA-CR-171849-VOL-2] p 49 N85-20001 Minimum weight design of truss structures with structures p 19 A85-13634 geometnc nonlinear behavior p 10 A85-18694 STORAGE TANKS An investigation dunng the system test phase of the Section 1 Method of determining mode shapes and Passive Orbital Disconnect Strut (PODS 3) structural test GOES spacecraft p32 A85-28126 natural frequencies of the NASA unmodified test structure program SYSTEMS ANALYSIS Section 2 Continuous beam closed from solution to the [NASA-CR-177325] p 16 N85-17020 Pnnapal component analysis of flexible systems - NASA-LSS astromast torsional vibration, appendix E Open-loop case p7 A85-16648 STRAIN ENERGY METHODS p25 N85-13844 Minimum weight design of truss structures with STRUCTURAL VIBRATION Development and application of new technologies in geometnc nonlinear behavior p 10 ASS-18694 Alleviation of observation spillover in continuous ESA's Olympus programme p 3 A85-27695 STRESS ANALYSIS structures p 17 A85-12434 Spacecraft systems engmeenng and geometry Space frame design, development and optimization of Continuum modelling of damping in large space modelling - The ESABASE-MATVIEW approach antenna platform structure for a mobile 3D radar structures p 18 A85-12478 p8 A8S-27696 p8 A85-24908 Dynamical modelling of a gravity-loaded rectangular Preliminary analysis of space mission applications for STRESS RELAXATION plate as a test configuration for attitude control of large electromagnetic launchers Effects of residual stresses in polymer matrix space structures [NASA-CR-174067] p 47 N85-12071 composites p35 A85-12395 [IAF PAPER 84-391] p 18 A85-13245 TSS Satellite overview pS N85-20343

A-18 SUBJECTINDEX THERMOMECHANICAL TREATMENT

SYSTEMS ENGINEERING An economic analysis of humans and machines for Propellant transfer Tethered depot Space station/space platform system design space construction P48 N85-17006 considerations p 7 A85-14429 [IAF PAPER 84-232] p 51 A85-13148 Applications of Tethers in Space, volume 1 The systems background for satellite commumcatjon TEMPERATURE CONTROL [NASA-CP-2364] p57 N85-20339 antennas p32 A85-23652 Space station thermal control - An interview with Robert Electrodynarrec interactions p 34 N85-20348 A methodology for organizing performance requirements Haslett p 13 A85-1B321 Summary presentation of the Electrodynamics for complex dynamical systems p3 A8S-25J17 Thermal management technology status Interactions Panel p 34 N85-20356 p 14 N85-I3895 Dynamics and controls working group summary Summary presentation of the Constellations Panel p26 N8S-13854 Active cooling requirements for propellant storage p57 N85-20359 p48 N85-17004 The investigation of tethered satellite system Summary presentation of the technology and test TEMPERATURE EFFECTS dynamics panel p 57 N85-20360 Inorganic composites for space applications [NASA-CR-171278] p 26 N85-15772 Report of the Transportation Panel p38 N85-11047 p57 N85-20364 SYSTEMS INTEGRATION Evaluation and prediction of long-term environmental Report of the Constellations Panel p 27 N85-20368 Integrated Power and Attitude Control Systems for effects of nonmetallic materials The Satellite sail p49 N85-20376 Space Station [NASA-CR-171353] p 39 N85-19137 A functional vehicle for autonomous mobile robot [AIAA PAPER 85-0358] p 31 A85-19695 Investigation of welded interconnection of large area research SYSTEMS MANAGEMENT wraparound contacted silicon solar cells [AD-A150052] p 42 N85-21666 A methodology for organizing performance requirements [NASA-Cfl-174438] p 39 N85-19519 TETHERLINES for complex dynamical systems p3 A85-25117 TENSILE STRENGTH Tether fundamentals p 57 N85-20345 SYSTEMS SIMULATION Influence of simulated space environment on the Pultrusion process for fabrication of tethers (preliminary Satellite grasping manipulator system behavior of carbon-fiber-reinforced plastics with +, -45 concepts) p40 N85-20371 [IAF PAPER 84-371 ] p 41 A85-13229 pty orientations II p36 A85-14163 Applications of Tethers in Space Simplified planar model of ground test verification TENSILE STRESS [NASA-CP-2366] p 59 N85-21659 structure, appendix B p 25 N85-13841 Tether fundamentals p 57 N85-20345 THERMAL ANALYSIS Elimination of uncontrollable rigid body mode, appendix TERMINAL GUIDANCE Thermal analytical model of bidimensional and C p25 N85-13842 A rectilinear guidance strategy for short orbital unidimensional structural elements in a space transfers p 52 A85-15509 SYSTEMS STABILITY environment Closed-form solutions for feedback control with terminal Stability of a ring of connected satellites [IAF PAPER 84-399] p 13 A85-13252 constraints p 20 ASS-18331 [IAF PAPER 84-342] p 18 A85-13206 Heat conduction problems in large space structure TEST FACILITIES [IAF PAPER 84-400] p 13 A85-13253 The dimensional stability of advanced composite NASA-VCOSS dynamic test facility antenna reflectors Analytical and test evaluation — Reduction method for thermal analysis of complex [NASA-TM-86491] p 27 N85-18998 satellite antennas p39 N85-14014 aerospace structures Ground test experiment for large space structures [NASA-TP-2373] p 15 N85-16066 [NASA-TM-86489] p9 N85-19013 THERMAL CONTROL COATINGS TEST VEHICLES Space environment simulation to test satellite thermal A functional vehicle for autonomous mobile robot control coatings, volume 1 research [CERT-4128-VOL-1] p 16 N85-17012 TAPES [AD-A150052] p 42 N85-21666 Space environment simulation to test satellite thermal Evaluation and prediction of long-term environmental TETHERED SATELLITES control coatings Volume 2 Annex 1 effects of nonmetallic materials Stability of a nng of connected satellites [ESA-CR(P)-1870-VOL-2] p 16 N85-17013 [NASA-CR-171353] p 39 N85-19137 [IAF PAPER 84-342] p 18 A85-13206 Space environment simulation to test satellite thermal TECHNOLOGICAL FORECASTING Applications of space tethers control coatings Volume 2 Annexes 2, 3, 4 Synergy in space - Man-robot cooperation [IAF PAPER 84-436] p 51 A85-13276 [ESA-CR(P)-1870-VOL-3] p 16 N85-17014 p 41 A85-20400 Tethered propellant resupply technique for space THERMAL CYCLING TESTS Orbit on demand - In this century if pushed stations Design preparations for large space structures p 46 A85-24788 [IAF PAPER 84-442] p 44 A85-13282 [IAF PAPER 84-392] p 35 A85-13246 Space - The future of mankind p 3 A85-25697 Stability of the stationary motions of a tethered system Influence of thermal cycling on the behavior of CFRP TECHNOLOGY ASSESSMENT of two bodies in orbit under the effect of gravitational and material for space structures p 39 N85-14013 Cost effective launch technology for communications aerodynamic forces p20 A85-15254 THERMAL ENERGY satellites On dynamical formulations of a tethered satellite system Electrodynamic interactions p 34 N85-20348 [IAF PAPER 84-04] p 50 A85-12979 with mass transport THERMAL ENVIRONMENTS NASA's mobile satellite communications program, [AIAA PAPER 85-0117] p 21 A85-19529 Thermal management technology status ground and space segment technologies Proceedings of a Workshop on Applications of Tethers p 14 N85-13895 [IAF PAPER 84-84] p 29 A85-13040 in Space, Executive Summary THERMAL EXPANSION Onentatron and trends in European technology — space [NASA-CR-171195] p 55 N85-12075 Effects of residual stresses in polymer matrix programs Proceedings of a Workshop on the Applications of composites p 35 A85-12395 [IAF PAPER 84-377] p2 A85-13233 Tethers in Space, Volume 1 An analytical investigation of shape control of large Sky-hooks, fish-warmers and hub-caps - Milestones in [NASA-CR-171196] p 55 N85-12076 space structures by applied temperatures satellite communications — technological development Proceedings of a Workshop on Applications of Tethers p 14 A85-25145 p32 A85-25101 in Space, Volume 2 The dimensional stability of advanced composite CRC handbook of space technology Status and [NASA-CR-171197] p55 N85-12077 antenna reflectors Analytical and test evaluation — Projections p3 A85-28275 The investigation of tethered satellite system satellite antennas P 39 N85-14014 Office of Technology Assessment p4 N85-10872 dynamics THERMAL INSTABILITY Doing business in space How to get there from here [NASA-CR-171278] p 26 N85-15772 Torsional vibration of booms with open cross section p55 N85-11057 Applications of Tethers in Space, volume 1 caused by unidirectional radiant heating Preliminary analysis of space mission applications for [NASA-CP-2364] p 57 N85-20339 P22 A85-26350 electromagnetic launchers Tethered satellite system project overview THERMAL PROTECTION [NASA-CR-174067] p 47 N85-12071 p5 N85-20341 Catalytic surface effect on ceramic coatings for an Missions/planning panel p4 N85-13886 TSS Satellite overview p5 N85-20343 aeroassisted orbital transfer vehicle p 38 A85-29730 Technology and test p57 N85-20353 Satellite module design p 9 N85-20344 Process for prepanng essentially colorless polyimide film TECHNOLOGY TRANSFER Tether fundamentals p 57 N85-20345 containing phenoxy-lmked diammes Proceedings of a Workshop on Applications of Tethers Science Applications, part 1 p 5 N85-20346 [NASA-CASE-LAR-13353-1] p 40 N85-20128 in Space, Executive Summary Science Applications, part 2 p 6 N85-20347 THERMAL STABILITY [NASA-CR-171195] p 55 N85-12075 Technology and test p57 N85-20353 Structural design and thermal stability of TELE-X Dynamics and controls working group summary Summary presentation of the technology and test antenna tower p 15 N85-14016 p26 N85-13854 panel p 57 N85-20360 THERMAL STRESSES TECHNOLOGY UTILIZATION Applications of Tethers in Space, volume 2 An analytical investigation of shape control of large Design consideration of space construction facility [NASA-CP-2365] p 57 N85-20361 space structures by applied temperatures [IAF PAPER 84-26] p6 A85-12992 Report of the Electrodynamic Interactions Panel p 14 A85-25145 Report of the student working group to the panel on p 34 N85-20363 THERMODYNAMIC PROPERTIES satellite communications — Space Applications Board Report of the Technology and Test Panel Analytical thermal formulations for antenna dishes — Crestwood 1982 Summer Study p 30 A85-14430 p 57 N85-20370 satellite antennas p 15 N85-14017 Space - The future of mankind p 3 A85-25697 Pultmston process for fabrication of tethers (preliminary Report of the Technology and Test Panel Development and application of new technologies in concepts) p40 N85-20371 p57 N85-20370 ESA's Olympus programme p 3 A85-27695 Instrumentation for Application Number 1 Mass THERMOELASnCfTY Applications of Tethers in Space spectrometnc analysis of the boundary layer associated Thermal analytical model of bidimensional and [NASA-CP-2386] p 59 N85-21659 with the tethered satellite p 58 N85-20372 unidimensional structural elements in a space TELECOMMUNICATION Application Number 3 Using tethers for attitude environment Some results of the MSAT phase B studies and their control p 27 N85-20373 [IAF PAPER 84-399] p 13 ASS-13252 impact on system design Applications of Tethers in Space Thermoelastic behaviour of space structures in [IAF PAPER 84-89] p 1 ASS-13045 [NASA-CP-2366] p 59 N85-21659 composite materials TELEOPERATORS TETHERING [IAF PAPER 84-404] p 35 A85-13257 Utilization of a teleoperated service vehicle for Selected tether applications in space An analysis of THERMOMECHANICAL TREATMENT spacecraft servicing five selected concepts Continuous graphite/polysulfone RP thermoforming for [IAF PAPER 84-48] p 1 ASS-13009 [NASA-CR-171222] p 55 N85-12921 largo space structure construction p 36 ASS-15638

A-19 THIN FILMS SUBJECTINDEX

THIN FILMS Variable geometry truss and its application to deployable LOG balancing and reduced LOG compensation of Research on large, highly accurate, inflatable truss and space crane arm symmetric passive systems — Linear Quadratic reflectors [IAF PAPER 84-394] p 10 A85-13248 Gaussian p 23 A85-27238 [AD-A145080] p11 N85-10099 Optimal design of a passive vibration absorber for a Modular design attitude control system THRUST truss beam p 19 A85-13638 [NASA-CR-171182] p 24 N85-10098 Summary presentation of the Electrodynamics Continuous graphite/polysulfone RP thermoforming for Experiments m control of flexible structures with Interactions Panel p 34 N85-20356 large space structure construction p 36 A85-15638 uncertain parameters p 24 N85-13837 Report of the Electrodynamic Interactions Panel VIBRATION MODE Minimum weight design of truss structures with p34 N85-20363 geometric nonlinear behavior p 10 A85-18694 The improvement of free-mode methods in component THRUSTOBS mode synthesis techniques and its accuracies Effects of member imperfections on the behavior of Design and benefits of pulsed MPD thruster orbit transfer p 17 A85-12442 space trusses p 11 N85-11363 vehicles p44 A85-16448 Evaluation of efficiently computed exact vibration TIME LAG Conceptual design for scaled truss antenna flight charactenstics of space platforms assembled from stayed Orbit-on-demand vehicles - Mission possible, but expenment columns p 13 A85-12884 one-day turnaround? p 53 A85-24790 [NASA-TM-85804] p4 N85-12932 VISCOELASTIC DAMPING TIME OPTIMAL CONTROL Space Station truss structures and construction Application of damping to spacecraft structures A signed switching time bang-bang attitude control law considerations p20 A85-15992 for fine pointing of flexible spacecraft p 19 ASS-13893 [NASA-TM-86338] p 15 N85-15796 VOLT-AMPERE CHARACTERISTICS TOPOLOGY Variable geometry truss concept Environmentally-induced voltage limitations in large Disturbance propagation in structural networks, control [REPT-614] p 12 N85-21697 space power systems p31 A85-18584 of large space structures p 26 N85-14856 TURBOROCKET ENGINES TORQUE Aerojet advanced engine concept p48 N85-16999 Autonomous momentum management for the COG w planar Space Station [AIAA PAPER 85-0031] p 21 A85-19468 u WAVE DISPERSION Autonomous momentum management for space Elastc dispersion effects on dynamics and control of UNITED NATIONS station large modular antennas — spacecraft antennas International space programmes and policies [NASA-CR-174065] p 24 N85-12931 p26 N85-14019 p2 A85-20507 WAVE PROPAGATION Autonomous momentum management for space station, UNITED STATES exhibit A Elastic waves propagation in bounded periodic International cooperation and competition in space structures — for modeling large space structures [NASA-CR-171256] p 33 N85-12933 [GPO-38-001] p4 N85-11911 TORSION [IAF PAPER 84-395] p 19 A85-13249 UNMANNED SPACECRAFT Disturbance propagation in structural networks, control Modelling and identification of the structural properties An unmanned platform as an initial capability in space of an astromast of large space structures p 26 N85-14856 p52 A85-16305 [CRC-1374] p 12 N85-18352 WAVEGUIDES UPPER STAGE ROCKET ENGINES Technology for the ERS-1 SAR antenna TORSIONAL VIBRATION Bipropellant propulsion in the new generation of Torsional vibration of booms with open cross section p33 N85-14008 satellites and upper stages The role of BPD Difesa-Spazio Interleaved array antenna technology development caused by unidirectional radiant heating in this field - Manufacturing facilities and technology p 22 A85-26350 [NASA-CR-171845] p 34 N85-19326 p43 ASS-12519 TOWERS WAVELENGTH DIVISION MULTIPLEXING URBAN DEVELOPMENT Wavelength division multiplexing for future Space Station Structural design and thermal stability of TELE-X National Aeronautics and Space Administration antenna tower p 15 N85-14016 data systems p32 A85-25359 p4 N85-10871 TRAJECTORY ANALYSIS WEIGHT (MASS) USER MANUALS (COMPUTER PROGRAMS) Potential of flywheels for spacecraft energy storage Trajectory analysis of radiative heating for planetary IAC user manual missions with aerobraking of spacecraft p 33 N85-13890 [NASA-CR-175300] p8 N85-10677 p 14 A85-21829 WEIGHT REDUCTION A user's guide to the Flexible Spacecraft Dynamics and TRAJECTORY OPTIMIZATION Minimum weight design of truss structures with Control Program Optimal low-thrust, three-bum orbit transfers with large geometric nonlinear behavior p 10 A85-18694 [NASA-TM-87389] p 24 N85-12586 plane changes p44 A85-18671 WELDING TRANSFER FUNCTIONS Investigation of welded interconnection of large area Poles and transmission zeros of flexible spacecraft wraparound contacted silicon solar cells control systems p 22 A85-26433 [NASA-CR-174438] p 39 N85-19519 WELDING MACHINES TRANSFER ORBITS VACUUM EFFECTS Toroid Joining Gun — thermoplastic welding system Applications of space tethers Evaluation and prediction of long-term environmental using induction heating [IAF PAPER 84-436] p 51 A85-13276 effects of nonmetallic matenals [SAE PAPER 850408] p 38 A85-25988 A rectilinear guidance strategy for short orbital [NASA-CR-171353] p 39 N85-19137 VALUE ENGINEERING WIND TUNNEL TESTS transfers p52 A85-15509 Experimental and predicted heating distributions for Optimal low-thrust, three-bum orbit transfers with large International FEM-Congress, Baden-Baden, West Germany, November 14, 15, 1983, Proceedings biconics at incidence in air at Mach 10 plane changes p 44 A85-18671 [NASA-TP-2334] p 14 N85-12313 p8 A85-26675 A survey of aeroassisted orbit transfer VARIABLE GEOMETRY STRUCTURES WINGS p53 A85-21826 Reduction method for thermal analysis of complex Variable geometry truss and its application to deployable The long term behaviour of Earth orbits and the truss and space crane arm aerospace structures implications for debns control p 58 N85-21213 [IAF PAPER 84-394] p 10 A85-13248 [NASA-TP-2373] p 15 N85-16066 TRANSIENT RESPONSE Variable geometry truss concept Experimental measurements of matenal damping in free [REPT-614] p 12 N85-21697 fall with tunable excitation p20 A85-18692 VELOCITY TRANSOCEANIC COMMUNICATION Speed test results and hardware/software study of XENON Some design concepts for Intelsat VII computational speed problem, appendix D Performance capabilities of the 12-centimeter Xenon ion p7 A85-15496 p25 N85-13843 thruster p 44 A85-16439 TRANSPARENCE VELOCITY MEASUREMENT Demonstration of transparent solar array module Assessment of satellite collision hazards by simulated design sampling in space p 40 N85-21195 [NASA-CR-174257] p 47 N85-16302 In situ orbital debns expenment concepts Process for preparing essentially colorless polyimide film p58 N85-21198 containing phenoxy-lmked diammes VIBRATION [NASA-CASE-LAR-13353-1] p 40 N85-20128 Human response to vibroacoustic environments of TRANSPORTATION space vehicles Proceedings of a Workshop on the Applications of [NASA-TM-86316] p 54 N85-10789 Tethers in Space, Volume 1 Vibration analysis of a multipurpose platform [NASA-CR-171196] p55 N85-12076 [NAL-TR-803] p 27 N85-18078 Identification of vibration parameters of flexible Proceedings of a Workshop on Applications of Tethers structures p 27 N85-18360 in Space, Volume 2 VIBRATION DAMPING [NASA-CR-171197] p 55 N85-12077 Alleviation of observation spillover in continuous TRAPPED PARTICLES structures p 17 A85-12434 SCATHA (spacecraft charging at high altitudes) plasma Continuum modelling of damping in large space interaction expenment SC-3 high energy particle structures p 18 A85-12478 spectrometer SC-8 energetic ion composition Optimal design of a passive vibration absorber for a expenment truss beam p 19 A85-13638 [AD-A149728] p 35 N85-21252 Application of damping to spacecraft structures TRUSSES p20 A85-15992 Continuum modelling of damping in large space Experimental measurements of matenal damping in free structures p 18 A85-12478 fall with tunable excitation p 20 A85-18692 The strongest structures with macrostiffness Adaptive modal control of structural dynamic systems constraints p 10 A85-12933 using recursive lattice filters p 23 A85-26435

A-20 PERSONAL AUTHOR INDEX

TECHNOLOGY FOR LARGE SPACE SYSTEMS / A Bibliography (Supplement 13) MARCH 1986

Typical Personal Author Index Listing

ARDUINI, C. BECK. D. E. PERSONAL AUTHOR Thermal analytical model of bKtanensional and Continuous graphtte/polysulfone RP thermoforming for unidimensional structural elements in a space large space structure construction p36 ASS-15638 environment BEKEY, I. HOWSMAN, T. O. [IAF PAPER 84-399] p 13 ASS-13252 Applications of space tethers [IAF PAPER 84-436] p 51 ASS-13276 r—Definition of ground test tar verification of large spcce Analytical thermal formulatnns for antenna dishes structure control p IS N85-14017 BELETSKII, V V [NASA-Cn-171208) p9 N85-13838 ARNBAK, J. C. Stability of a nng of connected satellites The systems background for satellite communication [IAF PAPER 84-342] p 18 ASS-13206 antennas p32 A8S-23652 BENDEN, W J Efficient inclination control for geostationary satellites ARNOLD, Q S. Kinetics of oxygen interaction with materials [AIAA PAPER 85-0216] p 21 A85-19595 I AIAA PAPER 85-0472) p 37 A85-19770 BENFORD, S Report of the Electrodynamtc Interactions Panel NASA REPORT PAGE ARRINQTON, J P P34 N85-20363 TITLE ACCESSION Performance assessment of aero-assisted orbital NUMBER NUMBER BENTON, D NUMBER transfer vehicles p 56 N85-16993 Effects of space environmental conditions on graphite ATLAS, D epoxy composites p 36 ASS-15990 A case for Gohrem - Geosynchronous orbit high BENTS, D J Listings in this index are arranged alphabetically by resolution earth monitoring p 50 ASS-10261 Report of the Constellations Panel p 27 N85-2036S personal author The title of the document provides AUBE.B BERGAMASUI, S. the user with a brief description of the subject Spacecraft systems engineering and geometry Report of the Constellations Panel p 27 N85-20368 modelling - The ESABASE-MATVIEW approach matter The report number helps to indicate the BERGER, C. p8 A85-27696 Utilization of a teleoperated service vehicle for type of document listed (e g, NASA report, AUBRUN.J-N spacecraft servicing translation, NASA contractor report) The page and Analytical and experimental research in large space [IAF PAPER 84-48] p 1 ASS-13009 accession numbers are located beneath and to the structures control BERGERON, R P [AIAA PAPER 85-0356] p 21 A85-19693 Vehicle/engine integration p 48 N85-17008 tight of the title Under any one author's name the AUCEL, S. Orbital transfer vehicle propulsion issues accession numbers are arranged in sequence with Technology and performances of structural thermal p48 N85-17009 the AIAA accession numbers appeanng first mechanical equipment used for antenna of TV SAT-TOF BERGMANN, H W 1 program p 15 N85-14012 Design preparations for large space structures AUER, W [IAF PAPER 64-392] p 35 A85-13246 Hemispherical antenna pointing mechanism Influence of simulated space environment on the p26 N85-14021 behavior of carbon-fiber-reinforced plastics with +, -45 ply orientations II p 36 A85-14163 BERNASCONI, M C. AERATE, S, B Inflatable space-ngidrzed structures - Recent Continuum modelling of damping in large space developments of the material technology structures p 18 ASS-12478 BACHTELL, E E [IAF PAPER 84-384] p 10 A85-13240 Operational fitness of box truss antennas in response Large spacebome antenna reflectors using inflatable ADAMS, I-R to dynamic slewing space ngidized structures p 12 N85-14004 Efficient structures for geosynchronous spacecraft solar [NASA-CR-172470] p 27 N85-19012 BERTRAM, A. arrays BAER, T Application of modal synthesis concepts to spacecraft [NASA-CR-174448] p 12 N85-19004 Space station thermal control - An interview with Robert design verification p17 A85-12455 ADELMAN, H.U. Hasten p 13 A85-18321 BESTE.D L An analytical investigation of shape control of large BAINUM, P M. IAC user manual space structures by applied temperatures Environmental effects on the dynamics and control of [ NASA-CR-175300 ] p 8 N85-10677 p 14 A85-25145 an orbiting large flexible antenna system BETTADAPUR, S. S. ADLER, C a [IAF PAPER 84-358] p 18 A85-13220 Operational fitness of box truss antennas in response The maximum efficiency of an isolated solar energy Report of the Transportation Panel to dynamic slewing conversion device in space p 46 A85-25797 pS7 NSS-20364 [NASA-CR-172470] p 27 N85-19012 BAIOCCHI, a BEVILACQUA, F ADORMATO. R J Bipropellant propulsion in the new generation of Report of the Constellations Panel p 27 N85-20368 Report of the Transportation Panel satellites and upper stages The role of BPD Dif esa-Spazio BIESS, J. J p57 N85-20364 in this field - Manutactunng facilities and technology Space power management and distnbution status and AGNENI, A. p43 A85-12519 trends p47 N85-13896 Baste waves propagation in bounded periodic BALDI. a BILEK, F V structures IRIS Spinning Stage - A pengee stage for satellites up Deployable folded antenna apparatus [IAF PAPER 84-395] p 19 A85-13249 to 900 kg to be launched from the Space Shuttle with [AD-D011503] p12 N85-21495 Elastic dispersion effects on dynamics and control of the IRIS system p 43 ASS-12520 BINDFORD, T O. large modular antennas p26 N85-14019 BANERJEE. J. R. Precise control of flexible manipulators AGRAWAL, S. K. Evaluation of efficiently computed exact vibration [NASA-CR-174210] p42 N85-16178 Effect of neutron and proton irradiation on some characteristics of space platforms assembled from stayed BINSACK.J H columns p 13 A85-12884 properties of Kapton P37 A8S-21S08 Report of the Electrodynarruc Interactions Panel BANKS, B. p34 N85-20363 AKIN, D. I. Definition of ground test for verification of large space Neutral buoyancy evaluation of technologies for space structure control BLACKWELL, M station extmnal operatxxis [NASA-CR-171208] p9 N85-13838 A functional vehicle for autonomous mobile robot research (IAF PAPER 84-38] p 41 A85-13001 BAR-KAMA, I. (AD-A150052) p42 N85-21666 ALBERINLO. Some applications of direct adaptive control to large Development of advanced composite tubular structures structural systems P 19 A85-13636 BLAIS.T tor antenna reflector p 10 A85-24817 BARAONA, C. R. Service manipulator system for maintenance and AMOS, A. K. Space station power system p33 N85-13881 servicing of future space platforms [IAF PAPER 84-369] p 41 A85-13227 Structural control research at AFOSR BARBON1, R. p21 A85-22S85 ThermoelastK behaviour of space structures in BOGOMOLOV, IU. A. The development of a frequency method for the ANDO. K.J. composite materials [IAF PAPER 64-404] p 35 A85-13257 mathematical modeling of the motion of an elastic space The NASA MLA program p 52 ASS-17573 BECHTEL, a T. vehicle p20 A85-170S4 AMOELO, J, JR. An Assessment of Integrated Flywheel System BOIAKHCH1AN, G. P Opening up the future in space with nuclear power Technology Effect of phase fluctuations in an incident beam on the (0685-002411) p<9 N85-20862 [NASA-CP-2346J p26 NB5-13850 characteristics of a rectenna system p 30 ASS-15760

B-1 BONHOMME, R. PERSONAL AUTHOR INDEX

BONHOMME, R CHATURVEDI, U K. CROSS, J B Development and application of new technologies in Effect of neutron and proton irradiation on some Atomic oxygen surface interactions - Mechanistic study ESA's Olympus programme p 3 A85-27695 properties of Kapton p 37 A85-21508 using ground-based facilities BOOK, W J CHICHESTER, F D [AIAA PAPER 85-0473] p 37 A85-19771 Recursive Langrangian dynamics of flexible manipulator Comparing attitude control effectiveness for actuators CURTIS, H. arms P 20 A85-15745 on two bodies of a six body model of a flexible spacecraft Near-optimum design of GaAs-based concentrator BOUQUET, F. L. with that for actuators restncted to a single body space solar cells for 80 C operation p30 A85-15800 Dielectric material in the space environment p17 A85-11086 CURTIS, S p37 A85-24672 Developing sensitivity coefficients for a state vanable Definition of ground test for verification of large space model of a flexible spacecraft with modular attitude BOUSSAUS, D structure control control p 17 A85-11087 Dynamic isolation of a spacecraft science platform via [NASA-CR-171208] p9 N85-13838 Modular design attitude control system momentum compensation p 17 A85-11082 [NASA-CR-171182] p 24 N85-10098 BOWDEN, M L. CHIDESTER, L G. Neutral buoyancy evaluation of technologies for space Unlimited power for our space vehicles station external operations p46 A85-25796 DAGEVILLE, H. [IAF PAPER 84-38] P 41 A85-13001 CHIPMAN, R. Technology and performances of structural thermal BRADFORD, R International space programmes and policies Research on large, highly accurate, inflatable mechanical equipment used for antenna of TV SAT-TDF p2 A85-20507 1 program p 15 N85-14012 reflectors CHOBOTOV, V A. [AD-A145080] p11 N85-10099 Assessment of satellite collision hazards by simulated DAHL.W E. BROWN, J. R. sampling in space p 40 N85-21195 Optimal simultaneous structural and control design of maneuvenng flexible spacecraft p7 A85-18338 Vehicle/engine integration p 48 N85-17008 CHU, F H DAHLGREN, J B BROWN, K. G. Advanced analysis methods for spacecraft composite Determination of atmospheric density using a structures p 37 A85-15993 Active control technology development at NASA p22 A85-22586 space-launched projectile CHUN, H. M [AIAA PAPER 85-0327] p2 A85-20866 Closed-form solutions for feedback control with terminal DANES), A. BUCKLEY, J D constraints p 20 A85-18331 An optimal shape control of a large flexible radiator in space Toroid Joining Gun COFFINIER, P [IAF PAPER 84-64] p 18 A85-13023 [SAE PAPER 850408] p 38 A85-25988 Spacecraft systems engmeenng and geometry BUOEN, D modelling - The ESABASE-MATVIEW approach DAVID, L. W Design of a nuclear electric propulsion orbital transfer p8 A85-27696 Space as motivational propulsion [IAF PAPER 84-407] p 51 A85-13259 vehicle p 46 A85-23394 COLINO, R R Nuclear reactors for space power p 46 A85-24793 Intelsat's twentieth anniversary - Two decades of DAVIS, H S. Nuclear-electnc power in space p30 A85-15812 Opening up the future in space with nuclear power innovation in global communications p 54 A85-26369 OAVISON, E J [DE85-002411] p49 N85-20862 COLLINS, P The decentralized control of large flexible space BUELL, D. N. Attitude control system and communications payload for structures p 17 A85-10071 Deployable folded antenna apparatus an amateur solar sail spacecraft [AD-D011503] p 12 N85-21495 [IAF PAPER 84-363] p 29 A85-13224 DE KRUYF, J Spacecraft systems engmeenng and geometry BUONJIOLNO, C. COLONY, J A. modelling - The ESABASE-MATVIEW approach Report of the Technology and Test Panel Analysis of Nonvolatile Residue (NVR) from spacecraft p8 A85-27696 p57 N85-20370 systems [NASA-TM-86184] p 39 N85-17019 DECASTRONODAL, M BURDESS, J S CASA activities in antenna technology COMPTON, H Alleviation of observation spillover in continuous p39 N85-14015 structures p 17 A85-12434 Report of the Technology and Test Panel DEGRAFFENREID, K J BUSH, H G p57 N85-20370 A plan for controlling electrostatic discharges on Space Station truss structures and construction CONLON, R J geosynchronous spacecraft p 32 A85-26685 considerations Preliminary analysis of space mission applications for DELAFONTAINE, J. [NASA-TM-86338] p 15 N85-15796 electromagnetic launchers Stability analysis of flexible spaceraft with PID BUTLER, M L. [NASA-CR-174067] p 47 N85-12071 controller ACOSS 17 (Active Control of Space Structures) COOPER, L. P [CRC-1372] p28 N85-21247 [AD-A150007] p28 N85-21253 OTV propulsion tecnology programmatic overview DJERASSI, S BYRD, J W p48 N85-16997 Equations of motion governing the deployment of a The maximum efficiency of an isolated solar energy Vehicle/engine integration p48 N85-17008 flexible linkage from a spacecraft conversion device in space p 46 A85-25797 CORTIAL, J. [AIAA PAPER 85-0023] p 20 A85-19462 Measurement of the mertial constants of a ngid or flexible DOANE, G B.lll structure of arbitrary share through a vibration test Definition of ground test for venfication of large space [NASA-TM-77557] p 24 N85-11381 structure control COTTS, D B [NASA-CR-171208] p9 N85-13838 CANNON, R H,JR Dielectnc matenal in the space environment NASA-VCOSS dynamic test facility Precise control of flexible manipulators p 37 A85-24672 [NASA-TM-86491] p 27 N85-18998 [NASA-CR-1742101 p 42 N85-16178 Active control of large space structures An introduction COUGNET, C CARIGNAN, C R and overview Number and placement of control system components Architecture and implementation of an in-orbit infrastructure [NASA-TM-86490] p 27 N85-19014 considering possible failures p 19 ASS-13634 Definition of ground test for Large Space Structure (LSS) [IAF PAPER 84-29] p6 A85-12995 CARMONA, R control venfication Control of large collector arrays The SSPS Utilization of a teleoperated service vehicle for [NASA-TM-86495] p 28 N85-21249 spacecraft servicing experience DOBROWOLNY, M [IAF PAPER 84-48] p 1 A85-13009 [DE85-001461] p34 N85-20553 Report of the Electrodynamic Interactions Panel CARROLL, C C CRAWLEY, E. F p34 N85-20363 The computer-communication link for the innovative use Expenmental measurements of matenal damping in free DODDS, S J. of Space Station p 32 N85-11016 fall with tunable excitation p 20 A85-18692 A signed switching time bang-bang attitude control law CASTELLANI, A. CREMA, L. B for fine pointing of flexible spacecraft p 19 A85-13893 Thermoelastic behaviour of space structures in Thermoelastic behaviour of space structures in OOETACH, K. H composite materials composite materials An overview of the space remote manipulator system [IAF PAPER 84-404] p 35 A85-13257 [IAF PAPER 84-404] p 35 A85-13257 p42 N85-16964 CAUGHEY, T. K. CREMERS, D A. DOWLING, K. Optimal low-thrust, three-burn orbit transfers with large Atomic oxygen surface interactions - Mechanistic study A functional vehicle for autonomous mobile robot plane changes p 44 A85-18671 using ground-based facilities research CEREMEU, C J [AIAA PAPER 85-0473] p 37 A85-19771 [AD-A150052] p 42 N85-21666 Design study of an integrated aerobraking orbital transfer CRON, A. C. DUCKETT, R. J vehicle Applications of Tethers in Space, volume 1 Report of the Technology and Test Panel INASA-TM-58264] p9 NB5-21262 [NASA-CP-2364] p 57 N85-20339 p57 N85-20370 CHANG, B. DUTAT, M Report of the Transportation Panel Applications of Tethers in Space, volume 2 [NASA-CP-2365] p 57 N85-20361 Space environment simulation to test satellite thermal p57 N85-20364 Applications of Tethers in Space control coatings, volume 1 CHANG, B J [CERT-4128-VOL-1] p 16 N85-17012 Engmeenng model system study for a regenerative fuel [NASA-CP-2366] p 59 N85-21659 cell Study report CROOMES, S D [NASA-CR-174801] p 47 N85-16292 Space Station truss structures and construction CHASE, V A. considerations Develop and demonstrate manufactunng processes for [NASA-TM-86338] p 15 N85-15796 EARHART, R W fabncating graphite filament reinforced polymide (Gr/PI) CROOPNICK, S. R. Preliminary analysis of space mission applications for composite structural elements A methodology for organizing performance requirements electromagnetic launchers [NASA-CR-172497] p 39 N85-20019 for complex dynamical systems p 3 A85-25117 [NASA-CR-174067] p 47 N85-12071

B-2 PERSONAL AUTHOR INDEX HONEYCUTT, W. D.

EDWARDS, L FREDERICKSON, A. R. GUYENNE, T. D Report of the Transportation Panel Dielectric material in the space environment Workshop on Mechanical Technology for Antennas p57 N85-20364 p37 A85-24672 [ESA-SP-225J p11 N85-13999 EISENHAURE.D B FREELAND, R. E. Integrated Power and Attitude Control Systems for Survey of deployable antenna concepts Space Station p 10 A85-23S63 H [AIAA PAPER 85^)358] p 31 A8S-19695 FURUYA, H HAFTKA.R. T ELROD. W C. Variable geometry truss and its application to deployable Optimal electric propulsion orbit transfer vehicle design An analytical investigation of shape control of large truss and space crane arm space structures by applied temperatures and operational effectiveness [IAF PAPER 84-394) p 10 ASS-13248 (AIAA PAPER 850431] p 45 A85-19744 p 14 A85-25145 EMERY, R. K. HAHN, E. BAe antenna hardware technology for current satellite Autonomous momentum management for the CDG projects p9 N85-14011 planar Space Station EMMANUEL, I. S. [AIAA PAPER 85-0031 ] p 21 ASS-19468 GAMBLE, J. D Comparing attitude control effectiveness for actuators Autonomous momentum management for space Design study of an integrated aerobraking orbital transfer on two bodies of a six body model of a flexible spacecraft station vehicle with that for actuators restricted to a single body [NASA-CR-174065] p 24 N85-12931 [NASA-TM-5B264] p9 N85-21262 p17 A85-11086 Autonomous momentum management for space station, ENGLISH, R. E. GAROW, J exhibit A Dynamic power systems for power generation Regenerative fuel cell energy storage system for a low [NASA-CR-171256] p 33 N85-12933 Earth orbit space station p33 N85-13892 HAHN, H. T. ENGRAND, D. [NASA-CR-174802] p 47 N85-13371 Effects of residual stresses in polymer matrix Measurement of the inertial constants of a rigid or flexible GARRISON, P W composites p35 A85-12395 structure of arbitrary share through a vibration test Integratable propulsion systems for the Space Station HALE, A. L. [NASA-TM-77557] p 24 N85-11381 p46 A85-23393 Optimal simultaneous structural and control design of ESTES.W. J Design of a nuclear electric propulsion orbital transfer maneuvering flexible spacecraft p 7 ASS-18338 Spectral characteristics of radar echoes from vehicle p46 A85-23394 HANAWA, T aircraft-dispensed chaff p23 A85-26606 GATES, R L. Vibration analysis of a multipurpose platform EVANS, R. C. SMP A solid modeling program [NAL-TR-803] p 27 N85-18078 A plan for controlling electrostatic discharges on [NASA-CR-172473] p8 N85-11570 HANLE, P. A. Astronomers, Congress, and the Large Space geosynchronous spacecraft p 32 A85-26685 GELDERLOOS, H C Telescope p 54 A85-27973 Computer aided design of multiple input/output control HANWECK, J systems for multibody flexible Space Station Report of the student working group to the panel on [AIAA PAPER 85-0223] p7 A85-19600 satellite communications p30 ASS-14430 GERMAN), G. FABRIZI, A. Development of advanced composite tubular structures HARDEE, J H. Bipropellant propulsion in the new generation of for antenna reflector p 10 A85-24817 The space shuttle orbiter remote manipulator positioning satellites and upper stages The role of BPD Drfesa-Spazio GHALLA-GORADIA, M. mechanism p42 N85-16963 in this field - Manufacturing facilities and technology Near-optimum design of GaAs-based concentrator HARRISON, E. S. p43 A85-12519 space solar cells for 80 C operation p30 ASS-15800 Develop and demonstrate manufactunng processes for FAVE, J G1RAUDBIT, J -N. fabncating graphite filament reinforced potymide (Gr/PI) Lay-out of a re-usable re-entry vehicle required in a Mure Oeployable reflector antennas - Mechanical design of composite structural elements European low earth orbit scenario the reflective surface [NASA-CR-172497] p 39 N85-20019 [IAF PAPER 84-06] p 50 A85-12981 [IAF PAPER 84-393] p6 A85-13247 HARTUNG, W FAYMON, K A. GLAESE, J R Influence of simulated space environment on the Report of the Transportation Panel Definition of ground test for venfication of large space behavior of carbon-fiber-reinforced plastics with +, -45 • p57 N85-20364 structure control ply orientations II p 36 A85-14163 FEDOR.J V [NASA-CR-171208] p9 N85-13838 Influence of thermal cycling on the behavior of CFRP A user's guide to the Rexible Spacecraft Dynamics and ACOSS 17 (Active Control of Space Structures) Control Program matenal for space structures p 39 N85-14013 [AD-A150007] p28 N85-21253 [NASA-TM-87389] p 24 N85-12586 HASLETT, R GOLDEN, C T FENDER, J & Heat rejection working group synopsis Graphite epoxy structure of the Space Telescope's Deployable optical systems. Proceedings of the Meeting, p15 N85-13906 optical telescope assembly p36 A85-15980 Los Angeles, CA, January 18,19,1983 HEARD, W L, JR GORADIA, C p 53 A85-22576 Swing-arm beam erector (SABER) concept for single Near-optimum design of GaAs-based concentrator FERRANTE.J G astronaut assembly of space structure space solar cells for 80 C operation p 30 A85-15800 Spacecraft systems engineenng and geometry [NASA-TP-2379] p 42 N85-19015 GOUNDER, R modelling - The ESABASE-MATVIEW approach HECK, B S Effects of space environmental conditions on graphite p8 A85-27696 Computer aided design of multiple input/output control epoxy composites p36 A85-15990 HELDER, J. A. systems for multibody flexible Space Station GOUNDER, R. N. Space greenhouse design p50 A85-12927 [AIAA PAPER 85-0223] p 7 A85-19600 Structures and matenals technologies for spacecraft FINLEY, l_ A. systems An overview p36 A85-15977 HEDGEPETH, J M Large-diameter astromast development GRAFF, S. Construction of large precision reflectors using the Aft [NASA-CR-171201] 11 N85-12200 P Report of the Technology and Test Panel Cargo Camer FINNEGAN, P p 57 N85-20370 [IAF PAPER 84-389] p2 A85-13244 Report of the Electrodynamic Interactions Panel GRAZIANI, F Design concepts for reflector antenna structures p 34 N85-20363 Elastic waves propagation in bounded penodic p7 A85-22579 FISCHER, T structures High performance deployable antenna structures Mechanical/thermal design of a polarization sensitive [IAF PAPER 84-395] p 19 A85-13249 p11 N85-14001 reflector p 15 N85-14009 Elastc dispersion effects on dynamics and control of HEFZY, M S. FLAKE, R H. large modular antennas p 26 N85-14019 Shear deformation plate connmia of large Spectral characteristics of radar echoes from GREEN, C E. double-layered space structures p 8 N85-10391 aircraft-dispensed chaff p 23 A85-26606 Natural environment design cntena for the Space Station HEMPEL, T FLANAGAN, P definition and preliminary design Development of a foldlme concept for automatic Report of the Technology and Test Panel [NASA-TM-86498] p 9 N85-21232 refolding of a flexible blanket (folding analysis) p57 N85-20370 GREGG, J [ESA-CR(P)-1933] p 12 N85-17428 FLORENCE, D E. IAC user manual HENDRICKS, H D. Vehicle/engine integration p 48 N85-17008 [NASA-CR-175300] p8 N85-10677 Wavelength division multiplexing for future Space Station FORDYCE.J S. GROOM, N. J data systems p 32 A85-25359 An Assessment of Integrated Flywheel System Missions/planning panel p 4 N85-13886 HERTZBERG, A. Technology FOX, R. L The liquid droplet radiator - an ultralightweight heat [NASA-CP-2346] p 26 N85-13850 Torotd Joining Gun rejection system for efficient energy conversion in space GROSS, D W [SAE PAPER 850408] p 38 A85-25988 p 15 N85-13900 Advanced analysis methods for spacecraft composite FRANXUN, I. V structures p 37 ASS-15993 HILL, A. S. Utilization and economics of a European low earth orbit GROSS, S. Modular experimental platform for science and Space Platform Potential of flywheels for spacecraft energy storage applications p 11 N85-11031 [IAF PAPER 84-57] p1 A85-13016 p33 N85-13890 HOLNICKhSZULC, J FRASER, W GROSS), M. D The strongest structures with macrostiffness Geosynchronous satellite collision avoidance Report of the Electrodynamic Interactions Panel constraints p 10 ASS-12933 p58 N85-2J197 p34 N85-S03S3 HONEYCWTT, W D FRAYSSE.R. GRUBBS.J R. Mass properties analysis and control of advanced space Looking back on the past - The decision of Europe to The low cost development, test, and production of a structures through computerized integration with design participate in the post-Apollo program commercial STS upper stage TOS and structural analysis pS3 A85-23824 [AIAA PAPER 85-0313] p 45 A85-19660 [SAWE PAPER 1527] p 13 A85-1S812

B-3 HOPKINS, M. PERSONAL AUTHOR INDEX

HOPKINS, M JONES, K. H KOELLE, D E Autonomous momentum management for the CDG SMP A solid modeling program Economics of permanent polar platforms (PPP) for global planar Space Station [NASA-CR-172473] p8 N85-11570 monitonng [AIAA PAPER 85-0031 ] P 21 A85-19468 JONES, V L [IAF PAPER 84-226] p2 A85-13144 HORO, R. M. ACOSS 17 (Active Control of Space Structures) KOPF, E H CRC handbook of space technology Status and [AD-A150007] p28 N85-21253 High precision active nutation control of a momentum Projections p3 A85-28275 JONGEWARD, G A. biased spacecraft with flexible appendages HOWSMAN, T G. Computer simulation of plasma electron collection by p 20 A85-18337 Definition of ground test for verification of large space PIX-II KOVACH, A. J structure control [AIAA PAPER 85-0386] p 45 A85-19715 Engineering model system study for a regenerative fuel [NASA-CR-171208] P9 N85-13838 JUANG, J -N. cell Study report Optimal design of a passive vibration absorber for a HUDSON, M. [NASA-CR-174801] p47 N85-16292 truss beam p 19 A85-13638 Report of the Electrodynamic Interactions Panel KOVALCHUK, B I p 34 N85-20363 Closed-form solutions for feedback control with terminal Expenmental study of the effect of the type of stress constraints p20 A85-18331 HUETTMANN, H J state on plastic strain in structural matenals at low JUOD, 0 C. Mechanical/thermal design of a polarization sensitive temperatures p37 A85-16499 Integratable propulsion systems for the Space Station reflector P 15 N85-14009 KOWALSKI, R p46 A85-23393 HUGHES, P C Parametnc analysis SOC meteoroid and debns The decentralized control of large flexible space protection p 16 N85-21209 structures P 17 A85-10071 KRISHNA, R. Environmental effects on the dynamics and control of HUNT, J. J an orbiting large flexible antenna system Workshop on Mechanical Technology for Antennas KAMAT, M P [IAF PAPER 84-358] p 18 A85-13220 [ESA-SP-225] p11 N85-13999 Minimum weight design of truss structures with KROLL, K. HUNTER, M. W geometnc nonlinear behavior p 10 A85-18694 Propellant transfer Tethered depot Report of the Transportation Panel KAMINSKAS, R p48 N85-17006 p57 N85-20364 Report of the Electrodynamic Interactions Panel KROLL, K R. p34 N85-20363 Tethered propellant resupply technique for space KANE, T R. stations Equations of motion governing the deployment of a [IAF PAPER 84-442] p 44 A85-13282 flexible linkage from a spacecraft KUO, S. P. IBRAHIM, A. M. [AIAA PAPER 85-0023] p 20 ASS-19462 Earth's magnetic field perturbations as the possible Dynamics of the Orbiter based construction of structural KANMNURI, A. environmental impact of the conceptualized solar power components Partial bleed expander cycle for low thrust LOX/LH2 satellite [IAF PAPER 84-359] P 18 A85-13221 rocket engine [AD-A149120] p30 A85-16641 IIDA, T [NAL-TR-837T] p 49 N85-19018 A space station experiment on large antenna assembly KARANIAN, L A. and measurement - A follow-on study Operational fitness of box truss antennas in response [IAF PAPER 84-58] P 41 A85-13017 to dynamic slewing LACOMBE, J.-L ILES, P A. [NASA-CR-172470] p 27 N85-19012 Solar cells for tomorrow's spacecraft Service manipulator system for maintenance and p54 A85-24794 KATZJ servicing of future space platforms Computer simulation of plasma electron collection by IMBRIALE, W. A. [IAF PAPER 84-369] p 41 A85-13227 PIX-II Satellite communication antenna technology LAGOUIN, M p 31 A85-23651 [AIAA PAPER 85-0386] p 45 A85-19715 Influence of starting material and technological INAL, O T KAUFMAN, H processes on the radiation resistance of silicon solar cells Radiation effects in matenals - Fieldnon microscope Some applications of direct adaptive control to large for space use p 38 A85-30024 characterizations P 37 A85-24675 structural systems p 19 ASS-13636 LAKE, M S INMAN, 0. J KAYA.N Space Station truss structures and construction Modal decoupling conditions for distributed control of Engineering aspect of the Microwave Ionosphere considerations flexible structures P 19 A85-13641 Nonlinear Interaction Expenment (MINIX) with a sounding [NASA-TM-86338] p 15 N85-15796 Qualitative results for distributed systems with discrete rocket LAMBI, M A damping and stiffness with application to control [IAF PAPER 84-289] p 29 A85-13177 Generalized transform methods based finite element [AD-A145525] p 24 N85-11382 KECKLER, C R methodology - Thermal/structural dynamic applications INOUYE, L An Assessment of Integrated Flywheel System [AIAA PAPER 85-0155] p 14 A85-19553 Space power management and distribution status and Technology LANG, D D trends p47 N85-13896 [NASA-CP-2346] p 26 N85-13850 Report of the Technology and Test Panel p 57 N85-20370 INTRILIGATOR, D KELLERMEIER, H LANGEREUX, P Report of the Electrodynamic Interactions Panel Offset unfurlable antenna concepts p5 N85-14002 p34 N85-20363 Europe in space 1985-2000 p 3 A85-26011 KENT, J D B LARSON, V R Some results of the MSAT phase B studies and their The challenge of advanced space transportation and impact on system design propulsion systems [IAF PAPER 84-89] p 1 A85-13045 [IAF PAPER 84-310] p 44 A85-13191 JAMES, E. F. KESSLER, D. J LASKIN, R A. Spacelab Hitchhiker, a quick reaction earner Orbital Debns High precision active nutation control of a momentum [AIAA PAPER 85-0504] p 53 A85-19795 [NASA-CP-2360] p 40 N85-21188 biased spacecraft with flexible appendages JASENTULIYANA, N KHOT, N. S p20 A85-18337 International space programmes and policies Minimum weight design of truss structures with LAUE, J H p2 A85-20507 geometnc nonlinear behavior p 10 ASS-18694 Tethered satellite system project overview The potential of solar power satellites for developing KIDA.T p5 N85-20341 countnes p 53 A85-24654 Poles and transmission zeros of flexible spacecraft LEBEDEV, A. A. JASIK, H control systems p 22 A85-26433 Expenmental study of the effect of the type of stress Antenna engineering handbook /2nd edition/ KIDGER, N state on plastic strain in structural materials at low p30 A85-16081 Salyut Mission Report p 3 A85-25700 temperatures p37 A85-16499 JENSEN, J. K. KING, M L LEE, M C Swing-arm beam erector (SABER) concept for single Six degrees of freedom control with each hand? Earth's magnetic field perturbations as the possible astronaut assembly of space structure p 42 N85-14492 environmental impact of the conceptualized solar power [NASA-TP-2379] p 42 N85-19015 KINPARA, A. satellite JERNIGAN, C M [AD-A149120] p30 A85-16641 A space station experiment on large antenna assembly Second Symposium on Space Industnalization and measurement - A follow-on study LEE, W H [NASA-CP-2313] p4 N85-11011 [IAF PAPER 84-58] p 41 A85-13017 Conceptual design for scaled truss antenna flight JOHNSON, G. K. expenment KITCHELL, J Efficient inclination control for geostationary satellites [NASA-TM-85804] p4 N85-12932 [AIAA PAPER 85-0216] p 21 ASS-19595 The real world The user p 32 N85-11017 LEGGETT, N. E. JOHNSON, R. C. KLEIN, G A. Space greenhouse design p 50 A85-12927 Antenna engineering handbook /2nd edition/ Active cooling requirements for propellant storage LEHTINEN, A. M p30 A85-16081 p48 N85-17004 Thermal storage analysis for large manned space JONCKHEERE, E. A. KNOLL, K R platforms Principal component analysis of flexible systems - Design study of an integrated aerobraking orbital transfer [AIAA PAPER 85-0066] p 14 A85-19493 Open-loop case p 7 A85-16648 vehicle LEIOICH, C LOG balancing and reduced LOG compensation of [NASA-TM-58264] p9 N85-21262 A modular approach to developing a large deployable symmetric passive systems p 23 A85-27238 KNOUSE, G. H reflector p 7 A85-22685 JONES, J. J. NASA's mobile satellite communications program, LEISER, D B Chemical nonequilibnum effects on flowfields for ground and space segment technologies Catalytic surface effect on ceramic coatings for an aeroasststed orbital transfer vehicles p 53 A85-21831 [IAF PAPER 84-84] p 29 A85-13040 aeroassisted orbital transfer vehicle p 38 A85-29730

B-4 PERSONAL AUTHOR INDEX MOBLEY, T. B.

LEUESSURIER. R. W MACCONOCHIE, I O MAZZOLA.C A. Orbrt-on-demand vehicles - Mission possible, but Pultrusion process for fabrication of tethers (preliminary Dynamic characteristics of a space reflector support one-day turnaround? p 53 A85-24790 concepts) p40 N85-20371 structure p 22 A85-24949 LERNER, E. J. MAODOX, L. W. MCALLISTER, J G. When spacecraft get charged up, they have minds of Optimal electric propulsion orbit transfer vehicle design Space based OTV servicing p 56 N85-17010 their own p 53 A85-247S7 and operational effectiveness MCCANDLESS, R S LESOTA.S.K. [AIAA PAPER 85-0431 ] p 45 A85-19744 Performance assessment of aero-assisted orbital Effect of phase fluctuations in an incident beam on the MAHARANA.P K. transfer vehicles p56 N85-16993 characteristics of a rectenna system p30 ASS-15760 Flexural vibration of gravity-stabilized, structurally MCCLAMROCH, N H. LEVIN, E. U. damped, large flexible satellites p22 A85-26434 Sampled data control of flexible structures using Stability of a nng of connected satellites MALCHOW, H L constant gain velocity feedback p 29 A85-13640 [IAF PAPER 84-342] p 18 A85-13206 A methodology for organizing performance requirements Displacement control of flexible structures using Stability of the stationary motions of a tethered system for complex dynamical systems p 3 A85-25117 electrohydraulic servo-actuators p 23 ASS-29144 of two bodies in orbit under the effect of gravitational and MALLETTE, L. A. MCDONALD, M. W aerodynamic forces p 20 ASS-15254 An investigation during the system test phase of the Evaluation of OMV ranging and docking systems LEWIS, S. GOES spacecraft p32 A85-28126 p 42 N85-22230 Report of the Transportation Panel MALLOY, a D MCINTYRE, S. D p 57 N85-20364 Ground test article for deployable space structure Dnves and benefits overview p 56 N85-16998 U, C P systems MCMURTREY, E. L. Design study of an integrated aerobraking orbital transfer [NASA-CR-171301] p9 N85-19011 An evaluation of grease type ball bearing lubricants vehicle MALMENDIER, J W. operating in various environments [NASA-TM-58264] p9 N85-21262 Inorganic composites for space applications [NASA-TM-66480] p 38 N85-11239 UANG, J. p38 N85-11047 MCNALLY, J. L. Robust attitude control of a large communication satellite MANARINI, G. Some results of the MSAT phase B studies and their with flexible solar arrays TSS Satellite overview p5 N85-20343 impact on system design [IAF PAPER 84-ST-06] p 19 A85-13293 MANDELL, M. J [IAF PAPER 84-89] p 1 A85-f3045 UEUT1ER, A. Computer simulation of plasma electron collection by MEDLER, E H Deployable reflector antennas - Mechanical design of PIX-II Satellite servicing A business opportunity? the reflective surface [AIAA PAPER 85-0386] p 45 A85-19715 pSS N85-11056 [IAF PAPER 84-393] p6 A85-13247 MANGANO, M. J MEEK, J L. LIGUTTI, M. Report of the Constellations Panel p 27 N85-20368 Geometncally nonlinear analysis of space frames by an Bipropellant propulsion in the new generation of MANTENIEKS, M incremental Iterative technique p 14 A85-19895 satellites and upper stages The role of BPO Oifesa-Spaao Performance capabilities of the 12-centimeter Xenon ion MEINEL, A. B in this field - Manufactunng facilities and technology thruster p 44 ASS-16439 Deployable reflector configurations p 2 A85-22577 p43 A85-12519 MARCHETTI, M MEINEL, M P LINDSAY, J. E Influence of the lamination and of some environmental Deployable reflector configurations p 2 A85-22577 Solar concentrator for space power generation effects on damping characteristics of advanced MEKARU, M M. [AIAA PAPER 85-0164] p 45 A85-19561 composites for space structures Optimal electric propulsion orbit transfer vehicle design LING, K. S [IAF PAPER 84-405] p 36 A8S-13258 and operational effectiveness Solar cells for tomorrow's spacecraft The dimensional stability of advanced composite [AIAA PAPER 85*431 ] p 45 A85-19744 p 54 A85-24794 antenna reflectors Analytical and test evaluation MENEES.G P LJNSSEN, P F J p39 N85-14014 Determination of atmosphenc density using a Ten years after the launch of ANS - Looking back in MARCO, J space-launched projectile perspective p54 A85-26770 Space environment simulation to test satellite thermal [AIAA PAPER 85-0327] p2 A85-20866 LIPS, K W. control coatings, volume 1 Trajectory analysis of radiative heating for planetary Damping synthesis for a spacecraft using substructure [CERT-4128-VOL-1] p 16 N85-17012 missions with aerobraking of spacecraft and component data MARIAN), F p 14 A85-21829 [CRC-1365] p24 N85-12082 Science Applications, part 1 p 5 N85-20346 METCALFE, A V LISOWSKI, R J MARSHALL, H R., JR. Alleviation of observation spillover in continuous structures p 17 A85-12434 Optimal simultaneous structural and control design of Commercialization of space - Incentives, impediments METZ, R. N. maneuvenng flexible spacecraft p7 A85-18338 and alternatives p 3 A85-27375 Circuit transients due to negative bias arcs on a high UU, F C MARSIK, S. J voltage solar array in low earth orbit On dynamical formulations of a tethered satellite system Advanced research and technology programs for advanced high-pressure oxygen-hydrogen rocket [AIAA PAPER 85*385] p 45 A85-19714 with mass transport MEYER, R X [AIAA PAPER 85-0117] p 21 A85-19529 propulsion [NASA-TM-86969] p 50 N85-21231 Precision of mesh-type reflectors for large space-borne LLORCA, M A. MARTIN, J A. antennas p 31 A85-21835 CASA technological effort in the field of antennas Orbit on demand - In this century if pushed MICHAELS, K B p33 N85-14010 p46 A85-24788 Regenerative fuel cell energy storage system for a low LOGAN, B A., JR MARTIN, J G. Earth orbit space station Space Station remote manipulator requirements Control of large collector arrays The SSPS [NASA-CR-174802] p 47 N85-13371 definition expenence MICHEL, R W [AIAA PAPER 85-0029] p 41 A85-19466 [DE85-001461] p 34 N85-20553 Vehicle/engine integration p48 N85-17008 LOHMAN, R L. MARTIN, R. E. MIKULAS, M M , JR. Spacelab Hitchhiker, a quick reaction earner Regenerative fuel cell energy storage system for a low Space Station truss structures and construction [AIAA PAPER 85*504] p 53 A85-19795 Earth orbit space station considerations LOHAS, N. [NASA-CR-174802] p 47 N85-13371 [NASA-TM-86338] p 15 N85-15796 In-orbit performance of INTELSAT V communications MASCY, F MILLER, C G.MI antennae deployment systems p 33 N85-14018 A modular approach to developing a large deployable Expenmental and predicted heating distributions for LONG, C reflector p7 AS5-226B5 biconics at incidence in air at Mach 10 ARABSAT spacecraft Rx and Tx antenna MATLOFF, G. L. [NASA-TP-2334] p 14 N85-12313 mechanisms p 34 N85-14022 The state of the art solar sail and the interstellar MILLER, D F LOPEZ, J M precursor mission p 43 ASS-12926 Modal control of structural systems Satellite grasping manipulator system On the potential performance of non-nuclear interstellar [AD-A149734] p 28 N85-21235 [ IAF PAPER 84-371 ] p 41 A85-13229 arks p46 A8S-25828 MILLER, L. A. LORENZINI, E. MATSUMOTO, H. Preliminary analysis of space mission applications for Engineering aspect ol the Microwave Ionosphere The investigation of tethered satellite system electromagnetic launchers dynamics Nonlinear Interaction Experiment (MINIX) with a sounding [NASA-CR-174067] p 47 N85-12071 rocket [NASA-CR-171278] p 26 N85-15772 MITSUMA, H [IAF PAPER 84-289] p 29 A8S-13177 LOTT, 0 H. Structural aspects of SAR antenna for Japanese Earth MATSUMOTO, K Investigation of welded interconnection of large area Resources Satellite 1 p 12 N85-14007 A space station experiment on large antenna assembly MITTRA,R wraparound contacted silicon solar cells and measurement - A follow-on study [NASA-CR-174438] p 39 N85-19519 Satellite communication antenna technology [IAF PAPER 84-58] p 41 A85-13017 p 31 A85-23651 LUDWIG, R A. MATTICK, A. T MIURA, K The potential of solar power satellites for developing The liquid droplet radiator - an ultralightweight heat Variable geometry truss and its application to deployable countnes p 53 A85-24654 reiecbon system for efficient energy conversion in space LUNDOUIST, C. A. p 15 N85-13900 truss and space crane arm [IAF PAPER 84-394] p 10 A85-13248 Report of the Constellations Panel p27 N85-2036B MAURETTE, M. Satellite grasping manipulator system Variable geometry truss concept [IAF PAPER 84-371] p 41 A85-13229 [REPT-614] p 12 N85-21697 M MAXWELL, M. & MOBLEY, T B A case for Gohrem - Geosynchronous orbit high Construction of large precision reflectors using the Aft MAANDERS, E. J resolution earth monitoring p 50 A85-10261 Cargo Camer Satellite communication antenna technology MAYER, H. L. [IAF PAPER 84-389] p 2 A85-13244 p 31 A85-23651 Report of the Constellations Panel p 27 N85-20368 External tank aft cargo earner p 8 N85-11050

B-5 MOCCIA, A. PERSONAL AUTHOR INDEX

MOCCIA, A. NAGATOMO, M. OPDENACKER, PH Factors affecting push-broom performances in future Design consideration of space construction facility LOG balancing and reduced LOG compensation of space platforms [IAF PAPER 84-26] p6 A85-12992 symmetnc passive systems p 23 A85-27238 [IAF PAPER 84-116] p29 A85-13066 Engineering aspect of the Microwave Ionosphere OTTERMAN, J MODI, V J Nonlinear Interaction Experiment (MINIX) with a sounding A case for Gohrem - Geosynchronous orbit high Dynamics of the Orbiter based construction of structural rocket resolution earth monitonng p 50 A85-10261 components [IAF PAPER 84-289] p 29 A85-13177 OVERMAN, A. [IAF PAPER 84-359] p 18 A85-13221 NAGLE-ESHLEMAN, J. Cost effective launch technology for communications Report of the Transportation Panel The Shock and Vibration Digest, volume 16, no 11 satellites p57 N85-20364 [AD-A148466] p 16 N85-17382 [IAF PAPER 84-04] p50 A85-12979 NAGY, K MOERTBERG, B. Space Station truss structures and construction Structural design and thermal stability of TELE-X antenna tower P 15 N85-14016 considerations [NASA-TM-86338] p 15 N85-15796 MOHR, D. G. Design study of an integrated aerobrakmg orbital transfer PACK, G. J Expenmental measurements of matenal damping in free vehicle Demonstration of transparent solar array module fall with tunable excitation p 20 A85-18692 [NASA-TM-58264] p9 N85-21262 design MOLETTE, P NAKAI, E. [NASA-CR-174257] p 47 N85-16302 Architecture and implementation of an morbit Vibration analysis of a multipurpose platform PAILLOUS, A. infrastructure [NAL-TR-803] p27 N85-18078 Space environment simulation to test satellite thermal [IAF PAPER 84-29] p6 A85-12995 NAKAI, J. H. control coatings, volume 1 MONTGOMERY, R C Mass properties analysis and control of advanced space [CERT-4128-VOL-1] p 16 N85-17012 Structural control research and experiments at structures through computerized integration with design PAOLOZZI, A. NASA/LaRC p 22 A85-22587 and structural analysis Heat conduction problems in large space structure Adaptive modal control of structural dynamic systems [SAWE PAPER 1527] p 13 A85-18812 [IAF PAPER 84-400] p 13 A85-13253 using recursive lattice filters p 23 A85-26435 NAYFEH, A. H PAPAZIAN, H MOORE, J W Shear deformation plate continua of large Evaluation and prediction of long-term environmental The future of space flight p 2 A85-16109 double-layered space structures p 8 N85-10391 effects of nonmetallic matenals MOREA, S. F NELSON, W G. [NASA-CR-171353] p 39 N85-19137 Advanced research and technology programs for Impacts of life support system on space station design PARISH, R. C advanced high-pressure oxygen-hydrogen rocket [IAF PAPER 84-166] p6 A85-13100 Thermal management technology status propulsion NERHEIM, C S. p 14 N85-13895 [NASA-TM-86969] p 50 N85-21231 Solar concentrator for space power generation Heat rejection working group synopsis [AIAA PAPER 85-0164] p 45 A85-19561 MORGAN, T H p 15 N85-13906 NESA.J Preliminary design of an Earth-based debns detection PARK, C system using current technology and existing Technology and performances of structural thermal Determination of atmosphenc density using a mechanical equipment used for antenna of TV SAT-TDF installations p40 N85-21199 space-launched projectile 1 program p 15 N85-14012 [AIAA PAPER 85-0327] p2 A85-20866 MORGANTI, F. NESTE, S. L. PARKINSON, R C Influence of the lamination and of some environmental In situ orbital debns expenment concepts Utilization and economics of a European low earth orbit effects on damping characteristics of advanced p58 N85-21198 Space Platform composites for space structures NICOGOSSIAN, A. [IAF PAPER 84-57] p 1 A85-13016 [IAF PAPER 84-405] p 36 A85-13258 Assessment of medical nsk in space flight PARMLEY, R T. The dimensional stability of advanced composite [IAF PAPER 84-189] p 51 A85-13114 Passive Orbital Disconnect Strut (PODS 3) structural test antenna reflectors Analytical and test evaluation NIGAM, A. K program p39 N85-14014 Effect of neutron and proton irradiation on some [NASA-CR-177325] p 16 N85-17020 MORIO, G properties of Kapton p 37 A85-21508 PEARSON, J. Technology and performances of structural thermal NIGHTINGALE, R W Active vibration control for lasers and spacecraft mechanical equipment used for antenna of TV SAT-TDF SCATHA (spacecraft charging at high altitudes) plasma p 21 A85-22584 1 program p 15 N85-14012 interaction expenment SC-3 high energy particle The Satellite sail p 49 N85-20376 MORRIS, W D spectrometer; SC-8 energetic ion composition PELISCHEK, T Orbit-on-demand vehicles - Mission possible, but expenment Space Station truss structures and construction one-day turnaround? p 53 A85-24790 [AD-A149728] p 35 N85-21252 considerations MORY, R. NOOSHIN, H [NASA-TM-86338] p 15 N85-15796 European retrievable earner (Eureca) and evolutionary Formex configuration processing in structural PEPLINSKI, D R space earner for microgravity, Earth observation and engmeenng p 14 A85-20916 Kinetics of oxygen interaction with matenals technology demonstration p 55 N85-11032 NOVELLINO, A. [AIAA PAPER 85-0472] p 37 A85-19770 MOVE, J. E. Development of advanced composite tubular structures PETITJEAN, L Spacelab Hitchhiker, a quick reaction earner for antenna reflector p 10 A85-24817 Satellite grasping manipulator system [AIAA PAPER 85-0504] p 53 A85-19795 NOVELLINO, A. D [IAF PAPER 84-371] p 41 A85-13229 MUCCIANTE, l_ Influence of the lamination and of some environmental PETRIVELLI, A. Influence of the lamination and of some environmental effects on damping charactenstics of advanced Bipropellant propulsion in the new generation of effects on damping charactenstics of advanced composites for space structures satellites and upper stages The role of BPD Difesa-Spazio composites for space structures [IAF PAPER 84-405] p 36 A85-13258 in this field - Manufactunng facilities and technology [IAF PAPER 84-405] p 36 A85-13258 p43 A85-12519 MUELLER, A. C PETTEX, J L, The long term behaviour of Earth orbits and the Technology and performances of structural thermal mechanical equipment used for antenna of TV SAT-TDF implications for debns control p 58 N85-21213 OGLEVIE, R E MUELLER, G 1 program p 15 N85-14012 Integrated Power and Attitude Control Systems for PETYT, M Space - The future of mankind p 3 A85-25697 Space Station MULLER, R. M. The improvement of free-mode methods in component [AIAA PAPER 85-0358] p 31 A85-19695 mode synthesis techniques and its accuracies Application Number 3 Using tethers for attitude Dynamics and controls working group summary control p27 N85-20373 p 17 A85-12442 p26 N85-13854 PICKERING, C. MUROZONO, M Perspectives on energy storage wheels for space station Torsional vibration of booms with open cross section Power subsystem automation study application p47 N85-13860 [NASA-CR-171213] p 33 N85-12299 caused by unidirectional radiant heating OHKAMI, Y p22 A85-26350 PINSON, C C. A space station expenment on large antenna assembly Spectral charactenstics of radar echoes from MURPHY, J P and measurement - A follow-on study Science Applications, part 2 p 6 N85-20347 aircraft-dispensed chaff p 23 A85-26606 [IAF PAPER 84-58] p 41 A85-13017 PINSON, L. D. MURRAY, N. D. Poles and transmission zeros of flexible spacecraft Wavelength division multiplexing for future Space Station Large space structures ground and flight progress control systems p22 A85-26433 [IAF PAPER 84-388] p 13 A85-13243 data systems p 32 A85-25359 Vibration analysis of a multipurpose platform PISARENKO, G S. MUZI, D [NAL-TR-803] p 27 N85-18078 Study of structure control dynamic interaction for radio Expenmental study of the effect of the type of stress OHTOMO, I frequency antenna control systems p26 N85-14020 state on plastic strain in structural matenals at low A space station expenment on large antenna assembly temperatures p 37 A85-16499 and measurement - A follow-on study PITTMAN, R. N [IAF PAPER 84-58] p 41 A85-13017 A modular approach to developing a large deployable OKAMOTO, K. reflector p7 A85-22685 NADER), F. A space station expenment on large antenna assembly PITTS, D. E. NASA's mobile satellite communications program, and measurement - A follow-on study A case for Gohrem - Geosynchronous orbit high ground and space segment technologies [IAF PAPER 84-58] p 41 A85-13017 resolution earth monitonng p 50 A85-10261 [IAF PAPER 84-84] p 29 A85-13040 OLMSTEAD, D PODNAR, G NAFTEL.J C The international environment UNISPACE '82 and the A functional vehicle for autonomous mobile robot Performance assessment of aero-assisted orbital ITU A relationship between orbit-spectrum resource research transfer vehicles p 56 N85-16993 allocation and orbital debns p 58 N85-21215 [AD-At 50052] p 42 N85-21666

B-6 PERSONAL AUTHOR INDEX SHRIVASTAVA, S. K.

PONTOPPIDAN, K. RICE.E.E. SCHNEIDER, W Electrical consequences of mechanical antenna Preliminary analysis of space mission applications for Space Station truss structures and construction characteristics p33 N85-14008 electromagnetic launchers considerations POOL.S. (NASA-Cfl-174067] p 47 N85-12071 [NASA-TM-86338] p 15 N85-15796 Assessment of medical risk in space flight ROBERTS, B. B. SCHOENMAN, l_ [IAF PAPER 84-189] p 51 A85-13114 Design study of an integrated aerobraking orbital transfer Aeroiet advanced engine concept p48 N85-16999 popp.a vehicle SCHUBERT, F H. Mechanical/thermal design of a polanzation sensitive [NASA-TM-58264] p9 N85-21262 Engineering model system study for a regenerative fuel reflector p 15 N85-14009 ROCHE, J. C. cell Study report POTAPENKO, E. U. Computer simulation of plasma electron collection by [NASA-CR-174801] p 47 N85-16292 The dynamics of the attitude control and stabilization PIX-II SCHULZ.H. systems of spacecraft with a controlled gravity gradient (AIAA PAPER 85-0386] p 45 A85-19715 Henusphencal antenna pointing mechanism p26 N85-14021 stabilizer p 23 A85-28903 ROSEN, J. POULEK.V Effects of space environmental conditions on graphite SCOTT, C D Design study of an integrated aerobraking orbital transfer In-orbit laser regeneration of the radiation damaged solar epoxy composites p36 A85-15990 arrays vehicle ROSENBERG, S. D [NASA-TM-58264] p9 N85-21262 [IAF PAPER 84-62] p 43 AB5-13021 Integratable propulsion systems for the Space Station POWELL, R W. p46 A85-23393 SEEHRA.S. Effects of space environmental conditions on graphite Performance assessment of aero-assisted orbital ROSENTHAL.D epoxy composites p36 ASS-15990 transfer vehicles p56 N85-16993 Experiments in control of flexible structures with PRICE, l_ R. uncertain parameters p 24 N85-13837 SEIBERT, G. European retnevable carrier (Eureca) and evolutionary Impacts of life support system on space station design RUDGE, A. W [IAF PAPER 84-166] p6 A85-13100 space carrier for microgravity. Earth observation and Sky-hooks, fish-warmers and hub-caps - Milestones in technology demonstration p55 N85-11032 satellite communications p 32 A85-25101 SEIZ, W RUDOLPH, l_ K. Inflatable space-ngidaed structures - Recent Design and benefits of pulsed MPD thruster orbit transfer developments of the matenal technology vehicles p 44 ASS-16448 QUINN, J. M. [IAF PAPER 84-384] p 10 A85-13240 RUM, G SELTZER, S. M. SCATHA (spacecraft charging at high altitudes) plasma Report of the Constellations Panel p 27 N85-20368 interaction experiment SC-3 high energy particle NASA/MSFC ground experiment for Large Space RUNAVOT, J. J. spectrometer; SC-8 energetic ion composition Structure control verification Satellite grasping manipulator system expenment [AIAA PAPER 85-0115] p 21 A85-19528 [IAF PAPER 84-371] p 41 ASS-13229 [AD-A149728] p 35 N85-21252 NASA-VCOSS dynamic test facility RUPP, C [NASA-TM-86491] p 27 N85-18998 Tether fundamentals p 57 IM85-20345 NASA/MSFC ground expenment for large space RYAN, R S. structure control verification Keynote address p 27 N85-18378 [NASA-TM-86496] p 28 N85-21248 RAI, V. N ACOSS 17 (Active Control of Space Structures) Effect of neutron and proton irradiation on some [AD-A150007] p28 N85-21253 properties of Kapton p 37 A85-21508 SEVRUK, D D RAINE, H R The cost effectiveness and optimal parameters of an Some results of the MSAT phase B studies and their SABROFF, A. E. electric rocket propulsion system for an interorbital impact on system design Space station/space platform system design transport vehicle p 46 A85-23990 considerations p 7 A85-14429 [IAF PAPER 84-89] p 1 AB5-13045 SEWY, D RAJARAM, S. SADUNAS, J. A. Power subsystem automation study Identification of vibration parameters of flexible Thermal storage analysis for large manned space [NASA-CR-171213] p33 N85-12299 platforms structures p 27 N85-18360 SGUBINI, S. [AIAA PAPER 85-0066) p 14 ASS-19493 RAMBAUT, P. Elastic waves propagation in bounded penodic Assessment of medical nsk in space flight SALOMONSON, V V. structures [IAF PAPER 84-189] p 51 A85-13114 A case for Gohrem - Geosynchronous orbit high [IAF PAPER 84-395] p 19 A85-13249 resolution earth monitoring p 50 A85-10261 RANDALL, D P. Elastic dispersion effects on dynamics and control of SMP A solid modeling program SAMBONGI, S. large modular antennas p26 N85-14019 Poles and transmission zeros of flexible spacecraft [NASA-Cfl-172473] p8 N85-11570 SHARP, R D. control systems p 22 A85-26433 RANDOLPH, R L. SCATHA (spacecraft charging at high altitudes) plasma Producing gallium arsenide crystals in space SANTINI, P interaction expenment SC-3 high energy particle p54 N85-11023 Heat conduction problems in large space structure spectrometer; SC-8 energetic ion composition RAPP, H [IAF PAPER 84-400] p 13 A85-13253 expenment Kevlar and T300 fabric prepregs - Their material SARYCHEV, V A. [AD-A149728] p 35 N85-21252 properties and their use in high loaded areas of a solar Effect of aerodynamic moment on the regime of the SHARPLES, R E. array gravity gradient stabilization of the Salyut-6 - Soyuz orbital Space station/space platform system design [IAF PAPER 84-402] p 35 A85-13255 system p 23 A85-28488 considerations p 7 A85-14429 RATH, J. SAUERS, R. SHELLEY, E G. Design and technology trends on large solar arrays for Power subsystem automation study SCATHA (spacecraft charging at high altitudes) plasma space stations [NASA-CR-171213] p33 N85-12299 interaction expenment SC-3 high energy particle [IAF PAPER 84-37] p 43 A85-13000 SAZOROV, V V spectrometer; SC-8 energetic ion composition RECK, R. J Effect of aerodynamic moment on the regime of the expenment Dynamic charactenstics of a space reflector support gravity gradient stabilization of the Salyut-6 - Soyuz orbital [ AD-A149728] p 35 N85-21252 structure p22 A85-24949 system p23 A85-28488 SHENK, W REGEL, l_ l_ SAZYKIN, B. V A case for Gohrem - Geosynchronous orbit high Material sciences in space p36 A85-13500 Multicntical optimization of a large space structure resolution earth monitoring p 50 A85-10261 p11 A85-28489 REHDER, J. J. SHEPHERD, R Performance assessment of aero-assisted orbital SCHAEFER, B. Dynamic characteristics of a space reflector support transfer vehicles p 56 N85-16993 Dynamical modelling of a gravity-loaded rectangular structure p 22 AB5-24949 REIBALDI, G. G. plate as a test configuration for attitude control of large SHESKIN, T. J Inflatable space-ngidized structures - Recent space structures An unmanned platform as an initial capability in space [IAF PAPER 84-391 ] p 18 A85-13245 developments of the material technology p52 A85-16305 [IAF PAPER 84-384] p 10 A85-13240 SCHAEFER, W SHININ, V K. Antenna mechanical technologies within ESA Offset unfurlable antenna concepts p5 N85-14002 The cost effectiveness and optimal parameters of an p11 N85-14000 Mechanical/thermal design of a polarization sensitive electnc rocket propulsion system for an interorbital reflector p 15 N65-14009 REID, R. C. transport vehicle p46 A85-23990 SCHARTEL.W A. Design study of an integrated aerobraking orbital transfer SHINN.J l_ Operational fitness of box truss antennas in response vehicle Chemical nonequilibnum effects on flowfields for to dynamic slewing [NASA-TM-58264] p9 N85-21262 aeroassisted orbital transfer vehicles p 53 A85-21831 [NASA-CR-172470] p 27 N85-19012 REPIC, R. A. SCHATZ.M. SHORE, C. P Modular computer system cuts spacecraft simulation Performance capabilities of the 12-centimeter Xenon ion Reduction method for thermal analysis of complex costs p 10 ASS-18435 thruster p44 ASS-16439 aerospace structures REPPUCCI, G. M. scHurrz,E. [NASA-TP-2373] p 15 N85-16066 Space power management and distribution status and Precise control of flexible manipulators SHRINET, V trends p47 N85-13896 [NASA-CR-174210] p42 N85-16178 Effect of neutron and proton irradiation on some RESS.R. SCHMITZ,W properties of Kapton p 37 AB5-21508 Simulation of reusable ctslunar space transportation Development of a foldlme concept lor automatic SHRIVASTAVA, S. K. systems with special consideration of chemical refolding of a flexible blanket (folding analysis) Flexural vibration of gravity-stabilized, structurally propulsion p44 AB5-15874 [ESA-CR(P)-1933] p 12 N85-17428 damped, large flexible satellites p 22 A85-26434

B-7 SHTYRLIN, A. F. PERSONAL AUTHOR INDEX

SHTYRLIN, A. F Environmental interactions working group report THOMPSON, B E The cost effectiveness and optimal parameters of an p5 N85-13908 The low cost development, test, and production of a electric rocket propulsion system for an mterorbital STEWARD, D A. commercial STS upper stage TOS transport vehicle p 46 A85-23990 Catalytic surface effect on ceramic coatings for an [AIAA PAPER 85-0313] p 45 A85-19660 SIEMERS, P aeroassisted orbital transfer vehicle p 38 A85-29730 THOMPSON, D W Technology and test p 57 N85-20353 STOEWER, H. TOS and AMS - Amenca's new capabilities in space Summary presentation of the technology and test Onentation and trends in European technology transportation panel p 57 N85-20360 [IAF PAPER 84-377] p2 A85-13233 [IAF PAPER 84-220] p 51 A85-13141 STONE, H W Report of the Technology and Test Panel TICE, S E p57 N85-20370 Performance assessment of aero-assisted orbital Modular computer system cuts spacecraft simulation transfer vehicles p 56 N85-16993 costs p 10 A85-18435 SILVI, M STONE, N H An optimal shape control of a large flexible radiator in TIETZ.J C Electrodynamic interactions p 34 N85-20348 space Power subsystem automation study Summary presentation of the Electrodynamics [NASA-CR-171213] p 33 N85-12299 [ IAF PAPER 84-64] p 18 A85-13023 Interactions Panel p 34 N85-20356 TOKI, K SIRMAIN, C Report of the Electrodynamic Interactions Panel Oeployable reflector antennas - Mechanical design of p34 N85-20363 Partial bleed expander cycle for low thrust LOX/LH2 rocket engine the reflective surface STOROZHENKO, V A. [NAL-TR-837T] p 49 N85-19018 [IAF PAPER 84-393] p6 A85-13247 Stability of the rotation of a body suspended by means SKAAR, S B of a system of rods connected in senes TOLLISON, D. K Closed form optimal control solutions for continuous p23 A85-28906 NASA/MSFC ground experiment for Large Space linear elastic systems p20 A85-18672 STRUB, H Structure control venfication SLAVINSKAS, D D The German remote sensing program [AIAA PAPER 85-0115] p 21 A85-19528 Efficient inclination control for geostationary satellites p52 A85-16881 Definition of ground test for venfication of large space [AIAA PAPER 85-0216] p 21 A85-19595 STUART, D G. structure control SMITH, A. C An economic analysis of humans and machines for [NASA-CR-171208] p9 N85-13838 A review of contamination issues associated with an space construction Ground test expenment for large space structures, orbiting Space Station external environment [IAF PAPER 84-232] p 51 A85-13148 appendix I p 56 N85-13847 p38 A85-24703 SU, S Y Ground test expenment for large space structures SMITH, D. G. Orbital Debns [NASA-TM-86489] p9 N85-19013 Debns impact on Earth-orbiting spacecraft [NASA-CP-2360] p40 N85-21188 Active control of large space structures An introduction p59 N85-22234 SUDDETH, D H. and overview SMITH, G D Debns in the geostationary orbit ring, the endless [NASA-TM-86490] p 27 N85-19014 shooting gallery The necessity for a disposal policy Effects of member imperfections on the behavior of NASA/MSFC ground expenment for large space p58 N85-21214 space trusses p11 N85-11363 structure control venfication SUM), S SNYDER, D B [NASA-TM-86496] p 28 N85-21248 Torsional vibration of booms with open cross section Charactenstics of arc currents on a negatively biased Definition of ground test for Large Space Structure (LSS) caused by unidirectional radiant heating solar cell array in a plasma p31 A85-18608 control venfication The effect of plasma on solar cell array arc p22 A85-26350 [NASA-TM-86495] p 28 N85-21249 Charactenstics SUN, C T [AIAA PAPER 85-0384] p 31 A85-19713 Continuum modelling of damping in large space ACOSS 17 (Active Control of Space Structures) SOLPANELU, G structures p 18 A85-12478 [AD-A150007] p28 N85-21253 TOUSSAINT, M IRIS Spinning Stage - A pengee stage for satellites up SUNDARARAJAN, N to 900 kg to be launched from the Space Shuttle with Adaptive modal control of structural dynamic systems Future prospects in space envisaged by a forum of European space companies p 52 A85-16302 the IRIS system p43 A85-12520 using recursive lattice filters p 23 A85-26435 TRUNDLE, C SOMMER, W F SUTTON, K Radiaton effects in matenals - Field-ion microscope Report of the Technology and Test Panel Advanced analysis methods for spacecraft composite charactenzations p 37 A85-24675 p 57 N85-20370 structures p 37 A85-15993 SONOYAMA, S SUZUKI, K. TRUSCELLO, V C. Design consideration of space construction facility Vanable geometry truss and its application to deployable Nuclear-electnc power in space p 30 A85-15812 TURNER, J D [IAF PAPER 84-26] p 6 A85-12992 truss and space crane arm Closed-form solutions for feedback control with terminal SOUCY, Y [IAF PAPER 84-394] p 10 A85-13248 Modelling and identification of the structural properties SWAIM, R J. constraints p 20 A85-18331 of an astromast Toroid Joining Gun TYREE, E [CRC-1374] p 12 N85-18352 [SAE PAPER 850408] p 38 A85-25988 The effect of plasma on solar cell array arc SPEAR, E E SWAN, P. Charactenstics [AIAA PAPER 85-0384] p 31 A85-19713 Graphite epoxy structure of the Space Telescope's Report of the Constellations Panel p 27 N85-20368 optical telescope assembly p 36 ASS-15980 SWENSON, B SPOFFORD.J R A modular approach to developing a large deployable Neutral buoyancy evaluation of technologies for space reflector p 7 A85-22685 u station external operations UEBELHACK, H T [IAF PAPER 84-38] p 41 A85-13001 Lay-out of a re-usable re-entry vehicle required in a future SPYRAKOS, C C European low earth orbit scenario Generalized transform methods based finite element TADAKAWA, T [IAF PAPER 84-06] p 50 A85-12981 methodology - Thermal/structural dynamic applications USSHER, T. H. [AIAA PAPER 85-0155] p 14 A85-19553 Vibration analysis of a multipurpose platform [NAL-TR-803] p 27 N85-18078 An overview of the space remote manipulator system ST CLAIR, A. K p42 N85-16964 Process for prepanng essentially colorless polyimide film TALAY, T A. containing phenoxy-lmked diamines Orbit-on-demand vehicles - Mission possible, but [NASA-CASE-LAR-13353-1] p 40 NB5-20128 one-day turnaround? p 53 A85-24790 ST CLAIR, T l_ Performance assessment of aero-assisted orbital Process for prepanng essentially colorless polyimide film transfer vehicles p 56 N85-16993 VAJRAVELU, K containing phenoxy-lmked diamines TAMMA, K. K. Space frame design, development and optimization of [NASA-CASE-LAR-13353-1] p 40 N85-20128 Generalized transform methods based finite element antenna platform structure for a mobile 3D radar STAHLE, C V methodology - Thermal/structural dynamic applications p 8 A85-24908 Application of damping to spacecraft structures [AIAA PAPER 85-0155] p 14 A85-19553 VALLERAIN, E TAN, H S p20 A85-15992 Space station related investigations in Europe Geometrically nonlinear analysis of space frames by an STALEY, J A. [IAF PAPER 84-28] p 50 A85-12994 Application of damping to spacecraft structures incremental iterative technique p 14 A85-19895 VALLERANI, E p20 ASS-15992 TAYLOR, P Space exploitation - Spacelab an easy approach for STARK, P M Design study of an integrated aerobrakmg orbital transfer developing countnes Prospectives and suggestions by Concept for a commercial space station laboratory vehicle Aentalia p 1 ASS-12502 [NASA-TM-58264] p 9 N85-21262 . p4 N85-11035 Report of the Transportation Panel Doing business in space How to get there from here TAYLOR, R S p 57 N85-20364 p55 N85-11057 Report of the Electrodynamic Interactions Panel VAN DUINEN, R J. p34 N85-20363 STEELS, R. The communication-satellite market to the year 2000 Development and application of new technologies in TAYLOR, T. C p3 A85-26771 ESA's Ofympus programme p 3 A85-27695 Cost effective launch technology for communications VANDENKERCKHOVE, J A. STEPHENSON, F satellites Mass optimisation of telecommunications satellites NASA OAST perspective p5 N85-16990 [IAF PAPER 84-04] p 50 A85-12979 [IAF PAPER 84-230] p 13 A85-13146 STERN, S. A. Construction of large precision reflectors using the Aft VANDER VELDE, W E. A rectilinear guidance strategy for short orbital Cargo Camer Number and placement of control system components transfers p 52 A85-15509 [IAF PAPER 84-389] p 2 A85-13244 considenng possible failures p 19 ASS-13634 STEVENS, N J TENNEY, D R VANKE, V A. Environmentally-induced voltage limitations in large Report of the Technology and Test Panel Effect of phase fluctuations in an incident beam on the space power systems p 31 A85-18584 p 57 N85-20370 Charactenstics of a rectenna system p30 A85-15760

B-8 PERSONAL AUTHOR INDEX ZONDERVAN, K. P.

VAUGHAN, W W. WEISS, W WOOD, P W Natural environment design criteria for the Space Station Kevlar and T300 fabnc prepregs - Their material Concept for a commercial space station laboratory definition and preliminary design properties and their use in high loaded areas of a solar p4 N85-11035 (NASA-TM-86498) p9 N85-21232 array Doing business in space How to get there from here VEREZ.B [IAF PAPER 84-402] p 35 A85-13255 p55 N85-11057 Technology and performances of structural thermal WELOON, V A. WOOLF.N J mechanical equipment used for antenna of TV SAT-TDF Vehicle/engine integration p48 N85-17008 Deployable reflector configurations p 2 A85-22577 1 program p 15 N85-14012 Orbital transfer vehicle propulsion issues WORLEY, H. E. VETRELLA.S. p48 N85-17009 ACOSS 17 (Active Control of Space Structures) Factors affecting push-broom performances in future [AD-A150007] p28 N85-21253 WELLS, W. H space platforms WYNVEEN, R. A. Modal control of structural systems [IAF PAPER 84-116] p29 A85-13066 [AD-A149734] p 28 N85-21235 Engineering model system study for a regenerative fuel VIDAL, C. cell Study report ARABSAT spacecraft. Rx and Tx antenna WELTI, G. R [NASA-CR-174801] p 47 N85-16292 Some design concepts for Intelsat VII mechanisms p 34 N85-14022 VIGERON, F R. p 7 A85-15496 Damping synthesis for a spacecraft using substructure WESSELSKI, C. and component data Space Station truss structures and construction [CRC-1365] p24 N85-12082 considerations YAKUT, M. M VIGNERON, F R [NASA-TM-86338] p 15 N85-15796 Impacts of life support system on space station design Modelling and identification of the structural properties WEST-VUKOVICH, G S. [IAF PAPER 84-166] p6 ASS-13100 of an astromast The decentralized control of large flexible space YAMANAKA, T [CRC-1374] p 12 N85-18352 structures p 17 A85-10071 Design consideration of space construction facility VIGNOU, M. WESTPHAL, W. [IAF PAPER 84-26] p6 A85-12992 Satellite module design p 9 N85-20344 Design and technology trends on large solar arrays for YANG, W VILLA, M. L. space stations Finite multiple bum orbit transfer error analysis via Satellite grasping manipulator system [IAF PAPER 84-37] p 43 A85-13000 covanance matrix p 45 A8S-22444 YGLESIAS, J [IAF PAPER 84-371 ] p 41 ASS-13229 WHITE, N H VINOPAL, T J. Performance assessment of aero-assisted orbital Report of the Transportation Panel Vehicle/engine integration p48 N85-17008 transfer vehicles p 56 N85-16993 p57 N85-20364 VONFLOTOW, A. H. WHITE, T W Disturbance propagation in structural networks, control The low cost development, test, and production of a of large space structures p26 N8S-14856 commercial STS upper stage TOS VONOFENHEIM, W. H [AIAA PAPER 85-0313] p 45 A85-19660 ZELON, J L. SMP A solid modeling program WIENSS, W Modular computer system cuts spacecraft simulation [NASA-CR-172473] p8 N85-11570 Space station related investigations in Europe costs p 10 ASS-18435 VONTIESENHAUSEN, G [IAF PAPER 84-28] p 50 ASS-12994 ZONDERVAN, K. P Report of the Constellations Panel p 27 N85-20368 WIESEL, W E Optimal low-thrust, three-bum orbit transfers with large VORBRUGG, H Optimal electnc propulsion orbit transfer vehicle design plane changes p 44 A85-18671 Off set unfurlable antenna concepts pS N85-14002 and operational effectiveness VOS, R G [AIAA PAPER 85-0431 ] p 45 A85-19744 IAC user manual WILHITE, A. W [NASA-CR-175300] p8 N85-10677 Performance assessment of aero-assisted orbital transfer vehicles p 56 N85-16993 WILLCOCKSON, W H W Flight operation considerations for an aero-braked OTV WAGNER, R [AIAA PAPER 85-0220] p 54 A85-26385 Technology for the ERS-1 SAR antenna WILLIAMS, F p33 N8S-14008 Summary presentation of the Constellations Panel WAtTES, H. B p 57 N85-20359 NASA/MSFC ground experiment for Large Space Report of the Constellations Panel p 27 N85-20368 Structure control verification WILLIAMS, F W tAIAA PAPER 85-0115] p 21 A85-19528 Evaluation of efficiently computed exact vibration Ground test experiment for large space structures, charactensucs of space platforms assembled from stayed appendix I p56 N85-13847 columns p 13 ASS-12884 NASA-VCOSS dynamic test facility WILLIAMS, J P [NASA-TM-86491] p 27 N85-18998 Adaptive modal control of structural dynamic systems using recursive lattice filters p 23 A85-26435 Ground test expenment for large space structures WILLIAMS, T [NASA-TM-86489] p9 N85-19013 Attitude control system and communications payload for Active control of large space structures An introduction an amateur solar sail spacecraft and overview [IAF PAPER 84-363] p 29 A85-13224 [NASA-TM-86490] p 27 N85-19014 WILLIAMSON, S E. NASA/MSFC ground expenment for large space A signed switching time bang-bang attitude control law structure control verification for fine pointing of flexible spacecraft p 19 A65-13893 [NASA-TM-86496] p 28 N85-21248 WILLSHIRE, K F Definition of ground test for Large Space Structure (LSS) Human response to vibroacoustic environments of control verification space vehicles [NASA-TM-86495] p 28 N85-21249 [NASA-TM-86316] p 54 N85-10789 WAKAMATSU, Y WILSON, J F Partial bleed expander cycle for low thrust LOX/LH2 Determination of atmosphenc density using a rocket engine space-launched proiectile [NAL-TR-837T] p 49 N85-19018 [AIAA PAPER 85-0327] p 2 A85-20866 WALBERG, G. D WILSON, M L. A survey of aeroassisted orbit transfer Pultrusion process for fabrication of tethers (preliminary p 53 A85-21826 concepts) p 40 N85-20371 WALL, J. A. WISKERCHEN, M Dielectric material in the space environment Environmental interactions working group report p5 N85-13908 p37 A85-24672 WALTERS, S. wirrc,i_c Characterization of heat transfer in nutnent materials Synergy in space - Man-robot cooperation [NASA-CR-171841] p56 N85-17551 p 41 A85-20400 WONG, R. E. WANG, Z.W Satellite servicing A business opportunity? The improvement of free-mode methods in component p55 N85-11056 mode synthesis techniques and its accuracies WOOD, G. p17 A85-12442 Report of the Technology and Test Panel WATSON, J J p57 N85-20370 Swing-arm beam erector (SABER) concept for single WOOD, G. M astronaut assembly of space structure Instrumentation for Application Number 1 Mass [NASA-TP-2379] p 42 N8S-19015 spectrometnc analysis of the boundary layer associated WEBER, W J with the tethered satellite p 58 N8S-20372 NASA's mobile satellite communications program, WOOD, L. J. ground and space segment technologies Optimal low-thrust, three-bum orbit transfers with large [IAF PAPER 84-84] p 29 A85-13040 plane changes p44 A85-18671

B-9 CORPORATE SOURCE INDEX

TECHNOLOGY FOR LARGE SPACE SYSTEMS / A Bibliography (Supplement 13) MARCH 1986

Typical Corporate Source Index Listing

Efficient structures for geosynchronous spacecraft solar Committee on Science and Technology (U. S. House). CORPORATE SOURCE arrays International cooperation and competition in space [NASA-CR-174448] p 12 N85-19004 [GPO-38-O01] p4 N85-11911 Auburn Unhr, Ala. Communications Research Centre, Ottawa (Ontario). The computer-communication link for the innovative use Damping synthesis for a spacecraft using substructure of Space Station p 32 N85-11016 and component data [CRC-1365] p24 N85-12082 Modelling and identification of the structural properties Ufa System*, Inc., Cleveland, Ohio B of an astromast P_ Engineering model system study for a regenerative fuel [CRC-1374] p 12 N85-18352 cell Study report Battelle Columbus Labs, Ohio Stability analysis of flexible spaceraft with PID [NASA-CR-174801] P47 N85-16292 Preliminary analysts of space mission applications for controller electromagnetic launchers [CRC-1372] p28 N85-21247 T [NASA-CR-174067] p 47 N85-12071 Computer Sciences Corp, Hampton, Va. Bendlx Corp, Tetertaoro. N J. SMP A solid modeling program Comparing attitude control effectiveness for actuators [NASA-CH-172473] p8 N85-11570| on two bodies of a six body model of a flexible spacecraft Connecticut Unhr, Storm. r with that for actuators restricted to a single body Effects of member imperfections on the behavior of I NASA TITLE REPORT PAGE p17 A85-11086 space trusses p 11 N85-11363 [ NUMBER NUMBER ACCESSION NUMBER Developing sensitivity coefficients for a state variable Conslgllo Nadonale delle Rlcerche, Rome (Italy). model of a flexible spacecraft with modular attitude TSS Satellite overview p5 N85-20343 | control P17 A85-11087 Construcclones Aeronautical &A, Madrid (Spain). Autonomous momentum management for the COG CASA technological effort in the field of antennas planar Space Station p33 N85-14010] [AIAA PAPER 65-0031 ] p 21 A8S-19468 Listings in this index are arranged alphabetically by CASA activities in antenna technology Modular design attitude control system p39 N85-14015] corporate source The title of the document is used [NASA-CR-171182] p 24 N85-10098 Contraves Corp, Zurich (Switzerland). to provide a brief description of the subject matter Autonomous momentum management for space station, Large spacebome antenna reflectors using inflatable I The page number and the accession number are exhibit A space ngidrzed structures p 12 NB5-14004 ' [NASA-CR-171256] p 33 N85-12933 Control Dynamic* Co, Huntavtlle, Ala. included in each entry to assist the user in locating Berry Coll, Mount Berry, Ga. NASA/MSFC ground experiment for Large Space the abstract in the abstract section If applicable, Evaluation of OMV ranging and docking systems p42 N85-22230 Structure control verification a report number is also included as an aid in [AIAA PAPER 85-0115] p 21 ASS-19528 Boeing Aerospace Co, Kent, Wash identifying the document IAC user manual Definition of ground test for verification of large space (NASA-CR-175300] p8 N85-10677 structure control Boeing Aerospace Co, Seattle, Wash [NASA-CR-171208] p9 N85-13838 Modular experimental platform for science and Level of effort p25 N85-13839 applications p11 N85-11031 Oral presentation of first year final report, appendix A Definition of technology development missions for early p25 N85-13840 space stations Large space structures Simplified planar model of ground test verification [NASA-CR-171209] p4 N85-12084 structure, appendix B p 25 N85-13841 AEG-Tetofunken, Wedel (West Germany) Potential of flywheels for spacecraft energy storage Elimination of uncontrollable ngid body mode, appendix Development of a foldlme concept for automatic p 33 N85-13890 C p25 N85-13842 refolding of a flexible blanket (folding analysis) Booz-Allen and Hamilton, Inc, Arlington, Va Speed test results and hardware/software study of [ESA-CR(P)-1933] p 12 N85-17428 Concept for a commercial space station laboratory computational speed problem, appendix D Aeritalla S4>A, Naples (Italy). p4 N85-1103S p25 N85-13843 Doing business in space How to get there from here Satellite module design p 9 N85-20344 Section 1 Method of determining mode shapes and p55 N8S-11057 Aeritalla S4>A, Torino (Italy). natural frequencies of the NASA unmodified test structure British Aerospace Dynamics Group, Stevenage Report of the Transportation Panel Section 2 Continuous beam closed from solution to the pS7 N85-20364 (England). NASA-LSS astromast torsnnal vibration, appendix E BAe antenna hardware technology for current satellite p25 N85-13844 Aerofe! Technical Systems Co, Sacramento, Calif. projects p9 N85-14011 Aerojet advanced engine concept p 48 N85-16999 Definition of ground test for Large Space Structure (LSS) Aerojet Techsystems Co, Sacramento, Calif control verification, appendix G p 25 N85-13845 Integratable propulsion systems for the Space Station Review of technical papers, appendix H P46 A85-23393 p25 N85-13846 Aerospace Corp, El Segundo, Calif CAE Electronic* Ltd, Montreal (Quebec). ACOSS 17 (Active Control of Space Structures) Assessment of satellite collision hazards by simulated Six degrees of freedom control with each hand? [AD-A150007] p28 N85-21253 p 42 N85-14492 sampling in space p40 N85-21195 Coming Glass Works, N Y. Aerospace Corp, Los Angeles, Cain California InsL of Tech, Pasadena. Inorganic composites for space applications Optimal low-thrust, three-bum orbit transfers with large Optimal low-thrust, three-bum orbit transfers with large p38 NB5-11047 plane changes p44 A85-18671 plane changes p44 A85-18671 Carnegie-Mellon Univ., Pittsburgh, Pa. Air Force Satellite Control Facility, Sunnyvale, Calif A functional vehicle for autonomous mobile robot Geosynchronous satellite collision avoidance research p58 N85-21197 [AD-A1500S2) p42 N85-21666 Department of the Air Force, Washington, D.C. Air Force Wright Aeronautical Lab*, Wright-Patterson Case Western Reserve Univ., Cleveland, Ohio. Determination of atmospheric density using a AFB.OMO. The effect of plasma on solar cell array arc space-launched projectile The Satellite sail p49 N85-20376 characteristics [AIAA PAPER 85-0327] p2 A85-20866 Anted Bendta Aerospace. Tetertaoro, N J [AIAA PAPER 85-0384) p 31 A85-19713 Deployable folded antenna apparatus Autonomous momentum management for space Cleveland State Unhr, Onto. [AD-O011503] p12 N85-21495 station Near-optimum design of GaAs-based concentrator [NASA-CH-174065] p 24 N85-12931 space solar cells for 80 C operation p30 A85-15800 Deut«che Forschung*- und Veraucnaanstatt fuer Lutt- Committee on Appropriation* (U. S. Senate). und Raumfahrt, Brunswick (West Germany). Arizona Unhr, Tucson. Influence of thermal cycling on the behavior of CFRP Deployable reflector configurations p 2 A85-22577 National Aeronautics and Space Administration p4 N85-10871 material for space structures p 39 N85-14013 Astro Research Corp, Carpmterta, Cattf Office of Technology Assessment p4 N85-10872 Deutsche Forachungs- und V*rsuch*an*tatt fuer Lutt- Large-diameter astromast development Committee on Commerce, Science, and Transportation und Raumtahrt, Cologne (West Germany). [NASA.CH-171201J P11 N85-12200 (U S. Senate). Control of large collector arrays. The SSPS High performance deptoyaWe antenna structures Commercial space launches experience pit N85-14001 (S-REPT-98-656) p6 N8S-2122S IDE8£001481] p34 N85-20553 C-1 Dornier-Werke G.m.b.H., Friedrichshafen (West Germany). CORPORA TE SOURCE

Domier-Werke G m.b.H, Friedrichshafen (West Martin Marietta Corp., Bethesda, Md Germany) Selected tether applications in space An analysis of Technology lor the ERS-1 SAP antenna Jet Propulsion Lab., California Inst of Tech, five selected concepts p33 N85-14008 Pasadena. [NASA-CR-171222] p 55 N85-12921 Draper (Charles StarK) Lab., Inc., Cambridge, Mass. Dynamic isolation of a spacecraft science platform via Martin Marietta Corp., Denver, Colo Closed-form solutions for feedback control with terminal momentum compensation p 17 A85-11082 Summary presentation of the Constellations Panel constraints p20 A85-18331 NASA's mobile satellite communications program, p 57 N85-20359 Integrated Power and Attitude Control Systems for ground and space segment technologies Massachusetts InsL of Tech, Cambridge Space Station [IAF PAPER 84-84] p 29 A85-13040 Neutral buoyancy evaluation of technologies for space [AIAA PAPER 85-0358] p 31 A85-19695 Nuclear-electnc power in space p 30 ASS-15812 station external operations High precision active nutation control of a momentum [IAF PAPER 84-38] p 41 A85-13001 biased spacecraft with flexible appendages Number and placement of control system components p 20 A85-18337 considenng possible failures p 19 A85-13634 Optimal low-thrust, three-bum orbit transfers with large plane changes p44 A85-18671 Experimental measurements of matenal damping in free European Space Agency, Paris (France). Integratable propulsion systems for the Space Station fall with tunable excitation p 20 A85-18692 European retrievable earner (Eureca) and evolutionary p46 A85-23393 McDonnell-Douglas Astronautics Co, Huntington space carrier for microgravity, Earth observation and Design of a nuclear electnc propulsion orbital transfer Beach, Calif technology demonstration p 55 N85-11032 vehicle p 46 A85-23394 The human role in space Volume 1 Executive European Space Agency European Space Research Satellite communication antenna technology summary and Technology Center, ESTEC, Noordwljk p 31 A85-23651 [NASA-CR-171223] p 56 N85-13473 (Netherlands) Survey of deployable antenna concepts Messerechmitt-Boelkow-Blohm GmbH., Munich (West Antenna mechanical technologies within ESA p 10 A85-23663 Germany). p 11 N8S-14000 Dielectnc matenal in the space environment Mechanical/thermal design of a polarization sensitive Study of structure control dynamic interaction for radio p37 A85-24672 reflector p 15 N85-14009 frequency antenna control systems p 26 N85-14020 Demonstration of transparent solar array module Messerschmltt-Boelkow-Blohm GmbH, Ottobrunn European Space Conference, Paris (France) design (West Germany) Workshop on Mechanical Technology for Antennas [NASA-CR-174257] p 47 N85-16302 Offset unfuriable antenna concepts p 5 N85-14002 [ESA-SP-225] p11 N85-13999 Active cooling requirements for propellant storage Microgravity Research Associates, Inc., Coral Gables, p48 N85-17004 Fla Investigation of welded interconnection of large area Producing gallium arsenide crystals in space wraparound contacted silicon solar cells p54 N85-11023 [NASA-CR-174438] p 39 N85-19519 General Dynamlcs/Convalr, San Diego, Calif Compensator development and examination of Develop and demonstrate manufacturing processes for performance and robustness N fabncatmg graphite filament reinforced polymide (Gr/PI) [NASA-CR-175470] p 34 N85-20244 composite structural elements Joint Publications Research Service, Arlington, Va National Academy of Sciences - National Research [NASA-CR-172497] p 39 N85-20019 Commercial space Europe should have independent Council, Washington, D C General Electric Co, Falrfleld, Conn. strategy p 5 N85-19205 Computer integration of engmeenng design and In situ orbital debris expenment concepts West Europe report Science and technology production A national opportunity p58 N85-21198 [JPRS-WST-85-008] p 57 N85-20174 [NASA-CR-175483] p 59 N85-21414 General Research Corp., McLean, Va National Aeronautics and Space Administration, Proceedings of a Workshop on Applications of Tethers Washington, D C in Space, Executive Summary K NASA's mobile satellite communications program, [NASA-CR-171195] p 55 N85-12075 ground and space segment technologies Proceedings of a Workshop on the Applications of Kentron International, Inc, Hampton, Va [IAF PAPER 84-84] p 29 A85-13040 Tethers in Space, Volume 1 Orbit-on-demand vehicles - Mission possible, but Assessment of medical nsk in space flight [NASA-CR-171196] p 55 N85-12076 one-day turnaround? p 53 A85-24790 [IAF PAPER 84-189] p 51 A85-13114 Proceedings of a Workshop on Applications of Tethers Applications of space tethers in Space, Volume 2 [IAF PAPER 84-436] p 51 A85-13276 [NASA-CR-171197] p 55 N85-12077 The future of space flight p2 A85-16109 The NASA MLA program p 52 A85-17573 Applications of Tethers in Space Spacelab Hitchhiker, a quick reaction earner [NASA-CP-2366] p 59 N85-21659 Lite Systems, Inc., Cleveland, Ohio [AIAA PAPER 85-0504] p 53 A85-19795 Goodyear Aerospace Corp, LJtchfield Park, Ariz. Engmeenng model system study for a regenerative fuel cell Study report Active control technology development at NASA Interleaved array antenna technology development p22 A85-22586 [NASA-CR-174801] p 47 N85-16292 [NASA-CR-171845] p 34 N85-19326 Measurement of the mertial constants of a ngid or flexible Grand Valley State Coll, Allendale, Mich Lockheed Missiles and Space Co, Palo Alto, Calif structure of arbitrary share through a vibration test Shear deformation plate continua of large Passive Orbital Disconnect Strut (PODS 3) structural test [NASA-TM-77557] p 24 N85-11381 program double-layered space structures p8 N85-10391 Space station power system p33 N85-13881 [NASA-CR-177325] p 16 N85-17020 NASA OAST perspective p5 N85-16990 SCATHA (spacecraft charging at high altitudes) plasma Science Applications, part 2 p 6 N85-20347 H interaction expenment SC-3 high energy particle The international environment UNISPACE '82 and the spectrometer; SC-8 energetic ion composition ITU A relationship between orbit-spectrum resource Houston Unlv, Tex expenment allocation and orbital debns p 58 N85-21215 Characterization of heat transfer in nutrient matenals [AD-A149728] p 35 N85-21252 National Aeronautics and Space Administration Ames [NASA-CR-171841] p 56 N85-17551 Lockheed Missiles and Space Co, Sunnyvale, Calif Research Center, Moffett Field, Calif Howard Univ., Washington, D. C Demonstration of transparent solar array module Determination of atmosphenc density using a Environmental effects on the dynamics and control of design space-launched projectile an orbiting large flexible antenna system [NASA-CR-174257] p 47 N85-16302 [AIAA PAPER 85-0327] p2 A85-20866 [IAF PAPER 84-358] p 18 A85-13220 Investigation of welded interconnection of large area Trajectory analysis of radiative heating for planetary Hughes Aircraft Co, Canoga Park, Calif wraparound contacted silicon solar cells missions with aerobraking of spacecraft Environmental interactions working group report [NASA-CR-174438] p 39 N85-19519 p 14 A85-21829 p5 N85-13908 Los Alamos Scientific Lab, N Hex. A modular approach to developing a large deployable Hughes Aircraft Co., El Segundo, Calif. Design of a nuclear electric propulsion orbital transfer reflector p7 A85-22685 Environmentally-induced voltage limitations in large vehicle p46 A85-23394 Catalytic surface effect on ceramic coatings for an space power systems p31 A85-18584 Opening up the future in space with nuclear power aeroassisted orbital transfer vehicle p 38 A85-29730 National Aeronautics and Space Administration. Hughes Aircraft Co., Los Angeles, Calif [DE85-002411] p49 N85-20862 Goddard Space Right Center, Greenbelt, Md An investigation dunng the system test phase of the A case for Gohrem - Geosynchronous orbit high GOES spacecraft p32 A85-28126 M resolution earth momtonng p 50 A85-10261 Hydraulic Research Textron, Irvine, Calif A user's guide to the Flexible Spacecraft Dynamics and Compensator development and examination of Control Program performance and robustness Martin Marietta Aerospace, Bethesda, Md Space based OTV servicing p 56 N85-17010 [NASA-TM-87389] p 24 N85-12586 [NASA-CR-175470] p 34 N85-20244 Analysis of Nonvolatile Residue (NVR) from spacecraft Martin Marietta Aerospace, Denver, Colo systems Power subsystem automaton study [NASA-TM-86184] p 39 N85-17019 [NASA-CR-171213] p33 N85-12299 Application Number 3 Using tethers for attitude Operational fitness of box truss antennas in response control p27 N85-20373 Illinois Unrv, Urbana. to dynamic slewing Debns in the geostationary orbit ring, the endless Satellite communication antenna technology [NASA-CR-172470] p27 N85-19012 shooting gallery- The necessity for a disposal policy p 31 A85-23651 Evaluation and prediction of long-term environmental p58 N85-21214 Informatics General Corp., Palo Alto, Calif effects of nonmetallic matenals National Aeronautics and Space Administration. Determination of atmosphenc density using a [NASA-CR-171353] p39 N85-19137 Johnson (Lyndon B) Space Center, space-launched projectile Martin Marietta Aerospace, New Orleans, La. A case for Gohrem - Geosynchronous orbit high [AIAA PAPER 85-0327] p2 A85-20866 External tank aft cargo earner p8 N85-11050 resolution earth momtonng p 50 ASS-10261

C-2 CORPORA TE SOURCE Stanford Univ., Calif.

Tethered propellant resupply technique for space Characteristics of arc currents on a negatively biased stations solar cell array in a plasma p31 A8S-18608 (IAF PAPER 84-442] p 44 ASS-13282 The effect of plasma on sola/ cell array arc Rensselaer Polytechnic Inst, Troy, N Y Thermal management technology status characteristics Some applications of direct adaptive control to large p14 N85-13895 (AIAA PAPER 854384] p 31 A85-19713 structural systems p 19 A85-13636 Heat rejection working group synopsis Computer simulation of plasma electron collection by Rockwell International Corp, Downey, Calif p 15 N85-13S06 PIX-II Integrated Power and Attitude Control Systems for Space Station truss structures and construction [AIAA PAPER 85-0386] p 45 A85-19715 Space Station considerations [AIAA PAPER 85-0358] p 31 ASS-19695 Space Power Dynamics and controls working group summary INASA-TM-86338] p 15 N85-15796 [NASA-CP-2352] p 56 N85-13880 The space shuttle orbiter remote manipulator positioning Missions/planning panel p 4 N85-13886 p26 N85-13854 Perspectives on energy storage wheels for space station mechanism p42 N85-16963 Dynamic power systems for power generation Propellant transfer Tethered depot application p47 N85-13860 p33 N85-13892 p48 N85-17006 Space Transportation System (STS) propellant OTV Propulsion Issues scavenging system study Volume 1 Technical report Orbital Debns [NASA-CP-2347] p 48 N85-16989 [NASA-CP-2360] p40 N85-21188 OTV propulsion tecnology programmatic overview [NASA-CR-171848-VOL-1] p 49 N85-20000 Space Transportation System (STS) propellant Parametric analysis SOC meteoroid and debns p48 N85-16997 protection p 16 N85-21209 Vehicle/engine integration p 48 N85-17008 scavenging system study Volume 2 Supporting research Environment definition, small particles, diameter less Report of the Constellations Panel p 27 N85-20368 and technology report [NASA-CR-171849-VOL-2] p 49 N85-20001 than or equal to 1 MM p 40 N85-21223 Advanced research and technology programs for Space Transportation System (STS) propellant Design study of an integrated aerobraking orbital transfer advanced high-pressure oxygen-hydrogen rocket vehicle propulsion scavenging system study Volume 3 Cost and work breakdown structure-dictionary [NASA-TM-58264] p9 N85-21262 [NASA-TM-86969] p 50 N85-21231 [NASA-CR-171850-VOL-3] p 49 N85-20002 National Aeronautics and Space Administration. National Aeronautics and Space Administration Rockwell International Corp, Pittsburgh, Pa. Langley Research Center, Hampton, Va. Marshall Space Right Center, Huntsvllle, Ala Large space structures ground and flight progress Autonomous momentum management for the CDG Ground test article for deployable space structure systems [IAF PAPER 84-388] p 13 A85-13243 planar Space Station Optimal design of a passive vibration absorber for a [AIAA PAPER 85-0031] p 21 A85-19468 [NASA-CR-171301] p9 N85-19011 truss beam p 19 ASS-13638 NASA/MSFC ground experiment for Large Space Rockwell International Corp, Richardson, Tex. Closed-form solutions for feedback control with terminal Structure control verification Orbital transfer vehicle propulsion issues constraints p20 A85-18331 [AIAA PAPER 85-0115] p 21 A85-19528 p48 N85-17009 A survey of aeroasststed orbit transfer Second Symposium on Space Industnalization Rockwell International Corp., Seal Beach, Calif p53 A85-21826 [NASA-CP-2313] p4 N85-11011 Thermal storage analysis for large manned space Chemical nonequilibnum effects on flowfields for An evaluation of grease type ball beanng lubricants platforms [AIAA PAPER 854066] p 14 A85-19493 aeroassisted orbital transfer vehicles p53 A85-21831 operating in vanous environments Rome Air Development Center, Hanscom AFB, Mass. Structural control research and expenments at [NASA-TM-86480] p 38 N85-11239 Dielectric matenal in the space environment NASA/LaRC p 22 A85-22S87 Ground test experiment for large space structures, A review of contamination issues associated with an appendix I p56 N85-13847 p 37 A85-24672 orbiting Space Station external environment Drives and benefits overview p 56 N85-16998 Rome Unlv (Italy). p38 A85-24703 Keynote address p 27 N85-18378 The dimensional stability of advanced composite antenna reflectors Analytical and test evaluation Orbit on demand - In this century if pushed NASA-VCOSS dynamic test facility p39 N85-14014 p46 A85-24788 [NASA-TM-86491] p 27 N85-18998 Analytical thermal formulations for antenna dishes Orbit-on-demand vehicles - Mission possible, but Ground test expenment for large space structures p15 N85-14017 one-day turnaround? p 53 A85-24790 [NASA-TM-86489] p 9 N85-19013 An analytical investigation of shape control of large Active control of large space structures An introduction In-orbit performance of INTELSAT V communications space structures by applied temperatures and overview antennae deployment systems p33 N85-14018 p14 A85-25145 Elastic dispersion effects on dynamics and control of [NASA-TM-86490] p 27 N85-19014 large modular antennas p 26 N85-14019 Wavelength division multiplexing for future Space Station Applications of Tethers in Space, volume 1 Science Applications, part 1 p 5 N85-20346 data systems p 32 A85-25359 [NASA-CP-2364] p 57 N85-20339 Toroid Joining Gun Tethered satellite system project overview [SAE PAPER 850408] p 38 A8S-25988 p5 N85-20341 Adaptive modal control of structural dynamic systems Tether fundamentals p 57 N85-20345 using recursive lattice filters p 23 A85-26435 Electrodynamic interactions p 34 N85-20348 Human response to vibroacoustic environments of Saab-Scanla, Unkoplng (Sweden). Summary presentation of the Electrodynamics Structural design and thermal stability of TELE-X space vehicles Interactions Panel p 34 N85-20356 [NASA-TM-86316] p 54 N85-10789 antenna tower p 15 N85-14016 Applications of Tethers in Space, volume 2 Expenmental and predicted heating distributions for Shock and Vibration Information Center (Defense), [NASA-CP-2365] p 57 N85-20361 Washington, D C biconics at incidence in air at Mach 10 Report of the Electrodynamic Interactions Panel [NASA-TP-2334] p 14 N85-12313 The Shock and Vibration Digest, volume 16, no 11 p34 N85-20363 Conceptual design for scaled truss antenna flight [AD-A148466] p 16 N85-17382 Natural environment design cntena for the Space Station Smithsonian Astrophysical Observatory, Cambridge, expenment definition and preliminary design [NASA-TM-85804] p4 N85-12932 Mass. [NASA-TM-86498] p9 N85-21232 An Assessment of Integrated Flywheel System The investigation of tethered satellite system NASA/MSFC ground expenment for large space Technology dynamics structure control verification [NASA-CR-171278] p 26 N85-15772 [NASA-CP-2346] p 26 N85-13850 [NASA-TM-86496] p 28 N85-21248 Soclete Natlonale Industrlelle Aerospatiale, Cannes Space Station truss structures and construction Definition of ground test for Large Space Structure (LSS) considerations (France) control venfication [NASA-TM-86338] p 15 N85-15796 ARABSAT spacecraft Rx and Tx antenna [NASA-TM-86495] p 28 N85-21249 Reduction method for thermal analysis of complex mechanisms P 34 N85-14022 National Aerospace Lab, Tokyo (Japan) aerospace structures Vibration analysis of a multipurpose platform Soclete Natlonale Industrlelle Aerospatiale, Les [NASA-TP-2373] p 15 N85-16066 [NAL-TR-803] p 27 N85-18078 Mureaux (France) Performance assessment of aero-assisted orbital Partial bleed expander cycle for low thrust LOX/LH2 Technology and performances of structural thermal transfer vehicles p56 N85-16993 rocket engine mechanical equipment used for antenna of TV SAT-TDF Swing-arm beam erector (SABER) concept for single [NAL-TR-837T] p 49 N85-19018 1 program p 15 N85-14012 astronaut assembly of space structure National Space Development Agency, Ibarakl (Japan). Southwestern Univ., Georgetown, Tex. [NASA-TP-2379] p 42 N85-19015 Structural aspects of SAR antenna for Japanese Earth Preliminary design of an Earth-based debns detection Process for preparing essentially colorless polyimide film Resources Satellite 1 p 12 N85-14007 system using current technology and existing containing phenoxy-linked diamines installations p40 N85-21199 [NASA-CASE-LAR-13353-1] p 40 N85-20128 Spar Aerospace Ltd, Toronto (Ontario). Technology and test p 57 N85-20353 An overview of the space remote manipulator system Summary presentation of the technology and test p42 N85-16964 OAO Corp, Greenbelt, Md panel p 57 N85-203SO Spectra Research Systems, Inc., Huntsvllle, Ala. Capillary Pump Loop (CPL) heat pipe development Report of the Technology and Test Panel Research on large, highly accurate, inflatable p 57 N85-20370 status report reflectors [NASA-CR-175273] p 16 N85-17323 Pultiusion process for fabrication of tethers (preliminary [AO-A145080] p11 N85-10099 Office National d'Etudes et do Recherches concepts) p 40 N85-20371 Aerospatlales, Toulouse (France). SRI International Corp, Menlo Park, Calif Instrumentation for Application Number 1 Mass Space environment simulation to test satellite thermal Dielectric matenal in the space environment p37 A85-24672 spectrometnc analysis of the boundary layer associated control coatings, volume 1 with the tethered satellite p58 N85-20372 [CERT-4128-VOL-1] p 16 N85-17012 Stanford Unlv, Calif National Aeronautics and Space Administration. Lewis Space environment simulation to test satellite thermal Expenments in control of flexible structures with Research Center, Cleveland, Ohio. control coatings. Volume 2- Annex 1 uncertain parameters p24 N85-13837 Near-optimum design of GaAs-based concentrator [ESA-CR(P)-1870-VOL-2] p 16 N85-17013 Disturbance propagation in structural networks, control space solar cells for 80 C operation p 30 A85-15600 Space environment simulation to test satellite thermal of large space structures p26 N85-14856 Performance capabilities of the 12-centimeter Xenon ion control coatings. Volume 2 Annexes 2, 3, 4 Precise control of flexible manipulators thruster p 44 A85-16439 [ESA-CR(P)-1870-VOL-3] p 16 N85-17014 [NASA-CR-174210] p42 N85-16178

C-3 State Univ. of New York, Buffalo. CORPORA TE SOURCE

State Univ. of New York, Buffalo Qualitative results for distributed systems with discrete clamping and stiffness with application to control [AD-A145525] p 24 N85-11382 System Science and Software, San Diego, Calif Computer simulation of plasma electron collection by PIX-II [AIAA PAPER 85-0386] p 45 A85-19715

Technlsche Hogeschool, Eindhoven (Netherlands) Satellite communication antenna technology p 31 A85-23651 Tel-Aviv Unrv (Israel). A case for Gohrem - Geosynchronous orbit high resolution earth monitoring p 50 A85-10261 Teldlx Luftfahrt-Ausruestungs G.m b H, Heidelberg (West Germany). Hemispherical antenna pointing mechanism p26 N85-14021 Tennessee Technological Univ., Cookevllle. Debns impact on Earth-orbiting spacecraft p59 N85-22234 Texas Univ., Austin. The long term behaviour of Earth orbits and the implications for debris control p 58 N85-21213 TICRA ApS, Copenhagen (Denmark). Electncal consequences of mechanical antenna charactenstics p 33 N85-14006 Tokyo Unlv (Japan) Variable geometry truss concept [REPT-614] p 12 N85-21697 TRW, Inc, Redondo Beach, Calif Space power management and distnbution status and trends p 47 N85-13896 TRW Space Technology Labs., Redondo Beach, Calif. Satellite servicing A business opportunity? p55 N85-11056 Turner Broadcasting System, Atlanta, Ga The real world The user p 32 N85-11017 u United Technologies Corp, South Windsor, Conn. Regenerative fuel cell energy storage system for a low Earth orbit space station [NASA-CR-174802] p 47 N85-13371

Virginia Polytechnic Inst and State Univ., Blacksburg An analytical investigation of shape control of large space structures by applied temperatures p14 A85-25145 Identification of vibration parameters of flexible structures p27 N85-18360 w Washington Univ., Seattle The liquid droplet radiator - an ultralightweight heat rejection system for efficient energy conversion in space p15 N85-13900 Wright State Univ., Dayton, Ohio Modal control of structural systems [AD-A149734] p28 N85-21235 Wyle Labs, Inc, El Segundo, Calif. Commerce Lab Miss/on analysts and payfoad integration study [NASA-CR-171272] p 56 N85-16981

C-4 FOREIGN TECHNOLOGY INDEX

TECHNOLOGY FOR LARGE SPACE SYSTEMS / A Bibliography (Supplement 13) MARCH 1986

Typical Foreign Technology Index Listing CZECHOSLOVAKIA Design preparations for large space structures ln-ort«t laser regeneration of the radiation damaged solar [IAF PAPER 84-392) p 35 A85-13246 arrays Kevlar and T300 fabric prepregs - Their material [IAF PAPER 84-62] p 43 A85-13021 properties and their use in high loaded areas of a solar array [IAF PAPER 84-402) p 35 A85-13255 Influence of simulated space environment on the behavior of carbon-fiber-reinforced plastics with +. -45 DENMARK Electncal consequences of mechanical antenna ply mentations II p36 A8S-14163 characteristics p33 N85-14006 Simulation of reusable oslunar space transportation systems with special consideration of chemical propulsion p44 A85-15874 ISRAEL The German remote sensing program r—A case (or Gohrem - Geosynchronous orbit high p52 A85-16881 resolution earth monrtonng p50 ASS-10261 FRANCE International FEM-Congress, Baden-Baden, West Architecture and implementation of an in-orbit Germany, November 14,15, 1983. Proceedings T infrastructure p8 A85-26675 [IAF PAPER 84-29] p6 A85-12995 Offset unfurtable antenna concepts p5 N85-14002 Utilization of a teleoperated service vehicle for spacecraft servicing Technology for the ERS-1 SAR antenna [IAF PAPER 84-48] p1 A85-13009 p33 N85-14008 Service manipulator system for maintenance and Mechanical/thermal design of a polarization sensitive I PAGE ACCESSION reflector p 15 N85-14009 NUMBER NUMBER servicing of future space platforms [IAF PAPER 84-369] p 41 A85-13227 Influence of thermal cycling on the behavior of CFRP Satellite grasping manipulator system material for space structures p39 N85-14013 | [IAF PAPER 84-371] p41 ASS-13229 Hemisphencal antenna pointing mechanism Deployatale reflector antennas - Mechanical design of p26 N85-14021 the reflective surface Development of a foldlme concept for automatic I [IAF PAPER 84-393] p6 A85-13247 refolding of a flexible blanket (folding analysis) Listings in this index are arranged alphabetically by Future prospects in space envisaged by a forum of [ESA-CR(P)-1933] p 12 N85-17428 | country of intellectual origin The title of the European space companies p 52 ASS-16302 West Europe report Science and technology document is used to provide a brief description of Europe in space 1985-2000 p 3 A85-26011 [JPRS-WST-85-008] p 57 N85-20174 I Spacecraft systems engineering and geometry Control of large collector arrays The SSPS [ the subject matter The page number and the modelling - The ESABASE-MATVIEW approach experience accession number are included in each entry to p8 A85-27696 [DE85-001461] p 34 N85-20553 I assist the user in locating the citation in the abstract Influence of starting material and technological section processes on the radiation resistance of silicon solar cells for space use p38 A85-30024 European retrievable earner (Eureca) and evolutionary space carrier for microgravity. Earth observation and technology demonstration p55 N85-11032 INDIA Effect of neutron and proton irradiation on some Measurement of the inertia! constants of a rigid or flexible properties of Kapton p37 A85-21508 structure of arbitrary share through a vibration test [NASA-TM-77557] p 24 N85-11381 Space frame design, development and optimization of AUSTRALIA Workshop on Mechanical Technology for Antennas antenna platform structure for a mobile 3D radar Geometrically nonlinear analysis of space frames by an [ESA-SP-225] p11 N85-13999 p8 A85-24908 incremental iterative technique p 14 ASS-19895 Technology and performances of structural thermal Flexural vibration of gravity-stabilized, structurally mechanical equipment used for antenna of TV SAT-TDF damped, large flexible satellites p22 A85-26434 1 program p 15 N85-14012 INTERNATIONAL ORGANIZATION ARABSAT spacecraft Rx and Tx antenna Mass optimisation of telecommunications satellites mechanisms p 34 N85-14022 [IAF PAPER 84-230] p 13 A85-13146 Space environment simulation to test satellite thermal CANADA Orientation and trends in European technology control coatings, volume 1 The decentralized control of large flexible space [IAF PAPER 84-377] p2 A85-13233 [CERT-4128-VOL-1] p 16 N85-17012 Looking back on the past - The decision of Europe to structures p 17 A85-10071 Space environment simulation to test satellite thermal participate in the post-Apollo program Some results of the MSAT phase B studies and their control coatings Volume 2 Annex 1 p53 A8S-23824 impact on system design [ESA-CR(P)-1870-VOL-2] p 16 N85-17013 The potential of solar power satellites for developing [IAF PAPER 84-89] p 1 A85-13045 Space environment simulation to test satellite thermal countries p53 A85-24654 Dynamics of the Obiter based construction of structural control coatings Volume 2 Annexes 2, 3. 4 Intelsat's twentieth anniversary - Two decades of components [ESA-CR(P)-1870-VOL-3J p 16 N85-17014 innovation in global communications p 54 A8S-26369 [IAF PAPER 84-359] p 18 A85-13221 Development and application of new technologies in Damping synthesis for a spacecraft using substructure ESA's Olympus programme p 3 A85-27695 and component data ISRAEL [CRC-1365] p24 N85-12082 A case for Gohrem - Geosynchronous orbit high QERUANY.FEDERAL REPUBLIC OF resolution earth monitonng p 50 A85-10261 Six degrees of freedom control with each hand? Application of modal synthesis concepts to spacecraft ITALY p42 N85-14492 design verification p 17 A85-12455 Space exploitation - Spacelab an easy approach for Lay-out of a re-usable re-entry vehicle required in a future An overview of the space remote manipulator system developing countries. Prospectves and suggestions by p42 N85-16964 European low earth orbit scenario Aentalia p 1 A8S-12502 [IAF PAPER 84-06] p 50 A85-12981 Modelling and identification of the structural properties Bipropellam propulsion in the new generation of Space station related investigations in Europe of an astromast " satellites and upper stages. The role of BPD Difesa-Spazto [IAF PAPER 84-28] p SO ASS-12994 [CRC-1374] p12 N85-18352 in this field - Manufacturing facilities and technology Design and technology trends on large solar arrays for p43 A85-12519 Stability analysis of flexible spaceratt with PID space stations IRIS Spinning Stage - A perigee stage for satellites up controller [IAF PAPER 84-37] p 43 A85-13000 [CRC-1372] p28 N85-21247 to 900 kg to be launched from the Space Shuttle with Economics of permanent polar platforms (PPP) for global the IRIS system p43 A85-12520 CHINA, PEOPLE'S REPUBLIC OF monitoring An optimal shape control of a large flexible radiator In Robust attitude control of a large communication satellite [IAF PAPER 84-226] p2 A8S-13144 with flexible solar arrays Dynamical modelling of a gravity-loaded rectangular [IAF PAPER 84-64] p 18 ASS-13023 [IAF PAPER 84-ST-06] p 19 A85-13293 plate as a test configuration tor attitude control of large Factors affecting push-broom performances in future Finite multiple bum orbit transfer error analysis via space structures space platforms covanance matrix p 45 A85-22444 [IAF PAPER 84-391] p 18 A85-13245 [IAF PAPER 84-116] p29 A85-13066

D-1 JAPAN FOREIGN TECHNOLOGY INDEX

Elastic waves propagation in bounded periodic SWEDEN structures Structural design and thermal stability of TELE-X [ IAF PAPER 84-395] p 19 A85-13249 antenna tower p 15 N85-14016 Thermal analytical model of bidimensional and SWITZERLAND unidimensional structural elements in a space Inflatable space-ngidized structures - Recent environment developments of the matenal technology [IAF PAPER 84-399] p 13 A85-13252 [IAF PAPER 84-384] p 10 A85-13240 Heat conduction problems in large space structure Office of Technology Assessment p4 N85-10872 [IAF PAPER 84-400] p 13 A85-13253 Large spacebome antenna reflectors using inflatable Thermoelastic behaviour of space structures in space ngidized structures p 12 N85-14004 composite materials Propellant transfer Tethered depot [IAF PAPER 84-404] p 35 A85-13257 p48 N85-17006 Influence of the lamination and of some environmental effects on damping characteristics of advanced composites for space structures u [IAF PAPER 84-405] p 36 A85-13258 Development of advanced composite tubular structures USS.R for antenna reflector p 10 A85-24817 Stability of a nng of connected satellites The dimensional stability of advanced composite [IAF PAPER 84-342] p 18 A85-13206 antenna reflectors Analytical and test evaluation Material sciences in space p 36 A85-13500 p39 N85-14014 Stability of the stationary motions of a tethered system Analytical thermal formulations for antenna dishes of two bodies in orbit under the effect of gravitational and p 15 N85-14017 aerodynamic forces p20 A85-15254 Elastic dispersion effects on dynamics and control of Effect of phase fluctuations in an incident beam on the large modular antennas p26 N85-14019 characteristics of a rectenna system p30 A85-15760 TSS Satellite overview p 5 N85-20343 Expenmental study of the effect of the type of stress Satellite module design p 9 N85-20344 state on plastic strain in structural materials at low Science Applications, part 1 p 5 N85-20346 temperatures p 37 A85-16499 Report of the Transportation Panel The development of a frequency method for the p57 N85-20364 mathematical modeling of the motion of an elastic space vehicle p 20 A85-17054 The cost effectiveness and optimal parameters of an electric rocket propulsion system for an mterorbital transport vehicle p 46 A85-23990 JAPAN Effect of aerodynamic moment on the regime of the Design consideraton of space construction facility gravity gradient stabilization of the Salyut-6 - Soyuz orbital [IAF PAPER 84-26] p6 A85-12992 system p 23 A85-28488 A space station expenment on large antenna assembly Multicntical optimization of a large space structure and measurement - A follow-on study p 11 A85-28489 [IAF PAPER 84-58] p 41 A85-13017 The dynamics of the attitude control and stabilization Engineering aspect of the Microwave Ionosphere systems of spacecraft with a controlled gravity gradient Nonlinear Interaction Expenment (MINIX) with a sounding stabilizer p 23 A85-28903 rocket Stability of the rotation of a body suspended by means [IAF PAPER 84-289] p 29 A85-13177 of a system of rods connected in senes Variable geometry truss and its application to employable p23 A85-28906 truss and space crane arm UNITED KINGDOM [IAF PAPER 84-394] p 10 A85-13248 Alleviation of observation spillover in continuous Torsional vibration of booms with open cross section structures p 17 A85-12434 caused by unidirectional radiant heating The improvement of free-mode methods in component p22 A85-26350 mode synthesis techniques and its accuracies Poles and transmission zeros of flexible spacecraft p17 A85-12442 control systems p 22 A85-26433 Evaluation of efficiently computed exact vibration Structural aspects of SAR antenna for Japanese Earth characteristics of space platforms assembled from stayed Resources Satellite 1 p 12 N85-14007 columns p 13 A85-12884 Vibration analysis of a multipurpose platform Space greenhouse design p50 A85-12927 [NAL-TR-803] p 27 N85-18078 Utilization and economics of a European low earth orbit Partial bleed expander cycle for low thrust LOX/LH2 Space Platform rocket engine [IAF PAPER 84-57] p 1 A85-13016 [NAL-TR-837T] p 49 N85-19018 Attitude control system and communications payload for Vanable geometry truss concept an amateur solar sail spacecraft [REPT-614] p 12 N85-21697 [IAF PAPER 84-363] p 29 A85-13224 A signed switching time bang-bang attitude control law for fine pointing of flexible spacecraft p 19 ASS-13893 N Formex configuration processing in structural engmeenng p 14 A85-20916 NETHERLANDS Sky-hooks, fish-warmers and hub-caps - Milestones in International space programmes and policies satellite communications p 32 A85-25101 p2 A85-20507 Salyut Mission Report p 3 A85-25700 The systems background for satellite communication BAe antenna hardware technology for current satellite antennas p 32 A85-23652 projects p9 N85-14011 Ten years after the launch of ANS - Looking back in In-orbit performance of INTELSAT V communications perspective p 54 A85-26770 antennae deployment systems p33 N85-14018 The communication-satellite market to the year 2000 p 3 A85-26771 Antenna mechanical technologies within ESA p11 N85-14000 Study of structure control dynamic interaction for radio frequency antenna control systems p 26 N85-14020 Commercial space Europe should have independent strategy pS N85-19205

POLAND The strongest structures with macrostrffness constraints p 10 A85-12933

SPAIN CASA technological effort in the field of antennas p 33 N85-14010 CASA activities in antenna technology p39 N85-14015

D-2 CONTRACT NUMBER INDEX

TECHNOLOGY FOR LARGE SPACE SYSTEMS / A Bibliography (Supplement 13) MARCH 1986

Typical Contract Number Index Listing

NAS3-23869 p31 A85-18584 NAS3-23881 P45 A85-19715 NAS5-24342 p32 A8 5-28126 NAS5-25767 pB N85-10677 NAS3-23354 p47 N85-12071 N AS 5-26660 p 16 N85-17323 NAS7-100 p17 A85-11082 NAS7-918 P12 N85-19004 p34 N85-20244 NAS8-33578 p39 N85-19137 r NAS8-33979 P17 AB5-11086 NASA PAGE P17 A85-11087 CONTRACT ACCESSION NUMBER p24 N85-10098 NUMBER NUMBER NAS8-34547 P11 N85-12200 NAS8-34657 p9 N85-19011 NAS8-34700 p9 N8S-13838 NAS8-34938 p33 N85-12299 Listings in this index are arranged alpha- NAS8-35043 P< N85-12084 NAS8-35349 ASS-19468 numencally by contract number Under each P21 p24 N85-12931 contract number, the accession numbers denoting P33 N85-12933 documents that have been produced as a result of NAS8-35403 p55 N85-12075 research done under that contract are arranged in p55 N85-12076 p55 N85-12077 ascending order with the AIAA accession numbers p57 N85-20339 appearing first The accession number denotes the p57 N85-20361 number by which the atatu identified in the NAS8-35408 p59 N85-21659 NAS8-35499 abstract section Preceding xessic.nn. number p55 N85-12921 NAS8-3561 1 p56 N85-13473 is the page number on whic citation may be NAS8-36109 p56 N85-16981 found NAS8-36160 p26 NJ5-15772 NAS9-16430 p34 N85-19326 NAS9-16782 p14 A85-19493 AF PROJ 3654 p28 N85-21253 NAS9- 16994 P49 N85-20000 AF-AFOSR-0242-82 P24 N85-11382 p49 N85-20001 AF-AFOSR-80-0013 P7 AB5-16648 P49 N85-20002 AF-AFOSR-82-0242 p 19 A85-13641 NSERC-A-4183 P17 A85-10071 A85-10071 AF-AFOSR-83-O001 p30 A85- 16641 NSERC-A-4396 P17 NSERC-67-066 p18 A85-13221 ARPA ORDER 3654 p28 N85-21253 NSFATM-83-15322 p30 A85-16641 CNR-83,02713,07 p36 ASS- 13258 NSF CEE-82-07375 p23 A85-29144 OAAD07-82-C-0230 p23 ASS- 26606 NSF ECS-80-16173 19 A85-13636 DAE PROJECT 34/4/81-G p37 A8S-21S08 P NSF ECS-82-12479 p23 A85-27238 DE-AC04-76DR-00789 p34 N85- 20553 NSFMEA-81-10777 p35 A85-12395 ESA-4023/79-NL-AK p10 A85-13240 NSG-1185 P8 N85-10391 ESTEC-4577/81 /NL-DG p16 N85-17012 NSG-1414 p18 ASS-13220 p 16 N85-17013 N00014-76-C-0444 p35 N85-21252 p 16 N85-17014 W-7405-ENG-36 49 N85-20862 ESTEC-5144/82-NL-OG p 16 N85-17014 P 505-35-13-20 p54 N85-10789 ESTEC-5144/82/NL-DG p 16 N85-17012 505-37-23-01 p8 N85-11570 p 16 N85-17013 506-51-13 14 N85-12313 ESTEC-5198/82/NL-PB(SC) p12 N85-17428 P 506-53-43-01 15 N85-15796 ESTEC-5310/82/NL/BI p18 A85-13245 P 506-53-43 p42 N85-19015 ESTEC-5494/84/NL-GM p15 N85-14009 506-53-53 p15 N85-16066 F04611-82-C-0049 44 A85-16448 P 506-57-13-10 p26 N85-13850 F04611-83-C-0053 p11 N85-10099 506-60-12 p50 N85-21231 F04701-81-C-0082 p31 A85-21835 506-62-23-01 p4 N85-12932 F04701-82-C-0083 p37 ASS- 19770 906*3-00 p9 N85-21262 F19628-83-K-0024 p30 ASS- 16641 906-75-22 p40 N85-21188 F30602-82-C-0053 p28 N85-21253 F33615-83-C-3000 p28 N85-21235 F49620-82-C-0089 p29 ASS- 13640 p23 AS 5- 291 44 JPL-9S5687 P2 A85-22577 JPL-955847 p12 N85-19004 JPL-956020 p39 N85-19519 JPL-956541 p34 N85-20244 JPL-956608 p47 N85- 16302 NAGW-121 P2 A85-22577 NAGW-21 P41 A85-13001 p20 A85-18692 NAG1-126 P19 A8S-13634 NAG1-171 p19 A85-13636 NAG1-322 p42 N85-16178 NASW-3199 p24 N85-11381 NASW-3811 p59 N8S-21414 NAS1-14784 p39 N85-20019 NAS1-16078 P8 N85-11570 NASM7551 P27 N85-19012 NASM7633 P31 A85-19695 NAS2-10848 P16 N85-17020 NAS2-11676 . . P56 N85-17551 NAS3-21287 P47 N85-16292 NAS3-22234 P47 N85-13371 NAS3-23354 P47 N85-12071

E-1 REPORT NUMBER INDEX

TECHNOLOGY FOR LARGE SPACE SYSTEMS / A Bibliography (Supplement 13) MARCH 1986

Typical Report Number Index Listing

CRC-136S . . p24 N85-12082 tt IAF PAPER 8444 p 18 ASS- 13023 tt CRC-1372 . p28 N85-21247 tt IAF PAPER 8444 p 29 ASS- 13040 * tt ...-. MICROFICHE 1 , IAF PAPER 8449 p 1 A85-13045 tt KXUMENT SYMBOL |~| CRC-1374 p12 N85-18352 i ISSN4285-6808 p 12 N8S-21697 tt DE85401461 P 34 N85-20553 I ISSN4379-6566 p11 N85-13999 tt UeB5-OOZ4incocjv\941«i np A*»Q MRR_9nflftN0O-CUOO43 ]i' ISSN4389-4010 p 27 NB5- 18078 tt JPL-9950-962 p 34 N85-2O244 • f ISSN4389-4010 p 49 N85-19018 tt 1 -T- 1 OOE/DH40789/T4 p 34 N85-205S3 t I P h JPL-9950-962 P 34 N85-20244 • # DH-4-VOL-1 P 56 N85-13473 " j' JPL-9950-975 p 39 N85-19519 • # REPORT PAGE ACTF^inw ( JPL-9950-980 p 12 N85-19004 * tt DflL-T-1811-VOL-l p49 N8S-20000 • / NUMBER NUMBER MIUI£NUMBcDH DHL-T-1811-VOL-2 P 49 N85-20001 • t JPRS-WST4S408 p 57 N85-20174 tt DRL-T-1811-VOL-3 P 49 N85-20002 ' / L-15777 p15 N85- 16066 # Listings in this index are arranged aJpha- 0180-27677-1 p 4 N85-12084 • t L-15785 p 14 N85-12313 tt numencally by report number The page number L- 15838 p4 N85-12932 tt E-2171 p 48 N85-16989 * t, indicates the page on which the citation is located L- 15876 p26 N85-13850 tt E-2305 P 56 N85-13880 • t L-15886 P42 N85-19015 tt The accession number denotes the number by E-2495 P 50 N85-21231 • t which the citation is identified An asterisk (*) LA-UR444388 p 49 N85-20862 tt indicates that the item is a NASA report A pound ESA-CR(P)-1870-VOL-1 P 16 N85-17012 t ESA-CR(P)-1870-VOL-2 P 16 N85-17013 H sign (*) indicates that the item is available on \ LMSC-0973421 p 39 N85-19519 ' # ESA-CR(P>1870-VOL-3 P 16 N85-17014 t LMSC-D973437 p 47 N85-16302 ' # microfiche ESA-CR(P)-1933 P 12 N85-17428 ll LSI-TR-37640 p 47 N85-16292 • tt ESA-SP-225 P11 N85-13999 t AD-A145080 pll N85-10099 tt M-464 p4 N85-11011 * tt AO-A145525 p24 N85-11382 # FCH-6128 P47 N85-13371 • t' M-475 p 57 N85-20339 ' # AD-A148466 p 16 N85-17382 tt M-476 p 57 N85-20361 * # AD-A149120 p30 A85- 16641 tt FSR-8 P38 N85-1 1239*1t! AD-A149728 p 35 N85-21252 tt MCfl44-594 p 27 N85-19012 • # AD-A1 49734 p28 N85-21235 # G-85F0284 P 39 N85-17019 * t' MCR-84-596 p33 N85-12299 " tt AD-A1 50007 p28 N85-21253 tt MCR-85-506 p39 N85-19137 * tt AD-A1 50052 p42 N85-21668 tt GERA-2702 p34 N85- 19326 * tt MDC-H1295-VOL-1 p 56 N85-13473 • tt AD-O011503 p 12 N85-21495 # GP048401 p4 N85-11911 t GPO-51410 p6 N85-21225 t' NAL-TR403 P 27 N85-18078 tt AFGL-TR444334 p 30 ASS- 16641 tt NAL-TR437T P 49 N85-19018 tt IAF PAPER 84-ST-O6 p 19 ASS- 13293 t. AFOSR444724TR p 24 N85-11382 ft IAF PAPER 8444 p 50 A85-12979 /' NAS 115 58264 p9 N85-21262 * # IAF PAPER 8446 P 50 A85-12981 t. NAS 11577557 p 24 N85-11381 ' # AFRPL-TR-84440 p 1 1 N85-10099 # IAF PAPER 64-1 16 P 29 A85-13066 t' NAS 1 1585804 p 4 N85-12932 * # IAF PAPER 84-166 p6 A85-13100 t NAS 11586184 p39 N85-17019 * # AFWAL-TR-84-3054 p 28 N85-21235 tt IAF PAPER 84-189 P 51 A85-13114 • t' NAS 1 1586316 P 54 N85-10789 * f IAF PAPER 84-220 P 51 A85-13141 ll NAS 11588338 P 15 N85-15796 • # AIAA PAPER 854023 p 20 ASS- 19462 f IAF PAPER 84-226 p2 A85-13144 / ' NAS 11586480 P 38 N85-11239 ' # AIAA PAPER 854029 p 41 ASS- 19468 tt IAF PAPER 64-230 P 13 A85-13146 ll' NAS 115 86489 p9 N85-19013 • # AIAA PAPER 854031 p 21 ASS- 19468 • tt IAF PAPER 64-232 P 51 A65-13148 / NAS 11586490 P 27 N85-19014 • # AIAA PAPER 854066 p 14 A85-19493 • # IAF PAPER 84-26 p6 A85-12992 ll NAS 115 86491 P27 N85-18998 * f AIAA PAPER 8541 15 p21 AB5-19528 * f IAF PAPER 84-289 p29 A85-13177 t' NAS t 1566495 P 28 N85-21249 ' tt AIAA PAPER 8541 17 p 21 ASS- 19529 tt IAF PAPER 84-28 P 50 A85-12994 t' NAS 1 1586496 P 28 N85-21248 ' tt AIAA PAPER 8541 55 p 14 ASS- 19553 tt IAF PAPER 64-29 P6 A85-12995 t NAS 1 1586498 P 9 N85-21232 ' # AIAA PAPER 854164 p 45 A85-19561 tt IAF PAPER 84-310 P 44 A85-13191 t[ NAS 11586969 P 50 N85-21231 ' t AIAA PAPER 85421 6 p21 A85- 19595 # IAF PAPER 84442 P 18 ASS- 13206 t' NAS 11587389 p24 N85-12586 ' # AIAA PAPER 854220 p 54 A85-26385 tt IAF PAPER 84458 P 18 A85-13220 ' l'l NAS 126 171182 P 24 N65-10098 ' # AIAA PAPER 854223 p7 ASS- 19600 # IAF PAPER 84459 P 18 A85- 13221 'i NAS 126 171195 P 55 N85-12075 ' # AIAA PAPER 854313 p45 ASS- 19660 # IAF PAPER 84-363 P 29 A65-13224 t' NAS 126 171 196 P 55 N85-12076 * # AIAA PAPER 854327 p 2 A85-20866 • tt IAF PAPER 84489 P41 A65-13227 t NAS 126 171187 P 55 N85-12077 ' # AIAA PAPER 854356 p21 AB5-19693 tt IAF PAPER 84471 P 41 A85-13229 ll NAS 126 171201 P11 N85-12200 ' # AIAA PAPER 854358 p 31 A85- 19695 • f IAF PAPER 84477 p2 ASS- 13233 t NAS 126 171208 p9 N85-13838 ' # AIAA PAPER 854384 p 31 ASS- 197 13 • # IAF PAPER 6447 P 43 A85-13000 t NAS 126 171209 p4 N85-12084 • # AIAA PAPER 854385 p45 A85-19714 tt IAF PAPER 84484 p 10 A85-13240 t NAS 126 171213 P33 N85-12299 • # AIAA PAPER 854386 p 45 ASS- 197 15 • » IAF PAPER 84488 P 13 A85-13243 • I NAS 126 171222 P 55 N85-12921 ' # AIAA PAPER 854431 p45 A85- 19744 » IAF PAPER 84489 p2 ASS- 13244 ( NAS 126 171223 P 56 N85-13473 * # AIAA PAPER 854472 p37 A85-19770 # IAF PAPER 6448 P 41 A85-13001 * t NAS 126 171256 p33 N85-12933 ' # AIAA PAPER 854473 p37 A85-I9771 # IAF PAPER 84491 P 18 A85-13245 t NAS 126 171272 P 56 N85- 16981 • AIAA PAPER 854504 p 53 ASS- 19795 • # IAF PAPER 84492 . p35 ASS- 13246 t NAS 1 26 171278 P 26 N85-15772 * IAF PAPER 84493 p6 A85-13247 t NAS 1 26.171301 p9 N85-19011 * ARC-TN-1125 .. p12 N85-19004 • » IAF PAPER 84494 P 10 A85- 13248 t ' NAS 126 171353 P 39 N85-19137 • IAF PAPER 84495 P 19 AB5-13249 / ARC-TN-1132 . pll N8S-12200'* NAS 126 171841 P56 N85-17551 ' IAF PAPER 84499 P 13 AB5-13252 t NAS 1 26 171845 P 34 N85- 19326 ' IAF PAPER 84-400 P 13 A85- 13253 / NAS 1 26 171646-VOL-1 p 49 N85-20000 * BMR-5 . .. p9 N85-19011 ' » IAF PAPER 84-402 . P 35 ASS- 13255 I NAS126171B49-VOL-2 p 49 N85-2O001 ' IAF PAPER 84-404 P35 A85-13257 i NAS 1 26 171650-VOL-3 p 49 N85-20002 * CDC43302B4TR-OA09-AC004 p28 N85-21253 » IAF PAPER 64-405 . . p 36 ASS- 13258 ( NAS 126 172470 p 27 N85-19012 • IAF PAPER 84-407 .... P 51 A85-13259 ( NAS 1^6.172473 p8 N85-11570 * IAF PAPER 84-438 . . P 51 ASS- 13276 • t CERT-4128-VOL-1 ... p 16 N85-17012 » ' MAS 1.26172497 . p 39 N85-20019 • IAF PAPER 84-442 . . . p 44 A85-13282 * i , NAS 1.26174065 p 24 N85-12931 • IAF PAPER 64-48 pi A85-13009 t CMU-RI-TR44-28 p42 N85-Z1668 # IAP rAmPAPFnR B4 D/ ft4_!*...... 7 . o|* i 1 noaA8&1301- ii»v 160 i I NAS 1 26.174067 p 47 N85-12071 ' IAF PAPER 84-58 P 41 ASS- 130 17 ti NAS 1.26 174210 p 42 N85-16178 • CONF450103-2 p49 N8S-20862 t IAF PAPER 84-62 P 43 A85-13021 t > NAS 1 26.174257 . . p 47 N85- 16302 • f

F-1 NAS 1.26:174438 REPORT NUMBER INDEX

NAS 126 174438 P39 N85-19519 * # REPT-614 P12 N85-21697 # NAS 126 174448 P12 N85-19004 ' # REPT-956541 -EXTENSION-1 p34 N85-20244 • #

NAS 1 26 174801 P47 N85-16292 • # S-REPT-98-656 p6 N85-21225 # NAS 1 26174802 p47 N85-13371 ' # NAS1 26175273 p 16 N85-17323 * # S-532 p40 N85-21188 *# NAS1 26175300 p8 N85-10677 ' # S-542 P9 N85-21262 •# NAS 126 175470 p34 N85-20244 • # NAS 1 26 175483 p59 N85-21414 ' # SAE PAPER 850408 p38 A85-25988 ' # NAS 1 26177325 p 16 N85-17020* # NAS 1 552313 P4 N85-11011 * # SAWE PAPER 1527 p13 A85-18812 # NAS 1 55 2346 p26 N85-13850 * # NAS 1 55 2347 p4B N85-16989 * # SRS-TR84-015-CU40 P11 N85-10099 # NAS 1 55 2352 p56 N85- 13880 ' # NAS 1 55 2360 p40 N85-21188 ' # SSPS-TR-4/84 p34 N85-20553 # NAS 1 55 2364 p57 N85-20339 * # NAS 1 55 2365 p57 N85-20361 ' # STS-64-0570-VOL-1 p49 N85-20000 ' # NAS 1 55 2366 p59 N85-21659 * # STS-84-0570-VOL-3 p49 N85-20002 • # NAS 1 60 2334 P14 N85-12313 ' # STS-S5-0570-VOL-2 p49 N85-20001 ' # NAS 1 60 2373 p15 N85-16066 ' # NAS 1 60 2379 P42 N85-19015 * # TAO-34100 p8 N85-11570-* NAS 1 71 LAR-13353-1 p40 N85-20128 * # US-PATENT-APPL-SN-41 7726 P12 N85-21495 # NASA-CASE-LAR-13353-1 p40 N85-20128 ' # US-PATENT-APPL-SN-643524 P40 N85-20128 * #

NASA-CP-2313 P4 N85-11011 * # US-PATENT-CLASS-4 1 7-726 P12 N85-21495 # NASA-CP-2346 p26 N85-13850 ' # NASA-CP-2347 p48 N85-16989 * # US-PATENT-4,482,900 p12 N85-21495 # NASA-CP-2352 pS6 N85-13680 * # NASA-CP-2360 p40 N85-21188 * # X-71 2-84-8 p24 N85-12586 ' # NASA-CP-2364 p57 N85-20339 ' # NASA-CP-2365 p57 N85-20361 * # NASA-CP-2366 p59 N85-21659 * #

NASA-CR-171182 p24 N85-10098 ' #

NASA-CR-171195 P55 N85-12075 * # NASA-CR-171196 p55 N65-12076 ' # NASA-CR-171197 p55 N85-12077 ' # NASA-CR-171201 P11 N85-12200 ' # NASA-CR-171208 p9 N85-13838 * #

NASA-CR-171209 P4 N85-12084 * # NASA-CR-171213 P33 N85-12299 * # NASA-CR-171222 p55 N85-12921 ' # NASA-CR-171223 p56 N85- 13473 ' # NASA-CR-171256 p33 N85-12933 * #

NASA-CR-171272 P56 N85-16981 ' # NASA-CR-171278 p26 N85-15772 ' # NASA-CR-171301 p9 N85-19011 ' # NASA-CR-171353 p39 N85-19137 ' # NASA-CR-171841 p56 N85-17551 ' # NASA-CR-171845 p34 N85-19326 ' # NASA-CR-171848-VOL-1 p49 N85-20000 * # NASA-CR-171849-VOL-2 p49 N85-20001 ' # NASA-CR-171850-VOL-3 p49 N85-20002 ' # NASA-CR-172470 P27 N85-19012 ' # NASA-CR-172473 p8 N85-11570 * # NASA-CR-172497 p39 N85-20019 * # NASA-CR-174065 p24 N85-12931 ' # NASA-CR-174067 P47 N85-12071 ' # NASA-CR-174210 p42 N85-16178 * #

NASA-CR-174257 P47 N85-16302 * # NASA-CR-174438 p39 N85-19519 ' # NASA-CR-174448 P12 N85-19004 ' # NASA-CR-174801 P47 N85-16292 ' # NASA-CR-174802 p47 N85-13371 ' # NASA-CR-175273 p 16 N85-17323 * # NASA-CR-175300 P8 N85-10677 ' # NASA-CR-175470 p34 N85-20244 * # NASA-CR-175483 p59 N85-21414 ' # NASA-CR-177325 p 16 N85-17020 * #

NASA-TM-58264 p9 N85-21262 * # NASA-TM-77557 p24 N85-11381 ' # NASA-TM-85804 p4 N85-12932 " # NASA-TM-86184 p39 N85-17019 * # NASA-TM-86316 P54 N85-10789 ' # NASA-TM-86338 p15 N85-15796 * # NASA-TM-86480 p38 N85-11239 ' # NASA-TM-86489 p9 N85-19013 ' # NASA-TM-86490 P27 N85-19014 * # NASA-TM-86491 P27 N85-1B998 * # NASA-TM-86495 p28 N85-21249 ' # NASA-TM-86496 p28 N85-21248 * # NASA-TM-66498 p9 N85-21232 * # NASA-TM-86969 pSO N8S-21231 ' # NASA-TM-87389 p24 N85-12586 * #

NASA-TP-2334 p14 N85-12313 ' # NASA-TP-2373 P1S N85-16066 * # NASA-TP-2379 p42 N85-19015 • #

PB85-128429 p59 N85-21414 * #

QPR-1 p26 N85-15772 * #

RADC-TR-84-186 p28 N85-21253 #

F-2 ACCESSION NUMBER INDEX

TECHNOLOGY FOR LARGE SPACE SYSTEMS / A Bibliography (Supplement 13) MARCH 1986

Typical Accession Number Index Listing

A85-18671 '# P44 A85-26770 # pS4 N85-14001 tt p11 A85-18672 tt p 20 A85-26771 # p3 N85- 14002 tt PS NASA A85-18692 •# p20 A85-27238 # P23 N85-14004 ft P12 ACCESSION A85-18694 tt p 10 N85-14O06 tt p33 A85-27375 # p3 NUMBER A85-18812 tt p13 N85-14007 # P12 A85-27695 # p3 A85-19462 tt p20 N85- 14008 # p33 A85-27696 # 8 ASS- 19466 # p41 P N85-14009 ft P15 A85-27973 # p54 A85- 19468 • tt P21 N85-14010 tt p33 A85-28126 * # p32 A85- 19493 • tt P14 N85-14011 tt P9 II A85-28275 # MS- 19528 '# p21 P3 N85-14012 tt P15 A85-28488 # p23 A85-19529 tt p21 N85-14013 tt p39 A85-28489 # P11 | | A85- 19553 tt P14 N85-14014 tt P39 A85-28903 # P23 ASS- 19561 ft 45 N85-14015 tt P39 NASA P A85-28906 # P23 MICROFICHE PAGE A85-19595 ft P21 N85-14016 tt P15 DOCUMENT A85-29144 # P23 SYMBOL NUMBER A85-19600 ft N85-14017 tt P15 NUMBER P? A8S-29730 • # P38 ASS- 19660 tt 45 N85-14018 tt p33 P A85-30024 # P38 ASS- 19693 tt p21 N85-14019 tt P26 ASS- 19695 * # p31 N85-14020 ft P26 bstings in this index are arranged alpha- N85-10098 ' # P24 A85-19713 '# 31 N85-14021 # p26 P N85-10099 # P11 numencally by accession number The page A85-19714 ft p45 N85-14022 tt p34 N85-10391 '# P8 number listed to the ngtit indicates the page on A85-19715 '# 45 N85-14492 'ft P42 P N85-10677 • # P8 A85-19744 # p45 N85-14856 # p26 which the citation is located An asterisk (*) N85-10789'# P54 A85-19770 # p37 N85-15772 •# p26 indicates that the item is a NASA report A pound N85-10871 # p4 A85- 19771 tt p37 N85-15796-# pis N85-10872 ft p4 sign (#) indicates that the item is available on A85-19795 '# p53 N85-16066 • tt p15 N85-11011 '# P4 A85-19895 tt P14 N85-16178 •# P42 microfiche N85-11016 '# P32 A85-20400 tt P41 N85- 16292 ' ft p47 N85-11017 •# p32 A85-20507 # N85-16302 ' tt p47 P2 N85-11023 '# p54 A85-10071 tt 17 A85-13252 tt p 13 A85-20866 ' # N85-16963 • tt P42 P P2 N85-11031 '# P11 A85-10261 P50 A85-13253 13 A85-20916 tt p 14 N85-16964 • tt P42 'ft tt P N8S-11032 •# p55 A85-11082 'ft P17 A85-21S08 tt P37 N85-16981 '# p56 A85-13255 tt p35 N85-11035 '# P4 A85-11086 'ft p17 A85-21826 ' tt p53 N85- 16989 •# p48 A85-132S7 tt P35 N85- 11047 '# P38 A85-11087 'ft P17 A85-21829 '# p14 N85-16990 •# p5 A85-13258 tt p36 N85-11050 '# P8 A85-12395 tt p35 A85-21831 •# p53 N85-16993 •# p56 A85-13259 ft p51 N85-11056 '# P55 A85-12434 ft p17 A85-21835 tt P31 N85- 16997 •# p48 N85-11057 •# P55 A85-12442 ft p17 A85-13276 •tt P51 A85-22444 # p45 N85-16998 '# p56 A85-13282 •tt p44 N8S-11239 •# p38 A85-12455 ft p17 A85-22576 # P53 N85-16999 ' tt p48 N85-11363 # P11 A85-1247B tt p18 A85-13293 ft P19 A85-22577 ' tt P2 N85- 17004 '# p48 A85-13SOO tt p36 N8S-11381 '# p24 A85-12502 ft P1 A85-22579 tt P7 N85-17006 •# p48 A85-13634 'ft P19 N85-11382 # p24 A85-12519 tt p43 A85-22584 tt P21 N85-17008 '# p48 A85-13636 'ft p19 N85-11570 '# p8 A85-12520 ft P43 A85-22585 tt p21 N85- 17009 •# p48 N8S-11911 # P4 A85-12884 ft p 13 A85-13638 •tt P19 A85-22586 ' # p22 N85-17010 '# p56 ASS- 13640 tt p29 N8S-12071 '# P47 A85-12926 tt P43 A85-22587 " # p22 NB5-17012 # p 16 N8S-12075 '# p55 A85-12927 ft p50 A85-13641 tt p19 A85-2268S ' ft P7 N85-17013 tt p 16 N85- 12076 •# p55 A85-12933 ft p 10 A85-13893 tt P19 A85-23393 ' tt p46 N85-17014 tt p16 A85-14163 ft p36 N85-12077 •# p55 A85-12979 ft p50 A85-23394 * tt P46 N85-17019 '# p39 A8S-14426 tt p51 N8S-12082 # p24 A85-12981 ff p50 A85-23651 '# P31 N85-17020 '# p 16 N85- 12084 •# P4 A85-12992 tt p6 A85-14429 tt P7 A85-23652 # p32 N85- 17323 '# p 16 N85-12200 '# p11 A85-12994 tt p50 A85-14430 ft p30 A85-23663 ' tt p 10 N85- 17382 tt p16 ASS- 15254 tt p20 N85- 12299 •# p33 A8S-12995 tt P6 A85-23824 tt p53 N85-17428 # P12 A8S-15496 tt P7 N85-12313 '# p14 A85-13000 ft P43 A85-23990 tt p46 N85-17551 •# p56 A85- 15509 tt p52 N85-12586 *# p24 A85-13001 •ft p41 A85-24654 tt P53 N85- 18078 tt P27 ASS- 15626 tt p36 N85-12921 '# p55 ASS- 13009 ft P1 A85-24672 * tt p37 N85-18352 tt P12 A85- 15638 tt p36 N85-12931 *# p24 A85-13016 ft P1 A85-24675 tt p37 N85-18360 tt p27 A85- 15745 tt p20 N85-12932 '# p4 A85-13017 tt p41 A85-24703 " # p38 N85- 18378 ' tt P27 ASS- 15760 tt p30 N85- 12933 '# p33 A85-13021 tt P43 A85-24787 tt p53 N85-18998 'ft P27 A85-15800 •ft p30 N85- 13371 '# P47 A85-13023 ft p 18 A85-24788 ' tt p46 N85- 19004 •# P12 A85-15812 •tt p30 N85-13473 • # p56 ASS- 13040 •tt P29 A85-24790 ' ft p53 N85-19011 '# P9 N85-13837 ft P24 A85-13045 ft A85-15874 It p44 A85-24793 tt p46 N85-19012 •# p27 P1 N85-13838 '# ASS- 13066 ft p29 A85-15976 tt p52 A85-24794 tt p54 p9 N85-19013 'tt p9 N85-13B39 • # 25 A85-13100 ft P6 A85-1S977 tt P36 A85-24817 tt p 10 P N85-19014 •# p27 ASS- 15980 N85- 13840 '# P25 A85-13114 •ft P51 tt p36 A85-24908 tt p8 N85-19015 '# p42 ASS- 15990 N85-13841 •# p25 A85-13141 ft P51 tt p36 A85-24949 tt p22 N85-19018 # p49 ASS- 15992 tt p20 N85- 13842 •# P25 A85-13144 ft P2 A85-25101 tt P32 N85-19137 •# p39 A8S-15993 tt p37 N85-13843 •# p25 A8 5-13146 ft P13 A85-25117 ft p3 N85-19205 # P5 N85- 13844 • tt p25 A85-13148 ft p51 A8S-16081 tt p30 A85-25145 ' ft p14 N85- 19326 ' tt p34 N85- 13845 '# 25 A85-13177 ft p29 A8S-16109 'ft P2 A85-25359 * tt p32 P N85-19519 •# p39 ASS- 16302 52 N85-13846 • # p25 A8S-13191 ft P44 ft P A85-25697 tt p3 N85-20000 ' tt P49 ASS- 16305 p52 N85- 13847 '# p56 ASS- 13206 ft p 18 tt A85-25700 ft p3 N85-20001 'ft P49 A85-16439 •tt p44 N8S-13850 ' # p26 A85-13220 •ft P18 A85-25796 tt p46 N85-20002 ' tt P49 AS 5- 16448 N85- 13854 • # p26 A85-13221 ft p 18 tt p44 A85-25797 ft p46 N85-20019 'ft p39 A85-16499 N8S-13860 • tt p47 A8 5-1 3224 tt P29 tt P37 A85-25828 tt p46 N85-20128 ' tt p40 ASS- 16641 N85-13880 '# p56 A85-13227 tt p41 tt p30 A85-25988 ' tt p38 N85-20174 tt p57 A85-16648 tt P7 N85-13881 •# p33 ASS- 13229 tt P41 A85-2601 1 tt p3 N85-20244 ' » p34 ASS- 16881 tt p52 N85-13886 " tt p4 ASS- 13233 tt P2 A85-26350 tt P22 N85-20339 • tt p57 A85- 17054 tt p20 N85- 13890 ' ft p33 ASS- 13240 tt p 10 A85-26369 tt P54 N85-20341 •# PS A85-17S73 'ft P52 NB5-13892 • tt p33 ASS- 13243 •ft P13 A85-26385 tt p54 N85-20343 • tt P5 ASS- 18321 tt P'3 N85- 13895 '# p 14 ASS- 13244 ft P2 A85-26433 # P22 N85-20344 • ft P9 A85-18331 'ft p20 N85- 13896 ' tt P47 A85-13245 tt P18 A85-26434 tt p22 N85-20345 ' tt P57 A85- 18337 p20 N85-13900 ' tt P15 'ft 5 ASS- 13246 tt P35 A85-26435 ' tt p23 N85-20346 ' tt P ASS- 18338 tt P7 N85-13906 ' # 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p 59

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NASA SPONSORED DOCUMENT AVAILABLE ON MICROFICHE NASA ACCESSION - N85-12932*# National Aeronautics and Space Administration • NUMBER Langley Research Center, Hampton, Va CORPORATE CONCEPTUAL DESIGN FOR SCALED TRUSS ANTENNA SOURCE FLIGHT EXPERIMENT TITLE • W H LEE Nov 1984 40 p refs r—^ (NASA-TM-85804, L-15838, NAS 1 1585804) Avail NTIS HC PUBLICATION A03/MF A01 CSCL 22B DATE AUTHOR The conceptual design for a scaled truss antenna structures expenment program (STASEP) is presented The hardware analysis of the scaled truss antenna structure (STAS) was performed by AVAILABILITY REPORT - interactive design and evaluation of advanced spacecraft (IDEAS) SOURCE NUMBER computer aided, interactive, design and analysis program Four STAS's were designed to be launched by the Shuttle, tested by using the space technology expenments platform (STEP) and space transportation system (STS), and then free flown in short lifetime orbits Data were gathered on deployment, structural characteristics, geometric accuracies, thermal performance, and drag and lifetime as an orbiting spacecraft Structural and thermal properties were determined for the STAS, including mass properties, thermal loading, structural natural frequencies, and mode shapes The necessary analysis, scaling, and ground testing are discussed E A K

TYPICAL CITATION AND ABSTRACT FROM IAA

NASA SPONSORED DOCUMENT -AVAILABLE ON MICROFICHE

AIAA ACCESSION • A85-13243*# National Aeronautics and Space Administration NUMBER Langley Research Center, Hampton, Va •LARGE SPACE STRUCTURES GROUND AND FLIGHT PROGRESS L 0. PINSON (NASA, Langley Research Center, Structural- AUTHOR TITLE- Dynamics Branch, Hampton, VA) International Astronautacal • AFFILIATION Federation, International Astronautical Congress, 35th, Lausanne, Switzerland, Oct 7-13, 1984 9 p refs (IAF PAPER 84-388) • CONFERENCE Unprecedented challenges anse in connection with the design and certification of space systems which are too large to be transported into orbit fully assembled Special situations ansmg in -CONFERENCE the case of such systems make it necessary to rely much more DATE on analysis than in past programs. The present investigation is concerned with the status of some research activities onented primarily to the improvement of analysis capabilities through coordinated ground and flight testing Aspects of system identification are explored, taking into account an eigensystem realization algorithm, and the Hoop-Column Antenna concept Attention is also given to a suitable method for analyzing the Hoop-Column antenna structure, a deployment analysis, certification issues for large space structures, a genenc space station model, and the use of actuators G R 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA SP-7046(13) 4. Title and Subtitle 5. Report Date March 1986 TECHNOLOGY FOR LARGE SPACE SYSTEMS A Bibliography with Indexes 6. Performing Organization Code

7. Author(s) 8. Performing Organization Report No.

10. Work Unit No. 9. Performing Organization Name and Address

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

14 Sponsoring Agency Code

15. Supplementary Notes Compiled by Technical Library Branch and edited by Space Systems Division, Lanoley Research Center, Hampton, Virginia. 16. Abstract

This bibliography lists 399 reports, articles and other documents introduced into the NASA scientific and technical information system between January 1, 1985 and June 30, 1985. Its purpose is to provide helpful information to the researcher, manager, and designer in technology development and mission design 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 Author(s)) 18. Distribution Statement

Large Space Systems Large Space Antenna Large Space Structures Unclassified - Unlimited

19. Security Qassif. (of this report) 20. Security Cassif (of this page) 21. No. of 22. Pnce* Unclassified Unclassified 116 A07/HC

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