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NASA SP-7046(17) Technology for October 1987 NASA Large Space Systems A Bibliography with Indexes

(NASA-SP-7046 (17) ) TECHNOLOGY FOR LAtiGi3 N 87- 2 9575 SPhCE SYSTEZS. A BIBLIOGBAPHY WITH IblOUES [SUPPLEHENT 17) (NASA) 140 p Avail: NTIS tlC A07 CSCL L2B unclas W/12 0102763 NASA SP-7046(17)

TECHNOLOGY FOR LARGE SPACE SYSTEMS

A BIBLIOGRAPHY WITH INDEXES

Supplement 17

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 30,1987 in

Scientific and Technical Aerospace Reports (STAR) international Aerospace Abstracts (IAA).

Scientific and Technical Information Division 1987 National Aeronautics and Space Administration Iu/\sJ\ 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. INTRODUCTION

This bibliography is designed to be helpful to the researcher and manager engaged in the developing technology within the discipline areas of the Large Space Systems Technol- ogy (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 512 reports, articles and other documents announced between January 1, 1987 and June 30, 1987 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 antennas which are fabricated, assembled, and packaged on Earth with automatic deployment in space, and space fabri- cated 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, as- sembly 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 Division Sue K. Seward, Technical Library Branch TABLE OF CONTENTS

Page Category 01 Systems 1 Includes mission and program concepts and requirements, focus missions, concep- tual studies, technology planning, systems analysis and integration, and flight experiments.

Category 02 Analysis and Design Techniques 11 Includes interactive techniques, computerized technology design and development programs, dynamic analysis techniques, environmental modeling, thermal model- ing, and math modeling.

Category 03 Structural Concepts 15 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 18 Includes structural analysis and design, thermal analysis and design, analysis and design techniques, and thermal control systems.

Category 05 Structural Dynamics and Control 23 Includes modeling, systems identification, attitude and control techniques, surface accuracy measurement and control techniques and systems, sensors and ac- tuators.

Category 06 Electronics 42 Includes techniques for power and data distribution, antenna RF performance analysis, communications systems, and spacecraft charging effects.

Category 07 Advanced Materials 48 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 58 Includes automated manipulator techniques, EVA, robot assembly, teleoperators, and equipment installation.

Category 09 Propulsion 63 Includes propulsion concepts and designs utilizing solar sailing, solar electric, ion, and low thrust chemical concepts.

Category 10 General 63 Includes either state-of-the-art or advanced technology which may apply to Large Space Systems and does not fit within the previous categories. Publications of conferences, seminars, and workshops are covered in this area. Subject Index ...... A-1 Personal Author Index ...... B-1 Corporate Source Index ...... C-1 Foreign Technology Index ...... D-1 Contract Number 'Index ...... E-'i Report Number Index ...... F-1 Accession Number Index ...... G-1

V TYPICAL REPORT CITATION AND ABSTRACT

NASA SPONSORED

ON MICROFICHE

ACCESSION NUMBER - N87-16870'# Astro Aerospace Corp., Carpinteria. Calif. CORPORATE SOURC TITLE -EVALUATION OF PACTRUSS DESIGN CHARACTERISTICS CRITICAL TO SPACE STATION PRIMARY STRUCTURE Final Report & PUBLICATION DATE AUTHOR -JOHN M. HEDGEPETH 20 Feb. 1987 74 p CONTRACT NUMBER (Contract NAS1-17536) REPORT NUMBERS -(NASA-CR-178171; NAS 1.26:178171; AAC-TN-1147-REV-A) AVAILABILITY SOURCE Avail: NTlS HC A04/MF A01 CSCL 22A 4 COSATI CODE - I PRICE CODE Several aspects of the possible application of the Pactruss concept to the primary truss structure of the space station are investigated. Estimates are made of the loads and hinge moments in deploying diagonal members as full deployment is approached. Included are the effects of beam columning and compliance of the surrounding structure. Requirements for joint design are suggested and a two-stage mid-diagonal latching hinge concept is described or analyzed. The problems with providing the experimental and theoretical tools needed for assuring reliable synchronous deployment are discussed and a first attempt at high-fidelity analytical simulation with NASTRAN is described. An alternative construction scenario in which the entire dual-keel truss structure is deployed as a single Shuttle payload is suggested. Author

TYPICAL JOURNAL ARTICLE CITATION AND ABSTRACT

NASA SPONSORED IrONMICROFICHE ACCESSION NUMBER -A87-27948'# Virginia Polytechnic Inst. and State Univ., Blacksburg. TITLE -EFFECT OF SENSOR AND ACTUATOR ERRORS ON STATIC SHAPECONTROLFOR LARGESPACESTRUCTURES AUTHOR -RAPHAEL T. HAFTKA (Virginia Polytechnic Institute and State -AUTHOR'S AFFlLlATlOr University, Blacksburg) and HOWARD M. ADELMAN (NASA, Langley Research Center, Hampton, VA) AlAA Journal (ISSN JOURNAL TITLE 0001-1452), vol. 25, Jan. 1987, p. 134-138. Previously announced t, JOURNAL DATE in STAR as N85-29998. refs An analytical study was performed to predict and assess the effect of actuator and sensor errors on the performance of a shape control procedure for flexible space structures using applied temperatures. Approximate formulas were derived for the expected value and variance of the rms distortion ratio (ratio of rms distortions with and without corrections) based on the assumption of zero-mean normally distributed random errors in measured distortions and actuator output temperatures. Studies were carried out for a 55-meter radiometer antenna reflector distorted from its ideal parabolic shape by nonuniform orbital heating. The first study consisted of varying the sensor and actuator errors for the case of 12 actuhtors and computing the distortion ratio. In the second study, sensor and actuator errors were prescribed and the effect of increasing the number of actuators was evaluated. Author

vi TECHNOLOGY FOR LARGE SPACE SYSTEMS A Bibliography (supp/. 17)

OCTOBER 1987

01 and the proposed Space Station. Recommendations for the future include a long-term program to establish a permanent manned SYSTEMS station on Mars, reinvestigation of a solar-power-satellite system, transfer of STS operations to an independent agency, longer-term funding of NASA R&D programs by Congress, competitive Includes mission and program concepts and requirements, focus development of a new lower-cast heavy-lift launcher, more use of missions, conceptual studies, technology planning, systems military rockets, and international cooperation on large-scale analysis and integration, and flight experiments. undertakings. T.K.

A87-10043' National Aeronautics and Space Administration, A87-14969 Washington, D.C. THE SPACE STATION - UNITED STATES PROPOSAL AND TECHNICAL ASPECTS OF THE UNITED STATES SPACE IMPLEMENTATION STATION E. GALLOWAY Journal of Space Law, vol. 14, no. 1, 1986, p. D. H. HERMAN (NASA, Washington, DC) and D. BRIEHL IN: 14-39. refs Space Congress, 23rd, Cocoa Beach, FL, April 22-25, 1986, NASA's Space Station program has unique technical Proceedings . Cape Canaveral, FL, Canaveral Council of Technical characteristics which distinguish it from past international space Societies, 1986, p. 7-1 to 7-6. programs; agreements for its establishment must take these The design and development of the Space Station are features into account. The engineering calculation of adding described. The proposed design of the Station is a dual keel modules over time should be matched with legal provisions for configuration which will include manned facilities and unmanned jurisdiction and control. Attention is presently given to the legal free flying platforms. The Station is to be utilized as a space-based aspects of launching authority, objects launched into outer space, laboratory for basic research and observations, a depot for repair registration of space objects, peaceful and military purposes, and servicing of spacecraft, a strorage area, and a manufacturing exploration and use of the moon, and .relationships with the United facility. International participation in the Space Station program Nations specialized agencies and other international and technological developments applicable for the Station are organizations. O.C. discussed. A diagram of the Space Station configuration and a Space Station development schedule are provided. I.F. A87-15377' National Aeronautics and Space Administration. Goddard Space Flight Center, Greenbelt, Md. A87-12086 THE SPACE STATION PROGRAM ON THE INITIATION OF SPS DEVELOPMENT N. W. HINNERS (NASA, Goddard Space Flight Center, Greenbelt, K. KURlKl (Tokyo, University, Japan) (University of Tokyo, Institute MD) IN: Space Station beyond IOC; Proceedings of the of Space and Astronautical Science, Space Energy Symposium, Thirty-second Annual International Conference, Los Angeles, CA, 4th. Tokyo, Japan, Mar. 1, 1985) Space Solar Power Review (ISSN November 6, 7, 1985 . San Diego, CA, Univelt, Inc., 1986, p. 0191-9067), vol. 5, no. 4, 1985, p. 315-320. 11-17. The concept of finite time availability, a new idea of (AAS PAPER 85-451) thermodynamics, is applied to decisions on when the development Cost constraints to a large degree control the functionality and of the solar power satellite (SPS) should be initiated and how form of the IOC of the Space Station. Planning of Station missions long a lead time should be taken. Admitting the errors in estimation must be delayed to retain flexibility, a goal also served by modular of parameters, an earlier start is concluded to be much safer development of the Station and by multi-use laboratory modules. than a delayed start. Author Early emphasis on servicing other spacecraft is recommended, as is using available Shuttle flight time for R&D on Space Station A87-14375 technologies and operations. M.S.K. GETTING BACK ON TRACK IN SPACE R. A. LEWIS (Arizona, University, Tucson) and J. S. LEWIS A87-15380 Technology Review (ISSN 0040-1692), vol. 89, Aug.-Sept. 1986, SPACE STATION EVOLUTION - THE AEROSPACE p. 30-40. TECHNOLOGY IMPACT The history, current status, and future of the US space program R. W. HAGER (Boeing Aerospace Co., Seattle, WA) IN: Space are examined critically from a science perspective. Topics Station beyond IOC; Proceedings of the Thirty-second Annual discussed include the early Soviet lead in heavy boosters, the International Conference, Los Angeles, CA, November 6, 7, 1985 success of the Apollo program, the lack of an Apollo follow-up . San Diego, CA, Univelt, Inc., 1986, p. 39-43. program, economic and political factors affecting the decision to (AAS PAPER 85-456) concentrate NASA efforts on the Space Shuttle (STS), the Space Station-related technologies which will be further abandonment of the Saturn boosters and Skylab, the increasing developed after IOC are described. The Station IOC may require costs of STS, concomitant decreases in overall NASA funding, 90-day resupply missions, each carrying 5000 Ib of oxygen, nitrogen military demands on STS, and the slow but continuing progress and water and picking up waste and delivering food for six of the Soviet space program. It is argued that space science astronauts. Logistics requirements will be reduced as the Station objectives would have been and will be better served by a evolves into an ecological system within 3-5 percent of complete diversified program of mainly unmanned missions than by independence. One standard 434 module can hold enough growing all-purpose (commercial/military/science) programs such as STS plants to supply 2.5 astronauts and transform their wastes. Expert

1 01 SYSTEMS systems and low-cost, high power sources will be required for A87-16096’# National Aeronautics and Space Administration, production-scale materials processing. M.S.K. Washington, D.C. TECHNOLOGIES FOR AFFORDABLE ACCESS TO SPACE A87-15814# R. S. COLLADAY and S. R. SADlN (NASA, Washington, DC) IAF, HUBBLE SPACE TELESCOPE - DAWN OF THE ERA OF International Astronautical Congress, 37th. Innsbruck, Austria, Oct. SERVICEABLE SPACECRAFT 4-1 1, 1986. 8 p. L. A. WICKMAN (Lockheed Missiles and Space Co., Inc., Sunnyvale, (IAF PAPER 86-442) CA) IAF, International Astronautical Congress, 37th. Innsbruck, NASA plans for advanced research and technology programs Austria, Oct. 4-1 1, 1986. 5 p. aimed at reducing operating costs and extending the capability of (IAF PAPER 86-20) future space systems are described. The evolution of an almost The Hubble Space Telescope, scheduled for launch in late entirely space-based mode is discussed, including the role of earth 1988, is designed to include on-orbit servicing as an integral part launch, servicing, fabrication and assembly and communications. of its operational plan. Here, the design philosophy of the Space The development of technology for affordable access to space is Telescope and the lessons learned are explored insofar as they examined, taking into account progress in the areas of telerobotics, can be applied to the design of future serviceable spacecraft. In machine autonomy, human autonomy, space-based manufacturing particular, attention is given to the use of orbital replaceable units, and construction, electric power, and space-based propulsion. redundancy, environmental considerations, workspace accessibility, C.D. and standardization of the design of mechanical fasteners. V.L. A87-16105# A87-15817’# National Aeronautics and Space Administration, MODELING AND SIMULATION OF LARGE SCALE SPACE Washington, D.C. SYSTEMS STRATEGIC PLANNING IMPLICATIONS SPACE CONSTRUCTION RESULTS - THE EASE/ACCESS S. NOZETTE, H. DAVIS (Large Scale Programs Institute, Austin, FLIGHT EXPERIMENT TX), and C. BILBY (Texas, University, Austin) IAF, International I. BEKEY (NASA, Office of Space Flight, Washington, DC) IAF, Astronautical Congress, 37th, Innsbruck, Austria, Oct. 4-1 1, 1986. International Astronautical Congress, 37th, Innsbruck, Austria, Oct. 6 p. refs 4-1 1, 1986. 6 p. (IAF PAPER 86-453) (IAF PAPER 86-26) NASA ground and flight test activities aimed at the development A87-16 1OS# of in-space construction techniques for the assembly of MOON FOR TERRESTRIAL ENERGETICS Space-Station-sizedstructures are described. In particular, attention M. POSPlSlL and I.POSPISILOVA IAF, InternationalAstronautical is given to the EASE and ACCESS flight experiments, the ground Congress, 37th, Innsbruck, Austria, Oct. 4-1 1, 1986. 4 p. refs and water tank program, and operations in-flight including (IAF PAPER 86-456) instrumentations. The baseline experiments demonstrate that The development of a space energy system for the earth using erectable structures can be assembled effectively by astronauts lunar resources is considered. The resources of the moon and in EVA. The average assembly time for a 45-foot truss was 25.5 their applications are discussed. The capabilities and costs of a minutes; the assembly rate was 3.6 struts per minute. V.L. lunar satellite power system and a lunar base are examined. I.F.

A87-15818# A87-161 lo‘# National Aeronautics and Space Administration. THE ESA/MBB UNFURLABLE MESH ANTENNA DEVELOPMENT Langley Research Center, Hampton, Va. FOR MOBILE SERVICES SPACE STATION DESIGN FOR GROWTH H. KELLERMEIER, H. VORBRUGG (MBBIERNO, Ottobrunn, West E. B. PRITCHARD (NASA, Langley Research Center, Hampton, Germany), K. PONTOPPIDAN (TICRA AIS, Copenhagen, VA) IAF, International Astronautical Congress, 37th, Innsbruck, Denmark), and D. C. G. EASTON (ESA, European Space Austria, Oct. 4-1 1, 1986. 9 p. Technology Centre, Noordwijk, Netherlands) IAF, International (IAF PAPER 86-461) Astronautical Congress, 37th. Innsbruck, Austria, Oct. 4-1 1, 1986. This paper reviews the current status of Space Station planning 8 p. refs for growth as the basis of an assessment of potential Space (IAF PAPER 86-27) Station evolution directions in the 21st Century to meet the The Offset Unfurlable Mesh Antenna (UMA) concept being challenges of the report of the US. National Commission on space, developed at MBB for communication missions ranging from 850 ’Pioneering the Space Frontier’. Thus future mission requirements MHz up to 12 GHz is reviewed with reference to the main stages are reviewed and assessed. Based on these requirements, of the program, its current status, the performance of the UMA evolution scenarios and potential configurations are developed. It concept, and technology demonstration. The design development is concluded that the Space Station, as a multipurpose facility, of the Technology Demonstration Model indicates that this type should evolve to a capability of 300 kW, crew of 18 and 5 lab of reflector can meet the objectives not only in relation to M-SAT modules. Beyond this capability it will be necessary to separate requirements but also in relation to other missions. These include functions and establish two separate Space Stations, one for meeting the surface tolerance and mesh characteristics required research and one for operational activities (e.g., transportation to reduce more stringent side lobe damping requirements and node, servicing, etc.). If the US. National Commission on space’s frequency reuse (multibeam capability) for a 5-m C-band lntelsat recommendations are adopted, this separation or ’branching’ could application and an 8-m L-band multibeam application. V.L. occur as early as 2005 to meet the needs of a permanent lunar base. Author A87-15904# COMPACT SPS FOR LUNAR DEVELOPMENT A87-16399 M. POSPlSlL and L. POSPISILOVA IAF. International Astronautical SPACE STATION - NASAS GREATEST CHALLENGE Congress, 37th. Innsbruck, Austria, Oct.’ 4-1 1, 1986. 6 p. refs T. FURNISS Flight International (ISSN 0015-3710), vol. 130, (IAF PAPER 86-156) Aug. 30, 1986, p. 137-140. The development of compact solar power satellites (SPS) for An account is given of the progress made by NASA on a use on a lunar base is examined. The SPS is to collect solar Space Station; attention is given to the apportionment of radiation in space and convert it to a usable form. The compact development tasks among NASA facilities and foreign participants SPS uses one structure for both the solar radiation reception and in this international project. When completed, the NASA Space transmitting beam emission and it produces a microwave beam of Station will encompass four manned modules, of which two will high power density. The proposed requirement and capabilities be from the US., one from Europe, and the last from Japan. For for a lunar power satellite are discussed. Potential uses for the the first time in any US. manned spacecraft, there will be a closed microwave beam are considered. I.F. loop environmental control and life support system. O.C.

2 01 SYSTEMS

A87-16930* # National Aeronautics and Space Administration, A87-18508* Jet Propulsion Lab., California Inst. of Tech., Washington, D.C. Pasadena. TELESCIENCE IN ORBIT SYSTEM CONCEPT FOR A MODERATE COST LARGE D. C. BLACK (NASA, Office of Space Station, Washington, DC) DEPLOYABLE REFLECTOR (LDR) Aerospace America (ISSN 0740-722X). vol. 24, Sept. 1986, p. P. N. SWANSON, J. B. BRECKINRIDGE. A. DINER, R. E. 44-46. FREELAND, W. R. IRACE, P. M. MCELROY, A. E. MEINEL, and A promising concept for the scientific use of the NASA Space A. F. TOLIVAR (California Institute of Technology, Jet Propulsion Station involves attaching payloads to the dual keel truss structure Laboratory, Pasadena) Optical Engineering (ISSN 0091 -3286), of the manned base, specifically on the upper and lower booms. vol. 25, Sept. 1986, p. 1045-1054. NASA-supported research. The lower boom will be primarily employed by the earth observation refs and space plasma studies community, while the upper boom will A study was carried out at JPL during the first quarter of 1985 be used by astronomers for such instruments as the Solar Optical to develop a system concept for NASA's LDR. Major features of Telescope and the Astrometric Telescope Facility. The the concept are a four-mirror, two-stage optical system; a indispensability of a robust Space Shuttle system for these Space lightweight structural composite segmented primary reflector; and Station uses is noted. O.C. a deployable truss backup structure with integral thermal shield. The two-stage optics uses active figure control at the quaternary reflector located at the primary reflector exit pupil, allowing the large primary to be passive. The lightweight composite reflector panels limit the short-wavelength operation to approximately 30 A87-18064'# National Aeronautics and Space Administration. microns but reduce the total primary reflector weight by a factor Lewis Research Center, Cleveland, Ohio. of 3 to 4 over competing technologies. On-orbit thermal analysis SPACECRAFT 2000 - THE CHALLENGE OF THE FUTURE indicates a primary reflector equilibrium temperature of less than H. W. BRANDHORST, JR., K. A. FAYMON, and R. W. BERCAW 200 K with a maximum gradient of about 5 C across the 20-m (NASA, Lewis Research Center, Cleveland, OH) IN: IECEC '86; aperture. Weight and volume estimates are consistent with a single Proceedings of the Twenty-first lntersociety Energy Conversion Shuttle launch, and are based on Space Station assembly and Engineering Conference, San Diego, CA, August 25-29, 1986. checkout. Author Volume 3 . Washington, DC, American Chemical Society, 1986, p. 1397-1400. A87-19789 The need for spacecraft bus technology advances in order to LARGE INFLATABLE PARABOLIC REFLECTORS IN SPACE develop the spacecraft for the 21st century is discussed. E. AUTHIER and L. HILL (CNRS, Laboratoire d'Astronomie Consideration is given to the power and electric propulsion systems Spatiale, Marseille, France) IN: Instrumentation for submillimeter for mass-limited satellites such as LEO and GEO. The goal of spectroscopy; Proceedings of the Meeting, Cannes, France, spacecraft bus technology programs is to design a cost-effective December 5, 6. 1985 . Bellingham, WA, Society of Photo-Optical spacecraft which operates well in the satellite environment. The Instrumentation Engineers, 1986, p. 126-132. possibility of collaboration between government and industry is A requirement is noted where large aperture parabolic reflectors examined. IF. are needed for space applications in different wavelength ranges where a high accuracy is required for the reflecting surfaces. It is proposed to get more accurate surfaces by replacing the preformed flexible membranes presently scheduled in the inflatable technology, by elastic disks whose thickness variation along a A87-18242 radius is calculated in order to obtain (after inflation) parabolic SIMPLEX MAST - AN EXTENDIBLE MAST FOR SPACE APPLICATIONS caps. To illustrate the method, polyester and polyimide membranes K. MIURA, M. NATORI, M. SAKAMAKI (Tokyo, University, Japan), are investigated. If a variable thickness from the center to the Y. KAKITSUBO, and H. YAHAGI (Japan Aircraft Manufacturing edge is obtainable, constructing large aperture parabolic caps by Co., Ltd., Yokohama) IN: International Symposium on Space this method appears feasible. The surface accuracy depends mainly Technology and Science, 14th, Tokyo, Japan, May 27-June 1, on the elastic properties of the material and control of thickness. 1984, Proceedings . Tokyo, AGNE Publishing, Inc., 1984, p. D.H. 357-362. refs A possible concept of an extendible mast for space applications A87-21807' National Aeronautics and Space Administration. which is called a Simplex Mast is introduced. It consists of Lewis Research Center, Cleveland, Ohio. continuous longerons, integrated radial spacers and diagonal wires. NASA GROWTH SPACE STATION MISSIONS AND CANDIDATE Model experiments to confirm the effectiveness of the concept is NUCLEAWSOLAR POWER SYSTEMS presented, and one of the applications of this mast to a scientific JACK A. HELLER and JOSEPH J. NAlNlGER (NASA, Lewis spacecraft is also introduced. Author Research Center, Cleveland, OH) IN: Space nuclear power systems 1985; Proceedings of the Second Symposium, Albuquerque, NM, Jan. 14-16, 1985. Volume 3 . Malabar, FL, Orbit Book Co., Inc., 1987, p. 47-52. NASA sponsored research. A brief summary is presented of a NASA study contract and A87-18453" National Aeronautics and Space Administration, in-house investigation on Growth Space Station missions and Washington, D.C. appropriate nuclear and solar space electric power systems. By AN OVERVIEW OF NASAS PROGRAMS AND PLANS the year 2000 some 300 kWe will be needed for missions and S. W. KELLER (NASA, Office of Space Science and Applications, housekeeping power for a 12 to 18 person Station crew. Several Washington, DC) IN: Space exploitation and utilization; Space Station configurations employing nuclear reactor power Proceedings of the Symposium, Honolulu, HI, December 15-19, systems are discussed, including shielding requirements and power 1985 . San Diego, CA, Univelt, Inc., 1986, p. 37-44. transmission schemes. Advantages of reactor power include a (AAS PAPER 85-647) greatly simplified Station orientation procedure, greatly reduced An overview is given of NASA's technical program offices and occultation of views of the earth and deep space, near elimination their status, recent accomplishments, and plans for the future, of energy storage requirements, and significantly reduced Programs covered include the Space Transportation System, TDRS, station-keeping propellant mass due to very low drag of the reactor the Deep Space Network, the various Spacelab missions, the power system. The in-house studies of viable alternative Growth Galileo mission to Jupiter, the Ulysses mission over the poles of Space Station power systems showed that at 300 kWe a rigid the sun, the Hubble Space Telescope, and the Space Station silicon solar cell array with NiCd batteries had the highest specific program. D.H. mass at 275 kg/kWe, with solar Stirling the lowest at 40 kg/kWe.

3 01 SYSTEMS

However, when 10 year propellant mass requirements are factored and terrestrial infrastructure of the Columbus including data in, the 300 kWe nuclear Stirling exhibits the lowest total mass. processing and telecommunication systems concerned with the Author coordination of operations on the Station are examined; various applications for the Station are proposed. Consideration is given A87-22721# to the financing of the program, the allocation of costs, the composition of the crew and workload, the allocation of time for COST REDUCTION~ ON LARGE SPACE SYSTEMS THROUGH COMMONALITY use of the Space Station facilities, and technology transfer. I.F. R. D. WAISS (Boeing Aerospace Co., Seattle, WA) AIAA, Aerospace Sciences Meeting, 25th, Reno, NV, Jan. 12-15, 1987. 9 p. refs (AIAA PAPER 87-0585) A87-25752 The need for commonality in large space systems is discussed. SPACE STATION - DESIGNING THE FUTURE The basic goal of a commonality program is to reduce total system ROBERT THOMPSON (McDonnell Douglas Astronautics Co., Saint cost by maximizing the use of standard and common parts, Louis, MO) IN: Space Tech '86; Proceedings of the International assemblies, subsystems, and/or systems. The application of Conference, Geneva, Switzerland, May 14-16, 1986 . London, commonality to the development, production, deployment, and Online International, Ltd., 1986, p. 9-20. operations of large space structure is examined. The economic Requirements for the proposed Space Station, which is to benefits of a commonality approach to large space system provide permanent life support and housing for an international development are evaluated. Consideration is given to mandated crew, are examined. The proposed dual-keel design of the Space and nonmandate approaches for implementing commonality. IF. Station, pressurized cylindrical crew modules, and subsystems (electrical, thermal control, data management, life support control, A87-22751*# National Aeronautics and Space Administration. and propulsion) are described. The Space Station is to be designed Marshall Space Flight Center, Huntsville, Ala. to meet users's demands and to be built using a phase development LARGE SPACE OBSERVATORIES OF THE 21ST CENTURY approach. The stages of the phase development are discussed. M. NEIN, J. HOWELL, S. MORGAN, C. DE SANCTIS (NASA, The basic missions of the Space Station include: (1) science, (2) Marshall Space Flight Center, Huntsville, AL), and D. KOCH commercial, (3) technology development, and (4) space operations. (Smithsonian Astrophysical Observatory, Cambridge, MA) AIAA, Consideration is given to the use of robotic devices on the Station Aerospace Sciences Meeting, 25th, Reno, NV, Jan. 12-15, 1987. and the development costs. I.F. 17 p. refs (AIAA PAPER 87-0636) Early in the 21st century, advanced space telescopes will be readied to continue the astronomical observations of the Great A87-25758 Observatories currently under development. This paper describes THE ROLE OF EXPERT SYSTEMS ON SPACE STATION representative concepts from the very large UV/optical and D. R. SLOGGETT (Software Sciences, Ltd.; Environmental and gamma-ray telescopes under study by NASA, the scientific Space Systems Group, Farnborough, England) IN: Space Tech community, and industry. These studies demonstrate that historical '86; Proceedings of the International Conference, Geneva, approaches to improving the resolution and sensitivity of space Switzerland, May 14-16, 1986 . London, Online International, Ltd., telescopes have reached technology barriers which can only be 1986, p. 91-107. refs overcome by innovative solutions to the telescope design. Some The planned deployment of the Space Station, and its of the key technology issues which are guiding the approaches associated orbital infrastructure, repreents a unique opportunity to for advanced space telescopes are discussed, and arguments are evaluate the potential of expert systems to assist in increasing presented that enabling technology development for these iuture the autonomy, productivity and effectiveness of the Space Station. systems must commence now. Author This paper seeks to address what current technology can provide to achieve this aim, and highlights previous practical examples of A87-22771 Space AI Systems. The paper makes suggestions for practical SOLAR POWER SATELLITE CONCEPT REVISITED research programs, that require urgent attention, to pave the way PETER E. GLASER (Arthur D. Little, Inc., Cambridge, MA) Space and demonstrate capability in areas of relatively new technology. Power (ISSN 0883-6272), vol. 6, 1986, p. 157-163. refs From this base the paper suggests some practical areas where The continued evolution of the solar power satellite (SPS) AI technology can be applied to the Space Station and their concept is reviewed. The advances in generic technologies resulting benefits. Specific attention is drawn to the application of applicable to the SPS resulting from the growth of commercial expert systems to planning and scheduling and the application of activities in space, the Space Station program and the strategic expert monitoring systens to assist in fault diagnosis and repair. defense initiative are highlighted. The growing international The paper concludes that urgent attention is required in the area literature on the SPS is cited to indicate that this concept continues of demonstration programs where low-risk state-of-the-art to receive consideration. Significant developments, including developments can be undertaken resulting in very real benefits to photovoltaic and solar dynamic conversion, space experiments to the Space Station system. Author test performance of critical technologies, power distribution subsystems, automation and teleoperators that are advancing the feasibility of the SPS are discussed. The possibility of a return to the moon and uses of lunar resources for SPS construction are A87-25759 mentioned as examples of space missions that will contribute to SPACE STATION - THE USE OF EXPERT SYSTEMS FOR the buildup of the industrial infrastructure that can be the foundation PLANNING for SPS development. Author JENS GULDBERG and JENS LANGELAND (Computer Resources International A/S, Denmark) IN: Space Tech '86; Proceedings A87-24123# of the International Conference, Geneva, Switzerland, May 14-16, THE INTERNATIONAL SPACE STATION TAKES SHAPE [DIE 1986 . London, Online International, Ltd., 1986, p. 109-117. refs INTERNATIONALE RAUMSTATION NIMMT GESTALT AN] Expert systems have been shown to provide useful techniques SABINE HOLL Luft- und Raumfahrt (ISSN 0173-6264), vol. 7, for handling planning problems related to the operation of complex 3rd Quarter, 1986, p. 76-79. In German. systems and to system engineering. A brief review of the principle European technological contributions to the proposed Space features of such planning systems is used as a reference for a Station are reviewed. The Europeans are involved in the design, discussion on relevant applications for the Space Station, which development, and utilization of such components as a pressurized include, e.g., mission planning, scheduling of maintenance, software module, polar platforms, and data processing units. The orbital development, payload design, and check-out procedures. Author

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A87-27455 advanced communications satellites using TDMA techniques, and RATlONALlSlNG SPACE STATION mobile communications systems are summarized, along with the TIM FURNISS Space (ISSN 0267-954X), vol. 2, Dec. 1986-Feb. NASA ACTS and MSAT-X satellites for exploring the necessary 1987, p. 28-30, 36. technologies. The roles the Space Station and unmanned GEO Design and applications requirements which are guiding the platforms will play in future satellite communications are definition of the configuration for the manned Space Station (MSS) discussed. M.S.K. are summarized. A dual-keel design is necessitated by the need to place the modules at the center of gravity to facilitate micro-g A87-31123’# National Aeronautics and Space Administration, materials processing studies. Solar dynamic generators will replace Washington, D.C. some of the solar panel capacity to reduce drag on the MSS. NASA’s TECHNOLOGY PLANS - WILL TECHNOLOGY BE Several details of the cabin atmosphere, payload servicing READY WHEN WE ARE accommodations, closed loop operations, and co-orbiting and polar RAYMOND S. COLLADAY (NASA, Office of Aeronautics and Space orbiting platform segments of the MSS are outlined, along with Technology, Washington, DC) AIAA, NASA, and USAF, design changes in the aftermath of the Challenger catastrophe. Symposium on Automation, Robotics and Advanced Computing M.S.K. for the National Space Program, 2nd. Arlington, VA, Mar. 9-11, 1987. 5 p. A87-27605# (AIAA PAPER 87-1695) FRONT END LOGISTICS INFLUENCE ON SPACE SYSTEM Recent low NASA science and technology budgets impacted HARDWARE DESIGN unfavorably on trade balances of aerospace products and lags in CHARLES 0. COOGAN (Acquisition Logistics Engineering, several technological areas impinged on other areas already in Worthington, OH) IN: Space Logistics Symposium, 1st, Huntsville, application which could not be exploited or did not achieve desired AL, Mar. 24-26, 1987, Technical Papers . New York, American performance levels. NASA has formed a Civil Space Technology Institute of Aeronautics and Astronautics, 1987, p. 5-11. Initiative, for 1988 start, to foster research on safe and efficient (AIAA PAPER 87-0658) access to space, earth orbiting operations, and science support The application of logistics analysis in systems engineering of technologies. R&D programs for fully reusable launch systems, designs for future space systems are described. The next phase aerobraking concepts, and a multi-arm, highly autonomous of space operations, i.e., long-duration large-scale missions, capability for space-based remote assembly, repair and servicing requires operational efficiency and reduced support burdens. of space vehicles are described. Regarding science, emphasis Logistics analysis can be applied during the R&D phase of training will be placed on large flexible structures and the associated control activities and the definition of space systems maintenance programs, sensors and data handling and analysis equipment and requirements, for projecting the support requirements of programs. Finally, technologies common to human activities in production-linespace components, for planning launch preparation regions beyond the Space Station are to be explored in the second activities, and for planning space servicing procedures, supplies phase of the NASA initiative, Pathfinder. M.S.K. and support requirements. Components and their lifetimes are considered; the combined subcomponent costs are a major A87-31208# determinant of systems costs, a view complementary to a systems CLEANING UP OUR SPACE ACT engineering approach. Logistics analysis is useful in the formation BRUCE FRISCH Aerospace America (ISSN 0740-722X), vol. 25, of design concepts, and is relatively ineffective if applied during Feb. 1987, p. 10, 11. operational phases. M.S.K. Space operations have left a significant, and increasing amount, of small debris in orbital slots which are preferred for manned A87-28953 activities. Outgassed material and solid rocket propellant grains EXTENDING THE SPACE STATION INFRASTRUCTURE can abrade spacecraft windows and degrade optical sensors. A C. M. HEMPSELL (British Aerospace, PLC, Space and hypervelocity microscopic paint chip once left a 4 mm diam crater Communications Div., Stevenage, England) British Interplanetary in an Orbiter window. Exploding final stages from the Delta and Society, Journal (Space Stations) (ISSN 0007-084X), vol. 40, Jan. Ariane rockets have left thousands of small pieces in LEO. The 1987, p. 19-26. number of particles multiplies as collisions occur. NORAD now The Space Station program will create an infrastructure of tracks 6000 pieces of debris in LEO. The problem will be acute support elements in the space environment. This program has for Space Station astronauts in EVA, who will wear new spacesuits widespread international collaboration producing many different with more rigid, impact-resistant parts, and the Space Station, elements, but despite this there remains a potential for expansion which will have a much larger cross section exposed to, e.g.. of the infrastructure in terms of new locations and the facilities screws travelling at 10 km/sc. M.S.K. offered. This paper lists 71 possible major systems of which only 21 are currently projected for development. The constraints on N87-10170*# National Aeronautics and Space Administration. further expansion being funding limitations. To allow expansion of Langley Research Center, Hampton, Va. the Station beyond the initial operational configuration the paper A SPACE STATION STRUCTURES AND ASSEMBLY proposes three approaches: (1) review funding sources, (2) design VERIFICATION EXPERIMENT, SAVE elements to allow expansion, and (3) introduce multifunction R. A. RUSSELL, J. P. RANEY, and L. J. DERYDER Aug. 1986 designs. Author 376 p (NASA-TM-89004; NAS 1.1589004) Avail: NTlS HC A1 7/MF A87-30891 A01 CSCL22B COMMUNICATIONS SPACECRAFT The Space Station structure has been baselined to be a 5 M SAMUEL W. FORDYCE IN: Space science and applications: (16.4 ft) erectable truss. This structure will provide the overall Progress and potential . New York, IEEE Press, 1986, p. 201-213. framework to attach laboratory modules and other systems, Progress in the designs and performance capabilities of subsystems and utilities. The assembly of this structure represents communications satellites is traced from the Echo 1 AI-coated a formidable EVA challenge. To validate this capability the Space mylar balloon in 1960 to systems planned for the 1990s and Station Structures/Dynamics Technical Integration Panel (TIP) met beyond. The services allowed with the passive balloon concept to develop the necessary data for an integrated STS structures were too limited and led to Telstar spacecraft, with 600 voice flight experiment. As a result of this meeting, the Langley Research channels, being placed in elliptical orbits. Geosynchronous Center initiated a joint LangleyIBoeing Aerospace Company study communications began in 1963 with the Syncom satellite, which which supported the structures/dynamics TIP in developing the also carried television signals. The evolution of subsequent lntelsat preliminary definition and design of a 5 M erectable space station and ANlK satellites is described, as are features of the Marisat, truss and the resources required for a proposed flight experiment. Marecs, and the DBS systems. The near-term capabilities for DBS, The purpose of the study was to: (1) devise methods of truss

5 01 SYSTEMS assembly by astronauts; (2) define a specific test matrix for dynamic made it necessary to install a number of exciters and characterization; (3) identify instrumentation and data system accelerometers at inaccessible structural points several months requirements; (4) determine the power, propulsion and control prior to testing. The test was performed using a computer-supported requirements for the truss on-orbit for 3 years; (5) study the classical phase resonance method. The day-by-day data transfer packaging of the experiment in the orbiter cargo bay; (6) prepare via data tape enabled the customer to correlate measured and a preliminary cost estimate and schedule for the experiment; and calculated eigenmodes immediately and to perform orthogonality (7) provide a list of potential follow-on experiments using the checks at the end of a working day. ESA structure as a free flyer. The results of this three month study are presented. M.G. N87-10922# Jet Propulsion Lab., California Inst. of Tech., Pasadena. N87-10265'# National Aeronautics and Space Administration, SPACECRAFT LOAD, DESIGN AND TEST PHILOSOPHIES Washington, D.C. B. K. WADA ln ESA Proceedings of an International Conference LIDAR REMOTE SENSING FROM SPACE: NASAS PLANS IN on Spacecraft Structures p 271-276 Apr. 1986 THE EARTH SCIENCES Avail: NTlS HC A19/MF A01 R. J. CURRAN ln NASA. Langley Research Center 13th The development of spacecraft loads, design and test International Laser Radar Conference 1 p Aug. 1986 philosophies at the Jet Propulsion Laboratory (JPL) during the Avail: NTlS HC A15/MF A01 CSCL 20E past 25 years is presented. Examples from the JPL's Viking, A multidisciplinary study of the Earth System to provide a better Voyager and Galileo spacecraft are used to explain the changes understanding of the complex interrelated processes involved in in philosophy necessary to meet the program requirements with a the system, the Earth Observing System (EOS), is being developed. reduction in cost and schedule. Approaches to validate Capabilities of the Space Station, both the polar orbiting platform mathematical models of large structures which can't be ground and the lower inclination platforms, will be used to accommodate tested as an overall system because of size and/or adverse effects a number of large active and/or passive sensors. Two lidar of terrestrial conditions such as gravity are presented. ESA instruments being considered as part of the Eos payload are the Lidar Atmospheric Sounder and Altimeter (LASA) and the Laser N87-11640# Committee on Science and Technology (US. Atmospheric Wind Sounder (LAWS). The LASA instrument is House). separable into two portions: the atmospheric sounder component NATIONAL AERONAUTICS AND SPACE ADMINISTRATION and the retroranging component. The LASA atmospheric sounder AUTHORIZATION ACT, 1987 will sample the spatial distribution of several atmospheric Washington GPO 1986 251 p Report to accompany H.R. parameters. The retroranging component will be used to determine 5495 presented by the Committee on Science and Technology to the precise three-dimensional position of specifically placed the Committee of the Whole House on the State of the Union, retro-reflectors and to sense how these retro-reflectors change 99th Congress, 2d Session, 16 Sep. 1986 position over monthly to yearly time periods. The LAWS utilizes a (H-REPT-99-829; GPO-58-629) Avail: US Capitol, House lidar system capable of measuring the Doppler shift in the Document Room backscattered intensity to determine the wind velocity profile. Authorization of appropriations to the National Aeronautics and B.G. Space Administration for the fiscal year 1987 for research and development; space flight, control, and data analysis; construction N87-10774# Committee on Appropriations (US. Senate). of facilities; and research and program management is discussed. NATIONAL AERONAUTICS AND SPACE ADMINISTRATION B.G. In its Department of Housing and Urban Development-Independent Agencies Appropriation Bill, 1987 p 64-70 1986 N87-11641# Committee on Commerce, Science, and Avail: US Capitol, Senate Document Room Transportation (US. Senate). The appropriations for research, development, and procurement NATIONAL AERONAUTICS AND SPACE ADMINISTRATION activities of NASA are discussed. B.G. AUTHORIZATION BILL, 1986 1986 26 p A bill, H.R. 5495, referred to the Committee on N87-10775# Committee on Science and Technology (US. Science and Technology, 99th Congress, 2d Session, 10 Sep. House). 1986 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (H-REPT-99-829) Avail: US Capitol, House Document Room AUTHORIZATION ACT, 1987 Authorized appropriations are summarized for the National Washington GPO 1986 37 p An act, H.R. 5495, referred to Aeronautics and Space Administration for the following: the Committee on Commerce, Science and Transportation, 99th permanently manned space station; space transportation capability Congress, 2d Session, 30 Sep. 1986 development; physics and astronomy; life sciences; planetary Avail: US Capitol, House Document Room exploration; solid earth observations; environmental observations; Appropriations are discussed for research and development; materials processing in space; communications; information space flight, control, and data communication; construction of systems; technology utilization; commercial use of space; facilities; and research and program management by NASA. transatmospheric research and technology; tracking and data B.G. advanced systems; space flight, control, and data communication; construction of facilities, including land acquisitions; and research N87-10919# Deutsche Forschungs- und Versuchsanstalt fuer and program management. B.G. Luft- und Raumfahrt, Goettingen (West Germany). Inst. of Aeroelasticity. N87-11827'# National Aeronautics and Space Administration. EXPERIENCE ON THE OLYMPUS MODAL SURVEY TEST Langley Research Center, Hampton, Va. M. KNORR and A. BERTRAM ln ESA Proceedings of an DESIGN, CONSTRUCTION AND UTILIZATION OF A SPACE International Conference on Spacecraft Structures p 247-252 Apr. STATION ASSEMBLED FROM 5-METER ERECTABLE STRUTS 1986 M. M. MIKULAS, JR. and H. G. BUSH Oct. 1986 40 p Avail: NTlS HC Al9/MF A01 (NASA-TM-89043; NAS 1.15:89043) Avail: NTlS HC A03/MF A modal survey test (MST) on two configurations of the large A01 CSCL22B structure test model of the Olympus communications satellite is Presented are the primary characteristics of the 5-meter described: A configuration with the main tanks 213 full, the second erectable truss designated for the space station. The relatively with empty tanks. The complete MSTs were finished within 4 weeks, large 5-meter truss dimension was chosen to provide a deep beam including installation and strip down of the test equipment. The for high bending stiff ness yet provide convenient mounting locations spacecraft was mounted on a 40 t seismic block. The satellite is for space shuttle cargo bay size payloads which are 14.5 R. (4.4 characterized by large dimensions, mass, and complexity. This m) in diameter. Truss nodes and quick-attachment erectable joints

6 01 SYSTEMS are described which provide for evolutionary three-dimensional In gathering information, both former and present NASA officials growth and for simple maintenance and repair. A mobile remote were interviewed as well as knowledgable individuals outside the manipulator system is described which is provided to assist in agency. B.G. station construction and maintenance. A discussion is also presented of the construction of the space station and the associated EVA time. Author N87-15908# Committee on Appropriations (US. Senate). NATIONAL AERONAUTICS AND SPACE ADMINISTRATION N87-12402# Committee on Science and Technology (US. In its Department of Housing and Urban Development, and Certain House). Independent Agencies Appropriations for Fiscal Year 1987, Part 2 HEARINGS BEFORE THE SUBCOMMITTEE ON SPACE p 985-1065 1986 SCIENCE AND APPLICATIONS OF THE COMMITTEE ON Avail: Subcommittee of the Committee on Appropriations SCIENCE AND TECHNOLOGY, 99TH CONGRESS, 2ND The budget request, along with its necessary revisions, will SESSION, NO. 132, 25, 27 FEBRUARY; 11, 13, 20 MARCH; 9, assist in the initiation of procurement for a replacement orbiter 10 APRIL, 1986, VOLUME 2 and inertial upper-stage airborne support equipment. Also included 1986 799 p are funds to augment activities directed toward resolution of space (GPO-61-777) Avail: US Capitol, House Document Room shuttle sytem anomalies and initiation of development of the Space The National Aeronautics and Space Administration fiscal year Station. B.G. 1987 budget is examined. The impact of the loss of the Challenger and its crew on the space program is assessed. B.G. N87- 16018'# Air Force Wright Aeronautical Labs., N87-12574# Committee on Science and Technology (US. Wright-Patterson AFB, Ohio. House). FLIGHT DYNAMICS LABORATORY OVERVIEW NATIONAL COMMISSION ON SPACE REPORT THADDEUS SANDFORD ln NASA. Langley Research Center 1986 76 p Hearing before the Subcommittee on Space Science NASAIDOD Control/Structures Interaction Technology, 1986 p and Applications of the Committee on Science and Technology, 41-65 NOV. 1986 99th Congress, 2d Session, No. 129, 22 Jul. 1986 Avail: NTlS HC A23/MF A01 CSCL 228 (GPO-63-143) Avail: Subcommittee on Space Science and The Flight Dynamics Laboratory (FDL) is one of four Air Force Applications Wright Aeronautical Laboratories (AFWAL) and part of the The National Commission on Space was established by Aeronautical Systems Division located at Wright-Patterson AFB, Congress in 1984 to formulate a long range agenda for US. civilian Ohio. The FDL is responsible for the planning and execution of space activity, so long range goals, opportunities, and policy options research and development programs in the areas of structures could be identified. The process which the Commission followed and dynamics, flight controls, vehicle equipment/subsystems, and to arrive at its conclusions, what those conclusions were, as well aeromechanics. Some of the areas being researched in the four as the alternatives that were considered are discussed. The FDL divisions are as follows: large space structures (LSS) materials objectives and the financial projection requested to achieve them and controls; advanced cockpit designs; bird-strike-tolerant are examined. B.G. windshields; and hypersonic interceptor system studies. Two of the FDL divisions are actively involved in programs that deal directly N87-12581'# National Aeronautics and Space Administration. with LSS controKstructures interaction: the Flight Controls Division Marshall Space Flight Center, Huntsville, Ala. and the Structures and Dynamics Division. Author SOLAR ARRAY FLIGHT DYNAMIC EXPERIMENT R. W. SCHOCK Washington May 1986 27 p (NASA-TP-2598; NAS 1.60:2598) Avail: NTlS HC A03/MF A01 N87-16022'# National Aeronautics and Space Administration. CSCL 10A Marshall Space Flight Center, Huntsville, Ala. The purpose of the Solar Array Flight Dynamic Experiment DEVELOPMENT OF THE LENS ANTENNA DEPLOYMENT (SAFDE) is to demonstrate the feasibility of on-orbit measurement DEMONSTRATION (LADD) SHUTTLE-ATTACHED FLIGHT and ground processing of large space structures dynamic EXPERIMENT characteristics. Test definition or verification provides the dynamic H. HILL, D. JOHNSTON, and H. FRAUENBERGER (Grumman characteristic accuracy required for control systems use. An Aerospace Corp., Bethpage. N.Y.) ln NASA. Langley Research illumination/measurement system was developed to fly on space Center NASAIDOD Control/Structures Interaction Technology, shuttle flight STS-31D. The system was designed to dynamically 1986 p 125-144 NOV.1986 evaluate a large solar array called the Solar Array Flight Experiment Avail: NTlS HC A23/MF A01 CSCL 20N (SAFE) that had been scheduled for this flight. The SAFDE system The primary objective of the LADD Program is to develop a consisted of a set of laser diode illuminators, retroreflective targets, technology demonstration test article that can be used for both an intelligent star tracker receiver and the associated equipment ground and flight tests to demonstrate the structural and to power, condition, and record the results. In six tests on STS-41D, mechanical feasibility and reliability of the single-axis roll-out space data was successfully acquired from 18 retroreflector targets and based radar (SBR) approach. As designed, the LADD will essentially ground processed, post flight, to define the solar array's dynamic be a generic strucutural experiment which incorporates all critical characteristic. The flight experiment proved the viability of on-orbit technology elements of the operational satellite and is applicable test definition of large space structures dynamic characteristics. to a number of future antenna systems. However, to fully determine Future large space structures controllability should be greatly its design integrity for meeting the lens flatness and constant enhanced by this capability. Author geometry requirements in a zero g environment under extreme thermal conditions, the LADD must be space flight tested. By N87-15898# National Academy of Public Administration, accurately surveying the structure under varying conditions the Washington, D. C. membrane tolerance-holding capabilities of the structure will be NASA THE VISION AND THE REALITY demonstrated. The flight test will provide data to verify analytical ERASMUS H. KLOMAN Oct. 1985 66 p tools used to predict thermal and structural behavior. Most (OP-5) Avail: NTlS HC A04/MF A01 important, the experiment will provide an initial indication of The complex of aspirations and national priorities lying behind structural damping in a zero g vacuum environment. The recently the original vision of the civilian space program and how that completed Solar Array Flight Experiment (SAFE) showed orbital program has fared in the real world of politics centering on damping greater than that experienced during ground testing. From Washington were explored. The programmatic evolution of NASA the experience and the information obtained from LADD it is hoped and some of the key administrative and management concepts that designs can be confidently extrapolated to operational satellites developed to govern the operation of the agency were examined. with apertures in the 20 m by 60 m size range. Author

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N87-16029*# National Aeronautics and Space Administration. N87-16323*# Dornier-Werke G.m.b.H., Friedrichshafen (West Langley Research Center, Hampton, Va. Germany). COFS 1 RESEARCH OVERVIEW EXTENDABLE RETRACTABLE TELESCOPIC MAST FOR G. C. HORNER ln its NASAIDOD ControVStructures Interaction DEPLOYABLE STRUCTURES Technology, 1986 p 233-251 Nov. 1986 M. SCHMID and M. AGUIRRE (European Space Agency. European Avail: NTlS HC A23/MF A01 CSCL 22A Space Research and Technology Center, ESTEC, Noordwijk, The Control of Flexible Structures (COFS) program is divided Netherlands) In NASA. Lewis Research Center The 20th into three areas of research. These three areas are Aerospace Mechanics Symposium p 13-29 May 1986 controls/structures analysis development, ground test experiments, Avail: NTlS HC A14/MF A01 CSCL 228 and in-space experiments. The ground test experiments are The Extendable and Retractable Mast (ERM) which is presently intended to validate analyses and to confirm through hardware developed by Dornier in the frame of an ESA-contract, will be tests our technical readiness to successfully fly the Mast hardware. used to deploy and retract large foldable structures. The design There is this close relation to the results of ground tests and is based on a telescopic carbon-fiber structure with high stiff ness, analytical predictions that must be understood before flight strength and pointing accuracy. To verify the chosen design, a experiments may be attempted. Details relative to each program breadboard model of an ERM was built and tested under thermal area are given. Author vacuum (TV)-conditions. It is planned as a follow-on development to manufacture and test an Engineering Model Mast. The Engineering Model will be used to establish the basis for an N87-16030'# Harris Corp., Palm Bay, Fla. ERM-family covering a wide range of requirements. Author DESCRIPTION OF THE MAST FLIGHT SYSTEM RONALD C. TALCOTT and JOHN W. SHIPLEY ln NASA. Langley Research Center NASAIDOD ControVStructures Interaction N87-16848'# National Aeronautics and Space Administration. Technology, 1986 p 253-263 Nov. 1986 Langley Research Center, Hampton, Va. Avail: NTlS HC A23/MF A01 CSCL 22A DESCRIPTION OF THE SPACECRAFT CONTROL LABORATORY The Mast Flight System is composed of several subsystems. EXPERIMENT (SCOLE) FACILITY Primary among these is the Deployable Mast Subsystem (DMS) JEFFREY P. WILLIAMS and ROSEMARY A. RALLO (Purdue Univ., which consists of a beam assembly and an associated mechanism West Lafayette, Ind.) Jan. 1987 45 p for deploying and retracting the beam. The beam assembly is a (NASA-TM-89057; NAS 1.15:89057) Avail: NTlS HC AO3/MF joint dominated graphite epoxy and titanium truss as is expected A01 CSCLOlC of future large space structures. Integral to the beam assembly A laboratory facility for the study of control laws for large flexible are actuators, sensors and associated electronics which are spacecraft is described. The facility fulfills the requirements of the available for excitation and damping as desired by the experimenter. Spacecraft Control Laboratory Experiment (SCOLE) design The beam structural characteristics can also be modified as desired challenge for laboratory experiments, which will allow slew by the experimenter using the Parameter Modification Device maneuvers and pointing operations. The structural apparatus is installed at the end of the beam. Data measured on the beam by described in detail sufficient for modelling purposes. The sensor the sensors and commands to the actuators are transmitted along and actuator types and characteristics are described so that the beam digitally at 150 Hz using a standard 1553 type bus. The identification and control algorithms may be designed. The control Modular Distributed Information Sybsystem (MDIS) computer implementation computer and real-time subroutines are also functions as bus master and ensures that all experimental data is described. Author saved for future analysis. The MDIS computer also performs a safing function to prevent inadvertent overexcitation of the beam. N87-16927# Contraves Corp.. Zurich (Switzerland). Space Finally, the Excitation and Damping Subsystem (EDS) computer is Dept. available to the experimenter for implementation of control DEVELOPMENT OF A 2.8 M OFFSET ANTENNA REFLECTOR algorithms or any other numerical operations as desired. Data USING INFLATABLE, SPACE-RIGIDIZED STRUCTURES from all system sensors can be accessed by the EDS computer. TECHNOLOGY Author M. C. BERNASCONI ln ESA Proceedings of the Second ESA Workshop on Mechanical Technology for Antennas p 31-37 Aug. 1986 N87-16033'# National Aeronautics and Space Administration. Avail: NTlS HC A12/MF A01 Langley Research Center, Hampton, Va. Results of the mechanical tests of an offset reflector structure, MAST FLIGHT SYSTEM OPERATIONS based on the technology of chemically-rigidized membranes are M. LARRY BRUMFIELD ln its NASA/DOD ControVStructures presented. Folding, stowage, and deployment tests confirm the Interaction Technology, 1986 p 299-317 Nov. 1986 high packaging efficiency, as well as the controllability of the Avail: NTlS HC A23/MF A01 CSCL 20K inflation process. Geometric measurements at different The integration process of the MAST flight system is surveyed. manufacturing stages were used to assess the quality of the Insight is given into the planned orbital experiment process. The surface; the typical surface deviation obtained is 0.9 mm rms. data flow necessary to support the flight operation is outlined. Folding and cure processes have a negligible impact on reflector Author quality. The packaging and deployment procedures were verified by a depolyment test in vacuum. ESA N87-16034'# National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. N87-16928# Toshiba Research and Development Center, COFS 1 GUEST INVESTIGATOR PROGRAM Kawasaki (Japan). Space Program Div. ANTHONY FONTANA and ROBERT L. WRIGHT In its NASAIDOD STUDY ON SOLID SURFACE, DEPLOYABLE ANTENNA ControVStructures Interaction Technology, 1986 p 319-325 Nov. REFLECTOR 1986 Y. TSUTSUMI, A. KASAHARA, Y. HISADA (National Space Avail: NTlS HC A23/MF A01 CSCL 22A Development Agency, Ibaraki, Japan), and Y. ITOH ln ESA The process for selecting guest investigators for participation Proceedings of the Second ESA Workshop on Mechanical in the Control of Flexible Structures (C0FS)-1 program is described. Technology for Antennas p 41-45 Aug. 1986 Contracts and grants will be awarded in late CY87. A straw-man Avail: NTlS HC A12/MF A01 list of types of experiments and a distribution of the experiments A study was carried out on the precision-contour solid surface, has been defined to initiate definition of an experiments package deployable reflector in the 20 to 30 GHz, center-fed Cassegrain which supports development and validation of control structures antenna to be mounted on data relay and tracking satellites. interaction technology. A schedule of guest investigator Reflector sizes are 1.8 m stowed diameter and 5 m deployed participation has been developed. Author diameter. As a solid surface deployable reflector to satisfy the

8 01 SYSTEMS

above requirements, two kinds of deployment concepts were N87-17152'# Dornier-Werke G.m.b.H., Friedrichshafen (West developed. Based on the kinematic analysis results, preliminary Germany). design was carried out and a partial model was built to confirm FEATURES AND TECHNOLOGIES OF ERS-1 (ESA) AND X-SAR the deployment kinematics. Deployment test results, using a partial ANTENNAS model, show that two deployment concepts can be applied to the R. SCHUESSLER and R. WAGNER In JPL The Second solid surface deployable reflector satisfying the requirements of a Spaceborne Imaging Radar Symposium p 125-129 1 Dec. 1986 large ratio of deployed/stowed dimensions. ESA Avail: NTlS HC AlO/MF A01 CSCL 09C Features and technologies of planar waveguide array antennas developed for spaceborne microwave sensors are described. Such antennas are made from carbon fiber reinforced plastic (CFRP) N87-16933# Nippon Telegraph and Telephone Public Corp., employing special manufacturing and metallization techniques to Yokosuka (Japan). achieve satisfactory electrical properties. Mechanical design DEVELOPMENT OF 30/20 GHZ SATELLITE ANTENNA enables deployable antenna structures necessary for satellite STRUCTURES applications (e.g., ESA ERS-1). The slotted waveguide concept M. MINOMO and T. YASAKA In ESA Proceedings of the Second provides high aperture efficiency, good beamshaping capabilities, ESA Workshop on Mechanical Technology for Antennas p 85-90 and low losses. These CFRP waveguide antennas feature low Aug. 1986 mass, high accuracy and stiffness, and can be operated within Avail: NTlS HC Al2/MF A01 wide temperature ranges. Author An antenna structural design for a large capacity communication satellite using 13 beams in the 30/20GHz frequency bands is discussed. This design is to be utilized in developing a more cost effective domestic satellite communication system for Japan. This system requires 2 high precision deployable antennas with N87-17571'# Jet Propulsion Lab., California Inst. of Tech., projected aperture diameters of 3.5m at 20GHz and 2.5m at 30GHz. Pasadena. The in-orbit demonstration will use the ETS-6 satellite. Based on THE LARGE DEPLOYABLE REFLECTOR: A NASA experience in the development of spaceborne antennas for SUBMILLIMETER-INFRARED ORBITING OBSERVATORY 30/20GHz bands (e.g., for the CS-2 and CS-3 satellites) activities PAUL N. SWANSON In ESA Proceedings of an ESA Workshop in structural design of high precision deployable antennas show on a Spaceborne Submillimeter Astronomy Mission. A Cornerstone the truss reflector structure is promising for achieving required structural properties. ESA of the ESA Long Term Science Program p 265-276 Aug. 1986 Avail: NTlS HC A14/MF A01 The Large Deployable Reflector (LDR) concept is outlined. The LDR telescope is based on a 20-m diameter reflector. The primary mirror is a filled aperture made up of 84 hexagonal panels, each N87-16935# Construcciones Aeronauticas S.A., Madrid (Spain). 2 m edge-to-edge. The panels are based on lightweight structural Space Div. composite materials. The optical configuration is a four mirror two CONSTRUCCIONES AERONAUTICAS S.A. (CASA) LARGE stage system. The primary mirror is passive. The active optical REFLECTOR ANTENNA elements for figure control are at the quaternary mirror. The primary J. ESCOBAR In ESA Proceedings of the Second ESA Workhop mirror panels are supported by a deployable PAC truss backup on Mechanical Technology for Antennas p 97-102 Aug. 1986 structure at the vertices of each hexagon. The four focal plane (Contract ESA-5277182-NL-PP) instruments covering the range of 30 to 1000 microns are located Avail: NTlS HC A12/MF A01 near the vertex of the primary mirror. Some instruments will be The development of a 11114 GHz large reflector assembly is cooled with stored cryogens to liquid helium temperatures, others reviewed. Investigations on CFRP properties, their design and to liquid nitrogen temperatures. The spacecraft functions will be calculation methods, the development of the associated software, located in a resource module behind the primary mirror. The LDR the gathering of a data base from tests at component level, and will be transferred to orbit by the space transportation system basic studies on the general configuration of antennas are outlined. and assembled and tested at the space station. It will then be A demonstration model to resolve the technological problems boosted to an orbit of greater than or = 700 km as a free flyer. related with the design, manufacture and test of a large reflector ESA was built. ESA

N87-16939# Dornier-Werke G.m.b.H., Friedrichshafen (West Germany). N87-17746'# National Aeronautics and Space Administration. DEVELOPMENT STATUS OF THE ERS-1 SAR ANTENNA Marshall Space Flight Center, Huntsville, Ala. R. WAGNER, H. J. LUHMANN, R. SIPPEL, and M. WESTPHAL MANNED MARS MISSION EARTH-TO-ORBIT (ETO) DELIVERY In ESA Proceedings of the Second ESA Workshop on Mechanical AND ORBIT ASSEMBLY OF THE MANNED MARS VEHICLE Technology for Antennas p 131-1 37 Aug. 1986 B. BARISA and G. SOLMON In its Manned Mars Missions. Avail: NTlS HC A12/MF A01 Working Group Papers, Volume 1, Section 1-4 p 306-315 May A 10 m x 1 m planar array antenna for the ERS-1 satellite is 1986 described. It features metallized CFRP waveguides as radiating Avail: NTlS HC A22/MF A01 CSCL 22A elements and feeding network components, CFRP sandwich The initial concepts developed for the in-orbit assembly of a reinforcements of the mechanical panels, a deployable truss Manned Mars Vehicle and for the Earth-to-Orbit (ETO) delivery of structure, and mechanism for launch fixation, release, and the required hardware and propellant are presented. Two (2) Mars deployment. Mechanical design of the antenna structure towards vehicle concepts (all-propulsive and all-aerobrake) and two (2) satisfactory dynamic properties in launch configuration within the ET0 Vehicle concepts were investigated. Both Mars Vehicle narrow constraints of mass, volume, and mechanical loads; concepts are described in Reference 1, and both ET0 Vehicle structural analysis of the stowed and deployment antenna, to concepts are described in Reference 2. The all-aerobrake determine dynamic properties, internal loads, and deformations; configuration reduces the number of launches and time required and design of the hold down and release mechanism arrangement to deliver the necessary hardware/propellent to orbit. Use of the of six hinged clamps for launch fixation, to be released via a larger of the 2 ET0 Vehicles (HLLV) further reduces the number system of springs and cables by a pyrotechnic device, are of launches and delivery time; however, this option requires a reviewed. ESA completely new vehicle and supporting facilities. Author

9 01 SYSTEMS

N87-17799'# National Aeronautics and Space Administration. N87-17846# Lawrence Livermore National Lab., Calif. Lyndon B. Johnson Space Center, Houston, Tex. PRELIMINARY FINDINGS FOR INTEGRATED MODELING AND BUDGET AVAILABILITY SIMULATION OF DIRECTED ENERGY WEAPONS KELLEY J. CYR ln NASA. Marshall Space Flight Center Manned K. D. PIMENTEL, D. T. GAVEL, and J. W. ROBLEE 22 May Mars Mission. Working Group Papers, V. 2, Sect. 5, App. p 929-935 1986 8 p Presented at the 2nd European Simulation Congress, May 1986 Antwerp, Belgium, 9 Sep. 1986 Avail: NTlS HC A24/MF A01 CSCL 05C (Contract W-7405-ENG-48) A forecast of the total NASA budget required to achieve a (DE86-011636; UCRL-93765; CONF-8609113-1) Avail: NTlS HC manned mission to Mars at around the end of this century is A02/MF A01 described. A methodology is presented for projecting the major A preliminary study was recently completed at Lawrence components of the NASA budget, including the NASA base, space Livermore National Laboratory of the issues important to the flight, space station, Shuttle Derived Launch Vehicle, and the integrated modeling and simulation of future directed energy Manned Mars Mission. The NASA base, including administrative weapon (DEW) space platforms. The preliminary study comprised expenses, construction of facilities and research and development three parts: (1) a preliminary survey of existing computer codes other than manned flight, is assumed to level off at the present used for integrated modeling and simulation; (2) work by a (1985) level and remain constant at approximately $3.5 billion multidisciplinary team on a simple optical beam expander model (constant fiscal year 1985 dollars). The budget for space flight, to motivate cooperation in the three technical areas of space which consists of Shuttle research and development, operations, structures, optics, and control systems; and (3) identifying needs and tracking and data acquisition costs, is projected to decrease in integrated modeling and simulation for DEW systems. Results from approximately $4 billion in 1985 to just under $2.5 billion by of this study indicate that much of the technology for end-to-end 1989 and then level off. Planning profiles for three major programs modeling and simulation of DEW space platforms may be in hand are constructed: a permanently manned space station; a Shuttle today. However, there may be critical needs in certain modeling Derived Vehicle; and a Manned Mars Mission. It is concluded that and simulation areas, particularly in the package integration and all of the programs can be conducted by the year 2002 with a 3 computer/human interface areas, that are beyond the current state percent real growth rate in the NASA budget. Author of the art to meet required levels of performance. DOE

N87-19310*# Jet Propulsion Lab., California Inst. of Tech., Pasadena. N87-17836'# National Aeronautics and Space Administration. THE LARGE DEPLOYABLE REFLECTOR (LDR) REPORT OF Langley Research Center, Hampton, Va. THE SCIENCE COORDINATION GROUP THE SCOLE DESIGN CHALLENGE 1 Oct. 1986 109 p LARRY TAYLOR and A. V. BALAKRISHNAN (California Univ., Los (Contract NAS7-918) Angeles) ln NASA. Langley Research Center Proceedings of (NASA-CR-180235; JPL-PUB-86-46; NAS 1.26:180235) Avail: the 3rd Annual SCOLE Workshop p 385-412 Jan. 1987 NTlS HC AO6/MF A01 CSCL 03A Avail: NTlS HC A2O/MF A01 CSCL 228 The Large Deployable Reflector (LDR) is a telescope designed An NASA program is discussed which was initiated to make to carry out high-angular resolution, high-sensitivity observations direct comparisons of control laws for, first, a mathematical at far-infrared and submillimeter wavelengths. The scientific problem, than an experimental test article is being assembled under rationale for the LDR is discussed in light of the recent Infrared the cognizance of the Spacecraft Control Branch. The physical Astronomical Satellite (IRAS) and Kuiper Airborne Observatory apparatus will consist of a softly supported dynamic model of an (KAO) results and the several new ground-based observatories antenna attached to the Shuttle by a flexible beam. The control planned for the late 1980s. The importance of high sensitivity and objective will include the task of directing the line of sight of the high angular resolution observations from space in the submillimeter Shuttlelantenna configuration toward a fixed target, under region is stressed. The scientific and technical problems of using conditions of noisy data, limited control authority and random the LDR in a light bucket mode at approx. less than 5 microns disturbances. A workshop will be planned to discuss and compare and in designing the LDR as an unfilled aperture with subarcsecond results of the design challange. Author resolution are also discussed. The need for an aperture as large as 20 m is established, along with the requirements of beam-shape stability, spatial chopping, thermal control, and surface figure stability. The instrument complement required to cover the wavelength-spectral resolution region of interest to the LDR is defined. Author

N87-17837*# National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. DESCRIPTION OF THE SPACECRAFT CONTROL LABORATORY EXPERIMENT (SCOLE) FACILITY N87-20064'# National Aeronautics and Space Administration. JEFFREY P. WILLIAMS and ROSEMARY A. RALLO ln its Marshall Space Flight Center, Huntsville, Ala. Proceedings of the 3rd Annual SCOLE Workshop p 413-458 THE INTERACTION OF SMALL AND LARGE SPACECRAFT Jan. 1987 WITH THEIR ENVIRONMENT Avail: NTlS HC A20/MF A01 CSCL 228 URI SAMlR (Michigan Univ., Ann Arbor) and NOBIE H. STONE A laboratory facility for the study of control laws for large flexible ln JPL, Space Technology Plasma Issues in 2001 p 69-91 1 spacecraft is described. The facility fulfills the requirements of the Oct. 1986 Prepared in cooperation with Tel-Aviv Univ., Israel Spacecraft Control Laboratory Experiment (SCOLE) design Avail: NTlS HC A20/MF A01 CSCL 201 challenge for a laboratory experiment, which will allow slew The most significant results from small scientific satellites and maneuvers and pointing operations. The structural apparatus is from the space shuttle mission STS-3 regarding body-plasma described in detail sufficient for modelling purposes. The sensor interactions are presented and discussed. The causes for the above and actuator types and characteristics are described so that information being meager and fragmentary are given. The research identification and control algorithms may be designed. The control avenues to be followed in the future in order to correct this situation implementation computer and real-time subroutines are also are mentioned, including practical ways to achieve this goal. described. Author Author

10 02 ANALYSIS AND DESIGN TECHNIQUES

02 A87-15893# SOLAR ARRAY MECHANISMS FOR INDIAN SATELLITES, ANALYSIS AND DESIGN TECHNIQUES APPLE, IRS AND INSAT-IITS S. DAS (Indian Space Research Organization, Vikram Sarabhai Space Centre, Trivandrum, India) and I. SELVARAJ (Indian Space Includes interactive techniques, computerized technology design Research Organization, Satellite Centre, Bangalore, India) IAF, and development programs, dynamic analysis techniques, International Astronautical Congress, 37th, Innsbruck, Austria, Oct. environmental modeling, thermal modeling, and math modeling. 4-11, 1986. 12 p. (IAF PAPER 86-142) Large-area rigid panel deployable and trackable solar arrays A87-10092 are widely used in the present day operational satellites. Three SPACE VEHICLE DESIGN [CONCEPTION DES VEHlCULES solar array mechanisms of this type for Indian spacecrafts are SPATIAUX] described, one of which has already undergone flight verification. D. MARTY (CNES, Direction des.Lanceurs. Evry, France) Paris, The other two mechanisms are of higher complexity and are being Masson, 1986, 666 p. In French. refs readied for launch in the immediate future, as essential for providing A general overview of the main problems encountered in space the country’s space services in communication and remote sensing vehicle design is presented in order to provide simple methods fields. The design approach, test program and implications of test for the working out of preliminary projects, the comparison of modeling towards achieving the design goal are discussed. architectures, and the verification of the feasibility of new systems. Performance characteristics of the solar array mechanisms The discussion on satellites includes such topics as earth escape achieved after flight verification and qualification tests are also conditions, theoretical and real movement, orbit plane correction, highlighted in the paper. Author and thermal control. Interplanetary vehicles are discussed with examinations of the influence sphere and orbit transfers. The A87- 17 146# performance, separation and jettisoning, and aerodynamics of HOPE FOR SIMULATING FLEXIBLE SPACECRAFT conventional space launchers are then considered. Problems R. GLUCK (TRW, Inc., Space and Technology Group, Redondo relating to reusable launch vehicles, ballistic missiles, the reentry Beach, CA) Aerospace America (ISSN 0740-722X), vol. 24, Nov. body, and the Space Station are also discussed. Finally, a general 1986, p. 40-44. discussion of the avionics, propulsion, and structural technology The application of a custom architectured parallel processing common to all space vehicles is presented, including system (CAPPS) to the simulation of a large angle maneuver of instrumentation, energy sources, launcher guidance and attitude the Space Shuttle’s remote manipulator system and power control, rocket engine thrust, and combustion. Also considered extension package, and to the despinning of a whirling flexible are propellants, engine characteristics, advanced propulsive beam by torques are described. The CAPPS is fully digital and systems, and structural materials and manufacturing. R.R. utilizes a large number of high-speed computational units (CUs); the design and operation of the system’s CUs are examined. The system software consists of programs for: (1) deriving the equations of motion, (2) converting the equations to machine language for execution, and (3) of special algorithms for efficient parallel processing. Potential applications for CAPPS are discussed. I.F. A87- 15196 EQUIPMENT DESIGNS FOR SPACE STATION EVA EXAMINED A87-21257# Aerospace Engineering (ISSN 0736-2536), vol. 6, Aug. 1986, p. SPACE STATION THRILLERS UNFOLD AT DRAPER LAB 11-14. DON EYLES (Charles Stark Draper Laboratory, Inc., Cambridge, A survey of projected Space Station operational requirements MA) Aerospace America (ISSN 0740-722X), vol. 24, Oct. 1986. has revealed that EVA is called for in 193 missions. A group of p. 38-41. EVA suit requirements has been derived, and three generic EVA The operational capabilities of a computer-graphics system suit architectures, characterized as ’soft’, ’hybrid’ and ’hard’, have designed for aiding operations in space (e.g., the recovery of a been evaluated against these requirements. Study results indicate troubled spacecraft) are described. The visualization system will that the hard suit concept is the most promising of the three let the astronaut place his eye at any point of space and simulate configurations. O.C. space operations. The system will first create a dynamic scene based on the vectors and transformations that specify the real-world interrelationships between spacecraft and other objects. It then allows a number of points of view to be chosen within the overall scene. I.S.

A87-158 19# A87-22363# S BAND 3.5-M-DIAMETER FAN RIB TYPE DEPLOYABLE MESH OPTIMAL STRUCTURAL DESIGN WITH CONTROL GAIN NORM ANTENNA FOR SATELLITE USE CONSTRAINT T. ITANAMI, M. MINOMO, and 1. OHTOMO (Nippon Telegraph N. S. KHOT, V. 6.VENKAYYA (USAF, Flight Dynamics Laboratory, and Telephone Public Corp., Electrical Communications Wright-Patterson AFB, OH), H. OZ (Ohio State University, Laboratories, Yokosuka, Japan) IAF, International Astronautical Columbus), R. V. GRANDHI (Wright State University, Dayton, OH), Congress, 37th, Innsbruck, Austria, Oct. 4-1 1, 1986. 8 p. refs and F. E. EASTEP (Dayton, University, OH) AIAA, Aerospace (IAF PAPER 86-28) Sciences Meeting, 25th, Reno, NV, Jan. 12-15, 1987. 1 1 p. refs A design is presented for a satellite-borne S-band fan rib type (AIAA PAPER 87-0019) deployable mesh antenna for the Japanese maritime satellite A structure/control system optimization problem has been communication system. The system proposed here uses an offset formulated with constraints on the closed-loop eigenvalue Cassegrain antenna with a main reflector focal length of 2.5 m, a distribution, structural frequencies and the minimum Frobenious subreflector focal length of 450 mm, and a subreflector eccentricity norm of the required control gains. A simultaneous optimization is of 2.5. The subreflector angular aperture, as determined by the suggested, where at each iteration control objective function is current distribution method, is 48 degrees, which is about 40 minimized first with the closed-loop eigenvalue constraints; and percent larger than the aperture determined by geometrical optics then structural optimization is performed to satisfy the constraints without allowance for the finite aperture edge. The design provides on the optimal control gain norm and structural frequencies. The a beam edge gain of more than 31 dB. Details of the structural, feasibility of the approach is demonstrated on a 2-Bar truss electrical, and thermal design of the antenna are examined. V.L. structure. For each locally optimal design, response simulations

11 02 ANALYSIS AND DESIGN TECHNIQUES were done and control efforts were observed. Qualitative aspects A87-3 112 1# of the optimal designs are also included. Author SOFTWARE ARCHITECTURE FOR MANUFACTURING AND SPACE ROBOTICS J. S. ALBUS, R. LUMIA, and H. MCCAIN (NBS, Robot Systems Div., Gaithersburg, MD) AIAA, NASA, and USAF, Symposium on A87-25978 Automation, Robotics and Advanced Computing for the National ARCHITECTURE AND DESIGN PROCESS FOR COMPLEX Space Program, 2nd. Arlington, VA, Mar. 9-1 1, 1987. 11 p. refs SYSTEMS SPACE STATION - A CASE STUDY (AIAA PAPER 87-1687) RICHARD T. LUKE (Hughes Aircraft Co., Space and A hierarchical architecture is described which supports Space Communications Group, El Segundo, CA) IN: Aerospace Station telerobots in a variety of modes. The system is divided Applications Conference, Steamboat Springs, CO, Feb. 1-8, 1986, into three hierarchies: task decomposition, world model, and sensor Digest . New York, Institute of Electrical and Electronics Engineers, processing. Goals at each level of the task decomposition hierarchy Inc., 1986, 16 p. are divided both spatially and temporally into simpler commands The system architecture and design (A&D) process involves for the next lower level. This decomposition is repeated until, at the identification of a set of mission objectives and the definition the lowest level, the drive signals to the robot actuators are of detailed block diagrams for each element of a system that can generated. To accomplish its goals, task decomposition modules accomplish said objectives. Attention is presently given to the must often use information stored in the world model. The purpose distinct phases of A&D, drawing upon examples from recent NASA of the sensory system is to update the world model as rapidly as Space Station activities in general and the Station’s possible to keep the model in registration with the physical world. communications system in particular; a specific segment of the This paper describes the architecture of the entire control system communications system is presented to illustrate the application hierarchy and how it can be applied to space telerobot of the complete A&D process. It is noted that the risk associated applications. Author with early freezing of baseline designs can be minimized by involving representatives from subsequent design phases in preceding ones. O.C.

A87-27617# N87-10418 Iowa State Univ. of Science and Technology, Ames. USE OF SUPPORT SIMULATION MODELING TECHNIQUES IN APPLICATION OF GRAPH THEORY TO THE NONLINEAR THE DEVELOPMENT OF LOGISTICS SUPPORT CONCEPTS FOR ANALYSIS OF LARGE SPACE STRUCTURES Ph.D. Thesis SDI ORBITAL PLATFORMS AND CONSTELLATIONS M. I. HINDAWY 1986 100 p RICHARD FLOWERREE, SCOTT BENSON, and MARK MCCRAY Avail: Univ. Microfilms Order No. DAB615055 (General Dynamics Corp., Space Systems Div., San Diego, CA) A new graph representation of nonlinear large space structures IN: Space Logistics Symposium, 1st, Huntsville, AL, Mar. 24-26, is introduced. During the loading process the structural graph 1987, Technical Papers . New York, American Institute of changes its levels as the nonlinear regions in the large space Aeronautics and Astronautics, 1987, p. 103-115. structure change configuration. This variable structured graph is (AIAA PAPER 87-0690) used to order the nodes and members of the discretized nonlinear Simulation modeling techniques being applied to explore structural model. A new algorithm is used to change the established logistics support systems for SDI orbital platforms are described. order of the nonlinear model and updates the condensed nonlinear The studies are targeted at optimizing the systems/subsystems stiffness matrix equation for the structure. In addition to accounting redundancy levels, defining constellation servicing schedules, for structural nonlinearities the algorithm can take into consideration identifying appropriate man-tended servicing missions, and plastic hinge formation and fracture of members in large space quantifying the reusable and consumable components necessary structures. Dissert. Abstr. for ensuring a given level of system availability. Consideration is also being given to robotics in on-orbit maintenance, constellation regrouping/reconfiguration after engagement, and the ground-based support services necessary for given levels of space systems deploy- ment and availability. War-game, design synthesis and space transpor- tation models being used in the studies are summarized. Sample N87-10894# Engineering System International, Rungis (France). results are provided from the SAGITTAR experiment, a simulation of EQUIVALENT CONTINUUM ANALYSES OF LARGE SPACE the fuel, orbital replacement units, aid other consumables needed TRUSSES for a platform. M.S.K. E. HAUG, P. DOWLATYARI, and J. DUBOIS ln ESA Proceedings of an International Conference on Spacecraft Structures p 57-65 Apr. 1986 A87-28552 (Contract ESTEC-5209/82-NL-PB(SC)) COMPARISON OF MULTIPLE INPUT RANDOM AND SINE Avail: NTlS HC A19/MF A01 EXCITATION METHODS FOR AEROSPACE STRUCTURES The techniques of discrete field methods, conventional DAVID L. HUNT (SDRC, Inc., San Diego, CA), BRUCE WENDLER, equivalent continua, and micropolar equivalent continua are and SAM SOULE (TRW, Inc., Federal Systems Div., Redondo introduced, and their usefulness for the calculation of large space Beach, CA) IN: International Modal Analysis Conference, 4th, structures and their ease of numerical implementation are Los Angeles, CA, Feb. 3-6, 1986, Proceedings. Volume 1 . assessed. An example of a large space truss was run on the Schenectady, NY, Union College, 1986, p. 563-571. computer, using the full model, and several equivalent continuum The results of modal tests on a communication-satellite structure finite element models. The full and equivalent continuum models are reported, comparing the effectiveness of methods employing of the chosen realistic sample space truss are loaded statically sine-dwell and multiple-input random-burst (MIRB) excitation. The with mechanical load cases characteristic of orbital transfer data are presented in graphs, tables, and matrices and briefly conditions and with thermal gradients which might arise in operating characterized. MlRB excitation is shown to give mode shapes of conditions. Dynamic behavior is studied by extracting vibration quality equal to those obtained with sine-dwell excitation and to frequencies and mode shapes. Results suggest that it is better to require significantly less testing and setup time. It is concluded channel development efforts into an integrated sandwich finite that MlRB is the method of choice for lightly damped structures element, uniting anisotropic membrane skins and an anisotropic with moderate mode density and coupling, whereas sine-dwell brick or thick shell core into one element. This type of element is excitation is preferable for verification testing or when likely to be useful as an equivalent continuum finite element for modal-response/force-level changes are being investigated. T.K. most practical space trusses. ESA

12 02 ANALYSIS AND DESIGN TECHNIQUES

N87-11761*# National Aeronautics and Space Administration. performance. Analysis reveals cross-polarization limitations in offset Langley Research Center, Hampton, Va. configuration, and phase shifts in dual-grid configuration with a IDEAS: A MULTIDISCIPLINARY COMPUTER-AIDED CONCEP- wide range of incidence angles. This leads to a depointing of the TUAL DESIGN SYSTEM FOR SPACECRAFT beam radiated by the antenna. To compensate, two solutions M. J. FEREBEE, JR. ln its Recent Experiences in Multidisciplinary appear feasible: either repoint the whole antenna, or vary the Analysis and Optimization, Part 2 21 p 1984 spacing between the two grids with respect to the incidence Avail: NTlS HC A22/MF A01 CSCL 228 angles. ESA During the conceptual development of advanced aerospace vehicles, many compromises must be considered to balance economy and performance of the total system. Subsystem tradeoffs may need to be made in order to satisfy system-sensitive attributes. Due to the increasingly complex nature of aerospace systems, these trade studies have become more difficult and time-consuming to complete and involve interactions of ever-larger numbers of N87-14059'# National Aeronautics and Space Administration. subsystems, components, and performance parameters. The Langley Research Center, Hampton, Va. current advances of computer-aided synthesis, modeling and THE IDENTIFICATION OF A DISTRIBUTED PARAMETER analysis techniques have greatly helped in the evaluation of MODEL FOR A FLEXIBLE STRUCTURE competing design concepts. Langley Research Center's Space H. T. BANKS (Brown Univ., Providence, R. I.), S. S. GATES (Draper Systems Division is currently engaged in trade studies for a variety (Charles Stark) Lab., Inc., Cambridge, Mass.), I. G. ROSEN of systems which include advanced ground-launched space (University of Southern California, Los Angeles.), and Y. WANG transportation systems, space-based orbital transfer vehicles, large Oct. 1986 44 p space antenna concepts and space stations. The need for (Contract NAS1-17070; NAS1-18107; NAG1-517; NSF engineering analysis tools to aid in the rapid synthesis and MCS-85-043 16; AF-AFOSR-84-0398; AF-AFOSR-84-0393) evaluation of spacecraft has led to the development of the (NASA-CR-178199; ICASE-86-71; NAS 1.26:178199) Avail: NTlS Interactive Design and Evaluation of Advanced Spacecraft (IDEAS) HC AO3/MF A01 CSCL 728 computer-aided design system. The ADEAS system has been used A computational method is developed for the estimation of to perform trade studies of competing technologies and parameters in a distributed model for a flexible structure. The requirements in order to pinpoint possible beneficial areas for structure we consider (part of the RPL experiment) consists of a research and development. IDEAS is presented as a cantilevered beam with a thruster and linear accelerometer at the multidisciplinary tool for the analysis of advanced space systems. free end. The thruster is fed by a pressurized hose whose horizontal Capabilities range from model generation and structural and thermal motion effects the transverse vibration of the beam. The analysis to subsystem synthesis and performance analysis. Euler-Bernoulli theory is used to model the vibration of the beam Author and treat the hose-thruster assembly as a lumped or point mass-dashpot-spring system at the tip. Using measurements of linear acceleration at the tip, it is estimated that the parameters N87-11762'# TRW Defense and Space Systems Group, Redondo (mass, stiffness, damping) and a Voight-Kelvin viscoelastic Beach, Calif. structural damping parameter for the beam using a least squares MICROCOMPUTER DESIGN AND ANALYSIS OF THE CABLE fit to the data. Spline based approximations to the hybrid (coupled CATENARY LARGESPACE ANTENNASYSTEM ordinary and partial differential equations) system are considered; W. AKLE ln NASA. Langley Research Center Recent Experiences theoretical convergence results and numerical studies with both in Multidisciplinary Analysis and Optimization, Part 2 14 p simulation and actual experimental data obtained from the structure 1984 Avail: NTlS HC A22/MF A01 CSCL 20K are presented and discussed. Author The use of microcomputers in the design of a cable catenary large space antenna system is discussed. The development of a system design capability, data base utilization, systems integration, program structure and logic, and integrated graphics output are discussed. R.J.F. N87-14370# Air Force Academy, Colo. N87-13626# MATRA Espace, Toulouse (France). MMU (MANNED MANEUVERING UNIT) TASK SIMULATOR Final STUDY OF FREQUENCY SELECTIVE SYSTEMS. PART 1: Report, Jun. 1985 - Jan.'1986 PRELIMINARY INVESTMENTS ON SHAPES AND LATTICES; S. ALFANO 15 Jan. 1986 80 p SOFTWARE DEVELOPMENTS. PART 2: INTERFACING OF (AD-A169552; USAFA-TR-86-2) Avail: NTlS HC A05/MF A01 POLITECNICO FSS PROGRAMS WITH MATRA REFLECTOR CSCL 22A ANTENNA SOFTWARE. PART 3: APPLICATION TO MACS Described are simplified mathematical models of the Manned PHASE 2 TX ANTENNA (MATRA) Maneuvering Unit (MMU) used in the USAFA Proximity Operations P. G. MANTICA, R. TASCONE, R. ORTA, and R. ZlCH Paris, Simulator for the VAX 11/780 and the Evans and Sutherland PS France ESA Dec. 1985 230 p Prepared in cooperation with 300 computers. This simulator serves as a learning aid for cadets Politechnico di Torino, Italy, and Satcom International, Toulouse, studying orbital dynamics and MMU mission planning and as a France research platform for the Department of Astronautics. The Manned (Contract ESA-5279/82-F-RD(SC)) Maneuvering Unit (MMU) Proximity Operations Simulator is a nine (ANT/NTEA/04.85; DE/GE/006.85; ESA-CR(P)-2271; degrees-of-freedom trajectory integrator (six degrees of freedom ETN-86-98140) Avail: NTlS HC A1 1/MF A01 for the MMU and three degrees of freedom for the target) which The impact of frequency selective surfaces (FSS) on an offset generates digital and graphical data to describe relative motion of Cassegrain satellite antenna comprising one solid main reflector, the MMU and a free-flying target. This motion is obtained by two dichroic subreflectors, and the feed clusters was assessed. applying the Clohessy-Wiltshire equations for terminal Patch shapes and lattices were studied in order to develop FSS rendezvous/docking with the Earth modeled as a uniform sphere software. The FSS programs were interfaced with reflector antenna and aerodynamic forces ignored. MMU position relative to target software. The complete package was applied to the MACS phase is computed by a first-order Euler integrator which uses quaternions 2 TX antenna. Results show that the software can analyze any to define the rotational state. The target is modeled as a Space common FSS configuration with all necessary details: single or Transportation System (STS) Orbiter. The MMU is treated as a 1 multigrid periodic structures (conductive patches) inserted in a rigid body whose mass properties (gross wt., moments and products sandwich of dielectric layers. The link with reflector antenna of inertia, and center of gravity location) are set within the porgram software allows an accurate prediction of overall antenna and remain constant. GRA

13 02 ANALYSIS AND DESIGN TECHNIQUES

N87-16042*# National Aeronautics and Space Administration. for 850 MHz or 30 for 12 GHz) and mesh fastening points (so-called Langley Research Center, Hampton, Va. stand-offs). Tests with a two rib test model prove that the COMPUTER-AIDED DESIGN AND DISTRIBUTED SYSTEM deployment and retraction system is reliable and that the mesh TECHNOLOGY DEVELOPMENT FOR LARGE SPACE provides the required reflector surface. The configuration of the STRUCTURES mesh is suitable in a range of frequencies up to 12 GHz. With ERNEST S. ARMSTRONG and SURESH M. JOSH1 ln its the right mesh tension there are no passive intermodulation NASA/DOD ControVStructures Interaction Technology, 1986 p products. ESA 441-456 NOV.1986 Avail: NTlS HC A23/MF A01 CSCL 22B N87-16934# Spar Aerospace Ltd., Ste-Anne-de-Bellevue Proposed large space structures have many characteristics that (Quebec). make them difficult to analyze and control. They are highly flexible, DESIGN OF A LOW DISTORTION SHARED APERTURE with components mathematically modeled by partial differential REFLECTOR equations or very large systems of ordinary differential equations. L. OONATO and V. K. JHA ln ESA Proceedings of the Second They have many resonant frequencies, typically low and closely ESA Workhop on Mechanical Technology for Antennas p 91-96 spaced. Natural damping may be low and/or improperly modeled. Aug. 1986 Coupled with stringent operational requirements of orientation, (Contract CAN-DEPT-COMM-21ST-361 00-3-031) shape control, and vibration suppression, and the inability to Avail: NTlS HC A12/MF A01 perform adequate ground testing, these characteristics present an A design concept for a low thermal distortion dual gridded unconventional identification and control design problem to the shared aperture reflector for satellite antennas is proposed. Low systems theorist. Some of the research underway within Langley's distortion characteristics result in improved on-orbit gain Spacecraft Control Branch, Guidance and Control Division aimed performance of the antenna system. The absence of an intercostal at developing theory and algorithms to treat large space structures structure between reflectors improves electrical cross polar and systems identification and control problems is described. The gain performance. A finite difference model to predict temperatures research areas to be considered are computer-aided design of the reflector assembly was generated. From the temperature algorithms, and systems identification and control of distributed profiles a finite element model was used to evaluate the distortions systems. Author of the parabolic surfaces. From the distorted best fit surfaces, pointing errors, defocussing, and rms deviation from the best fit N87-16058# American Society of Civil Engineers, New York. parabola were evaluated and compared to thermal distortions of IDENTIFICATION OF LARGE SPACE STRUCTURES ON ORBIT previous designs. The results show a significant improvement. Final Report, Sep. 1985 - Aug. 1986 ESA EUGENE DENMAN, TIMOTHY HASSELMAN, C. T. SUN, JER-NAN JUANG, and JOHN JUNKINS Sep. 1986 356 p N87-17828*# National Aeronautics and Space Administration. (Contract FO4611-85-C-0092) Langley Research Center, Hampton, Va. (AD-A173756; AFRPL-TR-86-054) Avail: NTlS HC A16/MF A01 FINITE ELEMENT MODEL OF SCOLE LABORATORY CSCL 22A CONFIGURATION The aspects of state of the practice modeling and identification BETH LEE, JEFFREY P. WILLIAMS, and DEAN SPARKS ln its of large space structures are discussed in this report. Methods of Proceedings of the 3rd Annual SCOLE Workshop p 149-162 modeling a structures as well as identification procedures are Jan. 1987 presented along with data acquisition and processing requirements. Avail: NTlS HC A20/MF A01 CSCL 226 Recommendations for developing algorithms for the task of space The Spacecraft Control Laboratory Experiment (SCOLE) is structure identification are given. GRA defined by element properties: material constants; mast, reflector, rigid links as beam elements; cable as bar element; and space N87-16322*# Messerschmitt-Boelkow-Blohm/Entwicklungspring shuttle as very stiff beam. Two boundary conditions are modeled: Nord, Bremen (West Germany). suspended (6 degrees of freedom for all joints except the top of DESIGN AND DEVELOPMENT OF A TELESCOPIC AXIAL the cable) and cantilevered cables (shuttle platform fixed in all BOOM degrees of freedon). Calculations include stiffness and mass ROLAND FELKAI ln NASA. Lewis Research Center The 20th matrices, initial stresses, static displacements and reactions, and Aerospace Mechanics Symposium p 1-12 May 1986 eigensolutions. B.G. Avail: NTlS HC A14/MF A01 CSCL 228 A special telescopic boom has been design-optimized, N87-20066'# Systems Science and Software, La Jolla, Calif. developed and qualified to carry an S-band antenna for the German A UNIFIED APPROACH TO COMPUTER ANALYSIS AND Telecommunication Satellite is discussed. The design driver MODELING OF SPACECRAFT ENVIRONMENTAL INTERAC- requirements, the alternatives investigated, the final technical TIONS solution, the tests performed, and special problem areas I. KATZ, M. J. MANDELL, and J. J. CASSIDY ln JPL, Space encountered during its development are discussed. Author Technology Plasma Issues in 2001 p 113-125 1 Oct. 1986 Avail: NTlS HC A2O/MF A01 CSCL 228 N87-16925# Messerschmitt-Boelkow-Blohm G.m.b.H., Munich A new, coordinated, unified approach to the development of (West Germany). spacecraft plasma interaction models is proposed. The objective EXPERIENCE GAINED BY SECTOR MODEL TESTING OF AN is to eliminate the unnecessary duplicative work in order to allow UNFURLABLE MESHlRlB ANTENNA researchers to concentrate on the scientific aspects. By H. HEINZE, H. HERBIG, and H. VORBRUGG ln ESA Proceedings streamlining the developmental process, the interchange between of the Second ESA Workhop on Mechanical Technology for theories and experimentalists is enhanced, and the transfer of Antennas p 17-22 Aug. 1986 technology to the spacecraft engineering community is faster. This (Contract ESTEC-5206/82-NL-PB(SC)) approach is called the UNlfied Spacecraft Interaction Model Avail: NTlS HC A12/MF A01 (UNISIM). UNlSlM is a coordinated system of software, hardware, An unfurlable offset mesh antenna for communication satellite and specifications. It is a tool for modeling and analyzing spacecraft applications in the range 850 MHz to 12 GHz was designed. The interactions. It will be used to design experiments, to interpret reflector design concept should cover aperture diameters from results of experiments, and to aid in future spacecraft design. It 3.2 (12 GHz) to 12 m (850 MHz) with surface errors between 0.1 breaks a Spacecraft lneraction analysis into several modules. Each mm and 1.4 mm RMS. This versatility is met by a radial rib concept module will perform an analysis for some physical process, using where foldable main ribs and intermediate ribs tension a gold phenomenology and algorithms which are well documented and plated molybdenum mesh to the required surface contour. The have been subject to review. This system and its characteristics accuracy is varied by applying a different number of ribs (e.g., 16 are discussed. E.R.

14 ~

03 STRUCTURAL CONCEPTS

03 A87-15933# DEVELOPMENT OF A 'HINGELESS MAST' AND ITS STRUCTURAL CONCEPTS APPLICATIONS T. KITAMURA, K. OKAZAKI, S. SAT0 (Japan Aircraft Manufacturing Co., Ltd., Yokohama), M.. NATORI, K. MIURA (Tokyo, University, Includes erectable structures (joints, struts, and columns), Japan) et al. IAF, International Astronautical Congress, 37th, deployable platforms and booms, solar sail, deployable reflectors, Innsbruck, Austria, Oct. 4-1 1, 1986. 7 p. refs space fabrication techniques, and protrusion processing. (IAF PAPER 86-205) An evaluation is made of the design features and space applications of an extendible mast whose stowage mode involves A87-11842" Lockheed Missiles and Space Co., Sunnyvale, very compact helical geometry coiling. This 'Hingeless Mast' Calif. concept yields structural accuracy and weight properties that are DEVELOPMENT OF SPACE STATION STRUT DESIGN judged superior to those of the more conventional 'simplex' mast, R. R. JOHNSON, R. M. BLUCK, A. M. C. HOLMES, and M. H. and is composed of flexible longerons, integral radial spacers, KURAL (Lockheed Missiles and Space Co., Inc., Sunnyvale, CA) and triangulating wires. O.C. SAMPE Quarterly (ISSN 0036-0821). vol. 17, July 1986, p. 1-9. (Contract NAS1-17660) Candidate Space Station struts exhibiting high stiffness (38-40 msi modulus of elasticity) were manufactured and experimentally evaluated. One and two inch diameter aluminum-clad evaluation A87-15934# specimens were manufactured using a unique dry fiber resin CONCEPT OF TENSION ACTIVATED CABLE LA'ITICE injection process. Preliminary tests were performed on strut ANTENNA elements having 80 percent high-modulus graphite epoxy and 20 K. MIURA (Tokyo, University, Japan) IAF, International percent aluminum. Performed tests included modulus of elasticity, Astronautical Congress, 37th, Innsbruck, Austria, Oct. 4-1 1, 1986. thermal cycling, and coefficient of thermal expansion. The paper 10 p. describes the design approach, including an analytical assessment (IAF PAPER 86-206) of strut thermal deformation behavior. The major thrust of this A new concept of a three-dimensional, integrated cable lattice paper is the manufacturing process which produces aluminum-clad system which can meet a variety of requirements concerning facet struts with precisely controlled properties which can be fine-tuned sizing and arrangement is presented. The geometric modelling of after fabrication. An impact test and evaluation procedure for the lattice, the boundary restraints, the reflector surface deviation, evaluating toughness is described. Author and the electromagnetic behavior of the tension truss antenna are discussed. The primary feature of the antenna is that its shape is uniquely determined by the member lengths and their A87- 15929# arrangement, and not by the equilibrium of forces. C.D. A NEW STRUCTURE TOWARD HIGH PRECISION LARGE ANTENNA T. YASAKA, M. MINOMO, and K. OHATA (Nippon Telegraph and Telephone Public Corp., Electrical Communications Laboratories, A87-16145# Yokosuka, Japan) IAF, International Astronautical Congress, 37th, Innsbruck, Austria, Oct. 4-1 1, 1986. 10 p. OPTIMIZATION OF A TRUSS MEMBER D. S. LEONARD (Iowa State University of Science and Technology, (IAF PAPER 86-201) Ames) IAF, International Astronautical Congress, 37th, Innsbruck, A new structure for a large precision antenna is considered, Austria, Oct. 4-1 1, 1986. 8 p. refs and the concept is demonstrated. This structure copes with the (IAF PAPER ST-66-17) problems related to distortion assessment with increasing flexibility The present study involves the determination of the shape of under 1 G, and to thermal deformation suppression over large a truss-type pin jointed member for which the buckling strength to areas with limited structural mass and volume. In the structure, near-zero truss elements are assembled to a base structure from weight ratio is maximized. From an analytical study using the ANSYS finite element code it was determined that a hollow which a thin paraboloidal shell is supported by a number of support cylindrical shell with varying cross section should be used. To elements with adjustment capability. The structural model of the keep the weight of the member to a minimum, an open lattice truss-shell reflectors were fabricated, and tests showed that they possessed the desired structural properties. C.D. construction was chosen. For the lattice structure, an additional advantage was attained by using uniaxial graphite-epoxy material in the design. Author

A87-15930'# Astro Aerospace Corp., Carpinteria, Calif. STRUCTURAL CONCEPTS FOR LARGE SOLAR CONCENTRATORS J. M. HEDGEPETH (Astro Aerospace Corp., Carpinteria, CA) and A87-18243 R. K. MILLER (Southern California, University, Los Angeles, CA) 2D-ARRAY MISSION - TWO-DIMENSIONALLY DEPLOYABLE IAF, International Astronautical Congress, 37th, Innsbruck, Austria, SOLAR CELL ARRAY MISSION Oct. 4-1 1, 1986. 11 p. refs K. MIURA, A. USHIROKAWA, M. NATORI. and M. SAKAMAKI (Contract NAS1-17536) (Tokyo, University, Japan) IN: International Symposium on Space (IAF PAPER 86-202) Technology and Science, 14th, Tokyo, Japan, May 27-June 1, Solar collectors for space use are examined, including both 1984, Proceedings . Tokyo, AGNE Publishing, Inc., 1984. p. I early designs and current concepts. In particular, attention is given 363-368. to stiff sandwich panels and aluminum dishes as well as inflated The main purposes of the 2D-Array mission are the verification and umbrella-type membrane configurations. The Sunflower in space of the effectiveness of tension-stabilized large space concentrator is described as an example of a high-efficiency structures which are absolutely necessary for future space collector. It is concluded that stiff reflector panels are most likely development of solar power generation using large thin solar cells. to provide the long-term consistent accuracy necessary for low-orbit The array consists of a large area of solar-cell blanket and a operation. A new configuration consisting of a Pactruss backup circumferential rim made of several extendible masts which structure, with identical panels installed after deployment in space, supports the blanket through tension wires and fixtures. The blanket is presented. It is estimated that concentration ratios in excess of is deployed and stowed through the two-dimensional deployment 2000 can be achieved with this concept. V.L. of a plane surface. Author

15 03 STRUCTURAL CONCEPTS

A87-18321 composites, must also be taken into account. In this paper a TRUNCATION ERROR ESTIMATION OF A SPACECRAFT calculation tool is presented for bonded structures, and procedures MODEL WITH A FLEXIBLE APPENDAGE for the accurate determination of the mechanical properties of T. KAI and Y. OHKAMI (National Aerospace Laboratory, Chofu, adhesive materials are given. Author Japan) IN: International Symposium on Space Technology and Science, 14th, Tokyo, Japan, May 27-June 1, 1984, Proceedings . A87-22395# Tokyo, AGNE Publishing, Inc., 1984, p. 957-962. refs OPTIMIZATION OF A TRUSS MEMBER A mathematical model expanded with constrained and DANIEL SHANE LEONARD (Iowa State University of Science and unconstrained modes is presented for a control experimental model Technology, Ames) AIAA, Aerospace Sciences Meeting, 25th, which is composed of a rigid part and an elastic part and is freely Reno, NV, Jan. 12-15, 1987. 8 p. refs rotatable around one axis. Frequency response functions of the (AIAA PAPER 87-0073) angle of rotation with respect to the control torque about the axis In designing large space structures for space application, weight are derived. Zeros and poles of these functions are calculated must be minimized. Such large structures are envisioned as an and the differences between the two mode systems are shown assembly of pin jointed truss-type members designed to withstand for several inertial ratios of the rigid part to the elastic part. predetermined compressive and tensile loads. Since buckling is Author of primary concern it is desirable to maximize the buckling strength to weight ratio for such members. The present study involves the A87-18489 determination of the shape of a truss-type pin jointed member for ON THE ORBITER BASED DEPLOYMENT OF FLEXIBLE which the buckling strength to weight ratio is maximized. From an MEMBERS analytical study using the ANSYS finite element code it was A. K. MISRA, D. M. XU (McGill University, Montreal, Canada), V. determined that a hollow cylindrical shell with varying cross section J. MODI (British Columbia, University, Vancouver, Canada; Tokyo, should be used. To keep the weight of the member to a minimum, University, Japan), and A. M. IBRAHIM IN: Space exploitation an open lattice construction was chosen. For the lattice structure, and utilization; Proceedings of the Symposium, Honolulu, HI, an additional advantage was attained by using uniaxial December 15-19, 1985 . San Diego, CA, Univelt, Inc., 1986, p. graphite-epoxy material in the design. Once designed the optimal 601-616. refs truss member was laid up over a plaster mandrel, intertwining the (Contract NSERC-67-1547) axial and ring elements. A finite elements analysis was then (AAS PAPER 85-673) completed for the truss member for comparison with the Using relatively general formulation procedures, the paper experimental outcome. Author attempts to study complex interactions between deployment, attitude dynamics and flexural rigidity for two distinct configurations A87-28882' Cincinnati Univ., Ohio. representing deployment of beam and tether type appendages SHEAR DEFORMATION PLATE CONTINUA OF LARGE DOUBLE from the Orbiter. The study suggests that under critical LAYEREDSPACE STRUCTURES combinations of parameters the systems can become unstable. MOHAMED SAMlR HEFZY and ADNAN H. NAYFEH (Cincinnati, The results have some relevance to the next generation of University, OH) International Journal of Solids and Structures communications satellites with large flexible beam type booms (ISSN 0020-7683), vol. 22, no. 12, 1986, p. 1455-1469. refs and solar panels as well as deployment and retrieval of tethered (Contract NSG-1185) subsatellite systems. Author A simple method is presented to model large rigid-jointed lattice structures as continuous elastic media with couple stresses using A87-18495 energy equivalence. In the analysis, the transition from the discrete OPTIMAL CONTROL OF COMPONENT DEPLOYMENT FOR THE system to the continuous media is achieved by expanding the SPACE RADIOTELESCOPE SYSTEM displacements and the rotations of the nodal points in a Taylor W. STUIVER (Hawaii, University, Honolulu) IN: Space exploitation series about a suitable chosen origin. The strain energy of the and utilization; Proceedings of the Symposium, Honolulu, HI, continuous media with couple stresses is then specialized to obtain December 15-19, 1985 . San Diego, CA. Univelt, Inc., 1986, p. shear deformation plate continua. Equivalent continua for single 679-684. layered grids, double layered grids, and three-dimensional lattices (AAS PAPER 85-683) are then obtained. Author Earlier work (Stuiver et al., 1981, and Stuiver, 1985) on the construction and deployment of a very large space-based A87-31175# radiotelescope for SET1 is extended. The configuration would OPTIMIZATION OF EQUIVALENT PERIODIC TRUSS consist of a self-contained, fully automated antenna system made STRUCTURES up of free-floating components. The large spherical reflecting M. LAJCZOK (Martin Marietta Corp., Denver, CO) AIAA Journal receiver dish would be backed up by an even larger, nominally (ISSN 0001-1452), vol. 25, March 1987, p. 502-504. planar, shield to block electromagnetic radiation. It has been Equivalent modeling is presently used in conjunction with simple postulated that because of their high area-to-mass ratios the dish calculations to optimize a struss structure of cantilever type having and shield would be fabricated at or near GEO altitude and moved ten bays. This approach, which deepens insight into the relative by solar sailing to the point of operation. D.H. performance of tubular member and solid member truss structures could be extended to more complex structures, given sufficient care in the selection of equivalent models. Attention is given to a A87-20148 comparison of the Bernoulli-Euler and Timoshenko beam BEHAVIOURAL ANALYSIS OF ADHESIVE-BONDED STRUC- approaches. O.C. TURAL JOINTS IN SPACE VEHICLES J.-P. MAIGRET and M. MARTIN (Aerospatiele, Saint-Medard-en- N87-10923# National Aeronautics and Space Administration. Jalles, France) International Journal of Adhesion and Adhesives Marshall Space Flight Center, Huntsville, Ala. (ISSN 0143-7496), vol. 6, Oct. 1986, p. 189-198. refs. DEVELOPMENT OF DEPLOYABLE TRUSS CONCEPT FOR In space structures, the design of adhesive-bonded joints SPACE STATION generally involves a very low safety ratio. This requires careful H. S. GREENBERG (Rockwell International Corp., Downey, Calif.) choice of the criteria applied to account for external factors and E. E. ENGLER ln ESA Proceedings of an International (mechanical, static and dynamic, and thermal effects). The situation Conference on Spacecraft Structures p 277-282 Apr. 1986 is complicated by the behavior of the materials involved, particularly Avail: NTlS HC Al9/MF A01 composites, which undergo large distortions, and whose fracture A single-fold, automatically deployable and retractable, criteria depend on load cycles. In addition, polymerization effects square-shaped truss concept that is a candidate for the strongback in joints between different materials, such as metals and of NASA's Space Station was developed. Compact stowage within

16 03 STRUCTURAL CONCEPTS a square-shaped housing is achieved by using folded longerons over-center for securely locking the joint in the unfolded position. and telescoping diagonal members. Deployment or retraction is Official Gazette of the US Patent and Trademark Office accomplished, bay by bay, in a controlled manner with root strength maintained at all times. Control is accomplished by motor-driven N87-16031'# Harris Corp., Palm Bay, Fla. jack-screws operated by a controller. Power, data, and fluid utility MAST FLIGHT SYSTEM BEAM STRUCTURE AND BEAM lines can be integrated onto trays that unfold with the truss. To STRUCTURAL PERFORMANCE verify performance a kinematically representative ground test article DAVID C. LENZI and JOHN W. SHIPLEY ln NASA. Langley version is used. ESA Research Center NASAIDOD Control/Structures Interaction Technology, 1986 p 265-279 Nov. 1986 Avail: NTlS HC A23/MF A01 CSCL 20K N87-10927# Societe Nationale lndustrielle Aerospatiale, Les An overall understanding of the beam assembly and data with Mureaux (France). which potential experimenters can begin to conduct analyses DEVELOPMENT OF A LIGHTENED STRUCTURE FOR THE GSR3 relevant to their experiments is given. Data is given on the beam SOLAR GENERATOR [DEVELOPPEMENT D'UNE STRUCTURE structural concept, the tip remote station layout, the intermediate ALLEGEE DE GENERATEUR SOLAIRE GSR31 remote station layout with and without actuators, beam element A. PLAGNE and J. P. REAU ln ESA Proceedings of an International Conference on Spacecraft Structures p 299-304 Apr. materials, equivalent beam characteristics, beam element properties, remote station mass properties, and MAST Flight 1986 In FRENCH System modal characteristics. R.J.F. Avail: NTlS HC Al9/MF A01 Weight reduction techniques employed in the GSR3 Solar generator (35W/kg end of life) are described. The surface mass N87-16055# McIntosh Structural Dynamics, Inc., Palo Alto, of the structure is 900 to 1050 g/sqm depending on the dsgree Calif. of optimization of stacking points. The structure is highly versatile, INVESTIGATION OF INTERACTIVE STRUCTURAL AND and can be used fully or partly deployed. Carbon fiber composite CONTROLLER SYNTHESIS FOR LARGE SPACECRAFT Final was chosen to meet weight and sizing constraints. ESA Report, 1 Mar. 1984 - 30 Oct. 1985 SAMUEL C. MCINTOSH, JR. and MICHEL A. FLOYD 22 Jan. 1986 45 p Prepared in cooperation with Integrated Systems, N87-14366*# Harris Corp., Melbourne, Fla. Inc. DEVELOPMENT OF THE 15 METER DIAMETER HOOP COLUMN (Contract F49620-84-C-0025) ANTENNA Final Report (AD-A172811; TR-86-1; AFOSR-86-0900TR) Avail: NTIS HC Washington NASA Dec. 1986 161 p A03/MF A01 CSCL 22B (Contract NAS1-15763) A technique is developed for least-weight optimal design of a (NASA-CR-4038; NAS 1.26:4038) Avail: NTlS HC A08/MF A01 tubular-truss space structure, subject to constraints on its natural CSCL 22B frequencies and its open-loop disturbance-rejection properties. The The building of a deployable 15-meter engineering model of disturbance-rejection properties of the structure are measured by the 100 meter antenna based on the point-design of an earlier disturbance-to-regulated-variable grammians. It is shown how this task of this contract, complete with an RF-capable surface is technique can be embedded in a model-reduction scheme based described. The 15 meter diameter was selected so that the model on internal balancing. Examples treated include a simple dumbell could be tested in existing manufacturing, near-field RF, thermal model and csdl model no. 1. Author (GRA) vacuum, and structural dynamics facilities. The antenna was designed with four offset paraboloidal reflector surfaces with a N87-16870'# Astro Aerospace Corp., Carpinteria, Calif. focal length of 366.85 in and a primary surface accuracy goal of EVALUATION OF PACTRUSS DESIGN CHARACTERISTICS .069 in rms. Surface adjustment capability was provided by manually CRITICAL TO SPACE STATION PRIMARY STRUCTURE Final resetting the length of 96 surface control cords which emanated Report from the lower column extremity. A detailed description of the JOHN M. HEDGEPETH 20 Feb. 1987 74 p 15-meter Hoop/Column Antenna, major subassemblies, and a (Contract NASI-17536) history of its fabrication, assembly, deployment testing, and (NASA-CR-178171; NAS 1.26:178171; AAC-TN-1147-REV-A) verification measurements are given. The deviation for one aperture Avail: NTlS HC A04/MF A01 CSCL 22A surface (except the outboard extremity) was measured after Several aspects of the possible application of the Pactruss adjustments in follow-on tests at the Martin Marietta Near-field concept to the primary truss structure of the space station are Facility to be ,061 in; thus the primary surface goal was achieved. investigated. Estimates are made of the loads and hinge moments Author in deploying diagonal members as full deployment is approached. Included are the effects of beam columning and compliance of N87-14373' National Aeronautics and Space Administration. the surrounding structure. Requirements for joint design are Lyndon B. Johnson Space Center, Houston, Tex. suggested and a two-stage mid-diagonal latching hinge concept FOLDABLE SELF-ERECTING JOINT Patent is described or analyzed. The problems with providing the T. E. PELISCHEK, inventor (to NASA) 7 Oct. 1986 8 p Filed experimental and theoretical tools needed for assuring reliable 9 Mar. 1984 Supersedes N84-32424 (22 - 22, p 3542) synchronous deployment are discussed and a first attempt at (NASA-CASE-MSC-20635-1; US-PATENT-4,615,637; high-fidelity analytical simulation with NASTRAN is described. An US-PATENT-APPL-SN-588039; US-PATENT-CLASS-403-85; alternative construction scenario in which the entire dual-keel truss US-PATENT-CLASS-403-102; US-PATENT-CLASS-403-119; structure is deployed as a single Shuttle payload is suggested. US-PATENT-CLASS-403-146; US-PATENT-CLASS-403-163; Author US-PATENT-CLASS-16-294; US-PATENT-CLASS-16-370) Avail: US Patent and Trademark Office CSCL 228 N87-16931# Turin Univ. (Italy). Dipt. di Elettronica. The invention relates to a foldable self erecting joint which DIELECTRIC SUPPORT STRUCTURES FOR SPACECRAFT may be used to deploy the tetratruss frame of the proposed shuttle ANTENNAFEEDS launched triangular space station. The frame must be folded into R. D. GRAGLIA, M. OREFICE, U. PONZI (Rome Univ., Italy), and the payload bay of the space shuttle orbiter. To deploy the frame S. SGUBlNl ln ESA Proceedings of the Second ESA Workshop the tubes are automatically unfolded and once in position should on Mechanical Technology for Antennas p 63-71 Aug. 1986 remain safely. A pair of hinged, tubular members in which the Avail: NTlS HC A12/MF A01 hinging is located at corresponding portions of the members are Analysis and design criteria for radio frequency transparent used. The opposite edge portions are connected by spring-based towers, to be used as support structures of feeds or subreflector toggle links which in the unfolded position of the members are in spacecraft reflector antennas are discussed. Candidate materials nested against one of the members in substantial alignment and are fiber reinforced plastics, in particular those with good

17 03 STRUCTURAL CONCEPTS mechanical and dielectric properties, as aramid fiber (Kevlar). The A87-15939# electromagnetic analysis is performed by subdividing the structure STRESS AND DEFORMATION ANALYSIS OF THERMALLY in simple members (planes, cylinders, etc.) and considering each LOADED LIGHT WEIGHT COMPOSITE STRUCTURES individual contribution to the scattering. Typical structures for offset K. PFEIFER and J. BODE (Messerschmitt-Boelkow-BlohmGmbH, and symmetrical configurations were considered, and design criteria Muenich, West Germany) IAF, International Astronautical are given. ESA Congress, 37th, Innsbruck, Austria, Oct. 4-11, 1986. 16 p. (IAF PAPER 86-212) The effect of thermally induced deformations and stresses on the dimensional stability of fiber composite structures is discussed N87-16938# European Space Agency. European Space with particular reference to the reflector shells of a space antenna Research and Technology Center, ESTEC, Noordwijk consisting of two Kevlar/Nomex sandwich shells approximately (Netherlands). 1100 mm in diameter, their edges connected by a Kevlar/glass GIOTTO SPACECRAFT HIGH GAIN ANTENNA MECHANICAL ring. The rear shell is fixed at the satellite by a conical carbon DESIGN AND DEVELOPMENT fiber composite cylinder and stiffened by four Kevlar/Nomex ribs. R. HALM, F. FELICI, H. J. SCHOEDEL (Dornier-Werke G.m.b.H., A finite-element model is used to determine the contour changes Friedrichshafen, West Germany), and H. RAUPP ln its Proceedings due to different Young's moduli and thermal expansion coefficients of the Second ESA Workshop on Mechanical Technology for of the core. V.L. Antennas (date) p 123-126 Aug. 1986 Avail: NTlS HC A12/MF A01 A87-18266 The development approach of the Giotto spacecraft high gain THE INFLUENCE OF INTERSTITIAL MEDIA ON SPACECRAFT antenna structure is presented. The antenna structure consists of THERMAL CONTROL a dynamically and statically balanced offset parabolic reflector and IN: a tripod support structure for the S/X-band feed. The reflector L. S. FLETCHER (Texas A & M University, College Station) dish is a sandwich construction having CFRP face sheets employing International Symposium on Space Technology and Science, 14th, ultra high module fibers bonded to an aluminum honeycomb core. Tokyo, Japan, May 27-June 1, 1984, Proceedings . Tokyo, AGNE The tripod is designed to provide the required eigenfrequencies Publishing, Inc., 1984, p. 527-532. refs by stiff profiles made of CFRP. ESA Thermal control is of significant importance in the design and operation of most aerospace systems. The importance of thermal protection systems and the concern for energy efficiency suggest the need for more reliable knowledge of energy transfer across metallic junctions with and without interstitial media. This paper discusses recent investigations of thermal contact conductance involving both gaseous and nongaseous interstitial media in terms 04 of thermal enhancement and thermal isolation characteristics. Author STRUCTURAL AND THERMAL ANALYSIS A87-18273 DEGRADATION OF SPACECRAFT THERMAL SHIELD Includes structural analysis and design, thermal analysis and MATERIALS BY IRRADIATION OF ENERGETIC PARTICLES design, analysis and design techniques, and thermal control M. KOITABASHI, S. SHIMOJI, T. IMAMURA, J. ENOMOTO systems. (Mitsubishi Electric Corp., Central Research Laboratory, Amagasaki, Japan), H. KIMURA (Mitsubishi Electric Corp., Kamakura Works, Japan) et al. IN: International Symposium on Space Technology A87-15197 and Science, 14th, Tokyo, Japan, May 27-June 1, 1984, CONTROLLING WASTE HEAT IN MILITARY SPACECRAFT Proceedings . Tokyo, AGNE Publishing, Inc., 1984, p. 577-582. J. H. BRAHNEY Aerospace Engineering (ISSN 0736-2536), vol. refs 6, Aug. 1986, p. 23-29. For studying the effect of the space radiation environment on The purpose of a spacecraft thermal management system (TMS) silver-teflon and aluminized kapton films, the irradiations of is to gather waste heat and reject it from the vehicle; attention is electrons and of protons simultaneously with ultraviolet rays were presently given to the anticipated compounding of already severe performed on these films in a high vacuum condition. The solar military space platform TMS requirements by the incorporation of absorptance, thermal emittance, tensile strength, and elongation a high pulsed power heat rejection capability. An evaluation is rate were measured. Silver-teflon was degraded more than conducted of several TMS configurations that appear promising; aluminumized kapton. The electron irradiation affected mostly the the capillary pumped-loop type being noteworthy. Also noted are mechanical property, while the proton irradiation affected the radiator systems and TMSs incorporating heat storage media. thermooptical property. The electron irradiation created many more O.C. small molecules in the teflon film than the proton irradiation, and the double bonds between carbon atoms increased with the fluences. Author A82-15936# NONLINEAR EFFECTS IN THERMAL CONDUCTION PROBLEMS A87-18487' Virginia Polytechnic Inst. and State Univ., OF LARGE SPACE STRUCTURES Blacksburg. P. SANTlNl (Roma, Universita, Rome, Italy) IAF, International PARAMETER IDENTIFICATION IN DISTRIBUTED SPACECRAFT Astronautical Congress, 37th, Innsbruck, Austria, Oct. 4-1 1, 1986. STRUCTURES 12 p. L. MElROVlTCH and M. A. NORRIS (Virginia Polytechnic Institute (IAF PAPER 86-208) and State University, Blacksburg) IN: Space exploitation and Some of the most important nonlinearities affecting the thermal utilization; Proceedings of the Symposium, Honolulu, HI, December behavior of space structures are considered and discussed. The 15-19, 1985 . San Diego, CA, Univelt, Inc., 1986, p. 573-586. basic equations for a single member are written, and the complete refs system in steady condition is described. Several methods of (Contract NAG1-225) numerical solutions are considered (successive approximations; (AAS PAPER 85-670) artificial unsteady; Newton Raphson), and the relevant relative This paper develops a new technique for the identification of merits are analyzed. Typical examples on a simple structure are parameters in distributed systems. The technique is based on the carried out, and final conclusions are drawn. Author finite element method. An an illustration, the method is applied to

18 04 STRUCTURAL AND THERMAL ANALYSIS the identification of the mass and stiffness distributions of a space monomials. Next, the monomials are linearized through logarithmic structure, simulated by a nonuniform free-free beam. Author transformation. The resulting linear programming (LP) problem is solved iteratively using a dual simplex algorithm until the optimal A87-18940'# California Univ., Los Angeles. feasible solution eventually coincides with a local optimum of the ALTERNATIVE APPROXIMATION CONCEPTS FOR SPACE approximated problem. This solution point is then used to formulate FRAME SYNTHESIS a new approximated problem and the same procedure is R. V. LUST and L. A. SCHMIT (California, University, Los automatically repeated until the solution of the original problem is Angeles) (Structures, Structural Dynamics, and Materials found. Five examples are presented to illustrate the application of Conference, 26th, Orlando, FL, April 15-17, 1985, Technical Papers. the algorithm presented in this paper. Author Part 1, p. 333-348) AlAA Journal (ISSN 0001-1452), vol. 24, Oct. 1986, p. 1676-1684. Previously cited in issue 13, p. 1853, Accession no. A85-30265. refs (Contract NSG-1490) A87-25687'# Old Dominion Univ., Norfolk, Va. FINITE-ELEMENT THERMAL-STRUCTURAL ANALYSES OF A A87-20082# CABLE-STIFFENED ORBITING ANTENNA EFFECTS OF THERMAL CYCLING ON THE MECHANICAL AND EARL A. THORTON, PRAMOTE DECHAUMPHAI (Old Dominion PHYSICAL PROPERTIES OF A SPACE QUALIFIED EPOXY University, Norfolk, VA), and AJAY E. PANDEY (Virginia Polytechnic ADHESIVE Institute and State University, Blacksburg) (Structures, Structural J. A. SANBORN and D. E. MOREL, JR. (Harris Corp., Government Dynamics, and Materials Conference, 26th, Orlando, FL, Apr. 15-17, Systems Sector, Melbourne, FL) IN: Reinforced 1985, Technical Papers. Part 1, p. 308-315) Journal of Spacecraft PlasticsKomposites Institute, Annual Conference, 41 st, Atlanta, and Rockets (ISSN 0022-4650), vol. 23, Nov.-Dec. 1986, p. GA, January 27-31, 1986, Preprint . Lancaster, PA, Technomic 620-624. USAF-NASA-supported research. Previously cited in issue Publishing Co., 1986, 5 p. 13, p. 1894, Accession no. A85-30262. refs Structural adhesives used for space applications must be able to survive large temperature fluctuations while maintaining their mechanical strength. This paper describes a series of experiments performed to document property degradation of EA 956 epoxy A87-28577 due to temperature extremes experienced in the orbital SUBSTRUCTURE COUPLING OF ANALYTICAL AND TEST environment. Testing included tension, lap shear, coefficient of MODELS FOR AN EXPERIMENTAL STRUCTURE thermal expansion (CTE) and differential scanning calorimetry FRANCOIS CHARRON, VIRENDRA K. JHA, HELENE LAPIERRE, (DSC). CTE data indicate that the exact value of strength decrease STEPHEN J. SOROCKY (Spar Aerospace, Ltd., Toronto, Canada), depends strongly on temperature; three distinct regions are and FRANK R. VIGNERON (CDG, Communications Research observed when sample strain is plotted as a function of temperature Centre, Ottawa, Canada) IN: International Modal Analysis with the CTE increasing with increasing temperature. DSC traces Conference, 4th, Los Angeles, CA, Feb. 3-6, 1986, Proceedings. on as cast and thermally cycled samples show that thermal cycling Volume 2 . Schenectady, NY, Union College, 1986, p. 1463-1470. produces a change in the physical structure of the resin resulting refs in a significant increase in the glass transition temperature of the Substructure coupling as a means of synthesizing the structural network. Author model for a large s?ructure is demonstrated. An experimental satellite structure consisting of two substructures was built and A87-20247 tested. Substructure experimental and analytical models were AN EXPLICIT EXPRESSION FOR THE TANGENT-STIFFNESS generated and coupled by using SYSTAN software. The OF A FINITELY DEFORMED 3-D BEAM AND ITS USE IN THE synthesized results were compared with the NASTRAN and test ANALYSIS OF SPACE FRAMES results of the complete structure. Results showed that modes of K. KONDOH, K. TANAKA, and S. N. ATLURI (Georgia Institute of the coupled structure sensitive to clamped boundary conditions Technology, Atlanta) Computers and Structures (ISSN 0045-7949), between substructures were better synthesized by using analytical vol. 24, no. 2, 1986, p. 253-271. refs substructure models, while those sensitive to certain asymmetries (Contract F33615-83-K-3205; AF-AFOSR-84-0020A) in substructure material properties were synthesized by using the Simplified procedures for finite-deformation analyses of space test derived model for the substructure. Author frames, using one beam element to model each member of the frame, are presented. Each element can undergo three-dimensional, arbitrarily large, rigid motions as well as moderately large nonrigid rotations. Each element can withstand three moments and three forces. The nonlinear bending-stretching A87-30296# coupling in each element is accounted for. By obtaining exact BUCKLING AND NONLINEAR RESPONSE OF IMPERFECT solutions to the approximate governing differential equations, an THREE-LEGGED TRUSS COLUMNS explicit expression for the tangent-stiffness matrix of each element, DOV ELYADA (Raphael Armament Development Authority, Haifa, valid at any stage during a wide range of finite deformations, is Israel) and CHARLES D. BABCOCK (California Institute of derived. An arc-length method is used to incrementally compute Technology, Pasadena) (Structures, Structural Dynamics and the large-deformation behavior of space frames. Author Materials Conference, 27th, San Antonio, TX, May 19-21, 1986, Technical Papers. Part 1, p. 495-501) AlAA Journal (ISSN A87-22814 0001-1452). vol. 25, Feb. 1987, p. 324-330. Research supported EFFICIENT OPTIMIZATION OF SPACE TRUSSES by the California Institute of Technology. Previously cited in issue HOJJAT ADELI (Ohio State University, Columbus) and OSAMA 18, p. 2656, Accession no. A86-38854. refs KAMAL Computers and Structures (ISSN 0045-7949), vol. 24, no. 3, 1986, p. 501-511. refs An efficient and robust algorithm is developed for minimum weight design of space trusses with fixed geometry employing the A87-31213# general geometric programming (GGP) technique. The nonlinear THERMAL CONTROL SYSTEMS FOR SPACECRAFT programming (NLP) problem is formulated based on the virtual INSTRUMENTATION work method of structural analysis. The objective function is linear, G. P. PETERSON (Texas A & M University, College Station) subjected to linear size and stress constraints and nonlinear Journal of Spacecraft and Rockets (ISSN 0022-4650), vol. 24, displacement constraints. Based on an arbitrary starting point, the Jan.-Feb. 1987, p. 7-13. Previously cited in issue 14, p. 1982, signomials are condensed into posynomials and subsequently into Accession no. A83-32736. refs

19 04 STRUCTURAL AND THERMAL ANALYSIS

A87-31225'# Jet Propulsion Lab., California Inst. of Tech., N87-10907# Centre National d'Etudes Spatiales, Toulouse Pasadena. (France). SPACECRAFT STRUCTURAL MODEL IMPROVEMENT BY PREDICTION AND CORRELATION OF STRUCTURAL MODAL TEST RESULTS RESPONSE IN ACOUSTIC CHAMBERS [PREVISION ET J.-C. CHEN, L. F. PERETTI, and J. A. GARBA (California Institute CORRELATION DE LA REPONSE DE STRUCTURES EN of Technology, Jet Propulsion Laboratory, Pasadena) (Structures, CHAMBRE ACOUSTIQUE] Structural Dynamics and Materials Conference, 25th, Palm Springs, F. MERCIER and H. DEFOSSE In ESA Proceedings of an CA, May 14-16, 1984, and AlAA Dynamics Specialists Conference, International Conference on Spacecraft Structures p 151-1 56 Apr. Palm Springs, CA, May 17, 18, 1984, Technical Papers. Part 2, p. 1986 In FRENCH 478-489) Journal of Spacecraft and Rockets (ISSN 0022-4650), Avail: NTlS HC Al9/MF A01 vol. 24, Jan.-Feb. 1987, p. 90-94. Previously cited in issue 13, p. Vibro-acoustic prediction methods in random noise used for 1847, Accession no. A84-31737. refs acoustic coupling analysis of large satellites are described. The (Contract NAS7-918) first method is for low frequencies, using modal superposition. The second is a high frequency method using a statistical energy method via a comparison of calculations and tests of a honeycomb panel. Using both methods, the response throughout the entire acoustic frequency range can be calculated. ESA

N87-10406*# Old Dominion Univ., Norfolk, Va. Dept. of N87-10910# Technische Hochschule, Aachen (West Germany). Mechanical Engineering and Mechanics. Inst. fuer Leichtbau. A TAYLOR-GALERKIN FINITE ELEMENT ALGORITHM FOR TRANSIENT EXTERNAL LOADS OR INTERFACE FORCES TRANSIENT NONLINEAR THERMAL-STRUCTURAL ANALYSIS RECONSTRUCTED FROM STRUCTURAL RESPONSE MEA- Progress Report, period ending 1 Jan. 1986 SUREMENTS E. A. THORNTON and P. DECHAUMPHAI Apr. 1986 12 p H. OERY, H. GLASER, and D. HOLZDEPPE ln ESA Proceedings Previously announced in IAA as A86-38823 of an International Conference on Spacecraft Structures p 171-177 (Contract NSG-1321) Apr. 1986 Sponsored by Deutsche Forschungsgemeinschaft and (NASA-CR-177064; NAS 1.26:177064) Avail: NTIS HC A02/MF MBB GmbH A01 CSCL20K Avail: NTlS HC Al9/MF A01 A Taylor-Galerkin finite element method for solving large, The procedure for the reconstruction of transient forcing nonlinear thermal-structural problems is presented. The algorithm functions based on measured structural responses during former is formulated for coupled transient and uncoupled quasistatic flights is described, Le., the inverse problem of the dynamic thermal-structural problems. Vectorizing strategies ensure response is investigated. The method is developed on the basis computational efficiency. Two applications demonstrate the validity of the combination and inversion of the phase-plane-method, which of the approach for analyzing transient and quasistatic delivers modal responses and the Williams method, which thermal-structural problems. Author separates the pure dynamic and the quasistatic parts of structural responses. Criteria influencing the reconstruction of the impulsive active load and its time-history are discussed. For a spacecraft transported by a launcher the interface motion time-history must be defined. ESA N87-10890# European Space Agency. European Space Research and Technology Center, ESTEC, Noordwijk N87-10911# Kassel Univ. (West Germany). (Netherlands). Mechanical Systems Div. STRUCTURAL SYSTEM IDENTIFICATION USING SINGLE AND DESIGN AND VERIFICATION ACTIVITIES AND REQUIREMENTS MULTIAXIAL VIBRATION TEST DATA FOR SPACECRAFT STRUCTURES M. LINK ln ESA Proceedings of an International Conference on C. STAVRlNlDlS In ESA Proceedings of an International Spacecraft Structures p 179-184 Apr. 1986 Conference on Spacecraft Structures p 27-33 Apr. 1986 Avail: NTlS HC Al9/MF A01 Avail: NTlS HC A19/MF A01 A method allowing for the verification of the mathematical model The scope and associated cost related with spacecraft of a structure in terms of its modal data and in terms of its structures design and verification are discussed. These depend physical mass, stiffness, and damping matrix is presented. Single on such factors as the geometrical dimensions of the spacecraft, and multiaxial shaking table excitation and the effect of incomplete weight criticality and the degree of dynamic interaction of the excitation and response data, Le., the effect that only a limited spacecraft with the launch vehicle. For large complex spacecraft number of modes may be excited are stressed. The numerical which often have significant dynamic interaction with the launch results of a study using a mathematical spacecraft model for vehicle, structural design and verification usually require a simulating test data from shaking table excitation are presented. combination of analysis, development testing, and qualification ESA testing. ESA N87-10912# Spar Aerospace Ltd., Ste-Anne-de-Bellevue (Quebec). DEMONSTRATION OF MODAL SYNTHESIS ON AN EXPERIMENTAL STRUCTURE AND ITS APPLICATION TO LARGE SPACECRAFT N87-10895# Deutsche Forschungs- und Versuchsanstalt fuer F. CHARRON, V. L. JHA, H. LAPIERRE, S. J. SOROCKY, and F. Luft- und Raumfahrt, Brunswick (West Germany). Inst. for Structural R. VIGNERON (Department of Communications, Ottawa, Ontario) Mechanics. ln ESA Proceedings of an International Conference on Spacecraft ANALYSIS OF LONG THIN-WALLED TUBES Structures p 185-190 Apr. 1986 B. GElER and A. K. RATH (Indian Space Research Organization, Avail: NTlS HC A19/MF A01 Trivandrum) In ESA Proceedings of an International Conference A substructural coupling method is demonstrated on an on Spacecraft Structures p 67-72 Apr. 1986 experimental structure. This method is used to compute the modal Avail: NTlS HC Al9/MF A01 parameters of the structure. The substructures are defined using Analysis of thin walled composite tubes for large space the modal parameters (natural frequencies, mode shapes and structures under buckling loads is discussed. Material law, nonlinear modal masses) measured from a modal survey or computed from theory of anisotropic shells, computation of fundamental states, a finite element model. Application of substructure coupling and computation of buckling loads are considered. ESA methods to large spacecraft is described. Results show

20 04 STRUCTURAL AND THERMAL ANALYSIS

inaccuracies (error in the natural frequency computation, inability N87-10928# Royal Netherlands Aircraft Factories Fokker, to compute some modes) for the system results. ESA Amsterdam. Space Div. ENGINEERING AND SOFTWARE INTERFACING FOR THERMAL, STRUCTURAL AND ATTITUDE CONTROL RELATED WITH SPACECRAFT J. J. WIJKER, H. GEYSELAERS, and A. C. M. VANSWIETEN ln ESA Proceedings of an International Conference on Spacecraft N87-10917# Ern0 Raumfahrttechnik G.m.b.H., Bremen (West Structures p 305-313 Apr. 1986 Germany). (Contract ESTEC-5158/82-NL-PB(SC)) INITIAL RESULTS FROM MULTIAXES TRANSIENT TESTING Avail: NTlS HC Al9/MF A01 K. ECKHARDT ln ESA Proceedings of an International Conference The engineering and software interfaces between the finite on Spacecraft Structures p 233-239 Apr. 1986 element package ASKA, the dynamic and control analysis package Avail: NTlS HC Al9/MF A01 DCAP, and the thermal analysis program SINDA are presented. The qualification testing of spacecraft structures is considered The engineering background of interface programs IFDCAP and and a methodology in which the various verification steps merge SINAS is discussed. ESA to a series of closely coordinated experimental and analytical activities is proposed. The concept means introducing multiaxes transient testing using hydraulic vibration systems for earthquake N87-11832# British Aerospace Public Ltd. Co., Bristol (England). simulation to replace conventional single-axes sine testing on Space and Communications Div. electrodynamic shakers. The idea is to cope with large flexible A STUDY OF LARGE SPACE STRUCTURES spacecraft structures and to realize a more realistic simulation of N. FOSTER 5 Jul. 1982 45 p loads by imposing transient base excitation with up to six degrees (LR46869; ETN-86-97949) Avail: NTlS HC A03/MF A01 of freedom simultaneously in order to achieve the correct load The structural design requirements for a large 'space structure vector (phase information). It is demonstrated that the required are identified. The preferred structural model is the tetrahedral environment can be simulated with sufficient accuracy. Results of truss, capable of being deployed automatically or constructed using the comparison of detailed test responses with applicable the Shuttle remote manipulator system. Preliminary analysis was responses measured in a shaker test using only axial transient performed to show how such a structure could be modelled to input are presented. ESA determine the structural characteristics. Aspects for investigation of the structural modelling are identified, including joint stiffness, thermal stability, manufacturing tolerances, deployment dynamics and dynamic interaction. ESA

N87-11966*# National Aeronautics and Space Administration. N87-10924# Saab-Scania, Linkoping (Sweden). Langley Research Center, Hampton, Va. TELE-X ANTENNA MODULE STRUCTURE QUALIFICATION THERMAL ANALYSIS OF RADIOMETER CONTAINERS FOR PROGRAM THE 122M HOOP COLUMN ANTENNA CONCEPT T. ANDERSSON ln ESA Proceedings of an International L. A. DILLON-TOWNES Sep. 1986 54 p Conference on Spacecraft Structures p 283-288 Apr. 1986 (NASA-TM-89026; NAS 1.1 589026) Avail: NTlS HC A04/MF Avail: NTlS HC A19/MF A01 A01 CSCL20D The qualification program for the TELE-X Spacecraft Antenna A thermal analysis was conducted for the 122 Meter Hoop Module Structure is presented. The CFRP structure is adapted to Column Antenna (HCA) Radiometer electronic package containers. a Cassegrain system with extreme thermal stability requirements. The HCA radiometer containers were modeled using the computer Requirements constraining the design and the qualification program aided graphics program, ANVIL 4000, and thermally simulated using to verify the structure ability to meet these requirements are two thermal programs, TRASYS and MITAS. The results of the described. Analysis models used and experience from test analysis provided relationships between the absorptance-emittance predictions and model correlations are presented. ESA ratio and the average surface temperature of the orbiting radiometer containers. These relationships can be used to specify the surface properties, absorptance and reflectance, of the radiometer containers. This is an initial effort in determining the passive thermal protection needs for the 122 m HCA radiometer containers. Several recommendations are provided which expand this effort so specific N87-10926# Jet Propulsion Lab., California Inst. of Tech., passive and active thermal protection systems can be defined Pasadena. and designed. Author LOADS ANALYSIS FOR THE GALILEO SPACECRAFT M. TRUBERT ln ESA Proceedings of an International Conference on Spacecraft Structures p 293-298 Apr. 1986 N87-12596# lnstituto de Pesquisas Espaciais, Sao Jose dos Avail: NTlS HC A19/MF A01 Campos (Brazil). The loads analysis for the design of the Galileo structure was COMPARISON OF METHODS FOR THE CALCULATION OF done by combining the transient analysis method with methods THERMAL CONTACT RESISTANCE OF THE FIRST BRAZILIAN aimed at reducing cost and schedule impact while increasing SATELLITE M.S. Thesis, 6 Dec. 1985 [COMPARACAO DE confidence in the estimation of the loads. The preliminary sizing METODOS PARA 0 CALCULO DA RESISTENCIA TERMICA DE was done by the mass acceleration curve. The loads iterations CONTATOS DO PRlMElRO SATELITE BRASILEIRO] were done by the generalized shock spectra method. Only a few M. B. H. MANTELLI Apr. 1986 105 p In PORTUGUESE; critical subsystems required a coupled transient analysis to show ENGLISH summary positive margins. Dynamic coupling between the launch vehicle (INPE-3864-TDLI217) Avail: NTlS HC AO6/MF A01 and the spacecraft was done by analytically removing and adding A comparative study of the methods developed for the a spacecraft to a given launch vehicle at the modal level, without calculation of thermal contact resistance between two surfaces re-solving the eigenvalue problem. The modal response resulting submitted to a perpendicular heat flux is presented. Several factors from the dynamic coupling between the launch vehicle and the affecting this resistance are analyzed and a brief historical review spacecraft was used only for the 28 Galileo modes below 40 Hz. of the works in this field is made, spotting the methods of interest In the absence of definition of the Shuttle/Centaur model and the for spacial applications. These are compared to experimental data forcing functions above 40 Hz, the mass acceleration curve was so as to establish the most proper method for the couplings of , used to generate modal bounds between 40 and 80 Hz. ESA the first Brazilian satellite. Author

21 04 STRUCTURAL AND THERMAL ANALYSIS

N87-13484# Engineering System International, Rungis (France). N87-16937# Societe Nationale lndustrielle Aerospatiale, Les APPLICATION OF DYNAMIC ELEMENTS AND CONTINUUM Mureaux (France). Div. des Systems Balistiques et Spatiaux. METHODS TO LARGE SPACE STRUCTURES, VOLUME 1 Final STRUCTURAL ANALYSIS, MANUFACTURING AND Report DEVELOPMENT STATUS OF LARGE POLARIZATION A. BOSSAVIT, J. CLINCKEMAILLIE, E. HAUG, J. DUBOIS, SENSITIVE DUAL-GRIDDED REFLECTORS DOWLATYARI, and Y. OUALI Paris, France ESA Dec. 1985 J. D. LEFEBVRE ln ESA Proceedings of the Second ESA 214 p Workshop on Mechanical Technology for Antennas p 11 1-121 (Contract ESTEC-5209/82-NL-PB(SC)) Aug. 1986 (ED/82-362/RD-VOL-1; ESA-CR(P)-2217-VOL-l; ETN-86-98150) Avail: NTlS HC A12/MF A01 Avail: Issuing Activity The design of a 2.5 m diameter dual-gridded reflector assembly Methods for the analysis of complex and large structures are including the dynamic, static, thermal, and thermoelastic analyses reviewed. Classical numerical approaches are analyzed (Ritz is presented. The reflectors consist of two Kevlar sandwich shells, methods, weighted residuals, boundary integrals) and substitute each being fitted with a grid of copper wires, and stiffened on the continuum and reduction methods are considered. The continuum back by a system of Kevlar webs and struts. Mechanical and RF methods are evaluated for application to a large space truss. It is test results, performed on earlier developed reflector assemblies concluded that lower order continua (for example: equivalent finite (1.4 m and 1.8 m) demonstrate the validity of the design. ESA elements) form a sufficiently accurate basis for practical representations of large space trusses. Improved equivalent finite N87-16948# European Space Agency. European Space elements are identified and are recommended. ESA Research and Technology Center, ESTEC, Noordwijk (Netherlands). Mechanical Systems Div. ENGINEERING AND SOFTWARE INTERFACING FOR N87-15264# Texas A&M Univ., College Station. Mechanics THERMAL, STRUCTURAL AND DYNAMIC CONTROL RELATED and Materials Center. WITH SPACECRAFT ACTIVITIES A MODEL FOR PREDICTING THERMOMECHANICAL C. STAVRINIDIS, M. KLEIN, and J. WIJKER (Royal Netherlands RESPONSE OF LARGE SPACE STRUCTURES Final Technical Aircraft Factories Fokker, Schiphol-Oost) ln its Proceedings of Report, Apr. 1983 - May 1986 the Second ESA Workshop on Mechanical Technology for D. H. ALLEN and W. E. HAISLER Jul. 1986 286 p Antennas p 219-225 Aug. 1986 (Contract F49620-83-C-0067) (Contract ESTEC-5158/82-NL-PB(SC)) (AD-A172966; MM-4875-86-16; AFOSR-86-0884TR) Avail: NTlS Avail: NTlS HC A12/MF A01 HC A13/MF A01 CSCL 13M Engineering practices and information needed by the different A report on predictions of the thermomechanical response of spacecraft disciplines, and the possibilities of coupling thermal, large space structures contains the following: Summary of structural, and attitude control analysis programs are discussed. Completed Research, Literature Survey, Selection of Constitutive Implementation of identified and developed methods for specific Equations, Coupled Energy Balance Law, Space Structural interfaces is described. Engineering and software interfaces Response Algorithms, Model Results for Large Space Structures; between the finite element package ASKA and the dynamic control Publications List; A Prediction of Heat Generation in a analysis package DCAP, and between the thermal analysis program Thermoviscoplastic Uniaxial Bar, An Efficient and Accurate SINDA and the finite element package ASKA are presented. The Alternative to Subincrementation for Elastic Plastic Analysis by software for the corresponding interface programs are identified the Finite Element Method, Predicted Axial Temperature Gradient as IFDCAP and SINAS. ESA in A Viscoplastic Uniaxial Bar Due to Thermomechanical Coupling, Predicted Temperature Field in a Thermomechanically Heated N87-16949# Liege Univ. (Belgium). Viscoplastic Space Truss Structure, Effect of Degradation of THE EXTENDABLE REFRACTABLE MAST (ERM) THERMAL Material Properties on the Dynamic Response of Large Space ANALYSIS A HEAT RADIATION CASE STUDY VIA THE FINITE Structures, A Fractographic Study of Damage Mechanisms in ELEMENT METHOD Short-Fiber Metal Matrix Composites, Analytical and Numerical Solution of a Time Dependent Thermoviscoplastic Problem in M. HOGGE, J. P. COBUT, J. FAGNOUL, E. STENNE, and P. M. LEONARD ln ESA Proceedings of the Second ESA Workshop Mechanics, A Finite Element Model for the Thermoelastic Analysis on Mechanical Technology for Antennas p 227-235 Aug. 1986 of Large Composite Space Structures, and Predicted Dynamic Avail: NTlS HC A12/MF A01 Response of a Composite Beam with Load History Dependent A heat radiation finite element procedure was developed for and Spatially Variable Damage. GRA the thermal analysis of an extendable retractable mast (ERM) for space shuttle solar arrays and antennas. Thermal loading of the mast is mainly by radiation, and such heat inputs are barely treated N87-16021*# General Dynamics Corp., San Diego, Calif. Space in a comprehensive way in finite element computer programs: Systems Div. radiative heat exchanges are defined in terms of surfaces whereas DEPLOYABLE TRUSS STRUCTURE ADVANCED TECHNOLOGY finite element models deal with nodal unknowns located at the J. E. DYER and M. P. DUDECK ln NASA. Langley Research boundary of the radiant areas. A procedure which enables an Center NASA/DOD ControVStructures Interaction Technology, automatic translation of surface data into nodal inputs via 1986 p 111-124 NOV. 1986 specialized surface elements was developed and may be used Avail: NTlS HC A23/MF A01 CSCL 228 along with standard codes for angle factors determination. The The 5-meter technology antenna program demonstrated the effectiveness of the method is demonstrated on ERM thermal overall feasibility of integrating a mesh reflector surface with a models. ESA deployable truss structure to achieve a precision surface contour compatible with future, high-performance antenna requirements. N87-16952# Rome Univ. (Italy). Dipt. Aerospaziale. Specifically, the program demonstrated: the feasibility of fabricating THERMOMECHANICAL CHARACTERISTICS OF DICHROIC a precision, edge-mounted, deployable, tetrahedral truss structure; SUBREFLECTORS the feasibility of adjusting a truss-supported mesh reflector contour C. ARDUINI, R. BARBONI, A. CASTELLANI, U. PONZI, and S. to a surface error less than 10 mils rms; and good RF test SGUBlNl ln ESA Proceedings of the Second ESA Workshop on performance, which correlated well with analytical predictions. Mechanical Technology for Antennas p 255-260 Aug. 1986 Further analysis and testing (including flight testing) programs are Avail: NTlS HC A12/MF A01 needed to fully verify all the technology issues, including structural Temperature, stress, and deformation aspects of Kevlar dynamics, thermodynamics, control, and on-orbit RF performance, composite dichroic reflectors were studied. Criteria to guarantee which are associated with large, deployable, truss antenna that thermal displacements do not exceed any maximum value in structures. Author the direction normal to the middle surface were derived. The skin

22 05 STRUCTURAL DYNAMICS AND CONTROL

of the sandwich was checked for thermal buckling to find a criterion N87-19442# National Aerospace Lab., Amsterdam (Netherlands). for safe sizing. Different cases of Sun illumination and transient Space Div. conditions were analyzed to determine the maximum gradient inside SENSORS FOR A SYSTEM TO CONTROL THE LIQUID FLOW the structure. The structural analysis was carried out via finite INTO AN EVAPORATION COLD PLATE OF A TWO-PHASE elements. The type of finite element and the number of grid nodes HEATTRANSPORT SYSTEM FOR LARGE SPACECRAFT were a compromise between the modeling requirements and the A. A. M. DELIL 4 Jan. 1986 89 p large number of cases which result from the structural concepts, (Contract NIVR-1073) design requirements, heating conditions, type of constraints, and (NLR-TR-86001-U; 88679797; ETN-87-99281) Avail: NTlS HC materials properties. Thermostructural results are presented. A05/MF A01 ESA Two-phase flow sensors to control liquid flow rates in the Columbus space platform thermal busses were assessed. The hollow core coaxial capacitor concept looks very promising for N87-16956'# Smithsonian Astrophysical Observatory, Cambridge, annular flow and to a lesser extent also for homogeneous flow. Mass. Its disadvantage is the extra flow resistance introduced by the SYSTEM ENGINEERING STUDY OF ELECTRODYNAMIC gage. The axial capacitor gage is the simplest one. It adds no TETHER AS A SPACEBORNE GENERATOR AND RADIATOR flow resistance since the electrodes are arranged flush with the OF ELECTROMAGNETIC WAVES IN THE ULF/ELF FREQUENCY flow line wall. Its sensitivity for void fraction variations is better BAND Final Report than the corresponding sensitivity of the hollow core coaxial ROBERT D. ESTES Feb. 1987 117 p capacitor. A disadvantage is the inability to accurately and (Contract NAG8-551) sensitively measure in the case of nonannular flow patterns or (NASA-CR-180156; NAS 1.26:180156) Avail: NTlS HC AO6/MF low void fraction mixtures. Both disadvantages are not very severe. A01 CSCL20N Only in homogeneous flow, the sonic velocity concept offers an An electrodynamic tether deployed from a satellite in low-Earth alternative to the hollow core coaxial capacitor. The velocity of orbit can perform, if properly instrumented, as a partially sound concept is a little more sensitive for the temperature self-powered generator of electromagnetic waves in the ULFIELF fluctuations since the velocity of sound depends more strongly on band, potentially at power levels high enough to be of practical the temperature than the permittivity does. ESA use. Two basic problems are examined. The first is that of the level of wave power that the system can be expected to generate in the ULF/ELF radiation band. The second major question is whether an electrodynamic tethered satellite system for transmitting waves can be made partially self-powering so that power requirements for drag compensation can be met within economical STRUCTURAL DYNAMICS AND CONTROL constraints of mass, cost, and complexity. The theoretical developments and the system applications study are presented. Includes modeling, systems identification, attitude and control The basic design criteria, the drag-compensation method, the techniques and systems, surface accuracy measurement and effects on the propagation paths from orbit to Earth surface of control techniques and systems, sensors, and actuators. high-altitude nuclear debris patches, and the estimate of masses and sizes are covered. An outline of recommended analytical work, to be performed as a follow-on to the present study, is contained. A87-10901 B.G. VIBRATION DATA REDUCTION FOR DESIGN, ANALYSIS AND TESTING OF SPACECRAFT N87-17783*# National Aeronautics and Space Administration. P. S. NAIR, M. SAMBASIVA RAO (Indian Space Research Marshall Space Flight Center, Huntsville, Ala. Organization, Satellite Centre, Bangalore, India), and S. MARS LANDING MISSION: A STRUCTURAL APPROACH DURVASULA (Indian Institute of Science, Bangalore, India) IN: STAN FULLER ln its Manned Mars Mission. Working Group Finite elements in computational mechanics - FEICOM '85; Papers, V. 2, Sect. 5, App. p 733-744 May 1986 Proceedings of the International Conference, Bombay, India, Avail: NTlS HC A24/MF A01 CSCL 22A December 2-6, 1985. Volume 2 . Oxford, Pergamon Press, 1985, A Mars landing mission in 2000 presents a structural challenge. p. 677-688. refs Earlier studies have indicated that a Mars landing was then feasible Techniques for reducing the vibrational data produced by current using current structural techniques. Since these earlier studies, FEM programs for large spacecraft structures are developed technology advances were made to enhance the capability. Lighter analytically and demonstrated. It is shown that the dynamical and stronger materials, large structures programs, and behavior of a structure can be understood by deriving the modal supercomputers now exist and even greater advances are effective mass, the effective inertance or flexibility, and the energy expected. The feasibility of a Mars landing does not depend on distribution from the FEM data, processes involving relatively small the structure. If the space travelers can withstand the trip, the computational effort. Numerical results for two sample problems necessary structures can be provided to deliver them. If artificial (a simple cantilever beam and the APPLE spacecraft - mounted gravity is required the structure can also provide for it. The structural between Meteosat and CAT as in the Ariane composite payload challenge is to provide structural designs that are lightweight with stack) are presented in tables and graphs and briefly characterized. high reliability. In order to do this advanced technology must be The reduction techniques are shown to be quite effective in sorting utilized to the fullest on all structural elements. Author the FEM data for interpretation by the designer. T.K. A87-11159 N87-17826'# Virginia Polytechnic Inst. and State Univ., THE TIDAL VELOCITY FIELD IN THE LOCAL SUPERCLUSTER Blacksburg. Dept. of Engineering Science and Mechanics. P. B. LILJE (Cambridge University, England), A. YAHIL (Cambridge MODELING AND IDENTIFICATION OF SCOLE University, England; New York, State University, Stony Brook), and L. MElROVlTCH and M. A. NORRIS In NASA. Langley Research B. J. T. JONES (Nordisk lnstitut for Teoretisk Atomfysik, Center Proceedings of the 3rd Annual SCOLE Workshop p 109-120 Copenhagen, Denmark) Astrophysical Journal, Part 1 (ISSN Jan. 1987 0004-637X), vol. 307, Aug. 1, 1986, p. 91-96. SERC-supported Avail: NTlS HC A20/MF A01 CSCL 228 research. refs Vector differential equations for distributed structures; (Contract DE-AC02-80ER-10719) discretization (in space) of distributed structures; and parameter In addition to the usual Virgocentric infall velocities, a significant identification for the Spacecraft Control Laboratory Experiment quadrupolar tidal velocity field has been detected in the Local (SCOLE) are examined. B.G. Supercluster, due to the density structure outside it. This tidal

23 05 STRUCTURAL DYNAMICS AND CONTROL field is not caused by a single external structure, but the undergoes nonlinear rigid-body motion and linear elastic motion. Hydra-Centaurus supercluster appears to be a major contributor, Author since the eigenvector associated with the largest positive eigenvalue of the quadrupole points in its direction. At the distance A87-13394' Ohio State Univ., Columbus. of the Virgo Cluster the eigenvalues of the tidal field are about DECENTRALIZED CONTROL EXPERIMENTS ON NASAS 200 km/s, but the component in the direction of Virgo is only 46 FLEXIBLE GRID + or - 70. The determination of the cosmological density parameter U. OZGUNER, S. YURKOWICH, J. MARTIN, Ill, and F. AL-ABBASS from the Virgocentric infall is therefore little affected by the addition (Ohio State University, Columbus ) IN: 1986 American Control of the tidal field. The residual random ('thermal') velocity of the Conference, 5th, Seattle, WA, June 18-20, 1986, Proceedings. Local Group relative to its nearest neighbors is 72 + or - 37 Volume 2 . New York, Institute of Electrical and Electronics km/s, which is not statistically significant. Author Engineers, 1986, p. 1045-1051. Research supported by Ohio State University. refs A87-12139 (Contract NASA ORDER L-91188-8) STABILIZATION OF A CLASS OF HYBRID SYSTEMS ARISING Methods arising from the area of decentralized control are IN FLEXIBLE SPACECRAFT emerging for analysis and control synthesis for large flexible S. K. BISWAS (Ottawa, University, Canada) and N. U. AHMED structures. In this paper the control strategy involves a decentralized Journal of Optimization Theory and Applications (ISSN 0022-3239), model reference adaptive approach using a variable structure vol. 50, July 1986, p. 83-108. refs control. Local models are formulated based on desired damping (Contract NSERC-A-7109) and response time in a model-following scheme for various modal Consideration is given to the problem of rigorous modeling of configurations. Variable structure controllers are then designed flexible spacecraft and their stabilization. It is shown that the employing co-located angular rate and position feedback. In this dynamics of the flexible spacecraft can be described by a coupled scheme local control forces the system to move on a local sliding system of ordinary differential equations and partial differential mode in some local error space. An important feature of this equations (hybrid system). Liapunov's approach is used to prove approach is that the local subsystem is made insensitive to the stabilizability of the system. Simple feedback controls are dynamical interactions with other subsystems once the sliding suggested for stabilization of flexible spacecraft. Author surface is reached. Experiments based on the above have been performed for NASA's flexible grid experimental apparatus. The grid is designed to admit appreciable low-frequency structural A87-13317' National Aeronautics and Space Administration. dynamics, and allows for implementation of distributed computing Langley Research Center, Hampton, Va. components, inertial sensors, and actuation devices. A FAILURE-ACCOMMODATING CONTROL OF LARGE FLEXIBLE finite-element analysis of the grid provides the model for control SPACECRAFT system design and simulation; results of several simulations are S. M. JOSH1 (NASA, Langley Research Center, Hampton, VA) reported on here, and a discussion of application experiments on IN: 1986 American Control Conference, 5th, Seattle, WA, June the apparatus is presented. Author 18-20, 1986, Proceedings. Volume 1 . New York, Institute of Electrical and Electronics Engineers, 1986, p. 156-161. refs 8 A87-13395* Jet Propulsion Lab., California Inst. of Tech., This paper considers the problem of designing Pasadena. failure-accommodating controllers for large flexible spacecraft when DESIGN OF ROBUST FAILURE DETECTION FILTERS there are sector-type nonlinearities in the loops. It is proved that A. M. SAN MARTIN (California Institute of Technology, Jet an LQG-type controller can be made failure tolerant by inserting Propulsion Laboratory, Pasadena) and W. E. VANDER VELDE (MIT, appropriate gains in the actuator paths and state estimator residual Cambridge, MA) IN: 1986 American Control Conference, 5th, paths. For the state feedback case, when the actuators are saturating type, it is proved that there exists a finite region of Seattle, WA, June 18-20, 1986, Proceedings, Volume 2 . New York, Institute of Electrical and Electronics Engineers, 1986, p. attraction, which is invariant in the presence of these gains. Another class of controllers, which employs collocated sensors and 1052-1059. refs (Contract NAGl-126) actuators is presented, and is shown to have excellent An essential aspect of the design of control systems for large, failure-accommodation properties in addition to its robustness flexible spacecraft is fault tolerance. Because it is anticipated that properties. Author a large number of sensors and actuators will be required to realize good control over these assemblies, the detection and isolation A87-13392 of component failures cannot be based on direct comparisons A LABORATORY EXPERIMENT IN CONTROL/STRUCTURE among replicated components. Instead, the notion of 'analytic INTERACTION redundancy' must be employed for the FDI function. Unfortunately J. A. BOSS1 and J.-W. TSOU (Washington, University, Seattle) this makes the FDI function sensitive to modeling errors which IN: 1986 American Control Conference, 5th, Seattle, WA, June are certain to exist in the large space structure problem due to 16-20, 1986, Proceedings. Volume 2 . New York, Institute of model truncation and parameter uncertainty. This paper addresses Electrical and Electronics Engineers, 1986, p. 1034-1038. Research the robustness to model error of one method of FDI residual supported by Boeing Aerospace Co. generation - the failure detection filter. Initial designs were found A laboratory simulation having the characteristics of a flexible to be extremely sensitive to modeling error. The sources of this spacecraft (Le. multiple, coupled rigid-body and flexible modes) is sensitivity are analyzed and modifications to the design are described. Initial test results utilizing the simulator as a test bed suggested. The improved filter is shown to have much better for multivariable control law designs are presented. Author visibility of the failure signatures relative to the background due to modeling error. Author A87-13393 SLEW MANEUVER CONTROL OF THE SPACECRAFT CONTROL A87-13431' Illinois Univ., Urbana. LABORATORY EXPERIMENT (SCOLE) AUTOMATIC DECOUPLING OF FLEXIBLE SPACECRAFT Y. P. KAKAD (North Carolina, University, Charlotte) IN: 1986 SLEWING MANEUVERS American Control Conference, 5th, Seattle, WA, June 18-20, 1986, T. A. W. DWYER, 111 (Illinois, University, Urbana) IN: 1986 American Proceedings. Volume 2 . New York, Institute of Electrical and Control Conference, 5th, Seattle, WA, June 18-20, 1986, Electronics Engineers, 1986, p. 1039-1044. refs Proceedings. Volume 3 . New York, Institute of Electrical and In this paper, the dynamics and control of the NASA-Spacecraft Electronics Engineers, 1986, p. 1529-1534. refs Control Laboratory Experiment (SCOLE) test article slew maneuver (Contract NSF ECS-85-16445; NAG1-436) are developed. The slew maneuver is specified about any arbitrary The capability for large angle slewing maneuvers with very axis of the spacecraft, and it is considered that the spacecraft demanding pointing accuracy and tracking speed is increasingly

24 05 STRUCTURAL DYNAMICS AND CONTROL required for space-based systems. This is particularly the case for control law which tends to dampen each vibrational mode of the space-based directed energy beam pointing. A method is thus structure at the same desirable exponential rate. The unique proposed in this paper for commanding general pointing and aspects of this method are that the control law is not explicitly tracking maneuvers with automatic correction for slew-excited dependent on the structural stiffness, the control forces are directly structural deformations. All existing rigid body multiaxial slewing proportional to the distribution of the structural mass, and the algorithms and flexible body vibration damping algorithms can then control law is natural and decentralized. The control law was applied be used simultaneously, without design iterations. In particular, an to a flexible planar truss structure and the various aspects of example is given of a retargeting maneuver with specified implementation of the control law examined are: actuator/sensor line-of-sight settling time and no torque saturation. Author number, placement, and the impact of the actuator/sensor number and placement on the necessary control 'power' requirements such A87-13433' Vigyan Research Associates, Inc., Hampton, Va. as peak power loads, total power requirements, etc. Also examined NONLINEAR AlTITUDE CONTROL OF ELASTIC SPACECRAFT- are the effects of using a limited number of active members in ANTENNA SYSTEM terms of the vibrational performance when compared with the S. N. SlNGH (Vigyan Research Associates, Inc., Hampton, VA) 'ideal' distributed control law. Author IN: 1986 American Control Conference, 5th. Seattle, WA, June 18-20, 1986, Proceedings. Volume 3 . New York, Institute of A87-13494' Colorado State Univ., Fort Collins. Electrical and Electronics Engineers, 1986, p. 1539-1544. refs NONLINEAR INTERFACES FOR ACCELERATION-COMMANDED (Contract NASI-17919) CONTROL OF SPACECRAFT AND MANIPULATORS An approach to large angle rotational maneuvers of a T. A. W. DWYER, 111, G. K. F. LEE, and N. CHEN (Colorado State spacecraft-beam-tip body (an antenna or a reflector) configuration University, Fort Collins) IN: Applied numerical modeling . San based on nonlinear invertibility and linear feedback stabilization is Diego, CA, Univelt, Inc., 1986, p. 517-522. refs presented. A control law u sub d is derived to obtain independent (Contract NSF ECS-83-04968; NAG 1-436; F49620-83-K-0032) decoupled control of attitude angles, lateral elastic deflections, Nominal command generation in real time for the control of slopes due to bending and angular deflection due to torsion at manipulators or of maneuvering spacecraft is hampered by the the tip of the beam using torquers and force actuators. For the nonlinearity of the equations of motion. Likewise the real time stabilization of the elastic oscillations, a linear feedback control tracking of a computed nominal trajectory in the presence of law, u sub s, is obtained based on a linearized model about the disturbances requires the computation of time-varying Jacobians terminal state augmented with a servo-compensator. Simulation of the motion. An alternative approach is the formulation of results obtained for single axis control, for simplicity, show that acceleration-commanded control laws in appropriately chosen large slewing and elastic mode stabilization can be accomplished generalized advantageous to design dedicated circuit interfaces in spite of uncertainty in the system using the total control u = u to perform the required transformation. It is also possible to sub d + u sub s. Author guarantee that actuator and sensor saturation limits are not exceeded, by means of feedback-biased circuits that implement A87-13437 automatic overload limitation of acceleration commands. Recent POINTING, CONTROL, AND STABILIZATION OF SOLAR developments following this 'hardware computation' point of view DYNAMIC SYSTEM ON A SPACE STATION will be discussed. Author E. T. FALANGAS and H. H. WOO (Rockwell International Corp., Space Station Systems Div., Downey, CA) IN: 1986 American A87-14074'# Howard Univ., Washington, D. C. Control Conference, 5th, Seattle, WA, June 18-20, 1986, THE DYNAMICS AND CONTROL OF A SPACE PLATFORM Proceedings. Volume 3 . New York, Institute of Electrical and CONNECTED TO A TETHERED SUBSATELLITE Electronics Engineers, 1986, p. 1563-1571. R. FAN (Howard University, Washington, DC; Beijing Institute of This paper presents the design and analysis of a drive system Control Engineering, People's Republic of China) and P. M. to soft couple the solar dynamic (SD) power systems from BAINUM (Howard University, Washington, DC) NASA, AIAA, and interaction with the structure of a single keel Space Station. The PSN, International Conference on Tethers in Space, Arlington, VA, drive system features a low bandwidth controller that attenuates Sept. 17-19, 1986, Paper. 19 p. Research supported by the Ministry the dominant transverse boom torsional mode. The objective is to of Astronautics of the People's Republic of China, Howard present some preliminary results. The pointing of the massive SD University, and NASA. refs system is sensitive to induced disturbance forces. Minimizing the A mathematical model of the open and closed loop dynamics effects of these disturbances on SD pointing is essential in of a space tethered-platform-subsatellite system (TPS) is achieving desired pointing accuracy. An integral loop is included developed. The IPS consists of a rigid platform from which an to attenuate low frequency disturbances. Beside the integration of (assumed massless) tether is deploying a subsatellite from an the two controllers, the viable concept presented in this paper attachment point which is offset from the mass center of the utilizes sun sensors mounted outboard of the alpha joint on the platform. Control is provided by modulation of the tension level in left and right transverse booms. Tracking error is minimized by the tether and by momentum-type platform-mounted devices. using the pointing error from the sun in the control logic for alpha Control-law gains are obtained based on linear quadratic regulator drive slewing. The system is capable of achieving good stability techniques. Typical transient responses are presented. Author robustness, performance, and acceptable disturbance rejection. Author AW-14941 ELF GENERATION IN THE LOWER IONOSPHERE VIA A87-13458' National Aeronautics and Space Administration. COLLISIONAL PARAMETRIC DECAY Langley Research Center, Hampton, Va. K. KO, C. R. MENYUK (Science Applications International Corp., VIBRATION SUPPRESSION OF PLANAR TRUSS STRUCTURES McLean, VA), A. REIMAN (Princeton University, NJ), V. TRIPATHI UTILIZING UNIFORM DAMPING CONTROL (Indian Institute of Technology, New Delhi, India), P. PALMADESSO G. C. ANDERSEN (NASA, Langley Research Center, Hampton, (U.S. Navy, Naval Research Laboratory, Washington, DC) et al. VA) and L. M. SILVERBERG (North Carolina State University, Journal of Geophysical Research (ISSN 0148-0227). vol. 91, Sept. Raleigh) IN: 1986 American Control Conference, 5th, Seattle, 1, 1986, p. 10097-101 07. refs WA, June 18-20, 1986, Proceedings. Volume 3 . New York, Institute (Contract NO0014-82-M-0133) of Electrical and Electronics Engineers, 1986, p. 2040-2047. Generation of ELF waves by stimulated parametric coupling of refs two HF waves in the lower ionosphere is considered. In this region A variety of methods has been devised for vibrational control the nonlinear force is dominated by the thermal rather than the of a structure using both passive and active controls. Presented ponderomotive nonlinearity. It is shown that this results in lowering in this paper is a relatively new method for vibration suppression, the pump threshold for complete decay by more than an order of uniform damping control. This method consists of implementing a magnitude while achieving efficiencies in excess of those expected

25 05 STRUCTURAL DYNAMICS AND CONTROL on the basis of the Manley-Rowe relations. The lower-frequency application is illustrated by structural modification of a nominal mode excited for E region altitudes is the helicon mode, which model with different constraints on the closed loop eigenvalues. continues to frequencies below the ion cyclotron frequency because O.C. ion-neutral collisions freeze the ion motion. The application of these results to ELF generation in the lower ionosphere, including power estimates for a proof of principle experiment, is discussed. A87-15957# Author DYNAMICS FORMULATION AND SIMULATION OF MULTI-BODY SPACESTRUCTURES Y. OHKAMI, 0. OKAMOTO, T. KIDA, I. YAMAGUCHI, and K. A87-15450 MATSUMOTO (National Aerospace Laboratory, Chofu, Japan) FLEXIBILITY CONTROL OF SOLAR ARRAYS BASED ON STATE IAF, International Astronautical Congress, 37th, Innsbruck, Austria, ESTIMATION BY KALMAN FILTERING Oct. 4-1 1, 1986. 8 p. refs T. FUKUDA, Y. KURIBAYASHI, H. HOSOKAI (Tokyo Science (IAF PAPER 86-238) University, Japan), and N. YAJIMA (Ministry of International Trade A matrix approach to dynamics formulation and simulation of and Industry, Mechanical Engineering Laboratory, Sakura, Japan) complex space structures is outlined. This approach can treat IN: Theoretical and applied mechanics. Volume 34 - Proceedings spacecraft dynamics consisting of an arbitrary number of rigid of the Thirty-fourth Japan National Congress for Applied Mechanics, bodies connected by an arbitrary number of hinges in a complex Tokyo, Japan, December 11, 12, 1984 , Tokyo/New York, University system configuration. The constraints on the hinges connecting of Tokyo Press/Columbia University Press, 1986, p. 405-41 1. these bodies can be free, kinetic, kinematic, or any combination refs The problem dealt with here is how to estimate and control of these. The characteristic features of this method make it the vibrational modes of flexible booms of solar arrays even in compatible with a general-purpose computer program system. C.D. large angle attitude maneuvers. The boom is controlled as a distributed parameter system, the dynamics of which is developed in the manner of the unconstrained mode. Differential solar cell A87-15963'# Howard Univ., Washington, D. C. sensors are used to measure vibrations of the boom, but the SYNTHESIS OF CONTROL LAWS FOR OPTIMALLY DESIGNED sensor outputs are contaminated by noises. Therefore, the Kalman LARGE SPACE STRUCTURES filtering method is employed to estimate states based on the K. SATYANARAYANA and P. M. BAINUM (Howard University, dynamics in the above. Then all estimated states are fed back to Washington, DC) IAF, International Astronautical Congress, 37th, control the whole system, and an optimal control strategy is Innsbruck, Austria, Oct. 4-1 1, 1986. 9 p. Research supported by employed so that the control performance can be improved. Howard University and NASA. refs Author (IAF PAPER 86-246) In this study, the vibration control of large space structures A87-15931'# Massachusetts Inst. of Tech., Cambridge. using the linear quadratic regulator technique is investigated. A PROCEDURE FOR CALCULATING THE DAMPING IN Emphasis is made on the control of both optimally designed MULTI-ELEMENT SPACE STRUCTURES structures and also the original (uniform) structures using the E. F. CRAWLEY and K. J. ODONNELL (MIT, Cambridge, MA) cantilever beam as an example. The open loop and closed loop IAF, International Astronautical Congress, 37th, Innsbruck, Austria, eigenvalues are compared and the transient responses are Oct. 4-1 1, 1986. 10 p. refs obtained to determine the effectiveness of the control system (Contract NAGW-21) design. Author (IAF PAPER 86-203) A procedure for analyzing the damping in a multielement space structure connected by joints is described, in which distributed A87-16187' National Aeronautics and Space Administration. material damping and discrete nonlinear joint properties are Langley Research Center, Hampton, Va. incorporated into a linear analysis. The procedure involves four ON-ORBIT SYSTEMS IDENTIFICATION OF FLEXIBLE steps: (1) creation of a linear undamped finite element model; (2) SPACECRAFT experimental measurements of the transient response of a truss L. W. TAYLOR, JR. (NASA, Langley Research Center, Hampton, member in free fall tests to obtain material damping properties; VA) IN: Identification and system parameter estimation 1985; with these properties incorporated into a linear damped finite Proceedings of the Seventh Symposium, York, England, July 3-7, element model of the structure; (3) the identification of the nonlinear 1985. Volume 1 . Oxford and New York, Pergamon Press, 1985, joint properties using the force-state mapping technique; and (4) p. 511-516. refs linearization of the identified nonlinear components, which are then The process of on-orbit systems identification of flexible incorporated into the linear damped model to create the linearized spacecraft is examined in terms of the difficulties that are expected damped finite element model. I.S. because of the potentially unmanageable number of unknown model parameters due to the very high order system models A87-15932# involved. A Jordon block canonical form and global model IMPROVING THE ACTIVE VIBRATIONAL CONTROL OF LARGE parameters are used to reduce the number of unknown parameters SPACE STRUCTURES THROUGH STRUCTURAL MODIFICA- to manageable numbers. A Bayesian approach is discussed which TIONS enables the merging of theoretical models with ground or on-orbit F. E. EASTEP (Dayton, University, OH), N. S. KHOT (USAF, Wright test results by using Unconditional Maximum Likelihood Parameter Aeronautical Laboratories, Wright Patterson AFB, OH), and R. V. Estimation. A Modified Newton-Raphson technique is proposed GRANDHI (Wright State University, Dayton, OH) IAF, International for determining the model parameter estimates and an expected Astronautical Congress, 37th, Innsbruck, Austria, Oct. 4-1 1, 1986. fit error criterion is recommended for the determination of the 9 p. refs model structure and order reduction. Author (IAF PAPER 86-204) Structural and control system design methods for large space structures are presently integrated in order to reduce structural A87-17760# response to the disturbances encountered. The design scheme MODELING AND SIMULATION OF SPACECRAFT SOLAR formulation is obtained by means of the structural modification of ARRAY DEPLOYMENT a nominal finite element model that is optimally controlled by a B. WIE, N. FURUMOTO, A. K. BANERJEE, and P. M. BARBA linear regulator, in order to increase the active modal damping (Ford Aerospace and Communications Corp., Palo Alto, CA) factor beyond that of the nominal structure. Because an optimal Journal of Guidance, Control, and Dynamics (ISSN 0731-5090), active control method is employed, the sensitivity of the Riccati vol. 9, Sept.-Oct. 1986, p. 593-598. Previously cited in issue 23, matrix to structural modifications is obtained. The algorithm's p. 3428, Accession no. A86-47923. refs

26 05 STRUCTURAL DYNAMICS AND CONTROL

A87-17761’# National Aeronautics and Space Administration. A87-18323 Langley Research Center, Hampton, Va. LOCAL OUTPUT-FEEDBACK CONTROL FOR LARGE FLEXIBLE A SLEWING CONTROL EXPERIMENT FOR FLEXIBLE SPACESTRUCTURES STRUCTURES T. KIDA, I. YAMAGUCHI, and Y. OHKAMI (National Aerospace J.-N. JUANG, L. G. HORTA (NASA, Langley Research Center, Laboratory, Chofu, Japan) IN: International Symposium on Space Hampton, VA), and H. H. ROBERTSHAW (Virginia Polytechnic Technology and Science, 14th, Tokyo, Japan, May 27-June 1, Institute and State University, Blacksburg) (Dynamics and control 1984, Proceedings . Tokyo, AGNE Publishing, Inc., 1984, p. of large structures; Proceedings of the Fifth Symposium, 969-974. refs Blacksburg, VA, June 12-14, 1985, p. 547-570) Journal of Guidance, This paper discusses the possibility of applying decentralized Control, and Dynamics (ISSN 0731-5090), vol. 9, Sept.-Oct. 1986, local control techniques to the LSS attitudelshape control p. 599-607. Previously cited in issue 18, p. 2614, Accession no. problems. The proposed controller is implemented by feeding back A86-39509. refs only the local outputs and their feedback gains are designed based on the decomposed small-size subsystems. The preliminary results A87-18241 obtained are both on its stability properties and the estimation of A BASIC STUDY FOR DIVIDED MODAL SURVEY OF FUTURE its convergence speeds. A simple numerical example is introduced LARGESPACECRAFT to illustrate the design procedures and the obtained results. H. MITSUMA (National Space Development Agency of Japan, Author Tsukuba Space Center, Sakura), K. SHlRAKl (National Space Development Agency of Japan, Tokyo), F. KUWAO, T. TAKAHASHI, A87-18324 S. SEKIMOTO (Toshiba Corp., Kawasaki, Japan) et al. IN: DYNAMICS OF THE ORBITER BASED FLEXIBLE MEMBERS International Symposium on Space Technology and Science, 14th, V. J. MODI (British Columbia, University, Vancouver, Canada) and Tokyo, Japan, May 27-June 1, 1984, Proceedings . Tokyo, AGNE A. M. IBRAHIM IN: International Symposium on Space Technology Publishing, Inc., 1984, p. 351-355. refs and Science, 14th. Tokyo, Japan, May 27-June 1, 1984, A modal-survey procedure for use in the dynamic design of Proceedings . Tokyo, AGNE Publishing, Inc., 1984, p. 975-984. large spacecraft is described and demonstrated. The large refs spacecraft is divided into a number of modules; the modules are (Contract NSERC-A-2181; NSERC-G-0662) subjected to single-point-excitation tests; and the results are The paper studies libration/vibration interaction dynamics combined using SABBA, a coupling-analysis software package. associated with the proposed NASAlLockheed Solar Array Flight The validity of the approach is confirmed in computations on several Experiment. Results suggest substantial influence of the inertia spacecraft configurations. T.K. parameter, flexural rigidity of the appendages, orbit eccentricity, deployment velocity, initial conditions, etc. on the system response. This would indicate additional demand on the orbiter’s control A87-18320 system during construction of space-platforms. Author ATTITUDE CONTROL EXPERIMENT FOR FLEXIBLE SPACECRAFT A87-18490 K. YAMADA, T. KASHIWASE, M. INOUE, and K. TSUCHIYA LARGE-ANGLE SLEWING OF FLEXIBLE SPACECRAFT (Mitsubishi Electric Corp., Central Research Laboratory, Amagasaki, H. SOGA, K. HIRAKO (Toshiba Corp., Kawasaki, Japan), Y. Japan) IN: International Symposium on Space Technology and OHKAMI, T. KIDA, and I. YAMAGUCHI (National Aerospace Science, 14th, Tokyo, Japan, May 27-June 1, 1984, Proceedings . Laboratory, Chofu, Japan) IN: Space exploitation and utilization; Tokyo, AGNE Publishing, Inc., 1986, p. 951-956. Proceedings of the Symposium, Honolulu, HI, December 15-19, An attitude control problem for a flexible spacecraft with 1985 . San Diego, CA, Univelt, Inc., 1986, p. 617-630. noncolocated sensor and actuator is considered. The plant (AAS PAPER 85-674) dynamics has become a nonminimum phase system, and both A sub-optimal slewing control method is proposed for dealing the classical control theory and the modern control theory are with the slewing maneuver problem of a flexible spacecraft. The applied to the controller design. Because the phase of the first rigid body mode is controlled by an open-loop optimal controller vibration mode is opposite to that of the rigid body mode, the of a design suitable for the optimal control approach such as the controller designed by the classical control theory becomes a maximum principle. The elastic bending modes are regulated to nonminimum phase system as a necessary consequence. The nominal undeformed states by the optimal LQ regulator. The control designed controllers are verified by physical experiments as well law is obtained easily and can be realized in an on-board controller. as numerical simulations and these results show the good The system is expected to be robust with regard to parameter performance of the controllers. Author errors and disturbances. Feasibility has been demonstrated through ground-based hardware experiments using a flexible spacecraft A87-18322 model mounted on a single-axis air-bearing table. D.H. NUMERICAL AND EXPERIMENTAL EVALUATION OF POLES AND SYSTEM ZEROS FOR LARGE FLEXIBLE SPACE A87-22364*# Flight Mechanics and Control, Inc., Hampton, Va. STRUCTURES DYNAMIC ANALYSIS OF SATELLITES WITH DEPLOYABLE Y. OHKAMI, 0. OKAMOTO, S. YOSHIMURA, T. KIDA, I. HINGED APPENDAGES YAMAGUCHI (National Aerospace Laboratory, Chofu, Japan) et KEVIN F. OAKES (Flight Mechanics and Control, Inc., Hampton, al. IN: International Symposium on Space Technology and VA) AIAA, Aerospace Sciences Meeting, 25th, Reno, NV, Jan. Science, 14th, Tokyo, Japan, May 27-June 1, 1984, Proceedings . 12-15, 1987. 13 p. Research sponsored by Old Dominion Tokyo, AGNE Publishing, Inc., 1984, p. 963-968. refs University. refs As a preliminary study on LSS attitude and figurelshape (Contract NGR-47-003-052) controller design, poles and zeros are evaluated numerically and (AIAA PAPER 87-0020) experimentally for a simple flexible space structure model. The The nonlinear equations of motion determining the planar model under consideration consists of a rigid primary body and a dynamical behavior of an orbiting satellite deploying both one and flexible appendage attached rigidly to the primary body, and a two rigid appendages have been formulated using Lagrange’s single-degree-of-freedom control moment gyro (CMG) on board equations. The analysis accounts for large angle rotations, Coriolis as an actuator. The transfer function of the system is derived effects, and the gravitational gradient, and the resulting coupled analytically, and open-loop responses are experimentally examined governing equations are integrated numerically. The analysis is under the impulsive disturbance to the appendage. The results of applied to the Space Shuttle based deployment of rigid truss-like the experiments show that the first vibration mode of the appendage members, and results show that spacecraft inertia parameters, and the interacted rotational motion of the primary body are damped appendage mass and length, deployment velocity, and initial in a short time. Author conditions all influence the system response. It is found that the

27 05 STRUCTURAL DYNAMICS AND CONTROL resulting librational movement is related to the size of the A87-23212# deployment payload, and that gravitational forces lead to vehicle ON THE DYNAMICS OF FLEXIBLE BEAMS UNDER LARGE stabilization. R.R. OVERALL MOTIONS - THE PLANE CASE. I, II J. C. SlMO (Stanford University, CA) and L. VU-OUOC (California, University, Berkeley) ASME, Transactions, Journal of Applied Mechanics (ISSN 0021-8936), vol. 53, Dec. 1986, p. 849-863. refs (Contract AF-AFOSR-83-0361) A87-22396# (ASME PAPER 86-WA/APM-41) VIBRATION CONTROL OF NONLINEAR FLEXIBLE A new approach to the dynamics of a plane beam under large STRUCTURES overall motions is presented which uses the fully nonlinear plane IRA R. ASTRACHAN and RICHARD J. FOURNIER AIAA, beam theory to account for finite rotations as well as finite strains. Aerospace Sciences Meeting, 25th, Reno, NV, Jan. 12-15, 1987. The expression of the inertial terms is obtained in the equations 7 p. NSF-supported research. of motions simply as mass times acceleration. The inherent (AIAA PAPER 87-0074) nonlinear character of the problem is transferred to the stiffness A simple yet effective method for controlling the undesired part of the equations of motion, resulting in equations of motion vibration of a nonlinear flexible structure is presented. The Control arising typically in nonlinear structural dynamics. It is shown that system will detect anomalous motion, calculate the necessary the dynamics of flexible beams under large overall motions can restoring force, and implement that restoring force at the optimum be analyzed in any existing nonlinear finite element program. time. The active vibration control system will keep the motion of Numerical examples that involve finite vibrations coupled with large the structure below a predetermined threshold during continuous overall motions and demonstrate the capability of the present excitation and significantly reduce the damping time required to formulation for handling multibody dynamics are presented. C.D. recover from single random disturbances. The effectiveness of the control strategy is demonstrated through actual testing on a structural model. Author A87-23213# FREE ROTATION OF AN ELASTIC ROD WITH AN END MASS C. Y. WANG (Michigan State University, East Lansing) ASME, Transactions, Journal of Applied Mechanics (ISSN 0021-8936), vol. 53, Dec. 1986, p. 864-868. This paper models a rotating space satellite with a long flexible A87-22462'# Cambridge Research Associates, Mass. antenna. Large deformations of the elastic rod are caused by the FREQUENCY-SHAPED LARGE-ANGLE MANEUVERS centrifugal forces. Bifurcation analysis shows the effect of end HON M. CHUN, JAMES D. TURNER (Cambridge Research mass on the critical rotation speeds above which sinuous Associates, MA), and JES-NAN JUANG (NASA, Langley Research equilibrium configurations occur. The nonlinear governing equations Center, Hampton, VA) AIAA, Aerospace Sciences Meeting, 25th, are then integrated numerically. A class of solutions with a looped Reno, NV, Jan. 12-15, 1987. 17 p. refs configuration is found whose existence requires a certain minimum (AIAA PAPER 87-01 74) total energy and minimum angular momentum. Catastrophic The paper considers the problem of maneuvering a flexible changes are possible. Author spacecraft through large angles in finite time. The basic control problem is divided into two parts. The first part consists of A87-23986# generating a frequency-shaped open-loop solution for the nonlinear WAVE-ABSORBING CONTROLLERS FOR A FLEXIBLE BEAM rigid body as the nominal solution. The resulting two-point A. H. VON FLOTOW and B. SCHAEFER (DFVLR, boundary-value problem is solved by introducing a continuation Oberpfaffenhofen, West Germany) (Guidance, Navigation and method for altering the mass distribution and boundary conditions Control Conference, Snowmass, CO, Aug. 19-21, 1985, Technical for the spacecraft. For the second part, a feedback control is Papers, p. 443-452) Journal of Guidance, Control, and Dynamics designed by linearizing the flexible body response about Several (ISSN 0731-5090), vol. 9, Nov.-Dec. 1986, p. 673-680. Previously points along the rigid body nominal solution. The perturbation gains cited in issue 22, p. 3238, Accession no. A85-45924. refs are designed by using a frequency-shaped cost functional approach. The gains are linearly interpolated to produce smooth A87-23989*# National Aeronautics and Space Administration. control time-histories as the linear piecewise constant plant models Langley Research Center, Hampton, Va. change during the maneuver. Author A SEQUENTIAL LINEAR OPTIMIZATION APPROACH FOR C3NTROLLER DESIGN LUCAS G. HORTA, JER-NAN JUANG (NASA, Langley Research Center, Hampton, VA), and JOHN L. JUNKINS (Texas A & M University, College Station) (Guidance, Navigation and Control A87-22831 Conference, Snowmass, CO, Aug. 19-21, 1985, Technical Papers, RESPONSE OF DISCRETIZED STRUCTURES WITH p. 725-731) Journal of Guidance, Control, and Dynamics (ISSN ELASTO-PLASTIC DEFORMATION TO NON-STATIONARY 0731 -5090), vol. 9, Nov.-Dec. 1986, p. 699-703. Previously cited RANDOM EXCITATION in issue 22, p. 3239, Accession no. A85-45953. refs C. W. S. TO (Calgary, University, Alberta, Canada) Journal of Sound and Vibration (ISSN 0022-4650), vol. 110, Nov. 8, 1986, p. A87-23995# 463-470. NSERC-supported research. refs EFFICIENT MODAL ANALYSIS OF DAMPED LARGE SPACE A formulation, within the framework of the finite element method, STRUCTURES for the analysis of the responses of symmetric and asymmetric TREVOR WILLIAMS (Kingston Polytechnic, Kingston-upon-Thames, nonlinear structures, involving elasto-plastic deformation, subjected England) Journal of Guidance, Control, and Dynamics (ISSN 0731- to nonstationary random excitation represented as a product of 5090), vol. 9, Nov.-Dec. 1986, p. 722-724. SERC-supported research. an arbitrary time modulating function and a stationary process, refs not necessarily white in nature, is proposed in this paper. A A novel eigenstructure perturbation technique that is valid for numerical strategy for implementing the proposed formulation is general feedback and minimizes numerical difficulties through the also included. Application of the method is made for the exclusive use of unitary transformations is presented. It is noted determination of the time-dependent variance of the response of that these complex matrices (or their real subclass, the orthogonal a quarter-scale physical model of a class of mast antenna matrices) are basic to nearly all numerically reliable algorithms structures. Computed results are included and discussed. Author developed in control theory. The method directly yields the order

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of error anticipated in its eigenvalue and eigenvector estimates. A87-25680# O.C. EXPERIMENTAL CHARACTERIZATION OF PASSIVELY DAMPED JOINTS FOR SPACE STRUCTURES JACKY PRUCZ (West Virginia University, Morgantown), A. D. REDDY, L. W. REHFIELD (Georgia Institute of Technology, Atlanta), and R. W. TRUDELL (McDonnell Douglas Astronautics Co., A87-24049' Vigyan Research Associates, Inc., Hampton, Va. Huntington Beach, CA) Journal of Spacecraft and Rockets (ISSN NONLINEAR ATTITUDE CONTROL OF FLEXIBLE SPACECRAFT 0022-4650), vol. 23, Nov.-Dec. 1986, p. 568-575. refs UNDER DISTURBANCE TORQUE (Contract F49620-83-C-0017) SAHJENDRA N. SINGH (Vigyan Research Associates, Inc., An innovative means to enhance the inherent damping in Hampton, VA) Acta Astronautica (ISSN 0094-5765), vol. 13, structures is provided by the designed-in incorporation of Aug. 1986, p. 507-514. refs viscoelastic materials in joints. The damping and stiffness properties (Contract NASl-17919) of such joints have been experimentally evaluated at room A control law for large-angle single-axis rotational maneuvers temperature and low frequencies on representative specimens. of a spacecraft-beam-tip body (an antenna or a reflector) The test data show that proper design configurations can yield configuration is presented. It is assumed that an unknown but significant damping benefits without unacceptable stiffness bounded disturbance torque is acting on the spacecraft. A model penalties. Three different test methods and a new data reduction reference adaptive torque control law is derived for the slewing of procedure have been utilized in the experimental program. Two of the space vehicle. This controller includes a dynamic system in the three methods are new. A simplified steady-state technique the feedback path and requires only attitude angle and rate of and a sine-pulse propagation approach have been developed and applied in this research. The results show relatively low data scatter the space vehicle for feedback. For damping out the elastic motion excited by the slewing maneuver, a stabilizer is designed assuming from repeated measurement sets, and there is good agreement among the different test methods. Author that a torquer and a force actuator are available at the tip body. The stabilizer uses only the flexible modes for the synthesis of the control law. Simulation results are presented to show that fast, large-angle rotational maneuvers can be performed using the adaptive controller and the stabilizer in spite of the presence of continuously acting unknown torque on the spacecraft. Author A87-27449 ON THE STABILITY OF MULTIPLE PARAMETER TIME-VARYING DYNAMIC SYSTEMS MEHDI AHMADIAN (Clemson University, SC) International Journal of Non-Linear Mechanics (ISSN 0020-7462), vol. 21, no. 6, 1986, A87-24552 p. 483-488. refs MODAL CONTROL OF TRAVELING WAVES IN FLEXIBLE A technique is presented for determining the stability of STRUCTURES lumped-parameter, time-varying, dynamic systems with aperiodic L. MElROVlTCH and J. K. BENNIGHOF (Virginia Polytechnic coefficients. An 'energy like' function is used to develop stability Institute and State University, Blacksburg) Journal of Sound and conditions which are direct in terms of the coefficient matrices. Vibration (ISSN 0022-460)0, vol. 111, Nov. 22, 1386, p. 131-144. The significance of what is presented here is twofold. First, it (Contract AF-AFOSR-83-0017) gives stability conditions applicable to systems which are not This paper is concerned with the control of a traveling wave in necessarily periodic. Second, it allows for a systematic a structure by the independent modal-space control method. It is categorization of the effects of the parameter changes on system demonstrated that the control forces tend to concentrate in the response and stability, in order to provide a better understanding immediate vicinity of the disturbance, and there are virtually no of the behavior of this class of dynamic systems as they arise in control forces acting at any point of the structure before the arrival various areas of engineering. Author of the disturbance. Two numerical examples are included, one for a string in transverse vibration and one for a beam in bending. Satisfactory control was achieved in spite of the fact that only a finite number of modes was retained for control. Author

A87-27948'# Virginia Polytechnic Inst. and State Univ., Blacksburg. EFFECT OF SENSOR AND ACTUATOR ERRORS ON STATIC A87-24902# SHAPECONTROLFOR LARGESPACESTRUCTURES DECENTRALIZED CONTROL OF MULTI-BODY SPACECRAFT - RAPHAEL T. HAFTKA (Virginia Polytechnic Institute and State A NUMERICAL EXPERIMENT University, Blacksburg) and HOWARD M. ADELMAN (NASA, R. G. MELTON (Pennsylvania State University, University Park) Langley Research Center, Hampton, VA) AIAA Journal (ISSN and M. A. THAMES (General Electric Co., Astro Space Div., Valley 0001-1452), vol. 25, Jan. 1987, p. 134-138. Previously announced Forge, PA) AIAA, Aerospace Sciences Meeting, 25th, Reno, NV, in STAR as N85-29998. refs Jan. 12-15, 1987. 9 p. refs An analytical study was performed to predict and assess the (AIAA PAPER 87-0018) effect of actuator and sensor errors on the performance of a This paper presents the results of numerical studies on the shape control procedure for flexible space structures using applied use of decentralized configuration control of spacecraft that can temperatures. Approximate formulas were derived for the expected be modelled as tree topologies of rigid bodies with non-rigid value and variance of the rms distortion ratio (ratio of rms distortions connections. The decentralized scheme consists of each body with and without corrections) based on the assumption of having an autonomous controller that uses state information of zero-mean normally distributed random errors in measured that body and the adjacent body that is closer to the tree root. It distortions and actuator output temperatures. Studies were carried is proposed that such a Control structure would have several out for a 55-meter radiometer antenna reflector distorted from its benefits of large modular Spacecraft. The results indicate good ideal parabolic shape by nonuniform orbital heating. The first study performance, even for simple position and rate feedback loops in consisted of varying the sensor and actuator errors for the case each body, leading to the suggestion that a rigorous stability of 12 actuators and computing the distortion ratio. In the second analysis be undertaken to demonstrate the applicability of this study, sensor and actuator errors were prescribed and the effect control to a wider variety of spacecraft configurations. Author of increasing the number of actuators was evaluated. Author I

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A87-28537 compared well with the polyreference approach, yielding results in MODAL SPACE DESIGN FOR ACTIVE VIBRATION CONTROL considerably less time with less user interaction. Author OF LARGE FLEXIBLE STRUCTURES HAGOP V. PANOSSIAN (HR Textron, Inc., Valencia, CA) IN: A87-28578 International Modal Analysis Conference, 4th, Los Angeles, CA, TRANSIENT MODAL TUNING Feb. 3-6, 1986, Proceedings. Volume 1 . Schenectady, NY, Union G. DUDLEY SHEPARD (Lowell, University, MA) IN: International College, 1986, p. 167-170. refs Modal Analysis Conference, 4th, Los Angeles, CA, Feb. 3-6, 1986, Modal space design and control for stochastic linear systems Proceedings. Volume 2 . Schenectady, NY, Union College, 1986, is considered herein. Uncertainties in the frequencies, damping p. 1482-1486. ratios, and mode shapes are assumed and the system dynamics Transient modal tuning for system identification in space is is formulated in a stochastic model. The theory of eigensystem considered, and the advantages of using the impulse response of assignment is then treated for the above mentioned model under a complex structural mode (where the damping properties of the complete controllability and observability assumptions. Moreover, system are not proportional to the mass or stiffness properties) direct output feedback control is achieved under minimum mean as an input to selectively enhance that mode is demonstrated. square error between the desired and actual eigensystems. Excitation transients are designed which will most efficiently Author concentrate energy in a selected bandwidth and yield a high percentage of the desired mode response relative to undesired A87-28544 modal responses. It is noted that because spatial tuning in space MODAL ANALYSIS TECHNIQUE USED IN GERMANY FOR is likely to be inefficient, transient modal tuning must largely rely AEROSPACE STRUCTURES on temporal tuning. R.R. N. NIEDBAL (DFVLR, lnstitut fuer Aeroelastik, Goettingen, West Germany) IN: International Modal Analysis Conference, 4th, Los A87-29368 Angeles, CA, Feb. 3-6, 1986, Proceedings. Volume 1 . Schenectady, THE DYNAMICAL QUALIFICATION OF PRESENT AND FUTURE NY, Union College, 1986, p. 378-385. refs SPACECRAFT STRUCTURES [DIE DYNAMISCHE QUALIFIKA- Modal-survey testing is an increasingly common part of the TlON HEUTIGER UND ZUKUENFTIGER RAUMFAHRTSTRUKTU- qualification procedure for aerospace structures, since it offers an REN] experimental verification of normal mode parameters determined AXEL BERTRAM, HORST HUENERS, and WERNER SACHS by dynamic finite-element analysis. Moreover, it permits (DFVLR, lnstitut fuer Aeroelastic, Goettingen, West Germany) identification of structural damping, knowledge of which is essential DFVLR-Nachrichten (ISSN 001 1-4901), Nov. 1986, p. 56-61. In for reliable flight-load calculations for space structures. A state of German. the art of modern modal-survey testing is given here, covering The dynamical design-verification procedures employed by the the phase-resonance method and various phase-separation DFVLR lnstitut fuer Aeroelastik for spacecraft development are methods. The use of modal-survey results in the dynamic discussed, with a focus on the performance and analysis of modal qualification of aerospace structures is discussed, emphasising the survey tests. The mobile static-vibration-test facility and the correlation of analytical and experimental modal data. This aspect modal-analysis programs for the Olympus platform, the Ariane-4 has attracted growing interest in recent years, due to the obvious payload shroud, and the ESA Simple and Complex Models need for convenient tools that allow finite-element models to be (hypothetical spacecraft designed to test the accuracy of updated with measured modal data. Author modal-synthesis techniques) are described and illustrated with drawings, diagrams, and photographs. In the latter tests, modal A87-28558 synthesis is found to be a very useful design tool, but one requiring IDENTIFICATION, APPLICATIONS, AND DYNAMIC ANALYSIS considerable experience on the part of the designer. The need OF NONLINEAR SPACECRAFT COMPONENTS for improved model-updating strategies and for new test concepts INGO KOLSCH and HORST BAlER (Dornier System GmbH, to simulate flight loads and analyze subassemblies is indicated. Friedrichshafen, West Germany) IN: International Modal Analysis T.K. Conference, 4th, Los Angeles, CA, Feb. 3-6, 1986, Proceedings. Volume 1 . Schenectady, NY, Union College, 1986, p. 720-729. A87-30294‘# Virginia Polytechnic Inst. and State Univ., refs Blacksburg. Techniques for the dynamical analysis of spacecraft structures AN ANALYTICAL AND EXPERIMENTAL STUDY OF A CONTROL with nonlinear components are discussed, considering both SYSTEM’S SENSITIVITY TO STRUCTURAL MODIFICATIONS undesirable nonlinearities (such as joint stiffness and bearing play) RAPHAEL T. HAFTKA, ZORAN N. MARTINOVIC, WILLIAM L. and designed nonlinearities (such as dampers and shock absorbers HALLAUER, JR., and GEORGE SCHAMEL (Virginia Polytechnic to isolate delicate equipment from launch or on-orbit accelerations). Institute and State University, Blacksburg) (Structures, Structural The sine-vibration testing, harmonic-balance analysis, and Dynamics, and Materials Conference, 26th, Orlando, FL, Apr. 15-17, Fourier-approximation analysis (to account for quasi-static 1985, Technical Papers. Part 2, p. 642-650) AlAA Journal (ISSN accelerations) of an actuator-bearing/solar-panelassembly for the 0001-1452), vol. 25, Feb. 1987, p. 310-315. Previously cited in TV-Sat/TDF-1 communication satellite are described and illustrated issue 13, p. 1855, Accession no. A85-30393. refs with graphs and diagrams. Good agreement between model (Contract NAG1-224) predictions and test measurements is demonstrated, and problems in determining the stiffness coefficients and evaluating the damping A87-30545 are indicated. T.K. A FOUR NODE MARGUERRE ELEMENT FOR NON-LINEAR SHELL ANALYSIS A87-28569 PHlLlPPE JETTEUR and FRANCOIS FREY (Lausanne, Ecole COMPUTATION OF TOTAL RESPONSE MODE SHAPES USING Polytechnique Federale, Switzerland) Engineering Computations TUNED FREQUENCY RESPONSE FUNCTIONS (ISSN 0264-4401), vol. 3, Dec. 1986, p. 276-282. refs RALPH BRILLHART and DAVID L. HUNT (SDRC, Inc., San Diego, (Contract SNSF-2,353,0,84) CA) IN: International Modal Analysis Conference, 4th. Los Angeles, A nonlinear shallow thin shell element is described. The element CA, Feb. 3-6, 1986, Proceedings. Volume 2 . Schenectady, NY, is a curved quadrilateral one with corner nodes only. At each Union College, 1986, p. 1228-1236. refs node, six degrees of freedom (i.e., three translations and three A new approach called Move Response on Trace allows rapid rotations) make the element easy to connect to space beams, computation of mode frequencies and shapes immediately following stiffeners or intersecting shells. The curvature is dealt with by data acquisition. The technique is applicable to multiple-input modal Marguerre’s theory. Membrane bending coupling is present at the tests in which frequency response functions are obtained. When element level and improves the element behavior, especially in this technique was applied to an aerospace structure, the results nonlinear analysis. The element converges to the deep shell

30 05 STRUCTURAL DYNAMICS AND CONTROL solution. The sixth degree of freedom is a true one, which can be N87-10891# Dornier-Werke G.m.b.H., Friedrichshafen (West assimilated to the in-plane rotation. The present paper describes Germany). how overstiffness due to membrane locking on the one hand and ON OPTIMAL PASSIVE AND ACTIVE CONTROL OF PRECISION to the sixth degree of freedom on the other hand can be corrected SPACECRAFTSTRUCTURES without making use of numerical adjusted factors. The behavior H. BAlER In ESA Proceedings of an International Conference of this new element is analyzed in linear and nonlinear static and on Spacecraft Structures p 35-39 Apr. 1986 dynamic tests. Author Avail: NTlS HC A19/MF A01 The application of structural optimization and control methods for precision spacecraft structures is discussed. The necessity of proper decomposition into subproblems is emphasized. The shape A87-31095*# National Aeronautics and Space Administration. adjustment and control of an antenna reflector is considered and Marshall Space Flight Center, Huntsville, Ala. results are presented. In the dynamic regime, active isolation is GROUND FACILITY FOR LARGE SPACE STRUCTURES applied for a sensitive payload and the benefit of such an approach DYNAMICS AND CONTROL VERIFICATION is outlined. For passive design purposes a control forces approach HENRY WAITES (NASA, Marshall Space Flight Center, Huntsville, which is numerically efficient but does not necessarily lead to an AL) International Test and Evaluation Association, Symposium, optimum is used. ESA Huntsville, AL, Sept. 30-Oct. 2, 1986, Paper. 20 p. NASA 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 N87-10896# Texas Univ., Austin. performance can be ensured. The facility consists of an LSS test A STUDY OF NODAL COUPLING METHODS article or payload which is connected to a 3-axis angular pointing R. R. CRAIG ln ESA Proceedings of an International Conference mount assembly that provides control torque commands. The on Spacecraft Structures p 75-80 Apr. 1986 angular pointing mount assembly is attached to a base excitation Avail: NTlS HC Al9/MF A01 system which will simulate disturbances most likely to occur for Component mode synthesis time-domain methods for Orbiter and DOD payloads. The control computer contains the undamped structures are introduced. Component normal modes calibration software, the reference systems, the alignment with fixed or free boundaries, constraint modes, and inertia-relief procedures, the telemetry software, and the control algorithms. attachment modes are described. An inertia attachment mode is The total system is suspended in such a fashion that the LSS defined. System eigensolutions based on various component mode test article has the characteristics common to all LSS. Author sets are compared. Work on the application of attachment modes to modal control of flexible structures is noted. ESA

N87-10138 lnstituto de Pesquisas Espaciais, Sao Jose dos Campos (Brazil). PARAMETER OPTIMIZATION AND ATTITUDE STABILIZATION N87-10897# Intespace, Toulouse (France). OF A FLEXIBLE SPACECRAFT EFFECTIVE MODAL PARAMETERS AND TRUNCATION D. C. CEBALLOS In CNES Proceedings of an International EFFECTS IN STRUCTURAL DYNAMICS [PARAMETRES Conference on Space Dynamics for Geostationary Satellites p MODAUX EFFECTIFS ET EFFETS DE TRONCATURE EN 405-412 1986 DYNAMIQUE DES STRUCTURES] Avail: CEPADUES-Editions, 111 rue Nicolas-Vauquelin, 31 100 A. GIRARD and J. F. IMBERT In ESA Proceedings of an Toulouse, France International Conference on Spacecraft Structures p 81-86 Apr. The synthesis and analysis of a control law for a flexible 1986 In FRENCH spacecraft are described. The control law is considered a simple Avail: NTlS HC Al9/MF A01 proportional, integral, and derivative law together with a second Modal superposition techniques used to calculate the low order structural filter. Parameter optimization is applied for finding frequency response of structures are discussed. A unified approach the controller parameters, to optimize behavior when applied to to the effective modal parameters method of interpreting the high order model. Frequency and Laplace domain analysis eigenmodes is outlined. These parameters obey summation rules which indicate the satisfactory behavior of the proposed controller to reconstruct the corresponding static properties, enabling are shown. ESA truncation effects to be estimated in terms of residual parameters representing the global contribution of higher modes. This reveals the role of flexibility, mass, transmissibility, and effective strains. ESA N87-10172*# Virginia Polytechnic Inst. and State Univ., Blacksburg. Dept. of Engineering Science and Mechancis. IDENTIFICATION AND CONTROL OF STRUCTURES IN SPACE Progress Report, 1 Jul. - 31 Dec. 1985 L. MElROVlTCH 1985 42 p N87-10898# Dornier-Werke G.m.b.H., Friedrichshafen (West (Contract NAG1-225) Germany). (NASA-CR-179811; NAS 1.26:179811) Avail: NTlS HC AOWMF DAMPING REPRESENTATION RELATED TO SPACECRAFT A01 CSCL22B STRUCTURAL DESIGN Work during the period July 1 - December 31, 1985, has E. HILBRANDT In ESA Proceedings of an International concentrated on the application of the equations derived in the Conference on Spacecraft Structures p 87-92 Apr. 1986 preceding period to the maneuvering and vibration suppression of Avail: NTlS HC AlS/MF A01 the Spacecraft Control Laboratory Experiment (SCOLE) model. Two Analysis methods for damping representation and damping different situations have been considered: (1) a space environment prediction and design measures to enhance damping properties and (2) a laboratory environment. This report covers the first case of space structures are reviewed. Isolation (filtering) absorption, and consists of a paper entitled Maneuvering and Vibration Control and discrete and continuous dampers (damping layers) are of Flexible Spacecraft, presented at the Workshop on Structural discussed. Test results on beam and plate structures are compared Dynamics and Control Interaction of Flexible Structures, Marshall to analytical models. It is shown that a design for damping concepts Space flight Center, Huntsville, AL, April 22 to 24, 1986. The in spacecraft structures may significantly reduce the response second case will be covered in the report for the next period. levels and thus have a beneficial effect on equipment design. Author ESA

31 05 STRUCTURAL DYNAMICS AND CONTROL

N87-10901# Rome Univ. (Italy). N87-10925# Messerschrnitt-Boelkow-BlohmG.m.b.H., Ottobrunn COMPUTATIONAL METHODS IN ELASTIC PERIODIC (West Germany). Space Group. STRUCTURES ANALYSES INFLUENCE OF FIBER ORIENTATION AND BOUNDARY F. GRAZlANl and S. SGUBINI ln ESA Proceedings of an CONDITIONS ON THE DYNAMIC BEHAVIOR OF A International Conference on Spacecraft Structures p 109-112 Apr. CY LlNDRlCALLY TELESCOPING SOLAR ARRAY (INTELSAT 1986 6) Avail: NTlS HC A19/MF A01 E. D. SACH, H. J. HUETTMANN, and E. FRITSCHE ln ESA A method for decomposing an eigenvalue problem of N-bays Proceedings of an International Conference on Spacecraft dimensions into N problems of 1-bay dimensions is indicated. The Structures p 289-292 Apr. 1986 results provide a contribution to obtain a recursive relationship in Avail: NTlS HC A19/MF A01 evaluating the eigenvalue equation and in computing the To meet the strong frequency requirements in stowed eigenvalues for axisymmetric and linear periodic structures. ESA configuration of the INTELSAT 6 solar array (2 central telescoping cylinders in sandwich design, the face sheets of which are made of aramid fiber fabric and carbon fiber fabric) analyses were performed to show the influence of fiber orientations, number of N87-10903# Footscray Inst. of Tech. (Australia). layers and stiffener rings and boundary conditions on the dynamic ON A SIMPLE VIBRATION CONTROL DESIGN FOR LARGE behavior. The investigations show that each reinforcement measure SPACE STRUCTURE MODELS WITH UNCERTAIN is effective only in a very limited range. To fulfill the frequency PARAMETERS requirement with a minimum structural mass, a combination of R. LICATA ln ESA Proceedings of an International Conference several reinforcements is necessary. ESA on Spacecraft Structures p 119-124 Apr. 1986 Avail: NTlS HC Al9/MF A01 The presence of unavoidable modeling errors and sizeable N87-10938# Societe Bertin et Cie, Plaisir (France). uncertainty in parameters of a reduced-order model of a large DYNAMICS OF FLEXIBLE MECHANISMS [DYNAMIQUE DE flexible space structure is addressed in relation to the controller MECANISMES FLEXIBLES] design problem. Due mainly to limitations placed by on-board G. GALLAY, F. GIRARD, and J. M. AUCLAIR ln ESA Proceedings computers (which cause on-line adaptive or self-tuning control of an International Conference on Spacecraft Structures p 381-386 schemes to become unrealizable on flexible spacecraft) a controller Apr. 1986 In FRENCH design solution in the form of a simple to implement time-invariant Avail: NTlS HC A19/MF A01 feedback, obtained by considering constant and with known A method for the automatic generation of the equations of statistics the uncertain model parameters, is presented. The motion of complex flexible mechanical systems such as large space proposed stochastic optimal control scheme, more insensitive to structures is presented. The equations are derived using the method parameter variation and spillover effects compared with that of virtual work of Kane (1901). The rigid body kinematics treatment obtained by deterministic approach, may be used in the design of uses relative coordinates. A model synthesis method is added to local or global controllers of a flexible spacecraft structure. ESA handle the problem of a deformable solid body. The method minimizes the number of equations, while being able to cope with complex topologies (closed chains). ESA

N87-10904# London Univ. (England). Queen Mary Coll. N87-10957# Groningen Rijksuniversiteit (Netherlands). Dept. of THE EFFECT OF THE NON-UNIFORM STRESS DISTRIBUTION Mathematics. IN THE BLANKETS OF SINGLE AND TWIN BOOM SOLAR LARGE FLEXIBLE SPACE STRUCTURES SOME SIMPLE ARRAY PANELS UPON THEIR MODAL CHARACTERISTICS MODELS J. R. WRIGHT ln ESA Proceedings of an International Conference J. BONTSEMA 1986 27 p on Spacecraft Structures p 125-130 Apr. 1986 (TW-269; 886661 69; ETN-86-98503) Avail: NTlS HC A03/MF Avail: NTlS HC A19/MF A01 A0 1 The modal behavior of deployed flexible solar arrays of the Simple models of large flexible space structures are used to single boom fold-out and twin boom roll-out types was studied study the effect of flexibility and damping. The models are a one with simple theoretical model configurations. The effect of the dimensional flexible beam (Euler-Bernouilli) and two flexible beams nonuniform stress distribution in the array blanket arising from connected through a central disk, where for simplicity it is assumed flexible end members was investigated for out-of-planelbending that the thickness of the disk in the direction of the beams is modes. It is found that the string-like modes important for control zero. Partial differential equations are derived for these structures are hardly affected so a uniform tension analysis is adequate. and it is proved that the equations are well posed. Equations for However, other modes needed for response behavior are affected, the eigenfrequencies and eigenmodes of the structures are given particularly for the single boom array where buckling can occur. It and the controls and observations are discussed. As an example is also found that bending stiffness in the blanket needs to be for finite dimensional control design the method of Curtain (1983) included to lead to a unique and complete set of array modes if is discussed. ESA uniform tension is assumed. ESA N87-11765*# Engineering Mechanics Association, Inc., Palo Verde, Calif. N87-10915# Old Dominion Univ., Norfolk, Va. Dept. of Mechanical COMPONENT TESTING FOR DYNAMIC MODEL Engineering and Mechanics. VERIFICATION A REVIEW OF TIME DOMAIN MODAL TEST METHODS AND T. K. HASSELMAN and J. D. CHROSTOWSKI ln NASA. Langley APPLICATIONS Research Center Recent Experiences in Multidisciplinary Analysis S. R. IBRAHIM ln ESA Proceedings of an International Conference and Optimization, Part 2 15 p 1984 on Spacecraft Structures p 205-21 1 Apr. 1986 Avail: NTlS HC A22/MF A01 CSCL 01A Avail: NTlS HC A1 9/MF A01 Dynamic model verification is the process whereby an analytical Time domain modal testing techniques based on direct use of model of a dynamic system is compared with experimental data, a structure’s free decay time response functions are reviewed. adjusted if necessary to bring it into agreement with the data, and They are economical and powerful tools for in-space, or in-orbit, then qualified for future use in predicting system response in a identification of space structures. Even though meritorious in different dynamic environment. These are various ways to conduct laboratory controlled modal tests, these techniques possess unique model verification. The approach taken here employs Bayesian and useful qualities when the only available responses are those statistical parameter estimation. Unlike curve fitting, whose obtained while the structure is in operation or use. Application to objective is to minimize the difference between some analytical solar array orbital dynamics is described. ESA function and a given quantity of test data (or curve), Bayesian

32 05 STRUCTURAL DYNAMICS AND CONTROL estimation attempts also to minimize the difference between the in each of the two size categories are provided. Suggestions for parameter values of that funciton (the model) and their initial CMG devices bases on these wheels are presented. ESA estimates, in a least squares sense. The objectives of dynamic model verification, therefore, are to produce a model which: (1) is N87-12802# Sandia National Labs., Albuquerque, N. Mex. in agreement with test data; (2) will assist in the interpretation of LI CORROSION RESISTANT GLASSES FOR HEADERS IN test data; (3) can be used to help verify a design; (4) will reliably AMBIENT TEMPERATURE LI BATTERIES Patent Application predict performance; and (5) in the case of space structures, will E. E. HELLSTROM, inventor (to DOE) and R. D. WATKINS, inventor facilitate dynamic control. Author (to DOE) 11 Oct. 1985 18 p (Contract DE-AC04-76DP-00789) (DE86-013754; US-PATENT-APPL-SN-786561) Avail: NTlS HC N87-11766*# Draper (Charles Stark) Lab., Inc., Cambridge, A02/MF A01 Mass. Glass compositions containing 10 to 50 mol% CaO, 10 to 50 DUAL STRUCTURAL-CONTROL OPTIMIZATION OF LARGE mol% AIO, 30 to 60 mol% SPACE STRUCTURES BO, and 0 to 30 mol% MgO are A. MESSAC and J. TURNER ln NASA. Langley Research Center provided. These compositions are capable of forming a stable glass-to-metal seal possessing electrical insulating properties for Recent Experiences in Multidisciplinary Analysis and Optimization, Part 2 28 p 1984 use in a lithium battery. Also provided are lithium cells containing a stainless steel body and molybdenum center pin electrically Avail: NTlS HC A22/MF A01 CSCL 228 A new approach is proposed for solving dual structural-control insulated by means of a seal produced according to the invention. DOE optimization problems for high-order flexible space structures where reduced-order structural models are employed. For a given initial structural dessign, a quadratic control cost is minimized subject to N87-13476*# Catholic Univ. of America, Washington, D.C. a constant-mass constraint. The sensitivity of the optimal control DISTRIBUTED ACTIVE CONTROL OF LARGE FLEXIBLE SPACE cost with respect to the stuctural design variables is then STRUCTURES Semiannual Progress Report determined and used to obtain successive structural redesigns C. C. NGUYEN and A. BAZ Nov. 1986 39 p using a contrained gradient optimization algorithm. This process is (Contract NAG5-749) repeated until the constrained control cost sensitivity becomes (NASA-CR-179941; NAS 1.26:179941) Avail: NTlS HC AO3/MF negligible. A numerical example is presented which demonstrates A01 CSCL 228 that this new approach effectively addresses the problem of dual This progress report summarizes the research work performed optimization for potentially very high-order structures. Author at the Catholic University of America on the research grant entitled Distributed Active Control of Large Flexible Space Structures, funded by NASAIGoddard Space Flight Center, under grant number N87-11829# State Univ. of New York, Buffalo. Dept. of NAG5-749, during the period of March 15, 1986 to September Mechanical and Aerospace Engineering. 15, 1986. Author QUALITATIVE RESULTS FOR DISTRIBUTED SYSTEMS WITH DISCRETE AND STIFFNESS WITH APPLICATION TO CONTROL N87-13478'# California Univ., Los Angeles. Dept. of Mechanical, Final Report, 1 Jul. 1982 - 30 Jun. 1985 Aerospace and Nuclear Engineering. D. J. INMAN 26 Aug. 1985 215 p UNIFIED CONTROL/STRUCTURE DESIGN AND MODELING (Contract AF-AFOSR-0242-82) RESEARCH Final Report (AD-A168622; AFOSR-86-0286TR) Avail: NTIS HC AlO/MF A01 D. L. MINGORI, J. S. GIBSON, P. A. BLELLOCH, and A. CSCL 228 ADAMIAN 8 Jan. 1986 143 p Prepared for JPL Distributed parameter models of large flexible space structures (Contract NAS7-918) subject to various control techniques have been studied. The main (NASA-CR-179948; JPL-9950-1206; NAS 1.26~179948; thrust has been to develop qualitative results which are independent REPT-957114-3) Avail: NTlS HC A07/MF A01 CSCL 228 of truncation of discretization approaches by treating the fully To demonstrate the applicability of the control theory for distributed model. Emphasis has been on controlling the transient distributed systems to large flexible space structures, research response of non-conservative linear partial differential equation was focused on a model of a space antenna which consists of a models of such structures subject to a few point actuators. rigid hub, flexible ribs, and a mesh reflecting surface. The space Inequalities have been developed between the stiffness and antenna model used is discussed along with the finite element damping operators which when satisfied guarantee that the approximation of the distributed model. The basic control problem response of a self-adjoint system will be uniformly exponentially is to design an optimal or near-optimal compensator to suppress stable. In addition, it has been shown that the inequalities insure the linear vibrations and rigid-body displacements of the structure. that finite dimensional versions of the control problem converge The application of an infinite dimensional Linear Quadratic Gaussian to an optimal control of the fully distributed system subject to (LQG) control theory to flexible structure is discussed. Two basic compact feedback as the number of modes in the finite model approaches for robustness enhancement were investigated: loop increases. The inequality developed constitutes a generalization transfer recovery and sensitivity optimization. A third approach of the concept of underdamping normally used with single degree synthesized from elements of these two basic approaches is of freedom systems and provides a physical interpretation of the currently under development. The control driven finite element result. GRA approximation of flexible structures is discussed. Three sets of finite element basic vectors for computing functional control gains N87-11834# Teldix Luftfahrt-Ausruestungs G.m.b.H., Heidelberg are compared. The possibility of constructing a finite element (West Germany). scheme to approximate the infinite dimensional Hamiltonian system LARGE WHEEL ACTUATORS DEFINITION STUDY Final directly, instead of indirectly is discussed. B.G. Report H. HEIMEL and H. H. SCHULZ Paris ESA Dec. 1985 243 p N87-13479# WEA, Cambridge, Mass. (Contract ESTEC-5907/84-NL-AN(SC)) WAVE PROPAGATION AND DYNAMICS OF LATTICE (TELDIX-15-020-880; ESA-CR(P)-2265; ETN-86-98144) Avail: STRUCTURES Final Report, 1 Apr. 1983 - 30 Sep. 1985 NTlS HC A1 1/MF A01 J. H. WILLIAMS, JR. 1 Oct. 1985 27 p Large momentum wheels for attitude stabilization and (Contract F49620-83-C-0092) maneuvering of large space vehicles and space structures were (AD-A17031 6; AFOSR-86-0489TR) Avail: NTlS HC A03/MF A01 studied. Wheels with diameters of 50 and 80 cm and momentum CSCL 228 ceilings of 300 and 1000 Nms, respectively, and control moment Many papers and reports have been written on the concepts, gyros (CMG) derived from them were considered. Spoked wheel design and potential uses of lattice structures in outer space. designs are preferred, and data tables that define wheel families Such structures include large antennae, solar power systems and

33 05 STRUCTURAL DYNAMICS AND CONTROL

habitable stations for support of space colonies. Currently, both each joint. Each bay measured 2 meters per side. Pins of varying deployable and erectable concepts are being investigated for the size were used to simulate various joint freeplay conditions. implementation of lattice structures. Also, investigations of size Single-point random excitation was the primary method of test. considerations indicate that small antennae ranging from tens of The rational fraction polynomial method was used to extract modal meters in span to solar power collectors ranging up to several characteristics from test data. A finite element model of the test I thousand meters have been proposed. Such structural sizes along article was generated from which modal characteristics were with stringent operational requirements will require considerable predicted. These were compared with those obtained from tests. information of dynamics, control, materials, nondestructive With the exception of the fundamental mode, correlation of evaluation (NDE), environmental effects and wave propagation theoretical and experimental results was poor, caused by the relating to their design and analysis. Much has been written on resonant coupling of local truss member bending modes with global the theoretical aspects of the control of such structures. Also, a truss beam modes. This coupling introduced many modes in the large number of vibration analyses have been undertaken. However, frequency range of interest whose frequencies were sensitive to despite a distinct recognition of the importance of wave propagation joint boundary conditions. It was concluded that local/global in many of the control, vibration and NDE investigations, virtually coupling must be avoided in the frequency range where accurate no thing can be found on wave propagation in large space modal characteristics are required. Author structures (LSS). The goals of this program were to initiate and to pursue the development of several aspects of wave propagation N87-15263# Virginia Polylechnic Inst. and State Univ., Blacksburg. analyses in LSS. Author (GRA) Dept. of Engineering Science and Mechanics. OPTIMIZATION OF CLOSED LOOP EIGENVALUES MANEUVER- N87-13485# Engineering System International, Rungis (France). ING, VIBRATION CONTROL AND STRUCTURUCONTROL DE- APPLICATION OF DYNAMIC ELEMENTS AND CONTINUUM SIGN ITERATION FOR FLEXIBLE SPACECRAFT Final Report, METHODS TO LARGE SPACE STRUCTURES, VOLUME 2 Final Jun. 1985 - May 1986 Report JOHN L. JUNKINS 31 May 1986 151 p Prepared in cooperation A. BOSSAVIT, J. CLINCKEMAILLIE, E. HAUG, J. DUBOIS, with Texas A and M Univ., College Station DOWLATYARI, and Y. OUALI Paris, France ESA Dec. 1985 (Contract F49620-83-K-0032) 293 p (AD-A172716; AFOSR-86-0905TR) Avail: NTlS HC AO8/MF A01 (Contract ESTEC-5209/82-NL-PB(SC)) CSCL 228 (ED/82-362/RD-VOL-2; ESA-CR(P)-2217-VOL-2;ETN-86-98151) This report summarizes new results on spacecraft dynamics Avail: NTlS HC A13/MF A01 and control. Perturbation methods are presented for computing Methods for the analysis of complex and large structures are nonlinear open and closed loop optimal maneuver control. reviewed. Dynamic synthesis and reduction methods taking the Homotopy optimization algorithms are presented for tuning linear symmetry of the structure into account are considered. regulators vis-a-vis eigenvalue placement and robustness. A Improvements of the accuracy of dynamic elements (bar, simultaneous structure/controller design optimization algorithm is continuum, beam) by a better discretization of the mass matrix developed. GRA are identified. The two identified approaches (Stavrinidis and Second Order) can reduce the error in frequency, stresses, etc., N87-16017'# Air Force Rocket Propulsion Lab., Edwards AFB, in typical cases by a factor of more than 2. It is recommended to Calif. Interdisciplinary Space Technology Branch. further explore these improvements since significant accuracy can SPACECRAFT DYNAMICS AND CONTROL PROGRAM AT be achieved with no extra computational effort. ESA AFRPL A. DAS, L. K. S. SLIMAK, and W. T. SCHLOEGEL ln NASA. N87-13788'# Catholic Univ. of America, Washington, D.C. Dept. Langley Research Center NASAIDOD ControVStructures of Mechanical Engineering. Interaction Technology, 1986 p 25-40 Nov. 1986 STATIC DEFLECTION CONTROL OF FLEXIBLE BEAMS BY Avail: NTlS HC A23/MF A01 CSCL 228 PIEZO-ELECTRIC ACTUATORS A number of future DOD and NASA spacecraft such as the A. M. 0AZ 19 Dec. 1986 43 p space based radar will be not only an order of magnitude larger (Contract NASA WORK ORDER 30429-D) in dimension than the current spacecraft, but will exhibit extreme (NASA-CR-179947; NAS 1.26:179947) Avail: NTlS HC AO3/MF structural flexibility with very low structural vibration frequencies. A01 CSCL20K Another class of spacecraft (such as the space defense platforms) This study deals with the utilization of piezo-electric actuators will combine large physical size with extremely precise pointing in controlling the static deformation of flexible beams. An optimum requirement. Such problems require a total departure from the design procedure is presented to enable the selection of the optimal traditional methods of modeling and control system design of location, thickness and excitation voltage of the piezo-electric spacecraft where structural flexibility is treated as a secondary actuators in a way that would minimize the deflection of the beam effect. With these problems in mind, the Air Force Rocket to which these actuators are bonded. Numerical examples are Propulsion Laboratory (AFRPL) initiated research to develop presented to illustrate the application of the developed optimization dynamics and control technology so as to enable the future large procedure in minimizing the structural deformation of beams of space structures (LSS). AFRPL's effort in this area can be different materials when subjected to different loading and end subdivided into the following three overlapping areas: (1) ground conditions using ceramic or polymeric piezo-electric actuators. The experiments, (2) spacecraft modeling and control, and (3) sensors results obtained emphasize the importance of the devised rational and actuators. Both the in-house and contractual efforts of the procedure in designing beam-actuator systems with minimal elastic AFRPL in LSS are summarized. Author distortions. Author N87-16019'# Air Force Wright Aeronautical Labs., N87-15262'# Martin Marietta Aerospace, Denver, Colo. Wright-Patterson AFB, Ohio. DYNAMIC TESTING OF A TWO-DIMENSIONAL BOX TRUSS ACTIVE CONTROL EVALUATION FOR SPACECRAFT (ACES) BEAM Final Report J. PEARSON and W. YUEN ln NASA. Langley Research Center CHARLES W. WHITE Washington NASA Jan. 1987 64 p NASA/DOD ControVStructures Interaction Technology, 1986 p (Contract NASl-17551) 67-84 NOV. 1986 (NASA-CR-4039; NAS 1.26:4039; MCR-86-575) Avail: NTlS HC Avail: NTlS HC A23/MF A01 CSCL 228 A04/MF A01 CSCL 226 The Air Force goal is to develop vibration control techniques Testing to determine the effects of joint freeplay and for large flexible spacecraft by addressing sensor, actuator, and pretensioning of diagonal members on the dynamic characteristics control hardware and dynamic testing. The Active Control of a two-dimensional box truss beam was conducted. The test Evaluation for Spacecraft (ACES) program will address the Air article was ten bays of planar truss suspended by long wires at Force goal by looking at two leading control techniques and

34 05 STRUCTURAL DYNAMICS AND CONTROL implementing them on a structural model of a flexible spacecraft N87-16028'# National Aeronautics and Space Administration. under laboratory testing. The first phase in the ACES program is Langley Research Center, Hampton, Va. to review and to assess the High Authority ControVLow Authority COFS 1: BEAM DYNAMICS AND CONTROL TECHNOLOGY Control (HAC/LAC) and Filter accomodated Model Error Sensitivity OVERVIEW Suppression (FAMESS) control techniques for testing on the JOHN L. ALLEN ln its NASA/DOD Control/Structures Interaction modified VCOSS structure. Appropriate sensors and actuators will Technology, 1986 p 221-232 Nov. 1986 be available for use with both techniques; locations will be the Avail: NTlS HC A23/MF A01 CSCL 20N same for both techniques. The control actuators will be positioned The Control of Flexible Structures (COFS) 1 Project provides at the midpoint and free end of the structure. The laser source the invaluable opportunity to test, validate, and measure the for the optical sensor is mounted on the feed mast. The beam effectiveness of theories, structural concepts, control systems, and will be reflected from a mirror on the offset antenna onto the flight certification processes for future missions through a research detectors mounted above the shaker table bay. The next phase program focusing on multiple issues in large flexible structures, is to develop an analysis simulation with the control algorithms dynamics, and controls. The COFS 1 Project consists of a series implemented for dynamics verification. The third phase is to convert of ground and flight activities building progressively from modeling the control laws into high level computer language and test them and dynamic characterization of large space systems to the more in the NASA-MSFC facility. The final phase is to compile all complex issues of flexible-body control. The program objectives analytical and test results for performance comparisons. Author are to: determine the degree to which theory and ground testing can predict flight performance of next-generation low-frequency structures; evaluate structural fidelity of representative next-generation large deployable precision structure; assess math N87-16025*# National Aeronautics and Space Administration. modeling requirements for large lightweight complex systems on Langley Research Center, Hampton, Va. which ground test results are questionable; determine degree to THE 15 METER HOOP-COLUMN ANTENNA DYNAMICS TEST which scale model analysis and tests can be correlated to full-scale AND ANALYSIS performance; evaluate system identification and state estimation W. KEITH BELVIN and HAROLD H. EDIGHOFFER (Edighoffer, algorithms on complex lightweight structures in the space Inc., Newport News, Va.) ln its NASA/DOD Control/Structures environment; evaluate and verify controWstructures modeling Interaction Technology, 1986 p 167-185 Nov. 1986 capability; evaluate control laws and control systems; and evaluate Avail: NTlS HC A23/MF A01 CSCL 20N damping effects in micro-g environment. Author A 15 meter model of the hoop-column antenna concept has been vibration tested for model characterization and analytical model verification. Linear finite element analysis predicted the global vibration frequencies accurately. Good agreement between analysis and test data was obtained only after the analytical model N87-16032*# National Aeronautics and Space Administration. was refined using static test data. As structures become more Langley Research Center, Hampton, Va. flexible, structural properties determined from static data become MAST FLIGHT SYSTEM DYNAMIC PERFORMANCE more accurate and should be used to update analytical models. L. DAVIS, D. HYLAND, T. OTTEN, and F. HAM ln its NASAIDOD Global vibration modes are not significantly affected by the surface ControVStructures Interaction Technology, 1986 p 281 -298 Nov. mesh which permits simplified analytical models to be used for 1986 prediction of global behavior. These reducsd models are believed Avail: NTIS HC A23/MF A01 CSCL 20K sufficient for preliminary design and controls simulations where The MAST Flight System as a test bed for large space structure only global behavior is desired. The mesh modes were highly control algorithms is discussed. An overview is given of the control damped due to the knit mesh used for the reflector surface. These system architecture. The actuators, the sensors, the control modes were also highly coupled and very difficult to measure in computer, and the baseline damping algorithm are discussed. the laboratory. The inability to fully characterize the antenna mesh R.J.F. modes in the laboratory indicates robust methods for active surface vibration suppression will be needed. Fortunately, the surface mesh exhibits high passive damping which should be beneficial to active control systems. Author N87-16035'# National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. N87-16026'# TRW, Inc., Redondo Beach, Calif. COFS 2 3-D DYNAMICS AND CONTROLS TECHNOLOGY APPLICATION OF PHYSICAL PARAMETER IDENTIFICATION JON S. PYLE ln its NASA/DOD Control/Structures Interaction TO FINITE ELEMENT MODELS Technology, 1986 p 327-345 Nov. 1986 ALLEN J. BRONOWICKI, MICHAEL S. LUKICH, and STEVEN P. Avail: NTlS HC A23/MF A01 CSCL 228 KURITZ ln NASA. Langley Research Center NASAIDOD The Control of Flexible Structures (COFS) 2 project is a complex Control/Structures Interaction Technology, 1986 p 187-206 Nov. and ambitious undertaking which will address several critical 1986 technology areas. Among them are modeling, structural dynamics, Avail: NTlS HC A23/MF A01 CSCL 12A controls, and ground testing issues which are not only germane A time domain technique for matching response predictions of to this effort, but to other large space structure programs being a structural dynamic model to test measurements is developed. contemplated. This effort requires the early integration of controls Significance is attached to prior estimates of physical model and structural dynamics considerations in order to achieve mission parameters and to experimental data. The Bayesian estimation success. Several technology advances must be achieved in the procedure allows confidence levels in predicted physical and modal areas of system modelling, control synthesis and methodology, parameters to be obtained. Structural optimization procedures are sensorlactuator development, and ground testing techniques for employed to minimize an error functional with physical model system evaluation and on-orbit performance prediction and parameters describing the finite element model as design variables. verification. This project offers a unique opportunity for the The number of complete FEM analyses are reduced using integration of several disciplines to produce technology advances approximation concepts, including the recently developed which will benefit many future programs. In addition, the convoluted Taylor series approach. The error function is opportunities available to participate in the various levels in the represented in closed form by converting free decay test data to phase of this project, e.g., analytical development and modelling, a time series model using Prony' method. The technique is ground testing, and flight testing, permit for the involvement of a demonstrated on simulated response of a simple truss structure. significant number of interested researchers and oganizations from Author government, universities and industry. Author

35 05 STRUCTURAL DYNAMICS AND CONTROL

N87-16036'# National Aeronautics and Space Administration. N87-16041'# National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. Marshall Space Flight Center, Huntsville, Ala. COFS 3 MULTIBODY DYNAMICS AND CONTROL DEVELOPMENT AND USE OF A LINEAR MOMENTUM TECHNOLOGY EXCHANGE DEVICE ROBERT LETCHWORTH and PAUL E. MCGOWAN ln its GEORGE B. DOANE, 111 (Control Dynamics Co., Huntsville, Ala.), NASAIDOD Control/Structures Interaction Technology, 1986 p HENRY WAITES, and G. DAVID EDGEMON ln NASA. Langley 347-370 NOV.1986 Research Center NASAIDOD ControVStructures Interaction Avail: NTlS HC A23/MF A01 CSCL 20K Technology, 1986 p 431-440 Nov. 1986 COFS 3 is the third project within the Control of Flexible Avail: NTlS HC A23/MF A01 CSCL 148 Structures (COFS) program. It deals with developing multibody In 1981 the Marshall Space Flight Center (MSFC) began dynamics and control technology for large space structures. It establishing an inhouse facility for testing control concepts to be differs from COFS 1 and 2 in two respects. First, it addresses a applied to Large Space Structures (LSS). The original concept more complex class of structure, and second it is basically a called for a long flexible beam suspended from the ceiling by a scale model ground test and analysis program while COFS 1 and low friction support system. The lower end of the beam was to 2 feature Shuttle flight experiments. The specific technology thrusts be mounted to the Advanced Gimbal System (AGS). Analysis and within COFS 3 are model sensitivities, test methods, analysis system engineering soon showed that a more tenable design would validation, systems identification, and vibration suppression. The be where the whole system was inverted, i.e., the AGS hung from COFS 3 project will develop the methods for using dynamically the ceiling with the beam hanging down from it. While this scaled models and analysis to predict the structural dynamics of configuration, augmented by a base excitation table (RET) was large space structures. The project uses the space station as a being built, an ASTROMAST obtained from the Jet Propulsion focus because it is typical of the structures of interest and provides Laboratory was extended, analyzed and tested. From that basic the first opportunity to obtain full-scale on-orbit dynamics data. configuration was evolved the cruciform, VCOSS and ACES Author configurations as shown. The addition of the cruciform added low frequency nested modes and the additional instrument package N87-16037*# General Electric Co., Philadelphia, Pa. Space at the tip contains gyros to monitor tip motion. Author Div. CONCEPTUAL DESIGN OF POINTING CONTROL SYSTEMS FOR N87-16043'# National Aeronautics and Space Administration. SPACE STATION GIMBALLED PAYLOADS Langley Research Center, Hampton, Va. ROBERT 0. HUGHES In NASA. Langley Research Center DISTRIBUTED CONTROL FOR COFS 1 NASA/DOD ControVStructures Interaction Technology, 1986 p R. C. MONTGOMERY, JEFF SULLA (PRC Kentron, Inc., Hampton, 371-381 Nov. 1986 Previously announced as A86-47411 Va.), and D. K. LINDNER (Virginia Polytechnic Inst. and State Avail: NTlS HC A23/MF A01 CSCL 228 Univ., Blacksburg) ln its NASAIDOD ControVStructures Interaction A conceptual design of the control system for Payload Pointing Technology, 1986 p 457-473 Nov. 1986 Systems (PPS) is developed using classic Proportional-Integral-De- Avail: NTlS HC A23/MF A01 CSCL 228 rivatives (PID) techniques. The major source of system pointing error An overview is given of the work being done at NASA LaRC is due to the disturbance-richenvironment of the space station in the on developing the Control of Flexible Structures (COFS) 1 Flight form of gimbal baseplate motions. These baseplate vibrations are Experiment Baseline Control Law. This control law currently characterized using Fast Fourier Transform (FFT) techniques. Both evolving to a generic control system software package designed time domain and frequency domain dynamics models are developed to supply many, but not all, guest investigators. A system simulator to assess control system performance. Three basic methods exist is also described. It is currently being developed for COFS-1 and for the improvement of PPS pointing performance: increase control will be used to develop the Baseline Control Law and to evaluate system bandwidth, add Image Motion Compensation, and/or reduce guest investigator control schemes. It will be available for use (or change) the baseplate disturbance environment. Author whether or not control schemes fall into the category of the Baseline Control Law. First, the hardware configuration for control experiments is described. This is followed by a description of the N87-16040'# Jet Propulsion Lab., California Inst. of Tech., simulation software. Open-loop sinusoid excitation time histories Pasadena. are next presented both with and without a local controller for the SYSTEM IDENTIFICATION FOR MODELING FOR CONTROL OF Linear DC Motor (LDCM) actuators currently planned for the flight. FLEXIBLE STRUCTURES The generic control law follows and algorithm processing EDWARD METTLER and MARK MILMAN ln NASA. Langley requirements are cited for a nominal case of interest. Finally, a Research Center NASAIDOD ControVStructures Interaction closed-loop simulation study is presented, and the state of the Technology, 1986 p 419-429 Nov. 1986 work is summarized in the concluding remarks. Author Avail: NTlS HC A23/MF A01 CSCL 22B The major components of a design and operational flight N87-16044'# Lockheed Missiles and Space Co., Sunnyvale, strategy for flexible structure control systems are presented. In Calif. this strategy an initial distributed parameter control design is PASSIVE DAMPING AUGMENTATION FOR FLEXIBLE developed and implemented from available ground test data and STRUCTURES on-orbit identification using sophisticated modeling and synthesis J. R. SESAK, M. J. GRONET, and G. M. MARINOS ln NASA. techniques. The reliability of this high performance controller is Langley Research Center NASAIDOD Control/Structures directly linked to the accuracy of the parameters on which the Interaction Technology, 1986 p 475-493 Nov. 1986 design is based. Because uncertainties inevitably grow without Avail: NTlS HC A23/MF A01 CSCL 228 system monitoring, maintaining the control system requires an The present work concentrates on the application and extension active on-line system identification function to supply parameter of absorber design and optimization techniques to a multimode, updates and covariance information. Control laws can then be multi-DOF, large space structure, namely the NASA space station. modified to improve performance when the error envelopes are The principal issue addressed is the optimal tuning of several decreased. In terms of system safety and stability the covariance absorbers for the transient response of a multi-DOF system, information is of equal importance as the parameter values including the effects of modal coupling, existing structural damping, themselves. If the on-line system ID function detects an increase absorber placement, and adsorber mass. The space station is in parameter error covariances, then corresponding adjustments subject to many transient disturbances such as docking, orbit must be made in the control laws to increase robustness. If the reboost, crew motion, and payload slewing. A notable steady-state error covariances exceed some threshold, an autonomous excitation source is the Science Research Centrifuge, which rotates calibration sequence could be initiated to restore the error at a frequency in the bandwidth of the primary structural modes. enveloped to an acceptable level. Author Because of the relatively advanced state of development of

36 05 STRUCTURAL DYNAMICS AND CONTROL steady-state absorber design techniques, only the transient cases wire mesh supported on a graphite cord truss structure which is are considered in this study. Author attached between the hoop and the column. The surface contour is controlled by 96 graphite cords from the antenna base to the N87-16045'# National Aeronautics and Space Administration. rear of the truss assembly. The antenna is actually a quadaperture Langley Research Center, Hampton, Va. reflector with each quadrant of the surface mesh shaped to produce MULTIDISCIPLINARY ANALYSIS OF ACTIVELY CONTROLLED an offset parabolic reflector. Results of near-field and structural LARGE FLEXIBLE SPACECRAFT tests are given. Controls structures and electromagnetics PAUL A. COOPER, JOHN W. YOUNG, and THOMAS R. SUTTER interaction, surface control system requirements, mesh control ln its NASA/DOD Control/Structures Interaction Technology, 1986 adjustment, surface control system actuator assembly, surface p 495-514 NOV. 1986 control system electronics, the system interface unit, and control Avail: NTlS HC A23/MF A01 CSCL 228 stations are discussed. Author The control of Flexible Structures (COFS) program has supported the development of an analysis capability at the Langley Research Center called the Integrated Multidisciplinary Analysis N87-16048'# National Aeronautics and Space Administration. Tool (IMAT) which provides an efficient data storage and transfer Langley Research Center, Hampton, Va. capability among commercial computer codes to aid in the dynamic ROBUST MULTIVARIABLE CONTROLLER DESIGN FOR analysis of actively controlled structures. IMAT is a system of FLEXIBLE SPACECRAFT computer programs which transfers Computer-Aided-Design (CAD) SURESH M. JOSH1 and ERNEST S. ARMSTRONG ln its configurations, structural finite element models, material property NASAIDOD ControVStructures Interaction Technology, 1986 p and stress information, structural and rigid-body dynamic model 547-562 NOV. 1986 information, and linear system matrices for control law formulation Avail: NTlS HC A23/MF A01 CSCL 228 among various commercial applications programs through a Large, flexible spacecraft are typically characterized by a large common database. Although general in its formulation, IMAT was number of significant elastic modes with very small inherent developed specifically to aid in the evaluation of the structures. A damping, low, closely spaced natural frequencies, and the lack of description of the IMAT system and results of an application of accurate knowledge of the structural parameters. Summarized here the system are given. Author is some recent research on the design of robust controllers for such spacecraft, which will maintain stability, and possible N87-16046'# National Aeronautics and Space Administration. performance, despite these problems. Two types of controllers Langley Research Center, Hampton, Va. are considered, the first being the linear-quadratic-Guassian-(LQG)- ANALYSIS AND SIMULATION OF THE MAST (COFS-1 FLIGHT type. The second type utilizes output feedback using collocated sen- HARDWARE) sors and actuators. The problem of designing robust LQG-type con- LUCAS G. HORTA, JOANNE L. WALSH, GARNETT C. HORNER, trollers using the frequency domain loop transfer recovery (LTR) and JAMES P. BAILEY (PRC Kentron, Inc., Hampton, Va.) /n its method is considered, and the method is applied to a large antenna NASA/DOD ControVStructures Interaction Technology, 1986 p model. Analytical results regarding the regions of stability for LQG-type 515-532 NOV.1986 controllers in the presence of actuator nonlinearities are also Avail: NTlS HC A23/MF A01 CSCL 228 presented. The results obtained for the large antenna indicate In-house analysis work in support of the Control of Flexible that the LQG/LTR method is a promising approach for control Structures (COFS) program is being performed at the NASA system design for flexible spacecraft. For the second type of Langley Research Center. The work involves evaluation of the controllers (collocated controllers), it is proved that the stability is proposed design configuration, controller design as well as actuator maintained in the presence of certain commonly encountered dynamic modeling, and MASTIactuator dynamic simulation of nonlinearities and first-order actuator dynamics. These results excitation and damping. A complete finite element model of the indicate that collocated controllers are good candidates for robust MAST has been developed. This finite element model has been control in situations where model errors are large. Author incorporated into an optimization procedure which minimizes total mass while maintaining modal coupling. Results show an increase N87-16050*# National Aeronautics and Space Administration. in the total mass due to additional constraints (namely, the diagonal Langley Research Center, Hampton, Va. frequency constraint) imposed on the baseline design. A valid DYNAMIC ANALYSIS OF THE LARGE DEPLOYABLE actuator dynamic model is presented and a complete test sequence REFLECTOR of the proposed flight experiment is demonstrated. The actuator ROBERT E. CALLESON and A. DON SCOTT Jan. 1987 34 p dynamic model is successfully used for damping and the stroke (NASA-TM-89056; NAS 1.1 5:89056) Avail: NTlS HC A03/MF limitations for first mode excitation are demonstrated. Plans are A01 CSCL22B to incorporate additional design variables and constraints into the The Large Deployable Reflector (LDR) is to be an astronomical optimization procedure (such as actuator location) and explore Observatory orbiting above Earth's obscuring atmosphere and alternative formulations of the objective function. A different operating in the spectral range between 30 microns and 1000 actuator dynamic model to include hardware limitations will be microns wavelength. The LDR will be used to study such investigated. Author astronomical phenomena as stellar and galactic formation, cosmology, and planetary atmospheres. The LDR will be the first N87-16047'# National Aeronautics and Space Administration. observatory to be erected and assembled in space. This distinction Langley Research Center, Hampton, Va. brings with it several major technological challenges such as the SURFACE CONTROL SYSTEM FOR THE 15 METER development of ultra-lightweight deployable mirrors, advanced HOOP-COLUMN ANTENNA mirror fabrication techniques, advanced structures, and control of JAMES B. MILLER, ELVIN L. AHL, JR., DAVID H. BUTLER, and vibrations due to various sources of excitation. The purpose of FRANK PERI, JR. /n its NASAIDOD Control/Structures Interaction this analysis is to provide an assessment of the vibrational response Technology, 1986 p 533-545 Nov. 1986 due to secondary mirror chopping and LDR slewing. The dynamic Avail: NTlS HC A23/MF A01 CSCL 22B response of two 20-m LDR configurations was studied. Two mirror The 15-meter hoop-column antenna fabricated by the Harris support configurations were investigated for the Ames concept, Corporation under contract to the NASA Langley Research Center the first employs a six-strut secondary mirror support structure, is described. The antenna is a deployable and restowable structure while the second uses a triple-bipod support design. All three consisting of a central telescoping column, a 15-meter-diameter configurations were modeled using a tetrahedral truss design for folding hoop, and a mesh reflector surface. The hoop is supported the primary mirror support structure. Response resulting from and positioned by 48 quartz cords attached to the column above secondary mirror chopping was obtained for the two Ames the hoop, and by 24 graphite cords from the base of the antenna configurations, and the response of the primary mirror from slewing column. The RF reflective surface is a gold plated molybdenum was obtained for all three configurations. Author

37 05 STRUCTURAL DYNAMICS AND CONTROL

N87-16056# Massachusetts Univ., Amherst. Dept. of Civil data as possible so that a feasible control law can be generated. Engineering. Using Hyland's Maximum Entropy/Optimal Projection Approach, a PARAMETRIC INVESTIGATION OF FACTORS INFLUENCING procedure was developed in which the maximum entropy principle THE MECHANICAL BEHAVIOR OF LARGE SPACE is used for stochastic modeling and the optimal projection technique STRUCTURES Final Technical Report, 1 Nov. 1982 - 30 Jun. is used for a reduced-order dynamic compensator design for a 1985 high-order plant. Author WILLIAM A. NASH and THOMAS J. LARDNER 30 May 1986 451 p (Contract AF-AFOSR-0025-83) (AD-A172880; AFOSR-86-0858TR) Avail: NTlS HC A20/MF A01 CSCL 228 The investigation has two objectives: (1) To investigate the relative importance of factors such as thermal gradients, differential gravitational effects, solar radiation pressure, albedo effects, and N87-16871# Integrated Systems, Inc., Palo Alto, Calif. spatial pressure gradients on structural behavior of large space ADAPTIVE CONTROL TECHNIQUES FOR LARGE SPACE structures; and (2) To investigate structural behavior of a very STRUCTURES Annual Report, 1 Jun. 1985 - 31 May 1986 thin membrane subject to combined internal pressure as well as ROBERT L. KOSUT and MICHAEL G. LYONS 15 Sep. 1986 mechanical and thermal loadings. GRA 117 p (Contract F49620-85-C-0094) N87-16059# Lockheed Missiles and Space Co., Palo Alto, Calif. (AD-A173083; ISI-85; AFOSR-86-0885TR) Avail: NTlS HC WAVE DISPERSION MECHANISMS IN LARGE SPACE AO6IMF A01 CSCL 22A The Large Space Structure (LSS) research program was STRUCTURES Final Report, Oct. 1983 Oct. 1985 - originally formulated in response to increasing concern that K. C. PARK 25 Nov. 1985 7 p performance robustness of Air Force LSS systems would be (Contract F49620-83-C-0018) inadequate to meet mission objectives. Uncertainties in both system (AD-A173967; LMSC-F104499; AFOSR-86-1007TR) Avail: NTlS HC A02/MF A01 CSCL 228 dynamics and disturbance spectra characterizations (both time varying and stochastic uncertainty) significantly limit the This report describes an investigation into wave dispersion phenomena in large lattice space structures. Particular results were: performance attainable with fixed gain, fixed architecture controls. Therefore, use of an adaptive system, where disturbances and/or (1) That local member dynamic characteristics significantly plant models are identified prior to or during control, gives systems influence global dynamic response; (2) That it is possible to designers more options for minimizing the risk in achieving increase dispersion of wave energy in lattice-truss structures by performance objectives. The aim of adaptive control is to implement adopting a nonuniform lattice construction; and (3) That local in real time and on line as many as possible of the design functions member dynamics characteristics require detailed modeling now performed off line by the control engineer to give the controller techniques which are capable of capturing member bending intelligence. To realize this aim, both a theory of stability and behavior in order to assess, realistically, the influence of local performance of such inherently nonlinear controls is essential as phenomena on global dynamic response. GRA well as a technology capable of achieving the implementation. The present research concentrated on: (1) on line robust design N87-16341*# Lockheed Missiles and Space Co., Sunnyvale, from identified models - what is referred to here as adaptive Calif. calibration; and (2) an analysis of slow-adaptation for adaptive DISCRETE MECHANISM DAMPING EFFECTS IN THE SOLAR control for LSS. GRA ARRAY FLIGHT EXPERIMENT E. D. PINSON ln NASA. Lewis Research Center The 20th Aerospace Mechanics Symposium p 277-289 May 1986 Avail: NTIS HC A14/MF A01 CSCL 20K Accelerometer data were collected during on-orbit structural dynamic testing of the Solar Array Flight Experiment aboard the Space Shuttle, and were analyzed at Lockheed Missile and Space Co. to determine the amount of damping present in the structure. N87-16872# Oklahoma Univ., Norman. Dept. of Mathematics. The results of this analysis indicated that the damping present in ESTIMATION AND CONTROL OF DISTRIBUTED MODELS FOR the fundamental in-plane mode of the structure substantially CERTAIN ELASTIC SYSTEMS ARISING IN LARGE SPACE exceeded that of the fundamental out-of-plane mode. In an effort STRUCTURES Annual Report, 2 Jul. 1984 - 1 Jan. 1986 to determine the source of the higher in-plane damping, a test LUTHER W. WHITE 1986 7 p was performed involving a small device known as a constant-force (Contract AF-AFOSR-0271-84) spring motor or constant-torque mechanism. Results from this test (AD-A17501 9; AFOSR-86-2193TR) Avail: NTlS HC A02/MF A01 indicate that this discrete device is at least partially responsible CSCL 20K for the increased in-plane modal damping of the Solar Array Flight This project is to study the estimation and control of elastic Experiment structure. Author systems composed of beams and plates in order to develop efficient and accurate estimation and control algorithms. Results N87-16766'# Alabama Univ., Huntsville. Dept. of Mathematics. have been obtained for the estimation in static beams and plates, STOCHASTIC MODELING AND CONTROL SYSTEM DESIGNS control and location of actuators for static beams and plates, and OF THE NASA/MSFC GROUND FACILITY FOR LARGE SPACE identifiability for discrete approximations of second order elliptic STRUCTURES THE MAXIMUM ENTROPY/OPTIMAL boundary value problems. Currently testing codes are being PROJECTION APPROACH developed for numerical experimentation for estimation of damping WEI-SHEN HSlA ln NASA. Marshall Space Flight Center Research and elastic coefficients in dynamic linear plate models, estimation Reports: 1986 NASAIASEE Summer Faculty Fellowship Program of boundary parameters for second order elliptic problems, 13 p Nov. 1986 estimation of elastic coefficients in cantilevered beams using Avail: NTlS HC A99/MF E04 CSCL 226 perturbed boundary conditions, optimal location of actuators for In the Control Systems Division of the Systems Dynamics the control of beams, and control of plates through forces at Laboratory of the NASAIMSFC, a Ground Facility (GF), in which points and forces distributed over sets of small measure and curves. the dynamics and control system concepts being considered for The plan is to next investigate boundary control and estimation, Large Space Structures (LSS) applications can be verified, was estimation and control in structures, use of friction as an active designed and built. One of the important aspects of the GF is to control, and parallelization of estimation and control algorithms. design an analytical model which will be as close to experimental GRA

38 05 STRUCTURAL DYNAMICS AND CONTROL

N87-16880'# National Aeronautics and Space Administration. and an LQG package providing for both analog and digital Lewis Research Center, Cleveland, Ohio. controls. ESA COMPOSITE SPACE ANTENNA STRUCTURES PROPERTIES AND ENVIRONMENTAL EFFECTS N87-17029 California Univ., Los Angeles. CAROL A. GINTY and NED M. ENDRES (Sverdrup Technology, A MODIFIED LOOP TRANSFER RECOVERY APPROACH FOR Inc., Cleveland, Ohio) 1986 22 p Presented at the 18th ROBUST CONTROL OF FLEXIBLE STRUCTURES Ph.D. Thesis International SAMPE Technical Conference, Seattle, Wash., 7-9 PAUL ANDREW BLELLOCH 1986 214 p Oct. 1986 Avail: Univ. Microfilms Order No. DA8621022 (NASA-TM-88859; E-3225; NAS 1.1 5:88859) Avail: NTlS HC A procedure is developed for dealing with performance and A02/MF A01 CSCL 11D robustness issues in the design of multi-input multi-output The thermal behavior of composite spacecraft antenna compensators for lightly damped flexible structures. The procedure reflectors has been investigated with the integrated Composites is based upon representing errors in the plant design model as Analyzer (ICAN) computer code. Parametric studies have been structured uncertainties, and applying a modified version of the conducted on the face sheets and honeycomb core which Loop Transfer Recovery (LTR) design method. Real parameter constitute the sandwich-type structures. Selected thermal and errors such as frequency errors, damping errors or modal mechanical properties of the composite faces and sandwich displacement errors can be treated. The modified method may be structures are presented graphically as functions of varying fiber implemented in either of two slightly different forms, both of which volume ratio, temperature, and moisture content. The coefficients permit a controlled tradeoff between performance and robustness. of thermal expansion are discussed in detail since these are the The first approach is the main focus. It involves adjusting the critical design parameters. In addition, existing experimental data cost function in the regulator problem and the process noise model are presented and compared to the ICAN predictions. Author in the estimator problem in a particular manner which reflects the assumed structure of the modeling errors. Numerical examples N87-16926# Societe Nationale lndustrielle Aerospatiale, Les dealing with the control of a large flexible space antenna with Mureaux (France). Space and Ballistics Systems. uncertain frequencies demonstrate that this approach represents MECHANICAL AND CONTROL STUDY OF A 7 M OFFSET a considerable improvement over standard LTR methods. UNFURLABLE TRACKING ANTENNA Convenient design parameters can be varied until a satisfactory G. LABRUYERE, L. PASSERON, M. PASTORINO, and E. compromise is achieved between performance and robustness. SCHAFFAR In ESA Proceedings of the Second ESA Workshop The second approach is a variation on the first in that it uses a on Mechanical Technology for Antennas p 23-30 Aug. 1986 similar procedure for adjusting the cost function in the (full-state Avail: NTlS HC A12/MF A01 feedback) regulator problem. Instead of implementing the controller An antenna module for a tracking S-band satellite antenna with an estimator, an algebraic procedure is used to achieve loop mechanical concept is presented. The offset unfurlable reflector, recovery with a compensator whose poles can be placed at arbitrary the 15 deg antenna pointing mechanism, and the feed system locations. Dissert. Abstr. support are described. Antenna pointing control, in presence of multiple flexible structures, is analyzed. ESA N87-17449 Stanford Univ., Calif. ADAPTIVE CONTROL OF A FLEXIBLE STRUCTURE Ph.D. N87-16942# TlCRA A/s, Copenhagen (Denmark). Thesis SIMPLE APPROACH FOR EVALUATING MECHANICAL MICHAEL DAVID SIDMAN 1986 205 p REFLECTOR ANTENNA DISTORTIONS Avail: Univ. Microfilms Order No. DAB619822 KNUD PONTOPPIDAN ln ESA Proceedings of the Second ESA The demonstration of a high-performance adaptive control Workshop on Mechanical Technology for Antennas p 165-170 system for a lightly-damped flexible mechanical structure, such as Aug. 1986 found in large space structures, lightweight robots, and computer Avail: NTlS HC A12/MF A01 peripherals, is discussed. The system accurately identifies the Satellite reflector surface degradations originating from relatively frequencies of three resonances and one anti-resonance, as well slowly varying distortions, such as thermal deformations and creep as the overall gain of the experimental plant, the Stanford Four are discussed. These surface errors scatter the field from the Disk System. The robustness and reliability of the system were main beam into the region of the first few sidelobes, thereby demonstrated in the presence of large, sudden changes in plant deteriorating the isolation between frequency reuse beams. To dynamics that include a complex pole-zero flip and near pole-zero investigate these errors, the concepts of Zernike modes are cancellation that occur as payload mass is added to the system. introduced. It is demonstrated how this method facilitates the insight Fixed-gain robust control performance, both colocated and and understanding of the physical phenomena occurring when a noncolocated, are compared to noncolocated adaptive control reflector surface is deformed. An inflatable antenna is used as a performance. A new method of pole-placement ensures excellent test example. ESA reference-command step responses, substantial active damping of modeled modes, modest amount of control effort and low N87-16947# Ricerche e Progetti s.r.l., Turin (Italy). computational intensity despite major changes in plant dynamics. DYNAMICS AND CONTROL ANALYSIS PACKAGE (DCAP): AN Techniques ensure stable control, at least a minimum level of AUTOMATED ANALYSIS AND DESIGN TOOL FOR performance at all times and fast recovery after large sudden STRUCTURALCONTROLOFSPACESTRUCTURES changes in plant parameters that occur even while the plant is in R. P. SINGH, R. J. VANDERVOORT, C. ARDUINI, A. FESTA a quiescent state. Dissert. Abstr. (Aeritalia S.p.A., Torino, Italy), C. MACCONE, and D. SCIACOVELLI (European Space Agency. European Space Research and N87-17822*# Howard Univ., Washington, D. C. Technology Center, ESTEC, Noordwijk, Netherlands) ln ESA ISSUES IN MODELING AND CONTROLLING THE SCOLE Proceedings of the Second ESA Workshop on Mechanical CONFIGURATION Technology for Antennas p 211-218 Aug. 1986 PETER M. BAINUM, A. S. S. R. REDDY, CHEICK MODIBO Avail: NTlS HC A12/MF A01 DIARRA, and FEIYUE LI In NASA. Langley Research Center The Dynamics and Control Analysis Package (DCAP) automated Proceedings of the 3rd Annual SCOLE Workshop p 11-67 Jan. design and checking tool for the dynamics and control of large 1987 flexible structures is described. The DCAP includes programs for Avail: NTlS HC A20/MF A01 CSCL 228 nonlinear simulation of multibody systems dynamics; linear or The parametric study of the in-plane Spacecraft Control linearized system analysis with frequency and time domain Laboratory Experiment (SCOLE) system, the Floquet Stability response, stability and sensitivity analysis; modal analysis and order Analysis, and three dimensional formulations of the SCOLE system reduction; and control design. It is presently being endowed with dynamics are examined. Control issues are discussed, such as: a user friendly interactive preprocessor, higher speed capabilities, control of large structures with delayed input in continuous time;

39 05 STRUCTURAL DYNAMICS AND CONTROL control with delayed input in discrete time; control law design for The model is then modified to include gravity effects and is SCOLE using Linear Quadratic Gaussian (LQC)/TRR technique; compared with experimental results. Author and optimal torque control for SCOLE slewing maneuvers. B.G. N87-17829'# Rensselaer Polytechnic Inst., Troy, N.Y. Dept. of N87-17823*# Howard Univ., Washington, D. C. Dept. of Electrical, Computer and Systems Engineering. Mechanical Engineering. MODEL REFERENCE CONTROL OF DISTRIBUTED OPTIMAL TORQUE CONTROL FOR SCOLE SLEWING PARAMETER SYSTEMS APPLICATION TO THE SCOLE MANEUVERS PROBLEM P. M. BAINUM and FEIYUE LI ln NASA. Langley Research H. KAUFMAN, D. MINNICK, M. BALAS, and A. MUSALEM ln Center Proceedings of the 3rd Annual SCOLE Workshop p 69-82 NASA. Langley Research Center Proceedings of the 3rd Annual Jan. 1987 SCOLE Workshop p 163-228 Jan. 1987 Avail: NTlS HC A20/MF A01 CSCL 22B Avail: NTlS HC A20/MF A01 CSCL 228 The Spacecraft Control Laboratory Experiment (SCOLE) was The model reference control of lumped linear systems and the slewed from one attitude to the required attitude and an integral model reference control of the distributed parameter system (DPS) performance index which involves the control torques was are presented with their theory and Spacecraft Control Laboratory minimized. Kinematic and dynamical equations, optimal control, Experiment (SCOLE) applications. B.G. two-point boundary-value problems, and estimation of unknown boundary conditions are presented. B.G. N87-17830'# Naval Research Lab., Washington, D. C. N87-17824'# National Aeronautics and Space Administration. PROOF-MASS ACTUATOR PLACEMENT STRATEGIES FOR Langley Research Center, Hampton, Va. REGULATION OF FLEXURE DURING THE SCOLE SLEW MATHEMATICAL MODELING OF SCOLE CONFIGURATION SHALOM (MIKE) FISHER ln NASA. Langley Research Center WITH LINE-OF-SIGHT ERROR AS THE OUTPUT Proceedings of the 3rd Annual SCOLE Workshop p 229-260 S. M. JOSH1 ln its Proceedings of the 3rd Annual SCOLE Jan. 1987 Workshop p 83-92 Jan. 1987 Avail: NTlS HC A20/MF A01 CSCL 228 Avail: NTlS HC A20/MF A01 CSCL 228 An analysis was performed in order to find the best placement The Spacecraft Control Laboratory Experiment (SCOLE) linear for proof-mass actuators and to determine the importance of model; Taylor's coordinate system; Robertson's system; and the placement, Le., what is the sensitivity of beam flexure to actuator flexible linear model are presented. B.G. placement. The analysis was performed by using the NASTRAN finite element model for a flexible beam with 21 grid points on beam, by using the nonlinear DISCOS simulation of 20 deg slew N87-17825'# North Carolina Univ., Charlotte. Dept. of Electrical and the use of a closed-loop linear quadratic regulator (Iqr). Some Engineering. conclusions reached are: (1 ) proof-mass actuators can reduce SLEW MANEUVER DYNAMICS OF THE SPACECRAFT flexure amplitude and damp oscillations; (2) amplitude of CONTROL LABORATORY EXPERIMENT deformations during slew is relatively insensitive to placement of Y. P. KAKAD ln NASA. Langley Research Center Proceedings actuators; (3) damping factor of oscillations is sensitive to actuator of the 3rd Annual SCOLE Workshop p 93-108 Jan. 1987 placement; and (4) the degree of controllability method indicates Avail: NTlS HC A2O/MF A01 CSCL 228 most effective placement for actuators. E.R. Mathematical expressions for slew maneuver dynamics are presented. The total kinetic energy expression of the system is given as T = T(0) + T(l) + T(2), where T(O), T(1). and T(2) N87-17831'# Control Research Corp., Lexington, Mass. refer to the kinetic energies of the shuttle, the flexible beam, and ACTIVE DAMPING OF VIBRATIONS IN SCOLE EXCITED BY the tip mass (the reflector), respectively. The specific equations SLEWING for each of these are defined and integrated into the total energy JIGUAN GENE LIN ln NASA. Langley Research Center expression. Using the chain rule in the Lagrange equations and Proceedings of the 3rd Annual SCOLE Workshop p 261-312 an expression allowing the transformation of the orbiter angular Jan. 1987 velocity from the inertial frame to the body-fixed frame, the Avail: NTlS HC A20/MF A01 CSCL 228 rotational equations are obtained. Finally, the vibration equations Control simulations were performed to study active damping of for the beam are derived, again using the Lagrange equations. vibrations in SCOLE excited by minimum-time rapid slewing. M.G. Highlights of the numerical results are presented. Some conclusions reached are: (1) modal-dashpot and modal-spring controllers N87-17827*# National Aeronautics and Space Administration. provide quick and effective vibration control; (2) high gain problems Langley Research Center, Hampton, Va. can be avoided by proper selection of modeled modes and proper ON INCORPORATING DAMPING AND GRAVITY EFFECTS IN level of augmentation; (3) modal dashpots and modal springs are MODELS OF STRUCTURAL DYNAMICS OF THE SCOLE most effective during the initial period of large vibrations; and (4) CONFIGURATION line of sight error due solely to each mode excited by the LARRY TAYLOR, TERRY LEARY (George Washington Univ., disturbance provides a sound measure of importance of individual Washington, D.C.), and ERIC STEWART ln its Proceedings of modes. E.R. the 3rd Annual SCOLE Workshop p 121-148 Jan. 1987 Avail: NTlS HC A20/MF A01 CSCL 228 The damping for structural dynamic models of flexible spacecraft N87-17832*# Virginia Polytechnic Inst. and State Univ., is usually ignored and then added after modal frequencies and Blacksburg. Dept. of Engineering Science and Mechanics. mode shapes are calculated. It is common practice to assume CONTROL OF SCOLE the same damping ratio for all modes, although it is known that L. MElROVlTCH and M. A. NORRIS In NASA. Langley Research damping due to bending and that due to torsion are sometimes Center Proceedings of the 3rd Annual SCOLE Workshop p 31 3-320 ignored. Two methods of including damping in the modeling process Jan. 1987 from its onset are examined. First, the partial derivative equations Avail: NTlS HC A2O/MF A01 CSCL 228 of motion are analyzed for a pinned-pinned beam with damping. A relatively low order model is used to control SCOLE. Drastic The end conditions are altered to handle bodies with mass and truncation of the discretized model is proposed by means of a inertia for the Spacecraft Control Laboratory Experiment (SCOLE) modal expansion. An open loop eigenvalue problem is illustrated configuration. Second, a massless beam approximation is used as is truncated modal equations, modal state equations, actual for the modes with low frequencies, and a clamped-clamped system output vector and modal Kalman filter. Also illustrated is is used to approximate the modes for arbitrarily high frequency. independent modal-space control. E.R.

40 05 STRUCTURAL DYNAMICS AND CONTROL

N87-17833*# Purdue Univ., West Lafayette, Ind. control sensors and actuators, should be considered as a candidate REGULATION OF THE SCOLE CONFIGURATION for implementation on first-generation LSS because of its stability GREGORY A. NORRIS, EMMANUEL G. COLLINS, and ROBERT robustness. The study of wave propagation is focused primarily E. SKELTON ln NASA. Langley Research Center Proceedings on transient flexural response of a two-dimensional grid structure of the 3rd Annual SCOLE Workshop p 321-336 Jan. 1987 to a suddenly applied sinusoidal force at one point. The study is Avail: NTlS HC A20/MF A01 CSCL 228 not completed, so results are not presented. New laboratory Studies were performed to determine location for proof mass structures with a maneuverable rigid body mode were built and actuators, if a significant reduction in the number of sensors would analyzed. They were relatively simple planar structures composed work, and to design a control law to meet requirements for line of of thin-walled beam members. They exhibited some unusual sight error and actuators. Conclusions are drawn and briefly dynamic characteristics such as variable natural frequencies, snap discussed. E.R. buckling, and other nonlinearities. Finite element modeling generally failed to predict the measured vibration modes and the unusual N87-17834'# University of Southern California, Los Angeles. characteristics. GRA EVALUATION OF ON-LINE PULSE CONTROL FOR VIBRATION SUPPRESSION IN FLEXIBLE SPACECRAFT N87-18101# Lawrence Livermore National Lab., Calif. G. A. BEKEY, S. F. MASRI, and R. K. MILLER ln NASA. Langley DECENTRALIZED OPTIMAL CONTROL OF LARGE FLEXIBLE Research Center Proceedings of the 3rd Annual SCOLE Workshop STRUCTURES p 337-366 Jan. 1987 S. H. WANG, S. C. LU, and I. K. FONG 14 Jul. 1986 12 p Avail: NTlS HC A20/MF A01 CSCL 22B Presented at the 29th Midwest Symposium on Circuits and Systems, On-line pulse control for vibration suppression in a flexible Lincoln, Nebr., 11 Aug. 1986 spacecraft was evaluated. A continuous beam vs. a truss was (Contract W-7405-ENG-48) modeled. A linear finite element model was used to determine (DE86-013906; UCRL-94993; CONF-860899-1) Avail: NTlS HC the truss characteristics. Control issues outlined are ED pulse A02/MF A01 actuator development, pseudo pulse algorithm development, and This paper studies the problem of controlling large flexible large nonlinear simulation problems. E.R. structures by using decentralized feedback control. The proposed algorithm is initially applied to the control of a flexible beam. Two N87-17835'# California Univ., Los Angeles. Dept. of Electrical independent forces are applied at each tip of the beam. One Engineering. displacement sensor and one velocity sensor are colocated with ACTIVE STABILITY AUGMENTATION OF LARGE SPACE each force actuator. Computer simulations indicate that the STRUCTURES A STOCHASTIC CONTROL PROBLEM decentralized feedback is effective in suppressing the structural A. V. BALAKRISHNAN ln NASA. Langley Research Center vibrations of the beam. DOE Proceedings of the 3rd Annual SCOLE Workshop p 367-384 Jan. 1987 Presented at the IFAC Conference on Stochastic N87-18600'# National Aeronautics and Space Administration. Control, Vilnius, May 1986 Marshall Space Flight Center, Huntsville, Ala. (Contract NAG1-464) GROUND FACILITY FOR LARGE SPACE STRUCTURES Avail: NTlS HC A20/MF A01 CSCL 228 DYNAMICS AND CONTROL VERIFICATION A problem in SCOLE is that of slewing an offset antenna on a HENRY WAITES Nov. 1986 15 p long flexible beam-like truss attached to the space shuttle, with (NASA-TM-86558; NAS 1.1 5:86558) Avail: NTlS HC AO2/MF rather stringent pointing accuracy requirements. The relevant A01 CSCL22B methodology aspects in robust feedback-control design for stability NASA Marshall Space Flight Center has developed a facility in augmentation of the beam using on-board sensors is examined. It which closed loop control of Large Space Structures (LSS) can is framed as a stochastic control problem, boundary control of a be demonstrated and verified. The main objective of the facility is distributed parameter system described by partial differential to verify LSS control system techniques so that on-orbit equations. While the framework is mathematical, the emphasis is performance can be unsured. The facility consists of an LSS test still on an engineering solution. An abstract mathematical article or payload which is connected to a 3-axis angular pointing formulation is developed as a nonlinear wave equation in a Hilbert mount assembly that provides control torque commands. The space. That the system is controllable is shown and a feedback angular pointing mount assembly is attached to a base excitation control law that is robust in the sense that it does not require system which will simulate disturbances most likely to occur for quantitative knowledge of system parameters is developed. The Orbiter and DOD payloads. The control computer contains the stochastic control problem that arises in instrumenting this law calibration software, the reference systems, the alignment using appropriate sensors is treated. Using an engineering first procedures, the telemetry software, and the control algorithms. approximation which is valid for small damping, formulas for optimal The total system is suspended in such a fashion that the LSS choice of the control gain are developed. Author test article has the characteristics common to all LSS. Author

N87-17845# Virginia Polytechnic Inst. and State Univ., Blacksburg. N87-18879'# National Aeronautics and Space Administration. Dept. of Aerospace and Ocean Engineering. Langley Research Center, Hampton, Va. EXPERIMENTAL STUDY OF ACTIVE VIBRATION CONTROL OPTIMIZATION PROCEDURE TO CONTROL THE COUPLING Annual Technical Report, 1 Jan. 1985 - 30 Jan. 1986 OF VIBRATION MODES IN FLEXIBLE SPACE STRUCTURES WILLIAM L. HALLAUER, JR. and ANTHONY J. KUBIS, JR. 31 JOANNE L. WALSH Feb. 1987 12 p Proposed for presentation Jul. 1986 88 p at the 28th AIAA/ASME/ASCE/AHS Structures, Structural (Contract F49620-85-C-0024) Dynamics and Materials Conference, Monterey, Calif., 6-8 Apr. (AD-A173144; AFOSR-86-1003TR) Avail: NTlS HC A05/MF A01 1987 CSCL 228 (NASA-TM-89115; NAS 1.1 5:89115) Avail: NTlS HC A02/MF Complementary experimental-theoretical studies were A01 CSCL20K conducted on three separate topics, all of which are related to As spacecraft structural concepts increase in size and flexibility, the dynamics and control of highly flexible large space structures the vibration frequencies become more closely-spaced. The (LSS) in Earth orbit: (1) active damping of vibrations; (2) structural identification and control of such closely-spaced frequencies wave propagation; and (3) development of small, flexible laboratory present a significant challenge. To validate system identification structures having a maneuverable rigid body mode. In the active and control methods prior to actual flight, simpler space structures damping study on a laboratory structure of moderate modal will be flown. To challenge the above technologies, it will be complexity, very good agreement was achieved between necessary to design these structures with closely-spaced or experimental measurements and theoretical predictions. The type coupled vibration modes. Thus, there exists a need to develop a of active damping applied, output feedback with dual (colocated) systematic method to design a structure which has closely-spaced

41 05 STRUCTURAL DYNAMICS AND CONTROL

vibration frequencies. This paper describes an optimization test program at the Georgia Institute of Technology as well as procedure which is used to design a large flexible structure to the development of data reduction computer programs; (5) the have closely-spaced vibration frequencies. The procedure uses a development and successful demonstration of transient pulse and general-purpose finite element analysis program for the vibration simplified steady state methods for evaluating energy losses in and sensitivity analyses and a general-purpose optimization joints; and (6) the performance of outgassing tests on several program. Results are presented from two studies. The first study viscoelastic materials. GRA uses a detailed model of a large flexible structure to design a structure with one pair of closely-spaced frequencies. The second N87-19755'# Lockheed Missiles and Space Co., Sunnyvale, study uses a simple equivalent beam model of a large flexible Calif. structure to obtain a design with two pairs of closely-spaced PASSIVE STABILIZATION FOR LARGE SPACE SYSTEMS frequencies. Author J. R. SESAK, M. J. GRONET, and G. M. MARINOS Washington NASA Apr. 1987 140 p N87-18880'# Catholic Univ. of America, Washington, D.C. Dept. (Contract NAS1-17660) of Mechanical Engineering. (NASA-CR-4067; NAS 1.26:4067) Avail: NTlS HC A07/MF A01 OPTIMUM VIBRATION CONTROL OF FLEXIBLE BEAMS BY CSCL 228 PIEZO-ELECTRIC ACTUATORS The optimal tuning of multiple tuned-mass dampers for the A. BAZ and S. POH Mar. 1987 71 p transient vibration damping of large space structures is investigated. (Contract NAG5-250; NASA ORDER 30429-D) A multidisciplinary approach is used. Structural dynamic techniques (NASA-CR-180209; NAS 1.26:180209) Avail: NTlS HC A04/MF are applied to gain physical insight into absorberlstructure A01 CSCL20K interaction and to optimize specific cases. Modern control theory The utilization of piezoelectric actuators in controlling the and parameter optimization techniques are applied to the general structural vibrations of flexible beams is examined. A Modified optimization problem. A design procedure for multi-absorber Independent Modal Space Control (MIMSC) method is devised to multi-DOF vibration damping problems is presented. Classical enable the selection of the optimal location, control gains and dynamic models are extended to investigate the effects of absorber excitation voltage of the piezoelectric actuators in a way that would placement, existing structural damping, and absorber minimize the amplitudes of vibrations of beams to which these cross-coupling on the optimal design synthesis. The control design actuators are bonded, as well as the input control energy necessary process for the general optimization problem is formulated as a to suppress these vibrations. The developed method accounts for linear output feedback control problem via the development of a the effects that the piezoelectric actuators have on changing the feedback control canonical form. The techniques are applied to elastic and inertial properties of the flexible beams. Numerical sample micro-g and pointing problems on the NASA dual keel examples are presented to illustrate the application of the space station. Author developed MIMSC method in minimizing the structural vibrations of beams of different materials when subjected to different loading and end conditions using ceramic or polymeric piezoelectric actuators. The obtained results emphasize the importance of the devised method in designing more realistic active control systems for flexible beams, in particular, and large flexible structures in ELECTRONICS general. Author Includes techniques for power and data distribution, antenna RF N87-19434# Boston Univ., Mass. performance analysis, communications systems, and spacecraft THE CONTROL THEORY OF FLEXIBLE AND ARTICULATED charging effects. SPACECRAFT Interim Report, 15 Apt. 1985 - 14 Apr. 1986 JOHN BAlLLlEUL and MARK LEVI 15 May 1986 45 p (Contract AF-AFOSR-0144-85) A87-15898# (AD-A174880; AFOSR-86-2082TR) Avail: NTIS HC AOB/MF A01 A CONCEPT OF THE ENERGY STORABLE ORBITAL POWER CSCL 228 STATION (ESOPS) This report summarizes work done on the dynamics and control R. AKIBA, T. TAKANO, and H. YOKOTA (Tokyo, University, of flexible and articulated spacecraft. The combined dynamical Japan) IAF, International Astronautical Congress, 37th, Innsbruck, effects of elasticity and a rotating reference frame have been Austria, Oct. 4-1 1, 1986. 9 p. refs explored for structures in a zero gravity environment. A simple yet (IAF PAPER 86-149) general approach to modeling was developed, and applied to To avoid the foreseeable difficulties and risks associated with analyze the dynamics of a specific prototypical structure. The large scale development of the Space Power Station on GEO at effects of energy dissipation were included and studied in depth a remote distance, the Energy Storable Orbital Power Station for a model problem. Equilibria, bifurcations, and asymptotic stability (ESOPS) placed in a near earth orbit is proposed. The most were analyzed in some carefully chosen examples which capture promising orbit for ESOPS is a fixed periapsis pseudo sun the essential general features of nonlinear distributed parameter synchronous orbit. A thermodynamical power generation is models of rotating elastic structures. GRA preferable owing to its inherent insensitive nature against radiation suffered on the medium altitude orbit. Thermal energy storage N87-19435# McDonnell-Douglas Astronautics Co., Huntington using latent heat of fusion seems the best choice for this system. Beach, Calif. The power transmission from ESOPS to the ground station presents PASSIVELY DAMPED JOINTS FOR ADVANCED SPACE the most critical problems due to nonstationary characteristics. STRUCTURES Final Report, 15 May 1983 - 15 Jan. 1986 Author JAMES H. PEEBLES, RICHARD W. TRUDELL, CREED E. BLEVINS, and JACKY C. PRUCZ 28 Mar. 1986 190 p A87-16019# (Contract F49620-83-C-0117) A 21ST CENTURY NUCLEAR POWER STRATEGY FOR MARS (AD-A17491 4; MDC-H2334; AFOSR-86-2075TR) Avail: NTlS HC J. A. ANGELO, JR. (Florida Institute of Technology, Melbourne) AO9/MF A01 CSCL 228 and D. BUDEN (Science Applications International Corp., This report includes: (1) the development of a viscoelastic Albuquerque, NM) IAF, International Astronautical Congress, 37th, materials selection guide for this research activity; (2) the Innsbruck, Austria, Oct. 4-1 1, 1986. 16 p. refs development of an analytic statics model of the joint specimens; (IAF PAPER 86-322) (3) the designs, fabrication and testing of 21 viscoelastic joint Within the context of an emerging extraterrestrial civilization, specimens, including the development of a new material; (4) the the paper details the power requirements associated with the procurement, fabrication and assembly of test equipment for the advanced exploration and eventual settlement of Mars. An account

42 06 ELECTRONICS is given of the most recent Mars exploration and development A87-17836'# National Aeronautics and Space Administration. scenarios and it is shown how the four basic nuclear energy source Lyndon 9. Johnson Space Center, Houston, Tex. phenomena could play a leading role in the conquest of Mars in A CONSIDERATION OF ATOMIC OXYGEN INTERACTIONS the next century. Radioactive decay and nuclear fission processes WITH THE SPACE STATION represent compact and self-sufficient power and propulsion L. J. LEGER and J. T. VlSENTlNE (NASA, Johnson Space Center, technologies for detailed surface exploration, manned operations, Houston, TX) Journal of Spacecraft and Rockets (ISSN base camp operations and the successful functioning of early 0022-4650), vol. 23, Sept.-Oct. 1986, p. 505-511. Previously cited settlements. Controlled thermonuclear fusion and/or the production in issue 07, p. 875, Accession no. A85-19773. refs and storage of useful quantities of antimatter represent energy technology breakthroughs that would revolutionize earth-to-Mars space transportation systems. K.K. A87-18075 ARABSAT SOLAR GENERATOR CONCEPT AND IN ORBIT PERFORMANCE A87- 1604 1# J. J. JUILLET and L. PELENC (Aerospatiale, Cannes, France) IN: ANTENNA SYSTEM ALTERNATIVES FOR DATA RELAY IECEC '86; Proceedings of the Twenty-first lntersociety Energy SATELLITES WITH MULTIPLE STEERABLE BEAMS Conversion Engineering Conference, San Diego, CA, August 25-29, H. DODEL, D. FASOLD, E. FRISCH, and M. LIEKE (MBWERNO, 1986. Volume 3 . Washington, DC, American Chemical Society, Ottobrunn, West Germany) IAF, International Astronautical 1986, p. 1452-1457. Congress, 37th, Innsbruck, Austria, Oct. 4-11, 1986. 7 p. The capabilities of the Arabsat solar generator are studied. ESA-supported research. refs The electrical power subsystem of the satellite which is based on (IAF PAPER 86-349) a dual bus direct energy transfer system is examined. The satellite Antenna system alternatives for data relay satellites are receives its electric energy from two single-axis sun-pointing solar presented. To that end, the European Data Relay Satellite (DRS) array wings. The components and operation of the solar array as planned by ESA is described in terms of its mission. Constraints wings are described; the solar network is based on silicon solar on the antenna system are discussed such as imposed by the cells. The performance of the solar array in transfer and launcher; the mission as planned foresees an Ariane double geosynchronous orbits and on-station are evaluated by analyzing launch/bottom position. Various possibilities of combining the telemetry data. I.F. S-Band and Ka-Band are outlined, including combined feeds, dichroic reflectors and subreflectors, auxiliary reflectors, beam-waveguide systems, and phased arrays. A considerable A87-18113 number of candidate antenna concepts satisfying the mission MULTIMEGAWATT POWER DISTRIBUTION CONSIDERATIONS requirements are presented (in deployed and stowed configuration S. K. GOT0 and J. H. HAYDEN (Hughes Aircraft Co., El Segundo, on a SPACEBUS-200 type of spacecraft) and their trade-off scores CA) IN: IECEC '86; Proceedings of the Twenty-first lntersociety listed. Author Energy Conversion Engineering Conference, San Diego, CA, August 25-29, 1986. Volume 3 . Washington, DC, American Chemical Society, 1986, p. 1660-1662. Strategic Defense Initiative (SDI) power systems are required A87-16132# to operate at low power for extended periods, yet provide burst LUNAR-BASED POWER SYSTEMS power of hundreds of megawatts for up to hundreds of seconds D. R. CRISWELL and R. D. WALDRON (California, University, La for electromagnetic launchers and various directed energy Jolla) IAF, International Astronautical Congress, 37th. Innsbruck, weapons. High power levels and the separation between the prime Austria, Oct. 4-1 1, 1986. 8 p. refs power source and the weapon because of the physical size of (IAF PAPER 86-507) each makes the design of the electrical power transmission and An evaluation is made of the feasibility and possible distribution system of great significance. Preliminary analysis of performance characteristics of various energy systems for the SDI power system architectures indicate that power distribution realization of a small lunar research base, with attention to the equipment and its thermal control are significant portions of the prospects for use of lunar materials in these construction efforts. total spacecraft weight. It appears that proper choice of distribution It is noted that a functionally superior version of the space solar voltage and conductor material can significantly reduce the total power satellite system can be built on the moon from lunar materials system mass by eliminating all active thermal control systems and used to beam microwave-converted solar power to the base. and allowing conductor temperatures to rise during the It is estimated that about 60 people, using less than 1000 tons of engagement. This paper examines several concepts to minimize manufacturing facilities, tools and habitats could manufacture one distribution system weight. Author installation of this kind in 30 days. O.C.

A87-18144 A87-17368 DESIGN OF A SUPERCONDUCTING ALTERNATOR FOR SPACECRAFT GLOWS FROM SURFACE-CATALYZED SPACE-BASED POWER GENERATION REACTIONS R. E. DODGE, JR., E. P. COOMES (Battelle Pacific Northwest I. L. KOFSKY and J. L. BARRETT (PhotoMetrics, Inc., Woburn, Laboratories, Richland, WA), J. L. KIRTLEY, JR., and S. J. MCCABE MA) Planetary and Space Science (ISSN 0032-0633), vol. 34, (MIT, Cambridge, MA) IN: IECEC '86; Proceedings of the Aug. 1986, p. 665-681. refs Twenty-first lntersociety Energy Conversion Engineering Existing data on the optical glows that extend from low Conference, San Diego, CA, August 25-29, 1986. Volume 3 , earth-orbiting spacecraft are shown to be consistent with Washington, DC, American Chemical Society, 1986, p. recombination of ambient atmospheric species on ram-exposed 1869-1874. refs surfaces. Surface-catalyzed exothermic recombination qualitatively A study was performed to assess the feasibility of using a explains the reported differences as well as similarities among superconducting alternator for space power generation and to spacecraft in spectral intensities and spatial distribution of glows, develop a preliminary machine design. The superconducting and predicts further emission at ultraviolet, infrared, and to a lesser alternator consists of a rotor with superconducting field windings extent visible, wavelengths. The contextual information concerning and a counter rotating armature with normally conducting helical such recombination is systematically reviewed with a view to windings. A unique feature of this design is the counter rotation designing experiments which will serve to predict the spectral of the alternator armature which permits balancing of the rotational intensities of optical foregrounds off spacecraft materials exposed inertia in the machine so that no torque is applied to the space to the thermosphere. C.D. platform. K.K.

43 06 ELECTRONICS

A87-18149 solar photovoltaic arrays, solar thermal dynamic and ultimately SOLAR ARRAYS FOR SPACE STATION AND PLATFORMS nuclear dynamic systems to reduce area are discussed. Also, higher R. V. ELMS (Lockheed Missiles and Space Co., Inc., Sunnyvale, energy storage systems such as nickel-hydrogen and the CA) IN: IECEC '86; Proceedings of the Twenty-first lntersociety regenerative fuel cell (RFC) and higher voltage power distribution Energy Conversion Engineering Conference, San Diego, CA, August which add system flexibility, simplicity and reduce weight are 25-29, 1986. Volume 3 . Washington, DC, American Chemical examined. Emphasis placed on the attributes and development Society, 1986, p. 1898-1902. status of emerging technologies that are sufficiently developed so Current large area solar array technology combined with short that they could be available for flight use in the early to mid term technology advancements can power the initial Space Station 1990's. Author and Platforms based on the NASA Phase B Space Station design requirements. This approach provides low schedule, cost, and performance risk for the initial Space Station. This approach also allows the Phase C/D program funding to be shaped to take advantage of the advanced technology status of large area solar arrays. The current approach to IOC Space Station power sources uses a hybrid photovoltaic (PV) - Solar Dynamic (SD) system. A87-19707 NASA has conducted studies to select the ratio of PV to SD. ADVANCED OPTO-ELECTRONICAL SENSORS FOR These studies involve a number of Space Station system variables AUTONOMOUS RENDEZVOUS-/DOCKING AND PROXIMITY as well as the closely related energy storage system design. This OPERATIONS IN SPACE paper discusses the current and advanced solar array technology B. KUNKEL, R. LUTZ, and S. MANHART (Messerschmitt-Boelkow- which will have application to the Space Station solar arrays. The Blohm GmbH, Munich, West Germany) IN: Solid state imagers and solar array sizes for supporting different fractions of the IOC Space their applications; Proceedings of the Meeting, Cannes, France, Station user bus power are presented along with the arrays for November 26, 27, 1985. Bellingham, WA, Society of Photo-Optical the platforms. Potential atomic oxygen protection designs are also Instrumentation Engineers, 1986, p. 138-148. refs. presented. Author Experimental work on three types of candidate optical sensors for rendezvous and docking tasks, active laser diode radars, CCD A87-18319 cameras and position detector sensors, plus a combination of CONTROL OF SOLAR BATTERY ARRAYS OF SPACECRAFT these is presented. The results obtained up to now with a test WITH CONSIDERATION OF THE STRUCTURAL FLEXIBILITY lab (including motion simulation) make each of them a promising T. FUKUDA, H. HOSOGAI (Tokyo, Science University, Japan), N. candidate for this kind of application for different range regimes. YAJIMA (Ministry of International Trade and Industry, Mechanical These sensors are conceived as multisensor head systems together Engineering Laboratory, Sakura, Japan), and Y. KURIBAYASHI IN: with a central processing unit to provide applicability beyond International Symposium on Space Technology and Science, 14th, docking of space platforms. A description of the sensors, their Tokyo, Japan, May 27-June 1, 1984, Proceedings . Tokyo, AGNE technical development requirements, achieved performance results, Publishing, Inc., 1984, p. 945-950. MOESC-supported research. and combination packages, plus a proposal for in-orbit test missions refs is given. Author The problem dealt with here is how to estimate and control vibrational modes of flexible booms of solar arrays of spacecrafts in a reliable way, even in large angle attitude maneuvers. A proposed mode estimation method based on differential outputs of instrument solar cells and a linear optimal filtering is shown to give good estimation results of vibrational modes. It is shown here that even static output maximization control of the flexible solar array in a desired direction cannot work stably without A87-19872 flexibility consideration based on the mode estimation, and that IN-ORBIT PERFORMANCE OF HUGHES HS 376 SOLAR the dynamic control can give good results to suppress the vibration ARRAYS of the arrays even in large angle attitude maneuvers. Furthermore, STEVEN W. GELB, LELAND J. GOLDHAMMER, and DANA X. a reliable control method is shown to have fault tolerant properties, KEROLA (Hughes Aircraft Co., Space and Communications Group, such as self-degradability as faults get worse. Author El Segundo, CA) IN: Photovoltaic Specialists Conference, 18th, Las Vegas, NV, October 21-25, 1985, Conference Record . New A87-18342' National Aeronautics and Space Administration. York, Institute of Electrical and Electronics Engineers, Inc., 1985, Lewis Research Center, Cleveland, Ohio. p. 362-367. refs THE POTENTIAL IMPACT OF NEW POWER SYSTEM The synchronous orbit performance of Hughes Aircraft Company TECHNOLOGY ON THE DESIGN OF A MANNED SPACE HS 376 spacecraft solar arrays employing the K7 solar cell is STATION presented and compared with ground-based computer predictions J. S. FORDYCE and H. J. SCHWARTZ (NASA, Lewis Research for orbital durations greater than 4 years. The HS 376 spacecraft Center, Cleveland, OH) IN: International Symposium on Space whose solar array performance is discussed include the Satellite Technology and Science, 14th, Tokyo, Japan, May 27-June 1, Business Systems SBS F-1, F-2, and F-3; the Telesat Canada 1984, Proceedings . Tokyo, AGNE Publishing, Inc., 1984, p. Anik C-2, C-3, D-1, and 0-2; and the Western Union Westar IV 1099-1105. Previously announced in STAR as N84-31272. refs and V. Launch of the first Hughes HS 376 satellite with a K7 Larger, more complex spacecraft of the future such as a manned solar array, the SBS F-3, occurred on November 15, 1980. A Space Station will require electric power systems of 100 kW and brief description of each solar array and the general methodology more, orders of magnitude greater than the present state of the for predicting solar array performance are presented. The in-space art. Power systems at this level will have a significant impact on performance data indicate forward solar array power degradation the spacecraft design. Historically, long-lived spacecraft have relied of 13.2 percent for SBS F-3 after 52 months in orbit, 11.2 percent on silicon solar cell arrays, a nickel-cadmium storage battery and for Anik C-3 after 28 months in orbit, and 11.7 percent for Anik operation at 28 V dc. These technologies lead to large array D-1 after 31 months in orbit. The predicted output of each of areas and heavy batteries for a Space Station application. This, these solar arrays is within 2 percent of the actual output as in turn, presents orbit altitude maintenance, attitude control, energy obtained through telemetry. The ability to accurately predict solar management and launch weight and volume constraints. Size (area) array performance within telemetry accuracy is demonstrated. This and weight of such a power system can be reduced if new higher capability combines the solar array electrical measurements in the efficiency conversion and lighter weight storage technologies are as-built configuration, manufacturing consistency, and sound used. Several promising technology options including concentrator computer modeling techniques. Author

44 06 ELECTRONICS

A87-19874'# National Aeronautics and Space Administration. undercutting of the silver layer and graphite-epoxy substrate Lewis Research Center, Cleveland, Ohio. continues in undamaged areas through adjacent, particle damaged PROTECTION OF SOLAR ARRAY BLANKETS FROM ATTACK defect sites. This may have implications for the use of such mirrors BY LOW EARTH ORBITAL ATOMIC OXYGEN in a space station solar dynamic power system. Author BRUCE A. BANKS, MICHAEL J. MIRTICH, SHARON K. RUTLEDGE, and HENRY K. NAHRA (NASA, Lewis Research A87-22659# Center, Cleveland, OH) IN: Photovoltaic Specialists Conference, A SEVERE SPACECRAFT-CHARGING EVENT ON SCATHA IN 18th, Las Vegas, NV. October 21-25, 1985, Conference Record . SEPTEMBER 1982 New York, Institute of Electrical and Electronics Engineers, Inc., H. C. KOONS, P. F. MIZERA, J. L. ROEDER, and J. F. FENNELL 1985, p. 381-386. refs (Aerospace Corp., Space Sciences Laboratory, El Segundo, CA) The ram impact of low earth orbital atomic oxygen causes AIAA, Aerospace Sciences Meeting, 25th, Reno, NV, Jan. 12-15, oxidation of spacecraft materials including polymers such as 1987. 6 p. refs polyimides. The rate of oxidation is sufficiently high to potentially (Contract FO4701-85-C-0086) compromise the long term durability of Kapton solar array blankets. (AIAA PAPER 87-0475) Ion beam sputter deposited atomic oxygen protective coatings of Large amplitude electrostatic discharges were detected by the aluminum oxide, silicon dioxide, and codeposited silicon dioxide engineering instruments aboard the SCATHA satellite on with small amounts of polytetrafluoroethylene were evaluated both September 22, 1982. The Pulse Analyzer detected 29 pulses on in RF plasma asher tests and in low earth orbit. Deposition that date. Seventeen of the pulses exceeded the maximum voltage techniques, mechanical properties, and atomic oxygen protection discrimination level which was set to 7.4 volts. This is the worst performance are presented. Author instance of electrostatic discharges encountered to date by the SCATHA satellite. Three different spacecraft anomalies occurred A87-19878 on SCATHA on September 22, 1982. The most serious was a HIGH VOLTAGE SOLAR ARRAY PLASMA PROTECTION two minute loss of data. Data from the Satellite Surface Potential TECHNIQUES Monitor confirmed that these electrostatic discharges occurred JOHN R. BARTON, WILLIAM G. DUNBAR, and AMY C. REISS during one of the largest spacecraft charging events recorded by (Boeing Aerospace Co., Seattle, WA) IN: Photovoltaic Specialists the instruments aboard the SCATHA satellite. Author Conference, 18th, Las Vegas, NV, October 21-25, 1985, Conference Record . New York, Institute of Electrical and A87-22968# Electronics Engineers, Inc., 1985, p. 41 1-417. refs FLEXIBILITY CONTROL OF SOLAR BATTERY ARRAYS. II - Spacecraft power levels have continuously increased since the VIBRATION AND ATTITUDE CONTROL BASED ON STATE inception of the Space Age, and this trend will continue into the ESTIMATION OF DIFFERENTIAL SOLAR CELL SENSORS distant future. Solar arrays requiring 100s of kilowatts are expected TOSHIO FUKUDA, HlDEMl HOSOKAI (Tokyo Science University, by the mid 199Os, and the higher power levels will require voltage Japan), YUTAKA KURIBAYASHI (Mitsubishi Electric Corp., levels of 100s if not 1000s of volts. Unfortunately, unprotected Kamakura, Japan), and NOBUYUKI YAJIMA (Ministry of solar arrays cannot operate at these high voltages because of International Trade and Industry, Mechanical Engineering the interaction between the solar array and the space plasma. Laboratory, Sakura, Japan) JSME, Bulletin (ISSN 0021-3764), This interaction can cause voltage-charge buildups to the kilovolt vol. 29, Sept. 1986, p. 3116-3120. refs level, followed by arc discharges, material damage, and the In this paper, a differential solar cell sensor consisting of a disruption of spacecraft electronics. Consequently, unprotected pair of adjacent solar cells is proposed as a new type of sensors solar arrays below altitudes of 10.000 km should be limited to to measure vibration of flexible solar battery arrays and to orient voltages less than 250 V dc, and lower than 150 V dc in some the array toward the sun correctly. This sensor, which is small low-altitude orbits. However, high-voltage designs can be used if and light, has linear characteristics and can be implemented easily plasma interaction is significantly reduced by protecting the solar without compensation for distance. To eliminate noises in the array. Solar array protection concepts are presented, including sensor outputs, the Kalman filtering method is employed, based encapsulation and the addition of zero-potential ground planes. on the dynamics of a flexible solar array which is developed Two concentrator configurations are presented which utilize their differently from the previous paper. Then all states can be fed inherent structure as ground planes, and planar arrays are back in an optimal closed control system, so that the control presented which utilize encapsulation and ground planes in the performance can be improved in vibration and attitude control. form of 'lightning rods', 'chicken wire', and/or conductive Author grid-pattern coatings. Author

A87-22417'# National Aeronautics and Space Administration. A87-22969# Lewis Research Center, Cleveland, Ohio. FLEXIBILITY CONTROL OF SOLAR BATTERY ARRAYS. 111 - EFFECT OF HARD PARTICLE IMPACTS ON THE ATOMIC VIBRATION AND ATTITUDE CONTROL WITH CONSIDERATION OXYGEN SURVIVABILITY OF REFLECTOR SURFACES WITH OF THE DYNAMICS OF A REACTION WHEEL AS AN TRANSPARENTPROTECTIVE OVERCOATS ACTUATOR DANIEL A. GULINO (NASA, Lewis Research Center, Cleveland, TOSHIO FUKUDA, HlDEMl HOSOKAI (Tokyo Science University, OH) AIAA, Aerospace Sciences Meeting, 25th, Reno, NV, Jan. Japan), and NOBUYUKI YAJIMA (Ministry of International Trade 12-15, 1987. 8 p. Previously announced in STAR as N87-11838. and Industry, Mechanical Engineering Laboratory, Sakura, Japan) refs JSME, Bulletin (ISSN 0021-3764). vol. 29, Sept. 1986, p. (AIAA PAPER 87-0104) 31 21-3125. Silver mirror samples with protective coatings were subjected to a stream of 27 microns alumina particles to induce pinhole A8 7 -2 5 5 33 defects. The protective coating consisted of a layer of aluminum THE USSR AND SPACE POWER PLANTS dioxide over silver followed by a layer of silicon dioxide over the ALAIN DUPAS (CNES, Paris, France) Space Policy (ISSN alumina. Samples were prepared on both graphite-epoxy composite 0265-9646), vol. 2, Nov. 1986, p. 361, 362. refs and fused quartz substrates. After exposure to the hard particle Soviet policy on space power plants is examined. Research stream, the samples were exposed to an oxygen plasma from Soviet space experts relating to the feasibility and environment in a laboratory plasma asher. The effects of both the development of space power plants is analyzed. Consideration is hard particles and the oxygen plasma were documented by both given to the time scale and costs of development, and the use of reflectance measurements and scanning electron microscopy. The laser technology in satellite solar power stations. The research results indicated that oxidative damage to the silver reflecting layer reveals that Soviet space experts are in favor of developing space continues beyond that of the erosively exposed silver. Oxidative power plants. I.F.

45 06 ELECTRONICS

A87-25700 A87-27180 RECTENNA COMPOSED OF A CIRCULAR MICROSTRIP MICROWAVE POWER TRANSMISSION FOR USE IN SPACE ANTENNA PETER E. GLASER (Arthur D. Little, Inc., Cambridge, MA) KlYOHlKO ITOH, TAKE0 OHGANE, and YASUTAKA OGAWA Microwave Journal (ISSN 0026-2897), vol. 29, Dec. 1986, p. 44, (Hokkaido University, Sapporo, Japan) (Institute of Electronics 46, 48 (6 ff.). refs and Communications Engineers of Japan, IEEE, and URSI, The availability of power for use in space is a key requirement International Symposium on Antennas and Propagation ASAP '851, for future space activities. The power levels needed to enable the Kyoto, Japan, Aug. 20-22, 1985) Space Power (ISSN 0883-6272), evolution of a space infrastructure that will support the Space vol. 6, no. 3, 1986, p. 193-198. Shuttle, a Space Station and lunar missions are reviewed in this (Contract MOESC-56460102) article from an industry point of view. The status of solar and One of the big problems in the SPS system is reradiation Of nuclear energy source developments for use in space and power the harmonic waves generated by the rectifying diode. The use of transmission technologies is discussed. Possible mission-specific a circular microstrip antenna (CMSA) is proposed as a solution, applications of microwave power transmission are highlighted. since the CMSA has no higher resonance-harmonic which is an Technology development directions for microwave power integer multiple of the dominant resonance frequency. However, transmission are summarized and related studies are cited. characteristics of a large rectenna array of CMSAs have not been Author clarified. This paper is concerned with the absorption efficiency of the rectenna composed of the CMSA. The efficiency is estimated A87-29753 explicitly using an infinite array model. The results show that the OPTIMIZATION OF A MICROWAVE-BEAM ENERGY absorption efficiency of the infinite rectenna array composed of TRANSMISSION CHANNEL [OPTIMIZATSIIA TRAKTA the CMSA is 100 percent. Also, this paper considers the effect of PEREDACHI ENERGll SVCH PUCHKOM] the losses of the CMSA. Author 6. A. BANKE, S. K. LESOTA, and A. V. RACHNIKOV Radiotekhnika (ISSN 0033-8486), Nov. 1986, p. 17-20. In Russian. refs The optimization of microwave energy transmission for a satellite A87-26060 solar power system is considered. Attention is given to the ACOUSTIC CLEANING OF LARGE SPACE STRUCTURES achievement of maximum energy transmission efficiency between J. BUSH, L. AGUILAR, and S. KWAN (Lockheed Missiles and apertures for a fixed ratio of the maximum power density at the Space Co., Inc., Sunnyvale, CA) IN: Institute of Environmental receiving antenna to the power density at its edge. Non-Gaussian Sciences, Annual Technical Meeting, 32nd, Dallas and Fort Worth, directivity patterns with a field-intensity gap at the beam axis are TX, May 6-8, 1986, Proceedings . Mount Prospect, IL, Institute of presented which assure high utilization coefficients of the receiving Environmental Sciences, 1986, p. 493-500. antenna and high levels of transmitted power. B.J. Two sets of acoustic experiments related to contamination control of the Hubble Space Telescope modules are reported. In the particle distribution experiments, the maximum fallout from the A87-30893' National Aeronautics and Space Administration, Washington, D.C. vertical one square foot source was 64 inches horizontally away COMMUNICATIONS TECHNOLOGY from the wall, and the 139 dB experiment resulted in a maximum C. LOUIS CUCCIA (NASA, Washington, DC) and JOSEPH SlVO fallout six inches away from the vertical surface. The experiment IN: Space science and applications: Progress and potential . New dealing with the acoustic cleaning of a Light Shield Test Specimen York, IEEE Press, 1986, p. 227-250. (LSTS) indicated that cleaning in a horizontal attitude during The technologies for optimized, i.e., state of the art, operation acoustic exposure results in lower surface level particulate count, but shows the same particulate fallout as the LSTS in the vertical of satellite-based communications systems are surveyed. Features orientation. R.R. of spaceborne active repeater systems, low-noise signal amplifiers, power amplifiers, and high frequency switches are described. Design features and capabilities of various satellite antenna systems are discussed, including multiple beam, shaped reflector A87-27018 shaped beam, offset reflector multiple beam, and mm-wave and THE IMPORTANCE OF ACCURATE SECONDARY ELECTRON laser antenna systems. Attitude control systems used with the YIELDS IN MODELING SPACECRAFT CHARGING antenna systems are explored, along with multiplexers, filters, and IRA KATZ, MYRON MANDELL, GARY JONGEWARD (Systems power generation, conditioning and amplification systems. The Science and Software, La Jolla, CA), and M. S. GUSSENHOVEN operational significance and techniques for exploiting channel (USAF, Geophysics Laboratory, Bedford, MA) Journal of bandwidth, baseband and modulation technologies are described. Geophysical Research (ISSN 0148-0227), vol. 91, Dec. 1, 1986, Finally, interconnectivity among communications satellites by p. 13739-13744. refs means of RF and laser links is examined, as are the roles to be (Contract F19628-82-C-0081) played by the Space Station and future large space antenna Spacecraft charging has commonly been attributed to electrons systems. M.S.K. with several kilovolts of energy impinging upon spacecraft surfaces. Recent experimental evidence from the SCATHA satellite has A87-31223*# National Aeronautics and Space Administration. shown that charging correlates well with electrons of energies Marshall Space Flight Center, Huntsville, Ala. greater than 30 keV. In this paper it is shown that the SCATHA PLASMA ELECTRON COLLECTION THROUGH BIASED SLITS observations are consistent with the model of charging in which a IN A DIELECTRIC satellite is immersed in a Maxwellian plasma, particle collection is M. R. CARRUTH, JR. (NASA, Marshall Space Flight Center, orbit limited, and dominant surface effects are the emission of Huntsville, AL) Journal of Spacecraft and Rockets (ISSN secondary and backscattered electrons. The energy dependence 0022-4650), vol. 24, Jan.-Feb. 1987, p. 79-85. refs of the secondary yield for multikilovolt incident electrons determines A large number of experimental and analytical efforts have the charging threshold. In the past, inadequate representations of been directed toward understanding the plasma sheath growth the secondary yield have led experimenters to question the validity and discharge phenomena which lead to high-voltage solar of the charging model. The accuracy of the secondary electron arraylspace plasma interactions. An important question which has yield formulation based on electron stopping power, such as the not been addressed is how the voltage gradient in the plasma one in NASA. Charging Analyzer Program (NASCAP), gives good sheath near the surface of such an array may affect these agreement with the SCATHA results. A Maxwellian representation interactions. The purpose of the experimental study described in of the magnetospheric plasma is justified by choosing effective this paper is to examine the merging of the sheaths around biased temperatures and densities that minimize the error in calculating slits in a dielectric and how this affects the collection of electrons charging current densities. Author through these slits. The data, which are obtained by emissive

46 06 ELECTRONICS probes and direct measurement of the current collected through N87-16941# Construcciones Aeronauticas S.A., Madrid (Spain). the slits, indicate that when the sheaths merge the current collection Space and Systems Div. by the slits is significantly altered with the most positive slit DEVELOPMENT OF MM-WAVE RADIOMETER ANTENNA collecting more electrons than it otherwise would. Therefore, the REFLECTOR effect of a voltage gradient in the sheath around a solar array P. CORDERO, G. LOPEZ, and R. GARCIA ln ESA Proceedings should be considered when evaluating solar array performance. of the Second ESA Workshop on Mechanical Technology for Author Antennas p 151-159 Aug. 1986 (Contract ESA-5263/82-NL-GM) Avail: NTlS HC A12/MF A01 N87-11352# British Aerospace Dynamics Group, Bristol (England). The development of an antenna for a passive microwave Space and Communications Div. radiometer for the 90 to 300 GHz frequency range is discussed. HPSA HIGH POWER SOLAR ARRAY STUDY Final Report The operating frequency-range imposes ultrahigh surface accuracy C. P. LEE Paris ESA Jul. 1985 156 p and stability, and electrical reflectivity close to that of the best (Contract ESA-6064/84-NL-PB) conductive metals. Critical design areas and technological problems (BAE-TP-8071; HPSA/RPT/8071; ESA-CR(P)-2201; (e.g., CFRP metallizing) are reviewed. ESA ETN-86-98086) Avail: NTlS HC AOB/MF A01 A 30 kW solar array design for ESA’s Columbus program was N87-16943# Centro Studi e Laboratori Telecomunicazioni, Turin established. Realistic array requirements were identified using the (Italy). ESA recommended designed reference mission. System and PREDICTION OF THE ELECTRICAL PERFORMANCE OF subsystem level studies lead to preferred design solutions for silicon INFLATABLE SPACE RlGlDlZED STRUCTURE (ISRS) OFFSET and gallium arsenide cell technologies. A development philosophy ANTENNA REFLECTORS AND CORRELATION WITH RF and test plan to pursue the identification of critical aspects was MEASUREMENTS derived and a preliminary cost appraisal was made. It is concluded E. PAGANA and M. C. BERNASCONI (Contraves Corp., Zurich, that a planar double roll out array employing silicon cells represents Switzerland) In ESA Proceedings of the Second ESA Workshop the most attractive solution, with a gallium arsenide roll out as a on Mechanical Technology for Antennas p 171-177 Aug. 1986 logical derivative. ESA Avail: NTlS HC A12/MF A01 The electrical design and testing at microwave frequencies (3 to 22 GHz) on the first Large Offset Antenna Demonstrator (LOAD) breadboard are summarized. The electrical analysis shows the N87-13864# Societe Nationale lndustrielle Aerospatiale, Cannes quality of mock-up reflector and contributes to an electrical antenna (France). Div. Systemes Balistiques et Spatiaux. model. The performance of a large inflatable antenna can be HIGH POWER RIGID SOLAR ARRAY Final Report predicted, with good accuracy, only on the basis of the mechanical L. PELENC Paris, France ESA 19 Sep. 1985 121 p measurements of a proper set of reflector surface points. ESA (Contract ESTEC-6061/84-NL-PB(SC)) (SNIAS-917A-CA/CG; ESA-CR(P)-2202; ETN-86-98087) Avail: N87-16971‘# Colby Coll., Waterville, Maine. Dept. of Physics NTlS HC AO6/MF A01 and Astronomy. The feasibility and complexity of a 30 kW solar array scaling LEO HIGH VOLTAGE SOLAR ARRAY ARCING RESPONSE 15 to 60 kW for the Columbus space station, with silicon cells MODEL Interim Report, Feb. 1987 and with gallium arsenide cells were studied. The specifications ROGER N. MET2 Feb. 1987 32 p were modified, thereby changing the concept choice for the study. (Contract NAG3-576) The multideployment/retraction (300 for the mission) and the 20% (NASA-CR-180073; NAS 1.26:180073) Avail: NTlS HC AO3/MF power required in partial deployment (under 3 kN reboost engines) A01 CSCL09A favor rigid arrays for both silicon and gallium arsenide cells, with A series of mathematical models were developed that describe a very simple and reliable pantograph deployment/retraction the electrical behavior of a large solar cell array floating electrically system. ESA in the low Earth orbit (LEO) space plasma and struck by an arc at a point of negative bias. There are now three models in this series: ARCH, which is a fully analytical, linearized model; ARCIII, N87-15377# European Space Agency. European Space which is an extension of ARClll that includes solar cell inductance Research and Technology Center, ESTEC, Noordwijk as well as load reactance; Nonlinear ARC, which is a numerical (Netherlands). model able to treat effects such as non-linearized, i.e., logarithmic L-BAND ANTENNAS FOR REGIONAL MOBILE COMMUNICATION solar cell I/V characteristics, conductance switching as a solar SATELLITES cell crosses plasma ground on a voltage excursion and non-ohmic A. ROEDERER In ESA Proceedings of an ESA Workshop on plasma leakage current collection. Author Land Mobile Services by Satellite p 75-80 Sep. 1986 Avail: NTlS HC A08/MF A01 Satellite L-band antennas ranging for state of the art small N87-17277# Naval Research Lab., Washington, D. C. Space reflector systems to multibeam arrays, to large array-fed reflectors, Systems and Technology Div. with frequency reuse, flexible channel to beam allocation and/or APPLICATION OF SPACEBORNE DISTRIBUTED APERTURE/ steerable beam capabilities over an extended European coverage COHERENT ARRAY PROCESSING (SDNCAP) TECHNOLOGY TO are reviewed. Both 2.5 to 5 m multifeed reflectors and foldable ACTIVE AND PASSIVE MICROWAVE REMOTE SENSING multibeam arrays are valid candidates for regional mobile M. S. KAPLAN In ESA Proceedings of the 1986 International communication satellites in the next decade. The foldable Geoscience and Remote Sensing Symposium (IGARSS ’86) on multibeam arrays have the major advantage over the multifeed Remote Sensing: Today’s Solutions for Tomorrow’s Information reflectors of quasi-total traffic to beam allocation flexibility. In the Needs, Volume 1 p 697-701 Aug. 1986 longer term, when increase in traffic is such that on board minimum Avail: NTlS HC A99/MF E03; ESA, Paris, France, 3 volume set gains greater than 35 dBi are required, unfurlable reflectors with $90 Member States, AU, CN, and NO (420% others) diameters greater than 10 m are preferable, since direct radiating Application of spaceborne distributed aperture/coherent array arrays with equivalent aperture area cannot easily be deployed. processing (SDAXAP) to environmental remote sensing missions Technologies for foldable arrays and reflectors up to 5 m diameter is discussed. This technology differs from conventional monostatic should be available for flight in the early nineties from present remote sensing approaches in that sensor elements are distributed hardware developments. The same technology is applicable up to among many space platforms. It is possible to coherently combine greater than 10 m, but with a serious additional effort required, the inputs from many receiving spacecraft in order to form a very particularly in testing. ESA large distributed aperture, thousands of kilometers in size. This

47 06 ELECTRONICS enormous effective aperture size can provide nanoradian resolution N87-20080'# York Univ., Toronto (Ontario). Dept. of Physics. in the microwave region of the spectrum. Relative spacecraft phase SPACECRAFT CHARGING IN THE AURORAL PLASMA measurement accuracies on the order of a fraction of a wavelength PROGRESS TOWARD UNDERSTANDING THE PHYSICAL are required to support the technology. Spacecraft relative position EFFECTS INVOLVED Abstract Only and time measurement via hydrogen maser time references On J. G. LAFRAMBOISE and L. W. PARKER (Parker, Lee W., Inc., each spacecraft and laser ranging between spacecraft is proposed. Concord, Mass.) ln JPL, Space Technology Plasma Issues in Intersatellite laser ranging technology needs to be developed to 2001 p 311 1 Oct. 1986 support the application of SDA/CAP techniques for advanced space (Contract F19628-83-K-0028) environmental remote sensor systems. ESA Avail: NTlS HC A20/MF A01 CSCL 228 The work is presented in four parts. First, main differences between the plasma environments in geostationary orbit and low polar orbit with regard to high-voltage charging situations are N87-18598*# National Aeronautics and Space Administration. reviewed. Next, results are presented from a calculation of Langley Research Center, Hampton, Va. secondary-electron escape currents from negatively-charged INTEGRATED STRUCTURE ELECTROMAGNETIC OPTIMIZA- spacecraft surfaces having various orientations relative to the local TION OF LARGE SPACE ANTENNA REFLECTORS magnetic-field direction. It is shown that for finite ranges of SHARON L. PADULA, HOWARD M. ADELMAN, and M. c. combinations of electric and magnetic field directions, BAILEY Feb. 1987 12 p Proposed for presentation at the secondary-electron escape is completely suppressed and therefore AIAA/ASME/ASCE/AHS 28th Structures, Structural Dynamics and cannot help to discharge the spacecraft. In such circumstances, Materials Conference, Monterey, Calif., 6-8 Apr. 1987 secondary electrons may travel distances many times their gyroradii (NASA-TM-89110; NAS 1.15:89110; AIAA-87-0824-CP) Avail: before reimpacting, and this may produce greatly increased NTlS HC AO2/MF A01 CSCL 228 secondary-electron surface currents. Thirdly, a simple rough The requirements for extremely precise and powerful large estimate of the required conditions for high-voltage auroral-zone space antenna reflectors have motivated the development of a charging is developed. The results suggest that for any given procedure for shape control of the reflector surface. A mathematical spacecraft, surface potentials are likely to depend more strongly optimization procedure has been developed which improves on the ratio of ambient flux of high-energy electrons to that of all antenna performance while minimizing necessary shape correction ions, than on any other environmental parameter. Finally, effort. In contrast to previous work which proposed controlling the preliminary results are presented of numerical simulation work rms distortion error of the surface thereby indirectly improving directed toward testing this hypothesis. Numerical instabilities antenna performance, the current work includes electromagnetic encountered in doing this simulation work probably are closely (EM) performance calculations as an integral of the control related to physical sensitivities inherent in the physics of the ion procedure. The application of the procedure to a radiometer design wake behind the spacecraft, and especially to beam-like with a tetrahedral truss backup structure demonstrates the potential constituents of the ion population in the wake. Author for significant improvement. The results indicate the benefit of including EM performance calculations in procedures for shape control of large space antenna reflectors. Author 07

ADVANCED MATERIALS N87-20063*# Air Force Geophysics Lab., Hanscom AFB, Mass. PLASMA INTERACTIONS WITH LARGE SPACECRAFT RITA C. SAGALYN and NELSON C. MAYNARD In JPL, Space Includes matrix composites, polyimide films, thermal control Technology Plasma Issues in 2001 p 51-68 1 Oct. 1986 coatings, bonding agents, antenna components, manufacturing Avail: NTlS HC A20/MF A01 CSCL 201 techniques, and space environmental effects on materials. Space is playing a rapidly expanding role in the conduct of the Air Force mission. Larger, more complex, high-power space platforms are planned and military astronauts will provide a new A87-11355'# National Aeronautics and Space Administration. capability in spacecraft servicing. Interactions of operational Goddard Space Flight Center, Greenbelt, Md. satellites with the environment have been shown to degrade space AN ESTIMATE OF THE OUTGASSING OF SPACE PAYLOADS sensors and electronics and to constrain systems operations. The AND ITS GASEOUS INFLUENCE ON THE ENVIRONMENT environmental interaction effects grow nonlinearly with increasing J. J. SCIALDONE (NASA, Goddard Space Flight Center, Greenbelt, size and power. Quantification of the interactions and development MD) Journal of Spacecraft and Rockets (ISSN 0022-4650), vol. of mitigation techniques for systems-limiting interactions is essential 23, July-Aug. 1986, p. 373-378. Previously cited in issue 17, p. to the success of future Air Force space operations. Author 2471, Accession no. A85-37616. refs

A87-11384 FABRICATION OF A CARBON FIBRE/ALUMINIUM ALLOY N87-20069'# TRW Space Technology Labs., Redondo Beach, COMPOSITE UNDER MICROGRAVITY Calif. System Integration Lab. Y. MISHIMA, M. HORI. T. SUZUKI, and S. UMEKAWA (Tokyo HIGH VOLTAGE SYSTEM: PLASMA INTERACTION SUMMARY Institute of Technology, Yokohama, Japan) Journal of Materials N. JOHN STEVENS ln JPL, Space Technology Plasma Issues Science (ISSN 0022-2461), vol. 21, Aug. 1986, p. 2763-2766. in 2001 p 167-193 1 Oct. 1986 Research supported by the National Space Development Agency Avail: NTlS HC A2O/MF A01 CSCL 201 of Japan and Science and Technology Agency. refs The possible interactions that could exist between a high voltage Fabrication of a composite material with ultralow density and system and the space plasma environment are reviewed. A solar high stiffness under microgravity is the objective of the present array is used as an example of such a system. The emphasis in investigation. The composite structure to be obtained is a random this review is on the discrepancies that exist in this technology in three-dimensional array of high modulus, short carbon fibers both flight and ground experiment data. It has been found that, in bounded at contact points by an aluminum alloy coating on the ground testing, there are facility effects, cell size effects and area fibers. The material is highly porous, and thus has a very low scaling uncertainties. For space applications there are area scaling density. The motivation toward the investigation, simulation and discharge concerns for an array as well as the influence of experiments, choice of the component materials, and in-flight the large space structures on the collection process. There are experiment during ballistic trajectory of a National Space still considerable uncertainties in the high voltage-space plasma Development Agency rocket, are described herein. Supporting interaction technology even after several years of effort. Author experimental evidence shows that the cohesion between the 07 ADVANCED MATERIALS carbon fiber and the aluminum alloy is excellent, by which the A87-13097 achievement of desired properties of such composites seems THERMOPLASTIC-BASED COMPOSITES WITH LOW CTE FOR probable. Author SPACE STRUCTURES AND CIRCUIT BOARD APPLICATIONS A. MAHAMAD IBRAHIM, T. K. SHAH, L. J. MATIENZO, and J. D. VENABLES (Martin Marietta Laboratories, Baltimore, MD) IN: A87-11847. National Aeronautics and Space Administration. International SAMPE Symposium and Exhibition, 31 st, Los Angeles, Langley Research Center, Hampton, Va. CA, April 7-10, 1986, Proceedings . Covina, CA, Society for the SPACE RADIATION EFFECTS ON THE DIMENSIONAL Advancement of Material and Process Engineering, 1986, p. STABILITY OF A TOUGHENED EPOXY GRAPHITE 669-680. refs COMPOSITE A variety of organic and inorganic woven fabric reinforced G. F. SYKES and D. E. BOWLES (NASA, Langley Research Center, high-performance thermoplastic composites have been investigated Hampton, VA) SAMPE Quarterly (ISSN 0036-0821). vol. 17, July with a view to developing new composite systems with a low or 1986, p. 39-45. refs near-zero coefficient of thermal expansion (CTE) in the X-Y The effects of a simulated space radiation environment on the direction and a reasonably low CTE in the Z direction. A dimensional stability of an elastomer-toughened epoxy-graphite high-performance semicrystalline thermoplastic, polyphenylene composite were determined. The response of the material was sulfide (PPS) has been selected as the model thermoplastic matrix characterized following exposure to radiation doses equivalent to system. The results obtained indicate that the use of this matrix geosynchronous orbit lifetimes ranging from 6 months to 30 years. system makes it possible to achieve more uniform thermal The results show that radiation interacts with the epoxy matrix to expansion behavior in all directions for composites used in space embrittle the composite, beginning at relatively low total doses structures and circuit board applications. V.L. (10 to the 7th power rads). The embrittlement results in thermal expansion changes and significant laminate microcracking during A87-13098 thermal cycling. These property changes could limit the service PROTECTIVE COATING FOR THE KU-BAND REFLECTOR life of this material in some spacecraft applications. Author J. R. DENMAN and L. C. MALDOON (Hughes Aircraft Co., Technology Support Div., Los Angeles) IN: International SAMPE Symposium and Exhibition, 31 st, Los Angeles, CA, April 7-10, 1986, A87-13067 Proceedings . Covina, CA, Society for the Advancement of Material SPACE MATERIALS IN EUROPE and Process Engineering, 1986, p. 681 -692. J. DAUPHIN (ESA, Materials Section, Noordwijk, Netherlands) IN: Several protective coatings have been tested with a view to International SAMPE Symposium and Exhibition, 31 st, Los Angeles, selecting a coating system capable of protecting the KU-band CA, April 7-10, 1986, Proceedings . Covina, CA, Society for the antenna reflector used on the Space Shuttle against damage in Advancement of Material and Process Engineering, 1986, p. the low earth orbit (LEO) environment. Of the coatings tested, CV 276-290. refs 1144, a flexible room temperature curing silicone coating, has A comprehensive evaluation is made of the development status been selected as the best product. This coating system does not of materials for such space structures as those of satellites and affect the operation of the reflector while providing protection space probes that have been constructed under the aegis of the against the hostile LEO environment for extended periods. Some ESA. Attention is given to the performance criteria for which test results are presented. V.L. spacecraft materials that will be subjected to ionizing radiation, temperature extremes and vacuum (potentially outgassing) A87-13159 conditions must be qualified. The organizational details of product FABRICATION OF A SPACE STATION COMPOSITE assurance and approval procedure management are also TETRATRUSS MODEL presented. Representative of advanced materials-employing J. F. DUBEL (McDonnell Douglas Astronautics Co., Huntington spacecraft are the Marecs maritime satellite, the Giotto Halley Beach, CA) IN: International SAMPE Symposium and Exhibition, comet probe, and the Space Telescope’s solar array; these 31st, Los Angeles, CA, April 7-10, 1986, Proceedings . Covina, respectively employ a carbon fiber-reinforced aluminum honeycomb CA, Society for the Advancement of Material and Process antenna, a ’Sepcarb’ carbonlcarbon composite rocket nozzle, and Engineering, 1986, p. 1469-1475. novel silicone adhesives. O.C. Attention is given to the design, fabrication and assembly processes associated with a prototype composites-employing ’tetratruss’ for Space Station-related use. Unidirectional and A87-13071 chopped fiber-reinforced composites have been chosen for the EFFECT OF ELECTRON-BEAM RADIATION ON GRAPHITE fabrication of the truss structure’s tubular struts and fittings, EPOXY COMPOSITES respectively. The tubes’ unidirectional material will be plied in order J. ENOMOT, K. NAKAZAKI, K. MURAYAMA, and K. SONODA to yield the requisite longitudinal modulus and thermal expansion (Mitsubishi Electric Corp., Amagasaki, Japan) IN: International coefficient while retaining acceptable transverse modulus; the SAMPE Symposium and Exhibition, 31st, Los Angeles, CA, April chopped graphite fiber reinforced for the frame’s nodes, tube ends 7-10, 1986, Proceedings . Covina, CA, Society for the Advancement and hinge fittings will produce somewhat greater thermal expansion. of Material and Process Engineering, 1986, p. 352-361. Research The overall design, test, verification, fabrication and assembly sponsored by the Agency of Industrial Science and Technology. process data generated by this prototype will be used as a basis refs for Space Station composite primary structure cost projections. Specimens of unidirectional graphitelepoxy laminates were O.C. irradiated by 10-MeV electrons up to a total dose of 5000 Mrads at 50, 150, and 250 C and then tested mechanically to determine A87-14312* Massachusetts Inst. of Tech., Cambridge. their flexural and interlaminar shear strengths. The FUNDAMENTALS AND ADVANCES IN THE DEVELOPMENT OF radiation-generated volatile products and the components extracted REMOTE WELDING FABRICATION SYSTEMS by a solvent from the irradiated specimens were analyzed by J. E. AGAPAKIS (Automatix, Inc., R&D Group, Billerica; MIT, gas-chromatographic and mass spectrometric techniques; the Cambridge, MA), K. MASUBUCHI (MIT, Cambridge, MA), and C. degradation of the matrix resin (bisphenol based epoxy) was VON ALT (Woods Hole Oceanographic Institute, MA) Welding characterized by FT-IR spectroscopy. It is found that the flexural Journal (ISSN 0043-2296), vol. 65, Sept. 1986, p. 21-32. strength of the specimens irradiated in air decreases with increasing MIT-NASA-supported research. refs dose. The flexural strength of the irradiated specimens, however, Operational and man-machine issues for welding underwater, can be almost completely restored through a thermal cycling in outer space, and at other remote sites are investigated, and treatment. It is also shown that the degradation of the matrix recent process developments are described. Probable remote increases with the irradiation dose. V.L. welding missions are classified, and the essential characteristics

49 07 ADVANCED MATERIALS of fundamental remote welding tasks are analyzed. Various possible A87-18867 operational modes for remote welding fabrication are identified, MATERIALS - THE CHALLENGE OF SPACE and appropriate roles for humans and machines are suggested. G. MARSH Space (ISSN 0267-954X), vol. 2, Sept.-Nov. 1986, p. Human operator performance in remote welding fabrication tasks 10-12, 14, 15. is discussed, and recent advances in the development of remote A comprehensive evaluation is made of the state of welding systems are described, including packaged welding development and applicability to spacecraft structures of various systems, stud welding systems, remotely operated welding systems, advanced materials technologies, some of which are noted to and vision-aided remote robotic welding and autonomous welding have been overlooked by designers despite substantial promises systems. C.D. of performance improvement in space environments characterized by extreme temperatures and radiation exposures. Attention is given to beryllium, lithium-aluminum and titanium alloys, carbon-carbon and ceramic composite refractories, and refractory metals, as well A87-16163 as space-applicable polymer-matrix composites. O.C. DESIGN AND MANUFACTURING ASPECTS OF TUBULAR CARBON FIBRE COMPOSITE/TITANIUM BONDED JOINTS J. FRANZ and H. LAUBE (Messerschmitt-Boelkow-Blohm GmbH, A87-19122* National Aeronautics and Space Administration. Ottobrunn, West Germany) (Imperial College of Science and Langley Research Center, Hampton, Va. Technology and Ciba-Geigy Plastics, International Symposium on THE EFFECTS OF RADIATION ON THE INTERLAMINAR Joining and Repair of Fibre-Reinforced Plastics, London, England, FRACTURE TOUGHNESS OF A GRAPHITE/EPOXY Sept. 10, 11, 1986) Composite Structures (ISSN 0263-8223), vol. COMPOSITE 6, no. 1-3, 1986, p. 183-196. J. G. FUNK and G. F. SYKES (NASA, Langley Research Center, The structure of the satellite SPAS-01 consists of a framework Hampton, VA) Journal of Composites Technology and Research built by carbon fiber composite/titanium strut and node elements. (ISSN 0885-6804), vol. 8, Fall 1986, p. 92-97. refs The key point of the whole structure is the connection between An experimental study is made of the effect of electron the carbon fiber composite tube and the titanium end fitting, which irradiation (10 to the 10th rad), simulating a 30-year geosynchronous has been designed and constructed in the form of a scarf, orbit exposure, on the fracture toughness of a graphitelepoxy double-shear bonded joint. The present paper describes the composite, T3001934. The double cantilever beam (DBC) test is structural requirements and their verification in the phases of used to determine Mode I (peel) critical strain energy release rate design, analysis, test and fabrication of the satellite structure. and the edge delamination tension (EDT) test is used to determine Author mixed Mode I and I1 (peel and shear) critical strain energy release rate. It is found that the electron interaction of the epoxy matrix material enhances the fracture toughness properties of the composite and that the test temperature has a significant effect A87-18271 THE ELECTRON IRRADIATION TEST OF THERMAL CONTROL on the fracture toughness of both baseline and irradiated MATERIAL material. V.L. T. MATSUSHITA, M. FUNAKI (National Space Development Agency of Japan, Tokyo), Y. IDO, K. IWAMOTO, Y. MlYAZAKl (Toshiba C3rp., Kawasaki, Japan) et al. IN: International A87-19342 Symposium on Space Technology and Science, 14th, Tokyo, Japan, USE OF GRAPHITE/EPOXY COMPOSITES IN SPACECRAFT May 27-June 1, 1984, Proceedings . Tokyo, AGNE Publishing, STRUCTURES - A CASE STUDY Inc., 1984, p. 565-569. R. D. JAMISON (U.S. Naval Academy, Annapolis, MD), 0. H. Facilities developed for NASDA to study the degradation and GRIFFIN, JR. (Virginia Polytechnic Institute and State University, charging effect of thermal control materials are described. The Blacksburg), J. A. ECKER, and W. E. SKULLNEY (Johns Hopkins combined irradiation test facility for thermal control materials and University, Laurel, MD) Johns Hopkins APL Technical Digest the electron irradiation test are presented. The test facility is (ISSN 0270-5214). vol. 7, July-Sept. 1986, p. 290-294. refs intended for the following two purposes: investigation of the effect The redesign of the Polar Bear satellite’s center support of individual parameters (UV wavelength, electron flux, and structure is taken as a demonstration case in evaluating the temperature) and investigation of combined irradiation of UV and applicability of graphite/epoxy composite structures for the electrons. The test samples of thermal-control material were fabrication of critical spacecraft structures. Attention is given to exposed to 20-keV electron irradiation with flux 2.7 x 10 to the the results of analyses conducted for the strength, stiffness, 14th e/sq cm hr. During the test, electrical discharges were thermal, and buckling characteristics of the support structure frequently observed on the surfaces of test samples such as design. It is found that the substitution of composite for metal silvered teflon and OSR. Their solar absorptance and emittance material is straightfoward and can be accomplished with available were measured in situ by using a dynamic thermal vacuum design tools. O.C. technique. Author A87-19343 EROSION STUDIES ON SOLAR MAX SAMPLES A87-18554 R. M. FRISTROM, R. C. BENSON, C. B. BARGERON, T. E. ELECTRICALLY CONDUCTIVE ORGANIC POLYMERS FOR PHILLIPS, C. E. VEST (Johns Hopkins University, Laurel, MD) et ADVANCED APPLICATIONS al. Johns Hopkins APL Technical Digest (ISSN 0270-5214), vol. D. €3. COTS and Z. REYES (SRI International, Menlo Park, CA) 7, July-Sept. 1986, p. 308-314. Research sponsored by the U.S. Air Force. Park Ridge, NJ, Noyes (Contract N00024-85-C-5301) Data Corp., 1986, 222 p. refs The condition of damaged material samples from the Solar Attention is given to the properties of electrically conducting, Max satellite, namely a kapton/dacron/aluminized mylar protective semiconducting, and semiinsulating polymers, with a view to the blanket, a piece of silver-coated teflon shielded from the sun, and conduction mechanisms involved and to the mechanical properties another such piece of teflon that had been exposed to solar and space-related systems applicability of the various substances. radiation, has been studied in order to infer the erosiveness of High electron mobilities are noted to be observed only in systems the near-space environment. Surface damage caused by high that form a periodic superlattice of localized states; substances energy molecular species, submicronic micrometeorite impacts, and synthesized on the basis of this model are not only highly low energy oxygen atom erosion are discussed in light of laboratory conductive but processable in organic solvents. Emphasis is given analyses of the materials after their subjection to simulations of to space applications. O.C. these processes. O.C.

50 07 ADVANCED MATERIALS

A87-19805 A87-21993 HOLOGRAPHIC NON-DESTRUCTIVE TESTING FOR ANALYSIS OF THE ION SPOT PHENOMENON ON COMPOSITE MATERIALS USED IN AEROSPACE BEAM-CHARGED DIELECTRICS M.-A. DE SMET (Bruxelles, Universite Libre, Brussels, Belgium) GORDON MCKEIL and K. G. BALMAIN (Toronto, University, IN: Optics in engineering measurement; Proceedings of the Canada) (IEEE, DNA, Sandia National Laboratories, and NASA, Meeting, Cannes, France, December 3-6, 1985 . Bellingham, WA, 1986 Annual Conference on Nuclear and Space Radiation Effects, Society of Photo-Optical Instrumentation Engineers, 1986, p. 23rd, Providence, RI, July 21-23, 1986) IEEE Transactions on 46-52. refs Nuclear Science (ISSN 0018-9499), vol. NS-33, Dec. 1986, pt. 1, An analysis and comparisons are presented for the holographic p. 1396-1401. refs interferometry and ultrasonic methods' results concerning the (Contract AF-AFOSR-84-0342; NSERC-A-4140) function of the application of external fields to a composite material Computer simulation of particle trajectories in two dimensions test specimen. Holographic interferometry is judged capable of using a simple static accumulated charge model reveals the yielding systematic process control data; it is noted that a slight mechanism for the focussing of ions into a central, sharply defined temperature elevation allows such defects as composite fiber 'spot', duplicating the luminescent spot which did not arc-discharge breaks, delaminations and disbonds to be visualized. O.C. observed during laboratory exposure of polymer film to monoenergetic electrons and low energy ions. A model which follows the time evolution of such charging situations is developed and initial results are presented. Author

A87-23702' National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. A87-20149 PROPERTIES AND POTENTIAL APPLICATIONS OF ADHESIVE BONDING OF AEROSPACE MATERIALS - SURFACE BROMINATED P-100 CARBON FIBERS CHARACTERIZATION OF METALLIC ADHERENDS D. A. JAWORSKE, J. R. GAIER, C. C. HUNG, and B. A. BANKS M. CHARBONNIER, M. ROMAND, A. ROCHE, and F. GAILLARD (NASA, Lewis Research Center, Cleveland, OH) SAMPE Quarterly (Lyon I, Universite, Villeurbanne, France) International Journal (ISSN 0036-0821). vol. 18, Oct. 1986, p. 9-14. refs of Adhesion and Adhesives (ISSN 0143-7496), vol. 6, Oct. 1986, A review of the properties and potential applications of p. 199-206. refs bromine-intercalated pitch-based carbon fibers is presented. The It is well known that surfaces of 'as-received' materials are dynamics of the intercalation reaction are summarized, and chemically very different from the bulk composition and are usually characteristics, such as resistivity, density, and stability, are unsuitable for adhesive bonding. Consequently, surfaces of such discussed. In addition, the mechanical and electrical properties of materials have to be submitted to appropriate chemical or bromine-intercalatedfiber-epoxy conposites will be addressed. With electrochemical prebonding treatments in order to modify both conductivities comparable to stainless steel, these brominated their morphology and chemistry. This paper discusses the surface carbon fibers may be used in a number of composite applications, characterization of aluminum, titanium, and their alloys at various such as electromagnetic interference shielding containers, large prebonding stages. Practical applications of X-ray fluorescence conductive space structures, lightning strike-tolerant aircraft spectroscopy, low-energy electron-induced X-ray spectroscopy, and surfaces, and aircraft deicing applications. Author glow discharge optical spectroscopy are described. Author A87-24919"# Physical Sciences, Inc., Andover, Mass. ENERGETIC OXYGEN ATOM MATERIAL DEGRADATION STUDIES GEORGE E. CALEDONIA and ROBERT H. KRECH (Physical Sciences, Inc., Andover, MA) AIAA, Aerospace Sciences Meeting, A87-21992' National Aeronautics and Space Administration. 25th, Reno, NV, Jan. 12-15, 1987. 12 p. refs Langley Research Center, Hampton, Va. (Contract NAS7-938) ELECTRON-RADIATION EFFECTS ON THE AC AND DC (AIAA PAPER 87-0105) ELECTRICAL PROPERTIES AND UNPAIRED ELECTRON As part of a study designed to test potential Shuttle surface DENSITIES OF THREE AEROSPACE POLYMERS materials for the extents of degradation and mass loss expected SHEILA ANN T. LONG, EDWARD R. LONG, JR. (NASA, Langley to be suffered in space from the velocity impacts of ambient oxygen Research Center, Hampton, VA), HEIDI R. RIES, and WYNFORD atoms, a novel technique was developed for generation of a high L. HARRIES (Old Dominion University, Norfolk, VA) (IEEE, DNA, flux of energetic oxygen atoms. The generation technique involves Sandia National Laboratories, and NASA, 1986 Annual Conference laser-induced breakdown of molecular oxygen followed by a rapid on Nuclear and Space Radiation Effects, 23rd, Providence, RI, expansion of energetic oxygen atoms. The high-velocity streams July 21-23, 1986) IEEE Transactions on Nuclear Science (ISSN developed in an evacuated hypersonic nozzle have average 0-atom 0018-9499), vol. NS-33, Dec. 1986, pt. 1, p. 1390-1395. refs velocities of about 5 to 13 km/s, with an estimated total production The effects of gigarad-level total absorbed doses from 1-MeV of 10 to the 18th atoms per pulse over pulse durations of several electrons on the post-irradiation alternating-current (ac) and microseconds. Results on preliminary material degradation tests direct-current (dc) electrical properties and the unpaired electron conducted with this test facility have been reported by Caledonia densities have been studied for Kapton, Ultem, and Mylar. The et al. (1987). Diagrams of the experimental setup are included. unpaired electron densities (determined from electron paramagnetic I.S. resonance spectroscopy) and the dc electrical conductivities of the irradiated materials were monitored as functions of time A87-27178" Virginia Polytechnic Inst. and State Univ., following the exposures to determine their decay characteristics Blacksburg. at room temperature. The elevated-temperature ac electrical SPACE RADIATION EFFECTS ON THE THERMO-MECHANICAL dissipations of the Ultem and Mylar were affected by the radiation. BEHAVIOR OF GRAPHITE-EPOXY COMPOSITES The dc conductivity of the Kapton increased by five orders of SCOTT M. MILKOVICH, CARL T. HERAKOVICH (Virginia magnitude, while the dc conductivities of the Ultem and Mylar Polytechnic Institute and State University, Blacksburg), and increased by less than an order of magnitude, due to the radiation. GEORGE F. SYKES (NASA, Langley Research Center, Hampton, The observed radiation-generated changes in the ac electrical VA) Journal of Composite Materials (ISSN 0021-9983), vol. 20, dissipations are explained in terms of known radiation-generated Nov. 1986, p. 579-593. refs changes in the molecular structures of the three materials. A (Contract NAG1 -343) preliminary model relating the dc electrical conductivity and the This investigation of composite material properties utilized unpaired electron density in the Kapton is proposed. Author T300/934 graphite-epoxy that was subjected to 1.O MeV electron

51 07 ADVANCED MATERIALS radiation for a total dose of 1.0 x 10 to the 10th rads at a rate of composites by reducing the residual fabrication stress and 5.0 x 10 to the 7th radslhour, simulating a worst-case exposure increased the matrix strength by metallurgical aging. Thermal equivalent to 30 years in space. Mechanical testing was performed expansion behavior of both groups after processing was insensitive on 4-ply unidirectional laminates over the temperature range of to thermal cycling. Data scatter was too large to determine effects -250 F (116 K) to +250 F (394 K). In-plane elastic tensile and of thermal cycling on the mechanical properties. The primary effects shear properties as well as strength were obtained. The results of processing and thermal cycling can be attributed to changes in show that electron radiation degrades the epoxy matrix and the metallurgical condition and stress state of the matrix. Author produces products that volatilize at the temperatures considered. These degradation products plasticize the epoxy at elevated N87-10932# Deutsche Forschungs- und Versuchsanstalt fuer temperatures and embrittle it at low temperatures, thereby altering Luft- und Raumfahrt, Brunswick (West Germany). Inst. fuer the mechanical properties of the composite. Author Strukturmechanik. THE K1-K2 INTERACTION FOR MATRIX SPLITTING IN A87-27936’# Physical Sciences, Inc., Andover, Mass. UNIDIRECTIONAL LAMINATES OF CARBON FIBER A HIGH FLUX SOURCE OF ENERGETIC OXYGEN ATOMS FOR REINFORCED EPOXY MATERIAL DEGRADATION STUDIES H. EGGERS and L. KIRSCHKE ln ESA Proceedings of an GEORGE E. CALEDONIA, ROBERT H. KRECH, and BYRON D. International Conference on Spacecraft Structures p 335-340 Apr. GREEN (Physical Sciences, Inc., Andover, MA) (Shuttle 1986 Environment and Operations II Conference, Houston, TX, Nov. Avail: NTlS HC A19/MF A01 13-15, 1985, Technical Papers, p. 153-159) AIAA Journal (ISSN Rectangular side-notched specimens of multilayered 0001-1452), vol. 25, Jan. 1987, p. 59-63. Previously cited in issue unidirectional off-axis laminates of carbon-fiber reinforced epoxy 03, p. 267, Accession no. A86-14399. refs T300-914C were tested for matrix splitting. For quasi-static loads (Contract NAS7-938) the notch opening displacements, specimen elongations and crack lengths were measured. A finite element technique combined with A87-31300’# National Aeronautics and Space Administration. theoretical formulas for the straining of the material at the crack Lewis Research Center, Cleveland, Ohio. tip were used. Cracks always develop parallel to the fibers. THE SURVIVABILITY OF LARGE SPACE-BORNE REFLECTORS Misaligned fibers or layers act as crack stoppers. In thin laminates UNDER ATOMIC OXYGEN AND MICROMETEOROID IMPACT the cracks initiate earlier but propagate with less speed than in DANIEL A. GULINO (NASA, Lewis Research Center, Cleveland, thick ones. The energy release rate is not a material constant, OH) AIAA, Aerospace Sciences Meeting, 25th, Reno, NV, Jan. suitable to describe the crack propagation uniquely. Cracks initiate 12-15, 1987. 9 p. Previously announced in STAR as N87-14423. by a critical combination of the stress intensity factors. Crack refs propagation depends predominatly on the crack opening mode 1 (AIAA PAPER 87-0341) and very little on the shear mode 2. ESA Solar dynamic power system mirrors for use on Space Station and other spacecraft flown in low earth orbit (LEO) are exposed N87-10933# Deutsche Forschungs- und Versuchsanstalt fuer to the harshness of the LEO environment. Both atomic oxygen Luft- und Raumfahrt, Oberpfaffenhofen (West Germany). and micrometeoroids/space debris can degrade the performance Fachbereich Technische Mechanik. of such mirrors. Protective coatings will be required to protect DEBONDING ANALYSIS OF THERMALLY STRESSED oxidizable reflecting media, such as silver and aluminum, from FIBER-REINFORCED COMPOSITE MATERIALS atomic oxygen attack. Several protective coating materials have F. G. BUCHHOLZ and K. H. SENGER ln ESA Proceedings of been identified as good candidates for use in this application. an International Conference on Spacecraft Structures p 341-346 The durability of these coating/mirror systems after pinhole defects Apr. 1986 have been inflicted during their fabrication and deployment or Avail: NTlS HC A19/MF A01 through micrometeoroid/space debris impact once on-orbit is of The effects of two ways of micromechanical modeling on the concern. Studies of the effect of an oxygen plasma environment debonding analysis of thermally stressed unidirectionally on protected mirror surfaces with intentionally induced pinhole fiber-reinforced composite materials are investigated. The models defects have been conducted at NASA Lewis and are reviewed. are a simple single circular unit cell and a more complex hexagonal It has been found that oxidation of the reflective layer and/or the unit cell embedded in the surrounding compound, as different substrate in areas adjacent to a pinhole defect, but not directly orders of approximation to a real composite material. Correlation exposed by the pinhole, can occur. Author between the thermally induced elastic strain energy and the energy release rate of a curved interface crack, debonding an individual N87-10184’# National Aeronautics and Space Administration. fiber from the adherent matrix material in both models is studied. Langley Research Center, Hampton, Va. The influence of increasing fiber volume fractions on the debonding EFFECTS OF THERMAL CYCLING ON GRAPHITE-FIBER-REIN- behavior is assessed. Results show that the elastic strain energies FORCED 6061 ALUMINUM induced in the models nearly coincide, although they differ distinctly G. A. DRIES (PRC Kentron, Inc., Hampton, Va.) and S. S. in their geometrical contours and boundary conditions. For fiber TOMPKINS Oct. 1986 29 p volume fractions 10% it is shown that only the more complex (NASA-TP-26’2; L-16139; NAS 1.60:2612) Avail: NTlS HC model can deliver relevant results for the thermally induced plane AO3/MF A01 CSCL 11D strain debonding process in a real material. ESA Graphite-reinforced aluminum alloy metal-matrix composites are among materials being considered for structural components in N87-10934# Societe Nationale lndustrielle Aerospatiale, Cannes dimensionally stable space structures. This application requires (France). materials with low values of thermal expansions and high specific SPACE TECHNOLOGIES AND MATERIALS: A LOOK BACK AND stiff nesses. They must remain stable during exposures to the space FUTURE PERSPECTIVES [TECHNOLOGIES ET MATERIAUX environment for periods extending to 20 years. The effects of SPATIAUX: RETROSPECTIVE ET PERSPECTIVES D’AVENIR] thermal cycling on the thermal expansion behavior and mechanical J. A. MASSONI and J. L. CECCONI ln ESA Proceedings of an properties of Thornel P100 graphite 6061 aluminum composites, International Conference on Spacecraft Structures p 347-351 Apr. as fabricated and after thermal processing to eliminate thermal 1986 In FRENCH strain hysteresis, have been investigated. Two groups of Avail: NTlS HC Al9/MF A01 composites were studied: one was fabricated by hot roll bonding The evolution in satellite construction materials from aluminum and the other by diffusion bonding. Processing significantly reduced alloys to carbon-resin structures is discussed. Future applications strain hysteresis during thermal cycling in both groups and improved of metal matrix composites, aluminum-lithium composites, and the ultimate tensile strength and modulus in the diffusion-bonded silicon carbide reinforced aluminum composites are examined. composites. Thermal cycling stabilized the as-fabricated ESA

52 07 ADVANCED MATERIALS

N87-10935# Deutsche Forschungs- und Versuchsanstalt fuer N87-10950# Office National d’Etudes et de Recherches Luft- und Raumfahrt, Brunswick (West Germany). Inst. for Structural Aerospatiales, Toulouse (France). Dept. d’Etudes et de Rech. en Mechanics. Technol. Spatiale. PERFORMANCE CHARACTERISTICS OF COMPOSITE DESIGN IMPROVEMENT AND RADIATION CONTAMINATION MATERIALS TESTS. PRESTUDY 1: ULTRAVIOLET RADIATION H. W. BERGMANN, M. GAEDKE, and H. C. GOETTING In ESA ACCELERATION. VOLUME 2 APPENDIX, DETAILED RESULTS Proceedings of an International Conference on Spacecraft Final Report [AMELIORATION ET ESSAIS: CONTAMINATION Structures p 353-359 Apr. 1986 PLUS IRRADIATION. PREETUDE 1: ACCELERATION DES Avail: NTlS HC Al9/MF A01 IRRADIATIONS ULTRAVIOLETTES. TOME 2 ANNEXES, Allowable stresses for multidirectional laminates with arbitrary RESULTATS DETAILLES] stacking orders are predicted analytically using the characteristics J. MARCO, P. MILLAN, A. PAILLOUS, C. SABLE, and J. SIFFRE of unidirectional plies established by test. The forecast properties Paris ESA Dec. 1985 200 p In FRENCH for static tension loading include first ply failure and ultimate (Contract ESTEC-5781/83-NL-AB) strength and take into account the state of prestress induced by (CERT-4193-VOL-2; ESA-CR(P)-2227-VOL-2; ETN-86-98106) widely varying environmental conditions. In laminates mechanically Avail: NTlS HC AO9/MF A01 fatigued at R = 0.1 the influences of temperature and moisture The influence of increasing ultraviolet radiation intensity on the are shown to be moderate. In matrix-controlled laminates, elevated degradation of satellite thermal control surface coatings is studied. temperature and moisture saturation degrade the fatigue strength, Several materials were insolated for the equivalent of 1000 hr while in fiber-controlled laminates the presence of moisture tends with intensities 2 to 8 times stronger than the radiation of the to be beneficial. In multidirectional laminates the slopes of the Sun, at wavelengths under 400 nm. Visible light and infrared were delta-N curves are essentially unaffected in various hot-wet filtered out. The materials included white paints, aluminized Kepton, conditions. Matrix-controlled laminates subjected to severe thermal black paints, alinum paints and silver coatings. The results are cycling exhibit strength and stiff ness degradations depending on extremely variable, the absorption spectra vary with the degradation the brittleness of the matrix systems. Moderate to severe matrix of the coating, and the degradation at the higher intensities is not cracking is observed. ESA always greater than at relatively low intensities. ESA

N87-10940# Societe Nationale lndustrielle Aerospatiale, N87-10951# Office National d’Etudes et de Recherches Saint-Medard-en-Jalles (France). Aerospatiales, Toulouse (France). Dept. d’Etudes et de Rech. en A METHOD OF STUDYING THE BEHAVIOR OF COMPOSITE Technol. Spatiale. MATERIALS IN SIMULATED SPACE ENVIRONMENTS [MOYEN IMPROVING THE IRRADIATION PLUS CONTAMINATION DETUDE DU COMPORTEMENT EN AMBIANCE SPATIALE TESTS. PRESTUDY 2: SUCCESSIVE IRRADIATIONS AND SIMULEE DE MATERIAUX COMPOSITES] SYNERGICS. VOLUME 1: TESTS AND CONCLUSIONS Final F. ALBUGUES, P. PLOTARD, M. F. GOMEZ (Office National Report [AMELIORATION ET ESSAIS: CONTAMINATION PLUS d’Etudes et de Recherches Aerospatiales, Toulouse, France), A. IRRADIATION. PREETUDE 2 IRRADIATIONS SUCCESSIVES ET PAILLOUS, and M. D. JUDD (European Space Agency. European SYNERGIE. TOME 1: ESSAIS ET CONCLUSIONS] Space Research and Technology Center, ESTEC, Noordwijk, J. MARCO, P. MILLAN, A. PAILLOUS, C. SABLE, and J. SIFFRE Netherlands) In ESA Proceedings of an International Conference Paris ESA Dec. 1985 65 p In FRENCH on Spacecraft Strictures p 393-397 Apr. 1986 In FRENCH (Contract ESTEC-5781/83-NL-AB) Avail: NTlS HC Al9/MF A01 (CERT-4193-VOL-3; CERT-419300/PR2/T01 -DERTS; A method to evaluate the mechanical properties of composite ESA-CR(P)-2227-VOL-3; ETN-86-98107) Avail: NTlS HC spacecraft structural materials in simulated space vacuum, A04/MF A01 radiation, and thermal conditions was developed. It can irradiate A simulation of 1 yr exposure to a geosynchronous orbit space in secondary vacuum a test batch of which a part is measured in environment was carried out. Ultraviolet radiation, protons, and situ and the rest afterwards. Different stages of aging due to UV electrons acted on surface coatings used on satellite thermal and electron irradiation can be accounted for. ESA control equipment. The low sensitivity of the optical measurement prevents quantitative comparison. Nevertheless, observations N87-10949# Office National d’Etudes et de Recherches regarding degradable materials are included. ESA Aerospatiales, Toulouse (France). Dept. d’Etudes et de Rech. en Technol. Spatiale. DESIGN IMPROVEMENT AND RADIATION, CONTAMINATION N87-10952# Office National d’Etudes et de Recherches TESTS. PRESTUDY 1: ULTRAVIOLET RADIATION Aerospatiales, Toulouse (France). Dept. d’Etudes et de Rech. en ACCELERATION, VOLUME 1 Final Report [AMELIORATION ET Technol. Spatiale. ESSAIS: CONTAMINATION PLUS IRRADIATION. PREETUDE 1: IMPROVING RADIATION PLUS CONTAMINATION TESTS. ACCELERATION DES IRRADIATIONS ULTRAVIOLETTES. PRESTUDY 2 SUCCESSIVE IRRADIATIONS AND SYNERGICS. TOME 1: ESSAIS ET CONCLUSIONS] VOLUME 2 ANNEXES. ANNEX 1: DETAILED RESULTS. ANNEX J. MARCO, P. MILLAN, A. PAILLOUS, C. SABLE, and J. SIFFRE 2 CONTROL AND IMPROVEMENT OF OPTICAL Paris ESA Dec. 1985 92 p In FRENCH MEASUREMENTS Final Report [AMELIORATION ET ESSAIS: (Contract ESTEC-5781/83-NL-AB) CONTAMINATION PLUS IRRADIATION. PREETUDE 2 (CERT-4193-VOL-1; CERT-419300/PRl /TO1 -DERTS; IRRADIATIONS SUCCESSIVES ET SYNERGIE. TOME 2 ESA-CR(P)-2227-VOL-l; ETN-86-98105) Avail: NTlS HC ANNEXES. ANNEXE 1: RESULTATS DETAILLES. ANNEXE 2 A05/MF A01 CONTROLE ET AMELIORATION DES MESURES OPTIQUES] The influence of increasing the ultraviolet radiation intensity on J. MARCO, P. MILLAN, A. PAILLOUS, C. SABLE, and J. SIFFRE the degradation of satellite thermal control surface coatings is Paris ESA Dec. 1985 63 p In FRENCH studied. Several materials were insolated for the equivalent of (Contract ESTEC-5781/83-NL-AB) 1000 solar hours with intensities 2 to 8 times stronger than the (CERT-4193-VOL-4; ESA-CR(P)-2227-VOL-4; ETN-86-98108) radiation of the Sun. at wavelengths under 400 nm. Visible light Avail: NTlS HC A04/MF A01 and infrared radiation were filtered out. The materials include white A simulation of 1 yr exposure to a geosynchronous orbit space paints, aluminized kapton, black paints, aluminum paints, and silver environment was carried out. Ultraviolet radiation, protons and coatings. The results are extremely variable, the absorption spectra electrons were used on surface coatings employed on satellite vary with the degradation of the coating, and the degradation at thermal control equipment. The low sensitivity of the optical the higher intensities is not always greater than at relatively low measurements precludes a quantitative comparison. Nevertheless, intensities. ESA observations regarding degradable materials are included. ESA

53 07 ADVANCED MATERIALS

N87-10954# Office National d'Etudes et de Recherches These included some new glasses, glass-ceramics, fibers and Aerospatiales, Toulouse (France). Dept. d'Etudes et de Rech. en composites such as low expansion copper aluminosilicate glasses, Technol. Spatiales. hollow and oval glass fibers and hollow fiber-glass-polymer IMPROVING RADIATION/CONTAMINATION TESTS Final composites. The low temperature expansion coefficients, elastic Report [AMELIORATION DES ESSAIS: CONTAMINATION PLUS moduli and damping constants were measured. Recommendations IRRADIATION] are made for further research and development of some selected J. MARC0 and A. PAILLOUS Paris ESA Jul. 1985 95 p materials which appeared to be promising candidates for spacecraft In FRENCH structures. G RA (Contract ESTEC-5781/83-NL-AB) (CERT-419300/1 -DERTS ESA-CR(P)-2245; ETN-86-98123; PS-4) Avail: NTlS HC A05/MF A01 The characteristics of optical fibers in the wavelengths from 300 to 2500 nm are studied in order to define an improved optical N87-13572# United Kingdom Atomic Energy Authority, Hatwell spectral measuring instrument able to determine in situ the (England). Polymer and Composites Group. reflection factor of satellite coatings. The measuring system would DEVELOPMENT OF A CONTINUOUS MANUFACTURING have fixed samples and movable detector (optical fibers) in a METHOD FOR A CFRP COLLAPSIBLE TUBE MAST Final high vacuum environment. A detailed study of optical fiber bundles Report is included. Energy balance of different systems using fibers is D. H. BOWEN, R. DAVIDSON, R. J. LEE, and T. THORPE Jun. compared. Possible solutions are examined concluding that 1986 105p improved systems based on the use of optical fibers are feasible. (Contract ESTEC-B106/84/NL/AN(SC)) ESA (AERE-G-3898; HL86/1252(C14)) Avail: NTlS HC AO6/MF A01 A sequential molding process was developed for forming N87-10960'# National Aeronautics and Space Administration. continuous lengths of profiled carbon fiber reinforced plastic (CFRP) Lewis Research Center, Cleveland, Ohio. sheet, and for the edge-bonding of two identical profiles to produce OXIDATION-RESISTANT REFLECTIVE SURFACES FOR SOLAR a lenticular-shaped collapsible tube mast (CTM). The process was DYNAMIC POWER GENERATION IN NEAR EARTH ORBIT designed to enable a wide range of CTM sizes, characterized by D. A. GULINO, R. A. EGGER (Cleveland State Univ., Ohio), and the shape radius r, to be produced, and it will accept either W. F. BANHOLZER (General Electric Co., Schenectady, N. Y.) thermosetting or thermoplastic matrix composites. The Tube 1986 16 p Presented at the 33rd National Symposium of the Manufacturing Method (TMM) was proved by the construction of National Vacuum Society, Baltimore, Md., 27-31 Oct. 1986 a laboratory scale rig and its use to produce continuously 10 m (NASA-TM-88865; E-3268; NAS 1.1 5:88865) Avail: NTlS HC lengths of mast profile of uniform section and surface finish. The A02/MF A01 CSCL 106 mechanical properties of the fabrics impregnated with the two Reflective surfaces for space station power generation systems resins were measured to provide basic tube mast design data. are required to withstand the atomic oxygen-dominated Viscoelastic relaxations in both types of composites were environment of near Earth orbit. Thin films of platinum and rhodium, determined after storing sections of mast profile in the flattened which are corrosion resistant reflective metals, have been deposited condition over periods of time as a function of temperature. by ion beam sputter deposition onto various substrate materials. Author Solar reflectances were then measured as a function of time of exposure to a RF-generated air plasma. Similarly, various protective coating materials, including MgF2, Si02, A1203, and Si3N4, were deposited onto silver-coated substrates and then exposed to the N87-13589# Deutsche Forschungs- und Versuchsanstalt fuer plasma. Analysis of the films both before and after exposure by Luft- und Raumfahrt, Cologne (West Germany). both ESCA and Auger spectroscopy was also performed. The ACTIVITIES REPORT IN MATERIALS AND CONSTRUCTION results indicate that Pt and Rh do not suffer any loss in reflectance Annual Report, 1985 [FORSCHUNGSBEREICH WERKSTOFFE over the duration of the tests. Also, each of the coating materiais UND BAUWEISEN] survived the plasma environment. The ESCA and Auger analyses 1985 114p In GERMAN are discussed as well. Author (ISSN-0174-3910; ETN-86-98280) Avail: NTlS HC AO6/MF A01 Research in materials and construction methods is presented. N87-10982# Ern0 Raumfahrttechnik G.m.b.H., Bremen (West Structural mechanics, aeroelasticity, and space simulation are Germany). covered. ESA COMPOSITES DESIGN HANDBOOK FOR SPACE STRUCTURE APPLICATIONS. EXECUTIVE SUMMARY Final Report Paris ESA Sep. 1985 6 p (Contract ESTEC-5816/84-NL-P6(SC)) (ESA-CR(P)-2196; ETN-86-98082) Avail: NTlS HC AOP/MF A01 N87-14383'# National Aeronautics and Space Administration. The ESA composites design handbook is divided into eight Goddard Space Flight Center, Greenbelt, Md. main chapters. These chapters are entitled: Handbook organization RESULTS OF EXAMINATION OF MATERIALS FROM THE and user instructions; Material properties and applications; SOLAR MAXIMUM RECOVERY MISSION Calculation methods of laminates; General design aspects; Load J. J. PARK ln its Proceedings of the SMRM Degradation Study transfer and design of joints; Structural design; Integrity control; Workshop p 21 1-226 1985 and Verification guidelines. ESA Avail: NTlS HC A16/MF A01 CSCL 226 Four years and two months in space at 310 nautical miles N87-12601# California Univ., Los Angeles. Dept. of Materials orbit has produced different effects on Kapton, silver/Teflon, and Science and Engineering. on aluminum. Kapton, a polyimide, lost up to 31% in thickness, NEW MATERIALS FOR SPACECRAFT STABILITY AND though other locations showed much less loss. The degradation DAMPING: A FEASIBILITY STUDY Final Technical Report, 1 of silver/Teflon was drastic but very localized, due perhaps to the Oct. 1983 - 30 Sep. 1984 formation of silver oxide, Ag20, through cracks in the protective J. D. MACKENZIE Nov. 1985 52 p lnconel layer which exposed the silver to the oxygen atom (Contract AF-AFOSR-0221-83) environment. Penetrations of the thin aluminum sheet in the form (AD-A169826; AFOSR-86-0308TR) Avail: NTlS HC A04/MF A01 of thermal louvers and also of the thermal blanket material due to CSCL 11D unknown particles were unexpected, making the debris a potentially A preliminary feasibility study has been conducted on some serious problem because of the threat of damage to components. new materials for use as structure components of spacecrafts. Author

54 07 ADVANCED MATERIALS

N87-14384'# Johns Hopkins Univ., Laurel, Md. Applied Physics N87-14388'# National Aeronautics and Space Administration. Lab. Marshall Space Flight Center, Huntsville, Ala. STUDIES OF EROSION OF SOLAR MAX SAMPLES OF KAPTON SSM ATOMIC OXYGEN REACTIONS ON KAPTON AND AND TEFLON SlLVERlZED TEFLON R. M. FRISTROM, R. C. BENSON, C. B. BARGERON, T. E. R. LINTON and A. WHITAKER ln NASA. Goddard Space Flight PHILLIPS, C. E. VEST, C. H. HOSHALL, F. G. SATKIEWICZ, and Center Proceedings of the SMRM Degradation Study Workshop 0. M. UY ln NASA. Goddard Space Flight Center Proceedings p 265-272 1985 of the SMRM Degradation Study Workshop p 227-242 1985 Avail: NTlS HC Al6/MF A01 CSCL 228 Avail: NTlS HC Al6/MF A01 CSCL 228 Surface morphology studies using scanning electron microscopy Several samples of Kapton and Teflon which was exposed to on Kapton and lnconel silver coated Teflon material samples solar radiation were examined. The samples represent material retrieved from the Solar Maximum Mission spacecraft revealed behavior in near Earth space. Clues to the identity of erosive significant changes attributed to orbital atomic oxygen induced processes and the responsible species were searched for. Interest reactions. The Kapton recession observed on the aluminized centered around oxygen atoms which are ubiquitous at these Kapton material samples appeared equivalent in nature with that altitudes and are known to erode some metal surfaces. Three observed on previous Space Shuttle LEO missions. SSM Teflon diagnostic methods were employed: optical microscopy, scanning taped material samples, coated on the back side with films of electron microscopy, and fourier transform infrared spectroscopy. lnconel protected silver were observed degraded on both sides. Two types of simulation were used: a flow containing low energy Visibly severe reactions on the back side produced total blackening, oxygen atoms and bombardment with 3000 volt Ar ions. Results generally restricted to areas of tape with a narrow direct view-factor and conclusions are presented. E.R. of the external orbital environment. High magnification scanning electron microscope views provided evidence of near total silver reaction, flaking, and subsequent erosion of the underlying Teflon itself. Only three of the extensive S.E.M. photographs illustrating the basic reactions observed are included pending further detailed investigations. E.R. N87-14385'# National Aeronautics and Space Administration. Lyndon B. Johnson Space Center, Houston, Tex. ANALYSIS OF MICROMETEORITE MATERIAL CAPTURED BY THE SOLAR MAX SATELLITE L. S. SCHRAMM (Lockheed Engineering and Management Services Co., Inc., Houston, Tex.), D. S. MCKAY, H. A. ZOOK, and G. A. ROBINSON ln NASA. Goddard Space Flight Center Proceedings N87-14389'# National Aeronautics and Space Administration. of the SMRM Degradation Study Workshop p 243-244 1985 Langley Research Center, Hampton, Va. Avail: NTlS HC Al6/MF A01 CSCL 228 PRELIMINARY RESULTS OF SMM EXPOSED ALUMINIZED A Solar Maximum satellite was retrieved and repaired after KAPTON AND SILVERED TEFLON being subjected for four years and 55 days to impacts by 6. SANTOS-MASON In NASA. Goddard Space Flight Center micrometeorites and Earth-orbiting space debris. The chemical Proceedings of the SMRM Degradation Study Workshop p 273-286 variety and physical condition of particles associated with two 1985 particular impact structures in the insulation blanket of the main Avail: NTlS HC AlG/MF A01 CSCL 228 electronics box are studied. A scanning electron microscope Early Space Shuttle flights revealed that organic materials, such equipped with an energy dispersive X ray analyzer was used to as those used in thermal control blankets and paints in the payload determine morphology and chemistry of impacted areas and bay, were adversely affected in the low Earth orbit environment. associated particles. Some details are discussed. E.R. Examination of eroded surfaces on these early flights and materials experiments performed on subsequent flights led to the conclusion that atomic oxygen present at Shuttle operating altitudes was responsible for surface degradation. The Solar Maximum Mission provided surfaces that had been exposed in real time to atomic oxygen and ultraviolet radiation. Preliminary results of studies of N87-14386*# National Aeronautics and Space Administration. the microscopic surface effects on silvered Teflon and aluminized Lyndon 6.Johnson Space Center, Houston, Tex. Kapton used for thermal control on the Solar Maximum Mission EXAMINATION OF RETURNED SOLAR-MAX SURFACES FOR are presented. E.R. IMPACTING ORBITAL DEBRIS AND METEOROIDS D. J. KESSLER, H. A. ZOOK, A. E. POTTER, D. S. MCKAY, U. S. CLANTON (Department of Energy, Las Vegas, Nev.), J. L. WARREN (Northrop Services, Inc., Houston, Tex.), L. A. WATTS, R. A. SCHULTZ (Purdue Univ., West Lafayette, Ind.), L. S. SCHRAMM (Lockheed Engineering and Management Services Co., Inc., Houston, Tex.), S. J. WENTWORTH et al. ln NASA. Goddard N87-14391*# National Aeronautics and Space Administration. Space Flight Center Proceedings of the SMRM Degradation Study Goddard Space Flight Center, Greenbelt, Md. Workshop p 245-246 1985 ANALYSIS OF NORMAL AND TRANSPARENT SILVER Avail: NTlS HC A16/MF A01 CSCL 228 TEFLON The thermal insulation of the Solar Maximum Mission launched W. K. STUCKEY, A. A. GALUSKA, and J. UHT ln its Proceedings on 14 February 1980 which consisted of 17 layers of alumized of the SMRM Degradation Study Workshop p 317-336 1985 Kapton offers an excellent opportunity to obtain chemistry of Avail: NTlS HC Al6/MF A01 CSCL 22B impacting particles. To date, approximately 0.7 sq. met. of the Samples of Inconel/silver/Teflon exposed to solar radiation, insulation and 0.05 sq. met. of the aluminum louvers have been and atomic oxygen on Solar Max were microcharacterized. Those mapped by optical microscope for crater diameters larger than 40 samples exposed to atomic oxygen from the metallic side had microns. Atomic oxygen has eroded up to 20 microns of the become transparent while those exposed from the Teflon side exposed Kapton surfaces removing the older and smaller craters. remained reflective. The difference between the transparent and The crater size distribution found on 3 different Kapton surfaces non-transparent material was determined. Microcharacterization of is shown. About 250 chemical spectra were recorded of particles these Inconel/silver/Teflon samples was performed using scanning observed in or around impact pits or in the debris pattern found electron microscopy with windowless energy dispersive X ray on the second layer beneath impact holes in the outer layer. The analysis, secondary ion mass spectrometry, and X ray debris populations are listed and discussed. E.R. photoelectron spectroscopy. Author

55 wl ADVANCED MATERIALS

N87-14392*# Jet Propulsion Lab., California Inst. of Tech., and projected material properties to provide an indication of key Pasadena. Applied Mechanics Technology Section. payoffs for material development. In Task 7, a set of material DEGRADATION STUDIES OF SMRM TEFLON development recommendations was generated. Author R. H. LIANG, K. L. ODA, and S. Y. CHUNG ln NASA. Goddard Space Flight Center Proceedings of the SMRM Degradation Study N87-16929# Dornier-Werke G.m.b.H., Friedrichshafen (West Workshop p 337-342 1985 Germany). Avail: NTlS HC Al6/MF A01 CSCL 228 ANALYSIS OF HIGH PRECISION COMPOSITE SANDWICH A working group was organized to study materials and ANTENNAS components of the Solar Max Satellite (SMS) that was returned G. HELWIG ln ESA Proceedings of the Second ESA Workshop by the STS 41C. These materials were exposed in space for 50 on Mechanical Technology for Antennas p 51-55 Aug. 1986 months and represent the only real time long term exposure data Avail: NTlS HC A12/MF A01 available to date. In the molecular modeling of material and A data base for all common types of spacecraft antenna skin energetic oxygen atom interaction, it is pointed out that the and core materials was established. Based on these material importance of developing correlation between accelerated exposure properties, it is possible to predict accurately the performance of data from STS and some real time data. In particular, it was high precision antennas, and there is good agreement between predicted that Teflon which showed no detectable degradation on analyses and tests. The orthotropic behavior of the sandwich should various STS flights may be susceptible to atomic oxygen be improved by developments of skin and core materials. The degradation under real time conditions. Initial inspection of returned research should be directed to a composite sandwich with an SMS samples showed that Teflon suffered visual damage such overall coefficient of expansion close to zero, giving composite as cracking and yellowing. The results of examination of these sandwich panels with accuracies better than 1 micron rms for samples are given. Author most kinds of temperature loads. ESA

N87-15252# Indian Space Research Organization, Trivandrum. N87-16930# Rome Univ. (Italy). Dept. of Aerospace. POSSIBLE AREAS OF COLLABORATION BETWEEN DFVLR EFFECTS OF CURING STRESSES ON COMPOSITE AND ISRO IN THE FIELDS OF STRUCTURES AND STRUCTURES MATERIALS M. MARCHETTI, F. MORGANTI (Selenia S.p.A., Rome, Italy), and V. GOWARIKER ln DFVLR Colloquium about Joint Projects within S. TlZZl ln ESA Proceedings of the Second ESA Workshop on the DFVLR/ISRO Cooperation p 143-148 Jul. 1986 Mechanical Technology for Antennas p 57-62 Aug. 1986 Avail: NTlS HC A08/MF A01; DFVLR, Cologne, West Germany Sponsored by Max-Planck Inst. DM 46 Avail: NTlS HC A12/MF A01 Research possibilities in large space structures and microgravity The effects of the residual stresses which arise during the experiments on composites and polymers are outlined. ESA manufacturing of laminates constituting the skins of high stability telecommunications antennas for space applications are discussed. N87-15990# Joint Publications Research Service, Arlington, Va. A dedicated software to simulate the behavior of a composite OVERVIEW OF PLANNED TESTS OF SPACE MATERIALS structure from the curing temperature to the room condition was In its Japan report: Science and Technology (JPRS-JST-86-018) developed. The numerical simulation method takes into account p 41-43 2 Jul. 1986 Transl. into ENGLISH from Toshi Keizai all the nonlinearity effects which influence the final results, like (Tokyo, Japan), Jan. 1986 p 52-53 viscoelastic properties of the material (creep) and the dependance Avail: NTlS HC A05/MF A01 of the mechanical properties on temperature. ESA The National Space Development Agency (Japan) started space materials tests by using the two-stage rocket TT Ill 500 A. As the N87-16936# Selenia S.p.A., Rome (Italy). next step, full scale space tests that make use of the Spacelab DEVELOPMENT OF LIGHTWEIGHT DIMENSIONALLY STABLE are scheduled to take place in early 1988. The next rounds of CARBON FIBER COMPOSITE ANTENNA REFLECTORS FOR tests that follow will take place on the space station. These projects THE INSAT-1 SATELLITE are briefly outlined. B.G. A. PACE, I. LAROSA, and R. STONIER ln ESA Proceedings of the Second ESA Workshop on Mechanical Technology for N87-16015*# Ametek, Inc., Anaheim, Calif. Composite Materials Antennas p 103-110 Aug. 1986 and Applications Div. Avail: NTlS HC A12/MF A01 ADVANCED COMPOSITES FOR LARGE NAVY SPACECRAFT A lightweight dimensionally stable carbon fiber composite WILLIAM E. DAVIS ln NASA. Langley Research Center deployable antenna reflector structure utilizing a rib stiffened thin NASA/DOD Control/Structures Interaction Technology, 1986 p shell design was developed. Reflectors based on this design were 1-10 NOV.1986 manufactured and tested for the INSAT-1 satellites, and the same Avail: NTlS HC A23/MF A01 CSCL 11D technology was used for the reflectors for the ARABSAT satellites. An overview is given of work conducted on contract for the Structural materials were qualified and used on antenna reflector Naval Sea Systems Command. The objective of this contract was structures. The outstanding in-orbit performance of eight antennas to provide direction for the development of high modulus graphite on two INSAT-1 and two ARABSAT satellites, clearly demonstrates reinforced metal matrix composites. These advanced materials can the technical success of the program. Three additional satellites have a significant effect on the performance of a spacecraft before, with six more antennas/reflectors will be launched. ESA during and after an evasive maneuver. The work conducted on this program was organized into seven technical tasks. Task 1 N87-17056# Aeritalia S.p.A., Torino (Italy). Space System Div. was development of a generic Navy spacecraft model. Finite THE WELDING OF ALUMINUM ALLOYS A NEW TECHNOLOGY element models of candidate structural designs were developed. IN SPACE APPLICATION In Task 2, the finite-element model(s) of the structure were used P. MARCHESE and G. BANING ln AGARD Advanced Joining of to conduct analytical assessments involving conventional materials, Aerospace Metallic Materials 11 p Jul. 1986 resin matrix composites and metal matrix composites (MMC). In Avail: NTlS HC A12/MF A01 Task 3 and 4, MMC material design, fabrication and evaluation The optimization of the structural weight of the Spacelab was conducted. This consisted of generating material designs and structure, the first European manned laboratory designed according developing a data base for a broad range of graphite reinforced to shuttle requirements, led to the choice of 2219-T851 aluminum MMC materials. All material was procured according to alloy, T.I.G. welded with the process completely developed and specifications which set material quality and material property qualified from Aeritalia as briefly described is this paper. To standards. In Task 5, a set of evasive maneuvering requirements demonstrate the high quality and reliability of the welded primary were derived and used in Task 6 to conduct analytical simulations. structure, new inspection techniques, many different tests on the These analytical simulations used current SOA material properties welded joint, and expensive fracture mechanics analysis were

56 07 ADVANCED MATERIALS

applied. The main assumptions and results are presented. The N87-18015# Centre d'Etudes et de Recherche de la main efforts were concentrated on the reduction of number and Machine-Outil, Saint-Martin-d'Heres (France). Lab. TIM3. size of welding defects, improving, on the one side, the welding DIGITAL IMAGE PROCESSING BINARY IMAGES technique and on the otherside, inspecting single defects after J. M. CHASSERY ln Von Karman Inst. for Fluid Dynamics Flow fracture mechanics analysis based on sophisticated measurement Visualization and Digital Image Processing 13 p 1986 of their dimensions, on the schematization of embedded flaw in Avail: NTlS HC A24/MF A01 tension and bending, and on carefull measurement of material The basic geometric concepts used to describe the spatial properties. Possible improvements of T.I.G. application for future organization of the points on the support of the image are analyzed. space programs (space station) or its substitution with plasma The definitions include connectedness, connected components, welding processes are also mentioned. Author interior and border, picture representation, structure representation, and interpretation modes. An iterative method for image labeling is described. Structure interpretation by Fourier representation of contour and filtering spline functions approximation methods are commented on. ESA

N87-17863# Martin Marietta Aerospace, Denver, Colo. N87-18613'# National Aeronautics and Space Administration. METALLURGICAL CHARACTERIZATION OF THE INTERFACES Langley Research Center, Hampton, Va. AND THE DAMPING MECHANISMS IN METAL MATRIX SEAMLESS METAL-CLAD FIBER-REINFORCED ORGANIC COMPOSITES Progress Report, 1 Oct. 1985 - 30 Sep. 1986 MATRIX COMPOSITE STRUCTURES AND PROCESS FOR MOHAN S. MlSRA 30 Sep. 1986 5 p THEIR MANUFACTURE Patent Application (Contract NO0014-84-C-0413) RAYMOND M. BLUCK, inventor (to NASA) (Lockheed Missiles (AD-A173470; MCR-85-605-ISSUE-4) Avail: NTlS HC A02/MF and Space Co., Sunnyvale, Calif.), HAROLD G. BUSH, inventor A01 CSCL 11D (to NASA), and ROBERT R. JOHNSON, inventor (to NASA) 21 High inherent damping is a material property requirement to Oct. 1986 10 p meet the need for dynamic dimensional precision and weight (NASA-CASE-LAR-13562-1; NAS 1.71 :LAR-13562-1; savings in space structures. A preliminary investigation indicates US-PATENT-APPL-SN-921572) Avail: NTlS HC A02/MF A01 that MMC exhibit improved damping with respect to conventional CSCL 11D structural alloys of aluminum or titanium. In the present The invention relates to seamless metal clad filament reinforced investigation, a graphite-aluminumcomposite (P55/6061) has been resin matrix composite tubular structures and processes for their selected to study the microstructural features and mechanisms manufacture and is particularly useful in the construction of responsible for damping in MMC. During this investigation, spacecraft and space structures. Metal clad composites make a methodology to measure damping by clamped free flexure and significant advancement over those composite systems being used uniaxial tension-tension test techniques were developed. Work for both spacecraft and aircraft; however, the material consolidation conducted within the reporting period: (1) Preliminary results with and tooling advances necessary to realize the potential of such free-free flexure indicate that this method can be used sucessfully metal clad composites had not hitherto been achieved. Accordingly, to measure damping in metal matrix composites; (2) TEM of Gr/AI it is an object of this invention to provide an efficient method of composites show that the dislocations adjacent to the fiber matrix producing seamless metal clad composite structures. A metallic interface are thermal expansion mismatch of the fiber and matrix outer sleeve is provided which is capable of enveloping a hollow during the fabrication process; (3) Strain amplitude dependent metallic inner member having continuous reinforcing fibers attached damping is the result of dislocation motion and correlates well to the distal end thereof. Inner member is then introduced into with the Granato-Lucke theory of dislocation damping. GRA outer sleeve until inner member is completely enveloped by outer sleeve. A liquid matrix material is then injected into the space between inner member and outer sleeve. A pressurized heat transfer medium is flowed through the inside of inner member, thereby forming a fiber reinforced matrix composite material. The wall thicknesses of both inner member and outer sleeve are then N87-17906*# National Aeronautics and Space Administration. reduced to the appropriate size by chemical etching, to adjust the Lewis Research Center, Cleveland, Ohio. thermal expansion coefficient of the metal-clad composite structure TRIBOLOGICAL PROPERTIES OF POLYMER FILMS AND SOLID to the desired value. The novelty of this invention resides in the BODIES IN A VACUUM ENVIRONMENT development of a efficient method of producing seamless metal ROBERT L. FUSARO 1987 34 p Prepared for presentation clad fiber reinforced organic matrix composite structures. NASA at the Annual Meeting of the American Society of Lubrication Engineers, Anaheim, Calif., 11-1 4 May 1987 N87-18669'# Boeing Aerospace Co., Seattle, Wash. (NASA-TM-88966; E-3429; NAS 1.1 5:88966) Avail: NTlS HC PROTECTIVE COATINGS FOR COMPOSITE TUBES IN SPACE A03/MF A01 CSCL 11B APPLICATIONS The tribological properties of ten different polymer based HARRY W. DURSCH and CARL L. HENDRICKS 1987 12 p materials were evaluated in a vacuum environment to determine Prepared for presentation at the 3rd International SAMPE their suitability for possible lubrication applications in a space Symposium, Anaheim, Calif., 6-9 Apr. 1987 environment, such as might be encountered on the proposed space (Contract NASl-16854) station. A pin-on-disk tribometer was used and the polymer (NASA-CR-178116; NAS 1.26:178116) Avail: NTlS HC A02/MF materials were evaluated either as solid body disks or as films A01 CSCL 118 applied to 440C HT stainless steel disks. A 440C HT stainless Protective coatings for graphitelepoxy (Gr/Ep) tubular steel hemispherically tipped pin was slid against the polymer structures for a Manned Space Station truss structure were materials. For comparison, similar tests were conducted in a evaluated. The success of the composite tube truss structure controlled air atmosphere of 50 percent relative humidity air. In depends on its stability to long-term exposure to the Low Earth most instances, the polymer materials lubricated much better under Orbit (LEO) environment with particular emphasis placed on atomic vacuum conditions than in air. Thus, several of the materials show oxygen. Concepts for protectively coating Gr/Ep tubes include promise as lubricants for vacuum applications. Friction coefficients use of inorganic coated metal foils and electroplating. These of 0.05 or less and polymer material wear rates of up to 2 orders coatings were applied to Gr/Ep tubes and then subjected to of magnitude less than in air were obtained. One material showed simulated LEO environmnet to evaluate survivability of coatings considerable promise as a traction drive material. Relatively high and coated tubes. Evaluation included: atomic oxygen resistance, friction coefficients (0.36 to 0.52) and reasonably low wear rates changes in optical properties and adhesion, abrasion resistancem were obtained in vacuum. Author surface preparation required, coating uniformity, and formation of

57 07 ADVANCED MATERIALS microcracks in the Gr/Ep tubes caused by thermal cycling. Program require, for a single or double curvature, two different solutions. results demonstrated that both phosphoric and chromic acid Author anodized AI foil provided excellent adhesion to Gr/Ep tubes and exhibited stable optical properties when subjected to simulated LEO environment. The Si02/AI coatings speuttered onto AI foils also resulted in an excellent protective coating. Electroplated Ni exhibited unaccepatble adhesion loss to Gr/Ep tubes during atomic A87-13706’ National Aeronautics and Space Administration, oxygen exposure. Author Washington, D.C. THE ROLE OF AUTOMATION AND ROBOTICS IN SPACE N87-19457# Materials Sciences Corp., Spring House, Pa. STATIONS THERMOVISCOELASTIC CHARACTERIZATION AND ANALYSIS D. C. BLACK (NASA, Office of Space Station, Washington, DC) OF FIBER COMPOSITE SPACE STRUCTURES Final Report, 1 IN: Space station automation; Proceedings of the Meeting, Oct. 1984 - 31 Dec. 1985 Cambridge, MA, September 17, 18, 1985 . Bellingham, WA, Society B. J. SULLIVAN, E. A. HUMPHREYS, and ZVI HASHIN Feb. of Photo-Optical Instrumentation Engineers, 1985, p. 2-9. 1986 170p Automation and robotics have played important roles in space (Contract F49620-85-C-0004) research, most notably in planetary exploration. While an increased (AD-A175024; MSC-TFR-1614/1505; AFOSR-86-2111TR) Avail: need for automation and robotics in space research is anticipated, NTlS HC A08/MF A01 CSCL 11D some of the major challenges and opportunities for automation This report begins with the development of the time and and robotics will be provided by the Space Station. Examples of temperature-dependent effective constitutive equations for these challenges are briefly reviewed. Author unidirectional fiber composites. The fibers were represented as transversely isotropic and linearly elastic, temperature dependent elements. The deviatoric components of the isotropic matrix material were treated as linearly viscoelastic and thermorheologically complex, while the dilatation components were A87-13707* National Aeronautics and Space Administration. represented as elastic and temperature dependent. Numerical Ames Research Center, Moffett Field, Calif. simulations of a series of isothermal creep tests were performed SPACE MISSIONS FOR AUTOMATION AND ROBOTICS to determine the effective creep compliance parameters of the TECHNOLOGIES (SMART) PROGRAM composite constitutive equations. The macromechanical response D. L. CIFFONE and H. LUM, JR. (NASA, Ames Research Center, of a composite structural element, as predicted by the effective Moffett Field, CA) IN: Space station automation; Proceedings of constitutive equations and their derived parameters, was then the Meeting, Cambridge, MA, September 17, 18, 1985. Bellingham, verified using results computed using a micromechanical model WA, Society of Photo-Optical Instrumentation Engineers, 1985, p. which explicitly included the fiber and matrix as discrete phases. 10-16. To determine the potential existence and form of a composite The motivations, features and expected benefits and complex modulus, the response of unidirectional composite applications of the NASA SMART program are summarized. SMART structural elements to simultaneous sinusoidal temperature and is intended to push the state of the art in automation and robotics, mechanical loads was investigated. Finally, solutions of free a goal that Public Law 98-371 mandated be an inherent part of vibration and transient dynamic analyses of some simple composite the Space Station program. The effort would first require tests of structures were performed to examine the effects of the sensors, manipulators, computers and other subsystems as seeds thermoviscoelastic behavior on the damped response of some for the evolution of flight-qualified subsystems. Consideration is simple composite structures. GRA currently being given to robotics systems as add-ons to the RMS, MMU and OMV and a self-contained automation and robotics module which would be tended by astronaut visits. Probable experimentation and development paths that would be pursued 08 with the equipment are discussed, along with the management structure and procedures for the program. The first hardware flight ASSEMBLY CONCEPTS is projected for 1989. M.S.K.

Includes automated manipulator techniques, EVA, robot assembly, teleoperators, and equipment installation. A87-13712 AN INTRODUCTION TO THE CONCEPT OF ROBOT FACTORS A87-11359# AND ITS APPLICATION TO SPACE STATION AUTOMATION SPACE CONSTRUCTIBLE RADIATOR ON-ORBIT ASSEMBLY W. C. CHIOU, SR. (Lockheed Research Laboratories, Palo Alto, P. J. OTTERSTEDT, J. HUSSEY, and J. P. ALARIO (Grumman CA) and S. A. STARKS (Texas, University, Arlington) IN: Space Aerospace Corp., Bethpage, NY) Journal of Spacecraft and station automation; Proceedings of the Meeting, Cambridge, MA, Rockets (ISSN 0022-4650), vol. 23, July-Aug. 1986, p. 397-400. September 17, 18, 1985 . Bellingham, WA, Society of Photo-Optical Previously cited in issue 17, p. 2472, Accession no. A85-37667. Instrumentation Engineers, 1985, p. 53-57. Basic operating considerations resulting from the unique A87-12285 environment of space are discussed, along with those resulting TWO-DIMENSIONAL ARTICULATED SYSTEMS DEVELOPABLE from the current and projected state of Automation and Robotics ON A SINGLE OR DOUBLE CURVATURE SURFACE (A&R) which will influence the initial layout and maintenance of A. ZANARDO (Padova, Universita, Padua, Italy) Meccanica (ISSN the Space Station. A concept called ’robot-factors’ is introduced 0025-6455), vol. 21, June 1986, p. 106-111. refs which deals with the telerobot working environment and its (Contract CNR-PSN-83-098) organizational relationships with other robots. The robot factors The geometry and the kinematics of two articulated systems are considered from the point of view of the overall system built up of a set of rigid rectilinear elements pin-jointed together architecture of the Space Station. Design considerations concerning are illustrated. In the first case, there is a kinematic grid which, the physical nature of the Space Station complex, as well as from its initial closed shape, expands along two directions on an those concerning the data management system, are examined. open (or closed) cylindrical surface. In the second case, the Emphasis is on making the robot’s tasks safe and easy to perform, kinematic grid expands on a double curvature surface like, for and on the telerobot’s welfare in terms of that of other cooperating instance, a paraboloid. The characteristics of the two surfaces telerobots in the performance of a common task. Author

58 08 ASSEMBLY CONCEPTS

A87-13714' Massachusetts Inst. of Tech., Cambridge. power is off or whenever commanded manually. During thermal REMOTELY MANIPULATED AND AUTONOMOUS ROBOTIC vacuum cycling qualification tests one of the brake motors suffered WELDING FABRICATION IN SPACE degradation of the slip torque and the brake failed failure to meet J. E. AGAPAKIS (Automatix, Inc., Billerica, MA) and K. MASUBUCHI specifications. Full capability returned in ambient atmosphere (MIT, Cambridge, MA) IN: Space station automation; Proceedings conditions. Subsequent brake tests were performed in temperatures of the Meeting, Cambridge, MA, September 17, 18, 1985 . at 10 C intervals between -36 to t-93 C and in ambient and Bellingham, WA, Society of Photo-Optical Instrumentation vacuum conditions while spinning the brakes in an unloaded Engineers, 1985, p. 68-77. NASA-MIT-supported research. refs condition. M.S.K. The results of a NASA sponsored study, performed in order to establish the feasibility of remotely manipulated or unmanned A87-15407 welding fabrication systems for space construction, are presented. MAINTAINABILITY TECHNOLOGY Possible space welding fabrication tasks and operational modes P. H. ZORGER (General Electric Co., Space Systems Div., Reston, are classified and the capabilities and limitations of human VA) IN: 1986 Annual Reliability and Maintainability Symposium, operators and machines are outlined. Human performance in Las Vegas, NV, January 28-30, 1986, Proceedings . New York, remote welding tasks was experimentally tested under the sensing Institute of Electrical and Electronics Engineers, Inc., 1986, p. and actuation constraints imposed by remote manipulation in outer 77-82. refs space environments. Proposals for the development of space A brief background and the current application status of welding technology are made and necessary future R&D efforts maintainability technology are presented. The application of this are identified. The development of improved visual sensing technology to large systems is discussed, emphasizing some of strategies and computer encoding of the human welding the problems associated with the technology when applied to a engineering expertise are identified as essential, both for human space environment. Three deficiencies in the technology are operator assistance and for autonomous operation in all phases discussed: the addition of a maintainability program task on of welding fabrication. Novel uses of machine vision for the testability to determine the 'time' to detect, locate, and isolate determination of the weld joint and bead geometry are proposed, faults/failures; 'time' data sources their application and use, and and a prototype of a rule-based expert system is described for a methodology to synthesize 'time' values; and the conversion of the interpretation of the visually detected weld features and 'time' values for use in a space environment. The frame work for defects. Author the discussion is a total and complete proposed maintainability program. Some additional and new tasks are suggested as needed A87-13715 additions to MIL-STD-470A and all tasks are defined for a complete MULTIARM COLLISION AVOIDANCE USING THE and comprehensive maintainability program. Author POTENTIAL-FIELD APPROACH J. K. MYERS (SRI International, Menlo Park, CA) IN: Space A87-15935# station automation; Proceedings of the Meeting, Cambridge, MA, ASSEMBLY OF THERMOELASTIC CONTINUOUS ELEMENTS September 17, 18, 1985 . Bellingham, WA, Society of Photo-Optical C. ARDUlNl (Roma, Universita, Rome, Italy) IAF, International Instrumentation Engineers, 1985, p. 78-87. refs Astronautical Congress, 37th, Innsbruck, Austria, Oct. 4-1 1, 1986. (Contract F49620-82-K-0034) 31 p. refs A generalized potential-field approach to manipulator collision (IAF PAPER 86-207) avoidance is presented. The potential-field approach consists of Techniques for assembling the continuous-scheme models of four algorithms: repulsion away from obstacles, attraction towards thermoelastic beams and plates derived by Arduini and Ponzi (1 982) a goal, a method of combining these, and a resulting method of and Arduini et al. (1985) into more complex structures are incrementing the arm. Alternatives for these algorithms are developed analytically and demonstrated. Both modal-synthesis discussed. A multiple-robot system demonstrating the concepts is and distributed-element approaches are extended to treat thermal described. The system uses a detailed rigid model of the entire and thermostructural problems, and numerical results for the static arms and surrounding objects to avoid collisions. The system heating of a tubular triangular beam are presented graphically. operates in close-to-real-time, and is demonstrated with two PUMA T.K. robots moving concurrently. Results are applicable to any type of anthropomorphic arm, including the Remote Manimulator System. A87-17401 Author ENGINEERING CONSIDERATIONS FOR ON-ORBIT WELDING OPERATIONS A87- 13949 J. K. WATSON (Rockwell International Corp., Rocketdyne Div., MATTER OF EASE Canoga Park, CA) Journal of the Astronautical Sciences (ISSN W. H. GREGORY Commercial Space (ISSN 8756-4831), vol. 2, 0021-9142), vol. 34, Apr.-June 1986, p. 121-132. refs Summer 1986, p. 58-60. The capability to perform on-orbit fabrication, maintenance, and The following human factors and robotics research vehicles, repair will become increasingly necessary with the deployment of developed at the Massachusetts Institute of Technology, are large, complex space systems in the 1990s and beyond. Just as presented: (1 ) Beam Assembly Teleoperator, (2) Multimode it is indispensible for such operations on earth, welding will be an proximity Operations Device, and (3) Integrated Control Station. important technology in space. This paper describes a number of Underwater simulations carried out to determine which tasks in welding processes that may be applicable, discusses requirements space should be accomplished by astronauts and which should for automation, and considers the supporting technologies required be handled by machine are described. Knowledge derived from for successful welding operations. Author the EASE (Experimental Assembly of Structures in EVA) experiment is reviewed. K.K. A87-18148 SPACE STATION CHALLENGE - ON-ORBIT ASSEMBLY OF A A87-15191# 75-KW POWER SYSTEM DEVELOPMENT OF A TEST PROCEDURE AND FACILITY FOR A. GLINES (TRW, Inc., TRW Space and Technology Group, THE INVESTIGATION OF A CANADARM JOINT BRAKE Redondo Beach, CA) IN: IECEC '86; Proceedings of the ANOMALY Twenty-first lntersociety Energy Conversion Engineering J. M. TRENOUTH (National Aeronautical Establishment, Ottawa, Conference, San Diego, CA, August 25-29, 1986. Volume 3 . Canada) and C. W. MACKENZIE (National Research Council of Washington, DC, American Chemical Society, 1986, p. Canada, Ottawa) Canadian Aeronautics and Space Journal (ISSN 1892-1897. refs 0008-2821), vol. 32, June 1986, p. 131-138. Designing the NASA Space Station (SS) presents formidable The 15 ft Remote Manipulator System arm of the Shuttle has challenges in all onboard systems. An excellent example is the spring-loaded clutch-type brakes which are activated whenever electrical power system (EPS), one of the largest systems on the

59 08 ASSEMBLY CONCEPTS station and the first to be assembled. This paper focuses on A87-20083*# National Aeronautics and Space Administration. those features of the SS EPS and its associated transverse truss Langley Research Center, Hampton, Va. which facilitate on-orbit assembly, servicing, and maintenance by PULTRUSION PROCESS DEVELOPMENT FOR LONG SPACE astronauts during extra-vehicular activity (EVA). It reviews NASA’s BOOM MODELS EPS assembly guidelines and design requirements, particularly MAYWOOD L. WILSON and ROBERT MISERENTINO (NASA, those relating to EVA. The paper concludes with a discussion of Langley Research Center, Hampton. VA) IN: Reinforced EVA design verification using astronauts working on full-scale PlasticsKomposites Institute, Annual Conference, 41st, Atlanta, equipment mock-ups in NASA’s neutral buoyancy facilities. GA, January 27-31, 1986, Preprint . Lancaster, PA, Technomic Author Publishing Co., 1986, 8 p. refs Long flexible boom models were required to develop ground vibration test methods for very low frequency space structures with applications to the proposed MAST program and Space Station. Pultruded quasi-isotropic composite beams were selected as an option over extruded aluminum alloy structures because of the lower cost potential, higher specific strength, flexural properties, A87-18481 and dynamic similarity considerations. A comparison is made of RESEARCH AND DEVELOPMENT OF A SMALL-SIZED SPACE four different pultrusions having varied matrices and fiber MANIPULATOR orientations. Test results indicate that the pultrusion process can K. MACHIDA, Y. TODA, T. IWATA, K. NAKAYAMA (Ministry of be used to produce quasi-isotropic composite structures by International Trade and Industry, Electrotechnical Laboratory, selective fiber orientation using the knit-lock fabric concept. Sakura, Japan), K. TSUCHIYA (Mitsubishi Electric Corp., Author Amagasaki, Japan) et al. IN: Space exploitation and utilization; Proceedings of the Symposium, Honolulu, HI, December 15-19, A87-23229*# National Aeronautics and Space Administration. 1985 . San Diego, CA, Univelt, Inc., 1986, p. 481-494. refs Langley Research Center, Hampton, Va. (AAS PAPER 85-660) A FLEXIBLE TELEROBOTIC SYSTEM FOR SPACE Recent space activities require many types of manipulators or OPERATIONS robots for assembling and servicing in space, and especially NANCY ORLANDO SLIWA and RALPH W. WILL (NASA, Langley demand small-sized manipulators for dexterous tasks. A 1meter Research Center, Hampton, VA) Workshop on Space Telerobotics, class articulated manipulator with space environment durability and Pasadena, CA, Jan. 20-22, 1987, Paper. 9 p. lightweight has been developed. This paper presents the system This paper describes the objective and design of a proposed design of the manipulator and development efforts of its goal-oriented knowledge-based telerobotic system for space components. Tribological study of mechanical elements in the operations. This design effort encompasses the elements of the vacuum environment, the design of actuator with high system executive and user interface and the distribution and general torque-to-weight ratio, the control system with the structure of the knowledge base, the displays, and the task multi-microprocessor and the dynamic control algorithm of the arm sequencing. The objective of the design effort is to provide an are described. A bilateral force-reflecting master-slave control expandable structure for a telerobotic system that provides system, using a six dimensional forceltorque sensor of the slave cooperative interaction between the human operator and computer arm is also discussed. Author control. The initial phase of the implementation provides a rule-based, goal-oriented script generator to interface to the existing control modes of a telerobotic research system, in the Intelligent Systems Research Lab at NASA Research Center. Author

A87-25756 THE ROLE OF ROBOTICS IN SPACE A87-18486 LELLAND A. C. WEAVER (Westinghouse Electric Advanced ROBOTICS CONCEPTS FOR THE U.S. SPACE STATION Production Technology, Ltd., Coventry, England) IN: Space Tech D. DORROUGH (Boeing Artificial Intelligence Center, Seattle, ’86; Proceedings of the International Conference, Geneva, WA) IN: Space exploitation and utilization; Proceedings of the Switzerland, May 14-16, 1986 . London, Online International, Ltd., Symposium, Honolulu, HI, December 15-19, 1985 . San Diego, 1986, p. 61-67. CA, Univelt, Inc., 1986, p. 539-568. refs Consideration is given to the monitoring and maintenance of (AAS PAPER 85-666) the Space Station’s systems and facilities using AI and robotics. The advanced basic concepts of machine intelligence are The applications of expert systems, signal processing, and voice covered that will be required to produce an operator system data entry or speech recognition to the Station are discussed and interface (OSI) to provide reasonable autonomy on the part of an examples are provided. The capabilities of the Remotely Operated extravehicular space-station automation. The OS1 is considered Service Arm, which is based on robotic systems and AI and is to for a free-flying robot that transits from one task space to another be utilized to repair the Station’s systems and facilities are in close proximity to the earth-orbiting Space Station. The OS1 described. The development of the Cell Management Language would thus perform path planning, track and control, object to coordinate the operations of different machines and create recognition, fault detection/isolation/correction, and plan automated factories with automated manufacturing and processing modifications in connection with the EV robot operations. To for the space Station is examined. I.F. implement such an OS1 implies the use of natural languages, voice recognition and synthesis, speech understanding, expert A87-25757 cooperative diagnostic and advisory knowledge systems, and A ROBOTIC SYSTEM FOR DEXTEROUS TASKS machine learning. The latter technologies are expected to evolve PlERGlOVANNl MAGNANI (Fabbrica ltaliana Apparecchiature through three distinct phases, where in the first phase the robot Radioelettriche S.p.A., Milan, Italy) IN: Space Tech ’86; is in the primary control loop (human directed), in the second the Proceedings of the International Conference, Geneva, Switzerland, robot is both primary controller and planner (human monitored), May 14-16, 1986 . London, Online International, Ltd., 1986, p. and in the third the robot provides its own goals (human instruction 69-89. and crisis intervention). Results of Project TAARGET (Transational There are a range of tasks and operative conditions in the Assessment of Autonomous Robotic Generational and Evolutionary space environment which may be efficiently managed by a ’small Technology) suggest that it will not be possible to deploy a fully dimension dexterous manipulator’. The configuration of such a autonomous EV robot and OS1 by the time the Space Station is manipulator and its main characteristics are considered in this constructed in orbit. D.H. paper. The aspects evaluated are: articulation, position/orientation

60 08 ASSEMBLY CONCEPTS envelope working area, actuation, and sensoriality. The robotic A87-31220# system analyzed is suitable to be mounted on a moving frame, to DEPLOYMENT ANALYSIS OF THE OLYMPUS ASTROMAST AND be brought in the working area, and then to perform a given COMPARISON WITH TEST MEASUREMENTS envelope of tasks. The moving frame can be a service manipulator M. EIDEN, 0. BRUNNER, and C. STAVRlNlDlS (ESA, European arm for external space applications or a moving guide for S/C Space Research and Technology Center, Noordwijk, Netherlands) internal applications. Author (Structures, Structural Dynamics, and Materials Conference, 26th, Orlando, FL, Apr. 15-17, 1985, Technical Papers. Part 1, p. 325-332) AW-27454 Journal of Spacecraft and Rockets (ISSN 0022-4650), vol. 24, SATELLITE CONSTRUCTION Jan.-Feb. 1987, p. 63-68. Previously cited in issue 13, p. 1894, GERARD MURPHY Space (ISSN 0267-954X), vol. 2, Dec. Accession no. A85-30264. 1986-Feb. 1987, p. 20, 21. Features and design goals of communications satellites which N87-10398 Stanford Univ., Calif. distinguish them from other high tech aerospace systems are RAPID PRECISE END POINT CONTROL OF A WRIST CARRIED outlined. Satellites must function reliably without maintenance, BY A FLEXIBLE MANIPULATOR Ph.D. Thesis thereby requiring redundant systems, expensive testing, and W. W. CHIANG 1986 141 p extensive failure mode identification analyses. Three-axis Avail: Univ. Microfilms Order No. DA8612724 stabilization is the favored mode for ensuring pointing accuracy The speed and accuracy of a robot manipulator can be for satellites. and for flexibility in spacecraft configuration design. increased by using end-point sensors for motion measurement AI components are being replaced by CFRP materials to lower and control, along with an accurate dynamic model of the the mass of spacecraft. Combination apogee and attitude thrusters mechanical system in the control algorithm. However, the have extended the lifetime of spacecraft to 10 yr. Finally, electric closed-loop control bandwidth of a robot manipulator is still pumps may replace He pressurant systems for electric propulsion physically limited ultimately by its structural flexibility, since the thrusters. M.S.K. end effector and the actuator are separated. Analyses were performed to study the dynamic interaction between the motion A87-276 16# of a minimanipulator and the structural flexibility of the main robot A PRELIMINARY LOGISTICS SUPPORT CONCEPT FOR arm. A plane-motion mechanical system was built to demonstrate SPACE-BASED SDI ASSETS several fast maneuvers of such a mini-macro manipulator system. FRANK W. MOSS, PAT R. ODOM, CLANCY J. HATLEBERG, A frequency identification scheme was also developed and THOMAS P. OBRIEN, BOBBIE L. JONES (Advanced Technology, implemented successfully in a closed-loop adaptive control on a Inc., Hutsville, AL) et al. IN: Space Logistics Symposium, 1st. separate mechanical laboratory system consisting of two inertia Huntsville, AL, Mar. 24-26, 1987, Technical Papers . New York, disks connected by a torsional rod. It is believed that the same American Institute of Aeronautics and Astronautics, 1987, p. frequency identification scheme can be used to improve further 94-102. the performance of the mini-macro manipulator system when (AIAA PAPER 87-0689) adaptive control is employed. Dissert. Abstr. Preliminary results are presented of studies being performed to define a logistics-support design for space-based SDI assets and the associated ground-based equipment. The studies are N87-15260*# National Aeronautics and Space Administration. considering the SDI systems architecture, the transportation Lyndon B. Johnson Space Center, Houston, Tex. architecture and the requirements for space assembly, maintenance MOBILE REMOTE MANIPULATOR SYSTEM FOR A and servicing. Several assumptions being made regarding the TETRAHEDRAL TRUSS Patent Application available launch systems, telerobotic systems, and the achievability CLARENCE J. WESSELSKI. inventor (to NASA) and WILLIAM C. of standardized parts are outlined, as are on-orbit hazards to repair SCHNEIDER. inventor (to NASA) 5 Sep. 1986 25 p crew and equipment. Optimized orbital positions for the weapons (NASA-CASE-MSC-20985-1; NAS 1.71 :MSC-20985-1; and surveillance systems being investigated are summarized, along US-PATENT-APPL-SN-904134) Avail: NTlS HC A02/MF A01 with the types of on-orbit support missions that would be flown. CSCL 228 The hardware requirements for the ground- and space-based SDI The mobile remote manipulator system (MRMS) was initially components are discussed. M.S.K. developed for transit about the trusses of the delta space station; however, it can be utilized just as easily for transit about the trusses of the dual keel station. The MRMS is comprised of a A87-31122# mobile platform B having a rail system formed of transversely DESIGN AND CONTROL OF MODULAR, KINEMATICALLY-RE- disposed T-shaped tracks, which engage with guide pins located DUNDANT MANIPULATORS at the nodes of the trusses. The guide pins form a grid and the JAMES P. KARLEN, JACK M. THOMPSON, JR., and JAMES D. tracks are so designed as to permit travel in either of two orthogonal FARRELL (Robotics Research Corp., Milford, OH) AIAA, NASA, directions. For travel the MRMS is provided with retractable, and USAF, Symposium on Automation, Robotics and Advanced reversible chain drive systems, which selectively engage sprockets Computing for the National Space Program, 2nd, Arlington, VA, on the guide pins for either longitudinal or transverse travel. The Mar. 9-1 1, 1987. 12 p. refs MRMS is also provided with direction changing means at the (AIAA PAPER 87-1694) intersection of the track systems to change from longitudinal to Design considerations, the database on robot manipulator arms transverse travel. The MRMS provides a near-uniform traversing and the requirements of manipulator arms for space applications velocity with minimal dynamic loading on the system. NASA are discussed. At least six degrees of freedom are needed for complete control of the position and orientation of the object held by a manipulator. For space applications, however, at least seven N87-15472# Fabrica ltaliana Apparecchi Radio S.p.A., Milan. degrees of freedom are asserted to be necessary for general ROBOT SYSTEM FOR DEXTEROUS TASKS (FOR SPACE purpose manipulation systems. Four basic types of general purpose APPLICATIONS) manipulator geometry are identified and the advantages of using PlERGlOVANNl MAGNANI 1986 16 p extra joints, i.e., kinematic redundancy, in an articulated arm are (ETN-86-98562) Avail: NTlS HC A02/MF A01 described, including extra Joints to permit flexibility in reaching A robot system for dexterous tasks in space applications, which around objects. Joint-mounted actuators are recommended for can be mounted on a moving frame, to be brought to the working spatial volume utilization efficiency. Techniques are described for area (by the moving frame) and then perform a given envelop of developing the motion Control software architecture, and design tasks, is discussed. The moving frame can be a service manipulator parameters are summarized for manipulator systems for various arm (for external space applications) or a moving guide (for internal space applications. M.S.K. applications). ESA

61 08 ASSEMBLY CONCEPTS

N87-16326*# National Aeronautics and Space Administration. arm-like assembly, thus providing an additional 3 degrees of Marshall Space Flight Center, Huntsville, Ala. freedom to the arm. NASA DESIGN AND ANALYSIS OF A KEEL LATCH FOR USE ON THE HUBBLE SPACE TELESCOPE JOHN CALVERT and MELANIE STINSON ln NASA. Lewis Research Center The 20th Aerospace Mechanics Symposium p 55-71 May 1986 Avail: NTlS HC A14/MF A01 CSCL 131 The mechanical design of the keel latch is discussed, as well N87-18984*# Grumman Aerospace Corp., Bethpage, N.Y. Space as the stress analysis of the keel latch. Background information; Systems Div. mechanical design requirements; some of the initial design TELEROBOTIC ASSEMBLY OF SPACE STATION TRUSS considerations; the design considerations that led to the selection STRUCTURE of the final design; the mechanics of the final design; testing that GRAHME FISCHER 1986 10 p Presented at the 1986 has been and will be accomplished to verify that design Space Telerobotics Workshop, Pasadena, Calif., 20-22 Jan. 1987 requirements have been met; and future tests are discussed. (Contract NAS9-17229) Author (NASA-CR-180239; NAS 1.26:180239) Avail: NTlS HC AO2/MF A01 CSCL05H N87-18595*# National Aeronautics and Space Administration. Discussed are methods of assembling the space station's Lyndon B. Johnson Space Center, Houston, Tex. structure utilizing only telerobotic devices, i.e.: (1) an approximately LOCKING HINGE Patent Application anthropomorphic telerobot with two dextrous arms; (2) the Shuttle CLARENCE J. WESSELSKI, inventor (to NASA) 29 Oct. 1986 Remote Manipulator System (SRNS); (3) various material handling 16 P machines. Timelines and task recommendations for autonomous (NASA-CASE-MSC-21056-1;NAS 1.71 :MSC-21056-1; operations are also included. Also described are some experimental US-PATENT-APPL-SN-924397) Avail: NTlS HC A02/MF A01 results comparing two manipulator control devices. Author CSCL 228 The space station configuration currently being studied utilizes structures which require struts to be hinged in the middle in stowed configuration and locked into place in the deployed configuration. Since there are hundreds of hinges involved, it is necessary that they have simple, positive locking features with a minimum of joint looseness or slack. The instant invention comprises two similar N87-19441# National Aerospace Lab., Amsterdam (Netherlands). housings hinged together with a spring loaded locking member Space Div. which assists in making the lock as well as breaking it. The instant RENDEZVOUS AND DOCKING AND SPACE ROBOTICS invention comprises a bracket hinge and bracket members with a PROXIMITY OPERATIONS. PART 5: EXECUTIVE SUMMARY spring biased and movable locking member. The locking or latch Final Report member has ear parts received in locking openings where wedging J. J. M. PRINS and C. N. A. PRONK 10 Jul. 1985 67 p surfaces on the ear parts cooperate with complimentary surfaces (Contract ESA-6060/84) on the bracket members for bringing the bracket members into a (NLR-TR-85099-U; ETN-87-99278) Avail: NTlS HC A04/MF A01 tight end-to-end alignment when the bracket members are in an In preparation for ESA's Columbus program, test requirements extended position. When the locking member is moved to an were derived for: full scale testing of final translation (last 10 m) unlocking position, pivoting of the hinge about a pivot pin including docking (RVD); full scale testing of any manipulator automatically places the locking member to retain the locking operations both for free space and during mechanical contact; member in an unlocked position. In pivoting the hinge from an and scaled testing of fly-around and translation along the docking extended position to a folded position, longitudinal spring members axis (RVD). Automatic as well as human operator controlled are placed under tension over annular rollers so that the spring operations need to be tested. ESA tension in a folded position assists in return of the hinge from a folded position to an extended position. Novelty lies in the creation of a locking hinge which allows compact storage and easy assembly of structural members having a minimal number of parts. NASA

N87-18596'# National Aeronautics and Space Administration. Lyndon B. Johnson Space Center, Houston, Tex. SPACE STATION ERECTABLE MANIPULATOR PLACEMENT N87-20351'# McDonnell-Douglas Astronautics Co., St. Louis, SYSTEM Patent Application Mo. MARGARET E. GRIMALDI, inventor (to NASA) 13 Nov. 1986 ADVANCED EVA SYSTEM DESIGN REQUIREMENTS STUDY 13 P EVASEPACE STATION SYTEM INTERFACE REQUIREMENTS (NASA-CASE-MSC-21096-1; NAS 1.71 :MSC-21096-1; T. G. WOODS 15 Nov. 1985 122 p US-PATENT-APPL-SN-929865) Avail: NTlS HC A02/MF A01 (Contract NAS9-17299) CSCL 228 (NASA-CR-171981; NAS 1.26:171981; MDC-W0070) Avail: NTlS A habitable space station has been proposed for low Earth HC AO6/MF A01 CSCL 228 orbit, to be constructed from components which will be separately The definition of the Extravehicular Activity (EVA) systems carried up from the Earth and thereafter assembled. A suitable interface requirements and accomodations for effective integration manipulating system having extraordinary manipulative capability of a production EVA capability into the space station are contained. is required. The invention is an erectable manipulator placement A description of the EVA systems for which the space station system for use on a space station and comprising an elongate, must provide the various interfaces and accomodations are lattice-like boom having guide tracks attached thereto, a provided. The discussion and analyses of the various space station carriage-like assembly pivotally mounted on and extending from areas in which the EVA interfaces are required and/or from which said dolly. The system further includes a turntable base pivotally implications for EVA system design requirements are derived, are interconnected with the proximal end of the boom and positioned included. The rationale is provided for all EVAS mechanical, fluid, either on a part of a transferring vehicle, or on another payload electrical, communications, and data system interfaces as well as component being carried by said transferring vehicle, or on the exterior and interior requirements necessary to facilitate EVA space station. Novelty resides in the use of a turntable base having operations. Results of the studies supporting these discussions a hinged boom with a dolly translatable therealong to carry the are presented in the appendix. B.G.

62 ~~

10 GENERAL

09 10

PROPULSION GENERAL

Includes propulsion concepts and designs utilizing solar sailing, Includes either state-of-the-art or advanced technology which may solar electric, ion, and low thrust chemical concepts. apply to Large Space Systems and does not fit within the previous categories. Publications of conferences, seminars, and workshops are covered in this area. A87-15913# ADVANCED PROPULSION STATUS IN WESTERN EUROPE M. ANDRENUCCI (Pisa, Universita, Italy), A. ATZEI, C. BARTOLI A87-10026 (ESA, European Space Research and Technology Centre, SPACE CONGRESS, 23RD, COCOA BEACH, FL, APRIL 22-25, Noordwijk, Netherlands), G. BAlOCCHl (SNIA-BPD S.p.A., 1986, PROCEEDINGS Colleferro, Italy), H. BASSNER (MBB/ERNO, Munich, West Congress sponsored by the Canaveral Council of Technical Germany) et al. IAF, International Astronautical Congress, 37th, Societies. Cape Canaveral, FL, Canaveral Council of Technical Innsbruck, Austria, Oct. 4-1 1, 1986. 22 p. refs Societies, 1986, 469 p. For individual items see A87-10027 to (IAF PAPER 86-172) A87-10053. A technology development assessment is made for Papers concerned with developing space for tomorrow’s society state-of-the-art spacecraft launch vehicles in Western Europe, are presented. Consideration is given to international space where ESA sponsorship is noted to have been extended to all activities, the use of computers in space, low-cost Shuttle payloads, major electric propulsion concepts and the full range of specific streamling ground operations, and the commercialization of space. impulse, thrust and power levels. Attention is given to such electric Topics discussed include contracts and management, Space propulsion concepts as field emission electric propulsion, RF ion Station technology, the effects of satellites on daily activities, thrusters, MPD, and electrostatic propulsion, as well as to activities second generation space transportation systems and launch under way in the universities of Giessen, Munich, Pisa, Rome, vehicles technology, and the use of robotics and AI in aerospace Stuttgart, and Vienna. The Comet Nucleus Sample Return mission’s operations. I.F. propulsion requirements are discussed. O.C.

A87-10997 A87-31133’# General Dynamics Corp., San Diego, Calif. LARGE OPTICS TECHNOLOGY; PROCEEDINGS OF THE EVALUATION OF ON-ORBIT CRYOGENIC PROPELLANT MEETING, SAN DIEGO, CA, AUGUST 19-21, 1985 DEPOT OPTIONS FOR THE ORBITAL TRANSFER VEHICLE G. M. SANGER, ED. (United Technologies Research Center, West J. R. SCHUSTER, F. 0. BENNETT, M. W. LIGGETT, C. N. TORRE Palm Beach, FL) Meeting sponsored by SPIE. Bellingham, WA, (General Dynamics Corp., Space Systems Div., San Diego, CA), Society of Photo-Optical Instrumentation Engineers (SPIE and N. BROWN (NASA, Marshall Space Flight Center, Huntsville, Proceedings. Volume 571), 1986, 276 p. For individual items see AL) ASME, lntersociety Cryogenics Symposium, 6th, New Orleans, A87-10998 to A87-11019. LA, Nov. 16-21, 1986, Paper. 43 p. refs (SPIE-571) (Contract NAS8-36612) The present conference on telescope primary mirror design An orbital cryogenic propellant storage facility will be required and manufacturing technologies considers topics in mirror for a space-based Orbital Transfer Vehicle. The facility tanks will fabrication and testing, novel technology currently under have features to permit fluid acquisition and transfer in low gravity development, recently instituted large optics development and to limit cryogen boiloff caused by environmental heating. Boiloff programs, and large mirror materials. Among the topics discussed management features will include thick multilayer insulation, are aspheric figure generation using feedback from an IR vapor-cooled shields, low conductance structural supports and phase-shifting interferometer, thermal stability tests of CFRP penetrations, and possibly refrigeration systems. Author sandwich panels for far-IR astronomy, ’Zerodur’ lightweight (large mirror) blanks, and the precision machining of grazing-incidence X-ray mirror substrates. Also treated are the rapid fabrication of N87-10151 Communications Satellite Corp., Washington, D.C. large aspheric optics, steps toward 8-m honeycomb mirrors, a EFFICIENCY ECCENTRICITY CONTROL USING CONTINUOUS, novel telescope design employing the refraction of prism rows, VECTORED THRUSTING FOR SATELLITES WITH LARGE telescope technology for the Far-UV Spectroscopic Explorer, hot AREA/MASS RATIOS isostatic-pressed Be for large optics, and a concept for a moderate V. J. SLABINSKI In CNES Proceedings of an International cost large deployable reflector. O.C. Conference on Space Dynamics for Geostationary Satellites p 589-613 1986 Avail: CEPADUES-Editions, 111 rue Nicolas-Vauquelin, 31 100 Toulouse, France A87-11003 It is shown that varying geostationary satellite thrust direction APPLICATION OF REPLICATED GLASS MIRRORS TO LARGE so as to counteract only the secular perturbations from the force SEGMENTED OPTICAL SYSTEMS can reduce the impulse requirement by 6.6%. For thrusting in the M. H. KRlM (Perkin-Elmer Corp., Space Science Div., Danbury, orbit plane, an analytic calculus-of-variations minimization shows CT) IN: Large optics technology; Proceedings of the Meeting, that the thrust direction should vary + or 19.5 deg at twice the San Diego, CA, August 19-21, 1985 . Bellingham, WA, Society of orbit frequency, about the Sun’s projection onto the orbit plane. Photo-Optical Instrumentation Engineers, 1986, p. 60-75. The thrust direction then lies between the Sun’s projection and Attention is given to the approach by which large, high specular the orbit tangent at the satellite. If the thrust can be vectored out reflectance, lightweight mirrors able to withstand thousands of deep of the orbit plane, the secular rotation of the orbit plane due to heating and cooling cycles without degradation (for unlimited orbital Sun and Moon gravity can also be countered. Minimization for operation) can be designed. An account is given to the principal this case shows that the thrust direction must oscillate sources of optics degradation, together with the effect of cumulative approximatively + or - 26 deg about the orbit plane with the orbit LCCs of different candidate materials. The potential advantages frequency, in addition to the in-plane oscillation. The impulse must of glass are noted. Concentrator segment design and fabrication also be increased by a m/sec/yr, but this eliminates the need for concepts are presented, with a view to their possible application 46 m/sec/yr of separate thrusting normal to the orbit plane for to such other projects as long wavelength IR imaging systems. orbit plane control. ESA O.C.

63 10 GENERAL

A87-11008 nonlinear systems, advances in model predictive control, simulation ITEK OPTICAL TECHNOLOGY IN MANUFACTURING AND tools for control systems, control of flexible spacecraft, missile METROLOGY navigation, guidance and control, and aerospace and aircraft control I. M. EGDALL and R. K. LEE (Litton Industries, Inc., ltek Optical applications. Other topics include real-time applications of parallel Systems Div., Lexington, MA) IN: Large optics technology; processing technology, identification, control in mechanical and Proceedings of the Meeting, San Diego, CA, August 19-21, 1985 . optical systems, web handling, and reconfiguration strategies for Bellingham, WA, Society of Photo-Optical Instrumentation flight control systems. R.R. Engineers, 1986, p. 115-122. refs There is a wide spectrum of optical systems contemplated for A87-13434" Jet Propulsion Lab., California Inst. of Tech., use in future astronomy missions. At Itek, the systems range from Pasadena. the large, lightweight, deployable optics required for the Large TRAJECTORY SHAPING RENDEZVOUS GUIDANCE Deployable Reflector (LDR) to the precision of grazing incidence A. R. KLUMPP (California Institute of Technology, Jet Propulsion X-ray optics for the Advanced X-ray Astrophysical Facility (AXAF). Laboratory, Pasadena) IN: 1986 American Control Conference, This paper describes some of the technological initiatives that 5th, Seattle, WA, June 18-20, 1986, Proceedings. Volume 3 . New ltek has developed to enhance the manufacturability and the York, Institute of Electrical and Electronics Engineers, 1986, p. measurement of the surface quality of the spectrum of optical 1545-1550. NASA-supported research. assemblies to be manufactured for the astronomical telescopes. The Space Station wi;l bring a great increase in rendezvous Author traffic. Formerly, rendezvous has been expensive in terms of time and crew involvement. Multiple trajectory adjustments on separate A87-11013 orbits have been required to meet safety, lighting, and geometry PARAMETRIC STUDY OF STABLE OPTICAL REFERENCES FOR requirements. This paper describes a new guidance technique in LARGE FLEXIBLE STRUCTURES IN SPACE which the approach trajectory is shaped by a sequence of velocity M. J. CLAYTON and A. L. WERTHEIMER (Eastman Kodak Co., increments in order to satisfy multiple constraints within a single Rochester, NY) IN: Large optics technology; Proceedings of the orbit. The approach phase is planned before the mission, leaving Meeting, San Diego, CA, August 19-21, 1985 . Bellingham, WA, a group of free parameters that are optimized by onboard guidance. Society of Photo-Optical Instrumentation Engineers, 1986, p. Fuel penalties are typically a few percent, compared to unshaped 149-157. Hohmann transfers, and total fuel costs can be less than those Several concepts for keeping track of small relative angular of more time-consuming ways of meeting the same requirements. motions between a reference point and a remote platform, when Author the two are located at separate points on a flexible structure, are discussed. The goal is to accurately transfer knowledge of the A87-13705 orientation of the remote platform relative to the reference point. SPACE STATION AUTOMATION; PROCEEDINGS OF THE First-order equations and order-of-magnitude calculations are MEETING, CAMBRIDGE, MA, SEPTEMBER 17, 18, 1985 presented for image centroiding and interference fringe projection W. C. CHIOU, SR., ED. (Lockheed Research Laboratories, Palo approaches for space station applications. Author Alto, CA) Meeting sponsored by SPIE. Bellingham, WA, Society of Photo-Optical Instrumentation Engineers (SPIE Proceedings. A87-13051' Jet Propulsion Lab., California Inst. of Tech., Volume 580), 1985, 105 p. For individual items see A87-13706 to Pasadena. A87-13717. INTERNATIONAL SAMPE SYMPOSIUM AND EXHIBITION, 31ST, (SPIE-580) LOS ANGELES, CA, APRIL 7-10, 1986, PROCEEDINGS Applications of artificial intelligence (AI), image science and J. L. BAUER, ED. (California Institute of Technology, Jet Propulsion robotics to enhancing automation for implementation in Space Laboratory, Pasadena) and R. DUNAETZ, ED. (Hughes Aircraft Station (SS) operations are discussed and current research is Co., El Segundo, CA) Symposium and Exhibition sponsored by reviewed. Attention is given to the functional requirements, missions the Society for the Advancement of Material and Process and potential configurations of automation and robotics on space Engineering. Covina, CA, Society for the Advancement of Material stations, orbital maneuvering vehicles and the Orbiter. Expert and Process Engineering (Science of Advanced Materials and systems are investigated for control of power transmission and Process Engineering Series. Volume 31), 1986, 1897 p. For consumption in the SS Common Modules. Automated guidance, individual items see A87-13052 to A87-13185. position and target location sensors and image processors and The present conference on the development status of advanced docking systems for orbital maneuver systems are described. structural materials considers topics arising in such areas as Consideration is devoted to robot vision techniques for welding, automated structural manufacturing, advanced material and collision avoidance, automated life sciences experimentation, and structure design techniques, environmental effects on materials, automated SS inspection systems. Finally, a systems approach is composite matrix processing, computer modeling for materials and delineated for use in the design of the SS and the selection of its processes, materials development trends in Europe and in Japan, missions. M.S.K. fiber and whisker reinforcement development status, and novel thermoplastic materials and their applications. Also discussed are A87-13708 pressure-sensitive adhesive systems, materials suitable for space THE SYSTEM APPROACH FOR APPLYING ARTIFICIAL applications, polyimide resin systems, electronic materials, novel INTELLIGENCE TO SPACE STATION AUTOMATION resin chemistries, ceramic and metallic systems, and the impact V. L. GROSE (National Transportation Safety Board, Washington, performance of state-of-the-art materials. O.C. DC) IN: Space station automation; Proceedings of the Meeting, Cambridge, MA, September 17, 18, 1985 . Bellingham, WA, Society A87-13301 of Photo-Optical Instrumentation Engineers, 1985, p. 21-27. 1986 AMERICAN CONTROL CONFERENCE, STH, SEATTLE, WA, The systems approach and an establishment issue Totem Pole JUNE 18-20, 1986, PROCEEDINGS. VOLUMES 1, 2, EL 3 (EITP) are described as a means to facilitate the incorporation of Conference sponsored by the American Automatic Control Council. artificial intelligence features into the Space Station (SS). It is New York, Institute of Electrical and Electronics Engineers, 1986. recommended that, in order to take a systems approach, the Vol. 1, 678 p.; vol. 2, 757 p.; vol. 3, 807 p. For individual items geography of the SS be defined explicitly, along with the known see A87-13302 to A87-13460. inputs and desired outputs and a balance between cost, Papers are presented on robustness and modeling issued in performance and schedule. The evolutionary, dynamic character process control, stochastic control, stability theory for adaptive of the SS must be acknowledged to recognize that the outputs control, robotics, artificial intelligence in process control, direct-drive will change the objectives. The EITP is to be developed from a robot arms, and estimation and tracking. Also considered are functional flow block diagram, which is a product of intended inputs performance/robustness tradeoffs inc ontroller design, linear and and desired outputs. The means used to achieve an SS which

64 10 GENERAL could use the inputs and produce the outputs are ranked in terms considered in order to select proper operating orbits are discussed. of criticality. AI then incorporates the hierarchy and will allocate Two orbits were selected for Columbus: the International Space resources in a sequence that will yield the best return on minimal Station orbit with an altitude of 463 km and an inclination of 28.5 resource investment. M.S.K. deg and the polar sun-synchronous orbit with an altitude of 850 km and an inclination of 98.8 deg. It is observed that ESA S-band A87-15376 stations provide good accuracy for navigating the polar platform SPACE STATION BEYOND IOC; PROCEEDINGS OF THE and the TDRSS will be used for communication on Columbus. THIRTY-SECOND ANNUAL INTERNATIONAL CONFERENCE, I.F. LOS ANGELES, CA, NOVEMBER 6, 7, 1985 M. J. FRIEDENTHAL, ED. (TRW, Inc., Federal Systems Div., A87-15871# Redondo Beach, CA) Conference sponsored by AAS. San Diego, FACTORS INFLUENCING SELECTION OF SPACE TRANSPORTA- CA, Univelt, Inc. , 1986, 187 p. For individual items see A87-15377 TION OPTIONS to A87-15390. R. H. MILLER, D. G. STUART, and A. AZARBAYEJANI IAF, The progress in the design of the Space Station, mainly for International Astronautical Congress, 37th, Innsbruck, Austria, Oct. the IOC, as of the end of 1985 is assessed, and plans for growth 4-1 1, 1986. 27 p. refs and applications of the Station are discussed. Emphasis is placed (IAF PAPER 86-108) on the technologies which will require further development if the An evaluation is made of the economic feasibility of two cost and timetable aspects of the Station are to be met. The concepts for the lofting of cargo into LEO, as will be required by tasks assigned in the individual Work Packages for the contracters the building of large Space-Station and satellite-power-system and subcontracters are described, as are Station uses as a structures. One of the alternatives considered is a fully reusable materials science, space physics, pharmaceuticals laboratory and horizontal-takeoff-and-landing aircraft whose first stage is astrometric observatory. M.S.K. airbreathing and manned, while the second is rocket-powered and unmanned; the second alternative is fully expendable, with vertical A87-15805# takeoff, two rocket stages, and no crew or reentry provisions. It is SATELLITE MOTION ANALYSIS VIA LASER REFLECTOR found that costs are critically dependent on the assumed future PATTERN PROCESSING FOR RENDEZ-VOUS AND DOCKING traffic demand as well as on the choice of vehicle payload I. NAKATANI, T. TANAMACHI, and K. NlNOMlYA (Tokyo, capability. O.C. University, Japan) IAF, International Astronautical Congress, 37th, Innsbruck, Austria, Oct. 4-11, 1986. 10 p. refs A87-15959# (IAF PAPER 86-06) INSTABILITY OF ROTATING BLADES IN SPACE A practical method for estimating the relative attitude and M. NATORI (Tokyo, University, Japan) and S. NEMAT-NASSER distance between a target satellite (TS) and a rendezvous satellite (California, University, La Jolla) IAF, International Astronautical using laser reflectors together with a CCD camera is discussed. A Congress, 37th, Innsbruck, Austria, Oct. 4-1 1, 1986. 9 p. refs new arrangement of the reflectors on the TS is proposed where (IAF PAPER 86-242) the data size required to identify and locate reflector points on Basic aspects of instability of a flexible rotating blade due to the image plane is quite small and the state equations of motion solar radiation pressure are studied as a first step toward an are remarkably simple because the proposed scheme makes it instability study of future bladed space vehicles. A fundamental possible to separate the rotational motion from translational motion. set of equations for coupled flap-lag-pitch motion of a very flexible Thus it is possible to estimate the motion of the TS in real time rotation blade is presented, including the coupling and nonlinear using ?he Kalman fi!!er technique and an onboard computer. terms associated with the structural, inertial, and solar dynamic C.D. operators. Basic instability characteristics of lag-pitch coupling through nonlinear terms are presented, and the effects of pitch A87-15806# control and torsional rigidity are clearly shown. C.D. RENDEZVOUS AND DOCKING VERIFICATION AND IN-ORBIT DEMONSTRATION A87-16081# P. P. NGUYEN (Aerospatiale, Paris, France), W. FEHSE (ESA, METEOROID AND ORBITAL DEBRIS PROTECTION European Space Research and Technology Centre, Noordwijk, CONCEPTS Netherlands), A. GETZSCHMANN (MEBIERNO, Bremen, West E. BAUER (ERN0 Raumfahrttechnik GmbH, Bremen, West Germany), and B. CLAUDINON (Matra, S.A., Velizy-Villacoublay, Germany) IAF, International Astronautical Congress, 37th, France) IAF, International Astronautical Congress, 37th, Innsbruck, Innsbruck, Austria, Oct. 4-1 1, 1986. 11 p. refs Austria, Oct. 4-11, 1986. 19 p. refs (IAF PAPER 86-419) (IAF PAPER 86-07) Meteoroid and orbital debris impacts are an important, design A novel, autonomous rendezvous and docking (RVD) concept driving requirement of future Space Station elements. For the is under development in Europe with a view to application in European Columbus elements, the potential safety requirements manned vehicles. The system encompasses navigation and as well as the resulting impact particle diameters and velocities guidance sensors, dockinglberthing mechanism hardware, and are discussed. Major parts of this presentation deal with the general onboard processors and software. The software is responsible for design and verification aspects necessary for the realization of an guidance and navigation intelligence, trajectory and attitude control, orbital impact protection system. Additionally, a caution and warning and control mode sequencing logic. Attention is given to a system needed for an immediate determination of the actual impact verification mission involving two Eureca platforms, one of which results is described. The possible repair activities required for is deployed and the other retrieved during a Space Shuttle flight. maintaining the safety critical space vehicle functions are O.C. explained. Author

A87-15808# A87-16141# NAVIGATION, GUIDANCE, RENDEZ-VOUS AND DOCKING - REDUCED MODELING AND ANALYSIS OF LARGE REPETITIVE ACTIVITIES CARRIED OUT FOR COLUMBUS BY THE FLIGHT SPACE STRUCTURES VIA CONTINUUM/DISCRETE OPERATIONS ORGANIZATION CONCEPTS A. BURAlTI IAF, International Astronautical Congress, 37th, K. C. SAW (West Virginia University, Morgantown) IAF, Innsbruck, Austria, Oct. 4-1 1, 1986. 9 p. International Astronautical Congress, 37th, Innsbruck, Austria, Oct. (IAF PAPER 86-09) 4-11, 1986. 12 p. refs Orbit and attitude optimization and control are examined. The (IAF PAPER ST-86-08) routine orbit is affected by the transfer orbits and the maneuvers A reduced modeling/analysis approach applicable for repetitive required for each experiment; additional factors which must be lattice configuration is described with emphasis on tetrahedral-type

65 10 GENERAL

space structures. Using scaling transformations and constitutive A87-18114 properties derived via the concept of 'equivalent continuum', the 1986 LECEC STABILITY AND TRANSIENT MODELING OF A actual models are transformed to significantly reduced discrete LARGESPACECRAFTPOWERSYSTEM configurations. Therein, the approach seeks to model/analyze the J. CHEN and M. GLASS (Lockheed Missiles and Space Co., Inc., much simpler and reduced configurations, wherein, transformations Sunnyvale, CA) IN: IECEC '86; Proceedings of the Twenty-first and extrapolation/interpolation procedures are utilized to relate lntersociety Energy Conversion Engineering Conference, San back the response to that of significantly complex actual Diego, CA, August 25-29, 1986. Volume 3 . Washington, DC, configurations. The effectiveness and accuracy of the approach is American Chemical Society, 1986, p. 1672-1676. demonstrated via comparisons with detailed analysis of the actual As space power systems grow and computer aided engineering models. Results obtained are in good agreement and the approach workstations mature, computer modeling becomes a critical design offers potential for further extension. The basic concepts can be step. This paper outlines the modeling process of a multi kw extended to general repetitive lattice structures as well. Author spacecraft power system comprised of eight solar powered converter/battery channels, three control loops including the peak power tracker, and a common output bus. The computer models predicted small signal stability margins, bus impedances, and fault induced voltage transients. Author A87-17834'# National Aeronautics and Space Administration. Lyndon B. Johnson Space Center, Houston, Tex. PATH-CONSTRAINED RENDEZVOUS - NECESSARY AND A87-18201 SUFFICIENT CONDITIONS INTERNATIONAL SYMPOSIUM ON SPACE TECHNOLOGY AND K. M. SOILEAU (NASA, Johnson Space Center, Houston, TX) SCIENCE, 14TH, TOKYO, JAPAN, MAY 27-JUNE 1, 1984, and S. A. STERN (Colorado, University, Boulder) Journal of PROCEEDINGS Spacecraft and Rockets (ISSN 0022-4650). vol. 23, Sept.-Oct. M. NAGATOMO, ED. Symposium sponsored by Ad-Melco Co., 1986, p. 492-498. refs Ltd., Akashi Seisakusho, Ltd., Anritsu Electric Co., Ltd., et al. Tokyo, The problem of path-constrained rendezvous in the vicinity of AGNE Publishing, Inc., 1984, 1718 p. For individual items see a Large Space Structure (LSS) was first introduced some years A87-18202 to A87-18418. ago. The present contribution to this field centers on a Progress in space science and technology is discussed in demonstration that the problem can be reduced from a reviews and reports, with emphasis on developments in Japan. path-constraint problem to one of end-point constraints or certain Topics examined include propulsion, materials and structure, fluid (common) LSS geometries, under the assumption of an unrestrictive dynamics, thermophysics and thermochemistry, electronic devices, upper limit on the transfer time. This finding has been made under space communication, guidance and control, systems engineering, the assumption of a circular Keplerian orbit, and has been balloons and recovery technology, earth and planetary normalized with respect to orbital semimajor axis and LSS size. In observations, astronomy, space medicine and biology, material addition to demonstrating this important simplification of the processing, and space law. T.K. path-constrained rendezvous problem, the results of numerical simulations of path-constrained transfers from point-to-point on A87-18247 large spherical structures in orbit are discussed, and a series of COLLISIONAL PROBABILITY IN SPACE AND THE DEBRIS conclusions having both architectural (design) and operational ENVIRONMENT IN FUTURE implications for LSS designers/operators is derived. Author K. SAT0 (Tokyo, University, Japan) and M. NAGATOMO IN: International Symposium on Space Technology and Science, 14th, Tokyo, Japan, May 27-June 1, 1984, Proceedings . Tokyo, AGNE Publishing, Inc., 1984, p. 393-398. The collision of an earth satellite with other orbiting debris is A87-17841# studied to predict the collision probability, using the NASA Satellite FEASIBILITY STUDY OF A LOW-TEMPERATURE EXPANDABLE Situation Report (1982). To obtain the tendency of number density MEGAWATT PULSE POWER RADIATOR of debris versus altitude, the lifetime of debris is calculated by the L. C. CHOW (Kentucky, University, Lexington), E. T. MAHEFKEY averaging method as a function of the masses of debris and the (USAF, Aero Propulsion Laboratory, Wright-Patterson AFB, OH), launch date (on the assumption that each orbit of debris is circular). and J. E. YOKAJTY Journal of Spacecraft and Rockets (ISSN It is shown that the effect of the periodic solar activity on the 0022-4650), vol. 23, Sept.-Oct. 1986, p. 539-541. Abridged. number density distribution is significant. The results show that USAF-sponsored research. Previously cited in issue 17, p. 2472, the number of debris continues to increase in the range of altitude Accession no. A85-37686. refs between 1000 and 1500 km. Accordingly the collision probability will increase in the same range. Author

A87-18451 A87-18026 SPACE EXPLOITATION AND UTILIZATION; PROCEEDINGS OF IECEC '86; PROCEEDINGS OF THE TWENTY-FIRST THE SYMPOSIUM, HONOLULU, HI, DECEMBER 15-19, 1985 INTERSOCIETY ENERGY CONVERSION ENGINEERING P. M. BAINUM, ED. (Howard University, Washington, DC), K. IKEDA, CONFERENCE, SAN DIEGO, CA, AUGUST 25-29, 1986. ED. (Mitsubishi Heavy Industries, Ltd., Tokyo, Japan), T. NOMURA, VOLUMES 1,2, & 3 ED. (Tokyo, University, Japan), T. YAMANAKA, ED. (National Conference sponsored by AChS, SAE, AIAA, et al. Washington, Aerospace Laboratory, Tokyo, Japan), G. L. MAY, ED. et al. DC, American Chemical Society, 1986, p. Vol. 1, 673 p.; vol. 2, Symposium organized and sponsored by AAS and Japanese 737 p.; vol. 3, 897 p. For individual items see A87-18027 to Rocket Society. San Diego, CA, Univelt, Inc. , 1986, 738 p. For A87-18181. individual items see A87-18452 to A87-18470, A87-18472 to Recent developments in the technology of energy conversion A87-18497. are discussed in reviews and reports. Topics examined include Various papers in the area of space exploitation and utilization advanced conversion Concepts, geothermal conversion, energy are presented. The general topics addressed include: national and policy, pyroelectric conversion materials, large cogeneration international space programs, advanced space-based systems, coal conversion, biomass energy, rock-fluid interactions, communications systems, remote sensing of the earth, earth hydrogen energy, and nuclear energy. Consideration is given to resources satellite technology, future trends in the development heat pumps and engines, MHD conversion, thermal storage, of launch vehicle technology, space-based manufacturing, future batteries, solar conversion, and power-conversion requirements and use of robotic technology for space application, and technologies for space use. T.K. astrodynamics. C.D.

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A87-18852 surfaces after sulfochromic pickling prior to bonding, and intrinsic AEROSPACE COMPUTER SECURITY CONFERENCE, 2ND, mechanical characterization of structural adhesives. I.S. MCLEAN, VA, DECEMBER 2-4, 1986, TECHNICAL PAPERS Conference sponsored by AIAA, American Society for Industrial Security, and DOD Computer Institute. New York, American Institute of Aeronautics and Astronautics, 1986, 142 p. For individual items A87-21801 see A87-18853 to A87-18865. SPACE NUCLEAR POWER SYSTEMS 1985; PROCEEDINGS OF Papers are presented on a model for the containment of THE SECOND SYMPOSIUM, ALBUQUERQUE, NM, JAN. 14-16, computer viruses, the Commercial Communications Security 1985. VOLUMES 3 & 4 Endorsement Program, and a design for a multilevel secure MOHAMED S. EL-GENK, ED. (New Mexico, University, database management system. Topics discussed include secure Albuquerque) and MARK D. HOOVER, ED. (Lovelace Inhalation computer systems, electronic mail privacy enhancement, multilevel Toxicology Research Institute, Albuquerque, NM) Symposium data storage design, and secure database management system organized by the University of New Mexico; Sponsored by American architectural analysis. Particular attention is given to access control Nuclear Society, Sandia National Laboratories, USAF, et al. and privacy in large distributed systems and the verification of Malabar, FL, Orbit Book Co., Inc., 1987. Vol. 3, 192 p.; vol. 4, integrity. I.F. 218 p. For individual items see A87-21802 to A87-21840. Papers are presented on the US space nuclear power program, A87-20055' Alabama Univ., Huntsville. civilian and military applications for nuclear power in space, and DUAL-SPACECRAFT MEASUREMENTS OF PLASMASPHERE- the designs, requirements, and costs of space nuclear power IONOSPHERE COUPLING missions and systems. Topics discussed include space nuclear J. L. HORWITZ, R. H. COMFORT (Alabama, University, Huntsville), reactor fuel and fuel performance, the properties of refractory metal L. H. BRACE (NASA, Goddard Space Flight Center, Greenbelt, alloys, the development of liquid droplet and heat pipe radiators MD), and C. R. CHAPPELL (NASA, Marshall Space Flight Center, for thermal management in space, and systems analysis and Huntsville, AL) Journal of Geophysical Research (ISSN testing. Consideration is given to methods for converting thermal 0148-0227), vol. 91, Oct. 1, 1986, p. 11203-11216. refs energy to useable electrical energy in space, control and power (Contract NSF ATM-83-00426; NSF ATM-85-06642; NAG5-475; conditioning electronics systems for space applications, reactors NAG8-054; NAG8-058; NAS8-33982) and shields, options for space nuclear propulsion, and the safety An extensive set of plasmaspheric measurements by the DE 1 and reliability of using nuclear reactors in space. I.F. satellite and ionospheric measurements by the DE 2 satellite are presented. The developments in the ionosphere and plasmasphere during the recovery phase of a magnetospheric storm are described. Isolated profile comparisons are used to indicate some A87-21975 of the structural relations and complexities involving the ionosphere PERSPECTIVE ON NON-U.S. PRESENTATIONS AT THE 37TH and plasmasphere latitudinal profiles. A transition in the ionospheric CONGRESS OF THE INTERNATIONAL ASTRONAUTICAL electron temperature Te from a relatively smooth profile of low FEDERATION - OCTOBER 4-1 1, 1986, INNSBRUCK, AUSTRIA Te at the base of the inner plasmasphere to enhanced and highly J. HARTFORD, ED. (AIAA, New York) New York, American structured Te at higher invariant latitudes occurs near or along a Institute of Aeronautics and Astronautics, 1987, 41 p. No individual plasmaspheric density gradient. Plasmaspheric enhancements of items are abstracted in this volume. the heavy ions O(+) and 0(2+) are often closely aligned with Highlights of the plenary events and technical sessions of the distinct ionospheric Te enhancements. C.D. 37th Congress of the International Astronautical Federation are presented. Particular attention is given to the state and direction A87-20076 of foreign space technology, and to foreign reaction to U.S. papers. REINFORCED PLASTICS/COMPOSITES INSTITUTE, ANNUAL Subject areas include astrodynamics, communications satellites, CONFERENCE, 41ST, ATLANTA, GA, JANUARY 27-31, 1986, earth observations, economics, education, global change, history, PREPRINT life sciences, materials and structures, microgravity processes, Lancaster, PA, Technomic Publishing Co., 1986, 679 p. For propulsion, and the search for extraterrestrial intelligence. individual items see A87-20077 to A87-20093. Consideration is also given to space exploration, space law, space The present conference on composite materials technologies power, space stations, space systems, and space transportation. encompasses topics in pultrusion techniques and products, K.K. matrix-reinforcement interface characteristics, filament winding and ply layup processes, resin curing cycles, marine applications, and reinforced thermoplastics. Also discussed are reaction injection molding processes, transportation applications, product markets, A87-224 16# fillers and additives, testing methods, sheet molding compounds, MODEL FOR RADIATION CONTAMINATION BY OUTGASSING corrosion prevention, design methods, basic research and FROM SPACE PLATFORMS development topics, and structural applications. O.C. STEPHEN J. YOUNG and RONALD R. HERM (Aerospace Corp., El Segundo, CA) AIAA, Aerospace Sciences Meeting, 25th, Reno, A87-20144 NV, Jan. 12-15, 1987. 12 p. refs INTERNATIONAL WEEK ON BONDING AND JOINING (Contract FO4701-85-C-0086) TECHNOLOGIES, lST, BORDEAUX, FRANCE, APRIL 15-18, (AIAA PAPER 87-0102) 1986, SELECTED PAPERS Infrared sensors mounted on space platforms (e.g. Space Week organized by Adhecom. International Journal of Adhesion Shuttle and satellites) may be subject to infrared radiation and Adhesives (ISSN 0143-7496), vol. 6, Oct. 1986, 72 p. For contamination from molecular gases released from the platform individual items see A87-20145 to A87-20151. itself. Models for order-of-magnitudeestimates of the contamination Papers are presented on bonding composites, stress analysis level caused by this effect are formulated. Application of the model at the interface in adhesive joints by special finite elements, and to estimate the effects that the outgassing of H20 from the Shuttle the analysis of adhesive-bonded structural joints in space vehicles. environment would have on the ClRRlS 1A earth-limb radiance Consideration is given to adhesive bonding of aerospace materials, mission indicates that detection in the 2.7-micron spectral region modeling the elementary mechanisms involved in grafting polymers would be only slightly degraded, but that detection around 6.3 onto metals, and the use of the wedge test to estimate the lifetime microns may be seriously impaired by the mechanism of absorption of an adhesive joint in an aggressive environment. Other subjects and reemission of earthshine radiation by the H20 contamination include the physicochemical characterization of aluminum alloy molecules. Author

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A87-22738*# Massachusetts Inst. of Tech., Cambridge. A87-24701 RADIATION FROM LARGE SPACE STRUCTURES IN LOW DIGITAL NETWORKS AND THEIR EVOLUTION - SPACE AND EARTH ORBIT WITH INDUCED AC CURRENTS TERRESTRIAL SYSTEMS; PROCEEDINGS OF THE THIRTY- D. E. HASTINGS and S. OLBERT (MIT, Cambridge, MA) AIAA, THIRD INTERNATIONAL CONGRESS ON ELECTRONICS AND Aerospace Sciences Meeting, 25th, Reno, NV, Jan. 12-15, 1987. TWENTY-SIXTH INTERNATIONAL MEETING ON SPACE, ROME, 19 p. refs ITALY, MAR. 18-20, 1986 (Contract NAG3-695) Conference supported by the Minister0 per il Coordinamento della (AIAA PAPER 87-0612) Ricerca Scientifica e Tecnologica, CNR, ESA, et al. Rome, Large conducting space structures in low earth orbit will have Rassegna lnternazionale dell’Elettronica, dell’Energia, e dello a nonnegligible motionally induced potential across their structures. Spazio, 1986, 474 p. For individual items see A87-24702 to The induced current flow through the body and the ionosphere A87-24712. causes the radiation of Alfven and lower hybrid waves. This current Among the topics presently discussed are the position of space flow is taken to be ac and the radiated power is studied as a and terrestrial systems in digital communications network evolution, function of the ac frequency. The current may be ac due either to research and experiments on broadband subscriber networks in inductive coupling from the power system on the structure or by Italy. ESA satellite communications activities and plans, research active modulation. A Space Station-like structure and tether are on the integrated switching of voice and video transmissions, studied. For the Space Station structure the radiation impedance advanced structures for digital broadband switching, and the use is particularly high for frequencies in the tens of kilohertz range of Banyan networks for high throughput switching exchanges. Also which suggests that the Space Station may be efficient source of considered are the interconnection of digital systems with different lower hybrid waves. The tether is also shown to be a generator standards, standard compatibility of ISND terminals, the global of VLF waves up to source ac frequencies in the megahertz range. plan for network layer addressing in open systems interconnection, The implications for these two structures are discussed. Author videoconferencing, ISND and office automation, intelligent networks, the European Data Relay Satellite, the Space Station’s data systems, and Columbus communications. O.C.

A87-25426 SOLAR POWER SATELLITE BUILT OF LUNAR MATERIALS A87-24198’ Air Force Geophysics Lab., Hanscom AFB, Mass. Space Power (ISSN 0883-6272), vol. 6, no. 1, 1986, 99 p. refs BOOM POTENTIAL OF A ROTATING SATELLITE IN The energy required for transporting lunar material to SUNLIGHT geosynchronous orbit is less than 8 percent that for terrestrial S. T. LAI, H. A. COHEN (USAF, Geophysics Laboratory, Bedford, materials; this is compounded by the lower cost of a launcher MA), T. L. AGGSON (NASA, Goddard Space Flight Center, that overcomes the moon’s low gravity to reach that orbit, to Greenbelt, MD), and W. J. MCNEIL (Radex, Inc., Carlisle, MA) yield a 50:l advantage over delivery of materials fron earth. An Journal of Geophysical Research (ISSN 0148-0227), vol. 91, Nov. economic evaluation is presently made of the prospects for a 1, 1986, p. 12137-12141. refs solar power satellite built in geosynchronous orbit. It is found that An interpretation is provided for the behavior of long boom a solar power satellite can be designed which employs less than potential measurements taken on the spinning P78-2 (SCATHA) one percent as much nonlunar material as a baseline, terrestrial satellite at near geosynchronous altitudes. This study uses data materials-employing satellite, despite total mass being 8 percent taken during a quiet day, with the satellite in sunlight. The data greater. Si solar cells are used for power generation; the structure show periodic variations with a maximum amplitude of 6 V. The is primarily aluminum, and the design is suited to automated theory explains why the variations correlate well with sun direction construction. O.C. but not with the geomagnetic field. A current balance model, assuming a Maxwellian distribution of photoelectrons, is studied. The photoelectron temperature, the degrees of positive charging A87-25451 of the boom and of the satellite, and the ambient electron flux SPACE STATION: GATEWAY TO SPACE MANUFACTURING; are calculated. Deviations from the model are discussed. Author PROCEEDINGS OF THE CONFERENCE, ORLANDO, FL, NOV. 7, 8, 1985 Conference sponsored by Pasha Publications. Arlington, VA, Pasha Publications, 1985, 437 p. For individual items see A87-25452 to A87-25461. Opportunities for commercial manufacturing operations on the Space Station are discussed in reviews and reports by NASA and A87-24625 industry experts. Topics examined include private initiatives and OPTIMAL SPACECRAFT ROTATIONAL MANEUVERS opportunities, promising new technologies, low-cost starting JOHN L. JUNKINS (Texas A & M University, College Station) and options, new types of space-operations financing, and initial space JAMES D. TURNER (PRA, Inc., Cambridge, MA) Research laboratories and factories. Extensive diagrams, tables, and drawings supported by the U.S. Air Force, Charles Stark Draper Laboratory, are provided. T.K. Inc., U.S. Navy, et al. Amsterdam and New York, Elsevier (Studies in Astronautics. Volume 3), 1986, 532 p. refs Methods of solving problems related to maneuvering spacecraft A87-25751 are discussed, emphasizing the most central analytical and SPACE TECH ’86; PROCEEDINGS OF THE INTERNATIONAL numerical methods for determining optimal rotational maneuvers CONFERENCE, GENEVA, SWITZERLAND, MAY 14-16, 1986 of spacecraft. Large-angle nonlinear maneuvers are focused on, London, Online International, Ltd., 1986, 261 p. For individual items and large rotational maneuvers of flexible vehicles with see A87-25752 to A87-25769. simultaneous vibration suppression/arrest are considered. The Papers are presented on the development of the Space Station, individual chapters discuss: geometry and kinematics of rotational the Japanese laboratory proposal, and the Columbus program. motion, basic principles of dynamics, rotational dynamics of rigid Topics discussed include free flying platforms, the role of robotics and multiple rigid body spacecraft, dynamics of flexible spacecraft, in space, switches, lasers, and electronically-hopped beam elements of optimal control theory, numerical solution of two point antennas in space, new communications satellite configurations, boundary value problems, optimal maneuvers of rigid spacecraft, geostationary platforms, the mobile communications satellite, and optimal large-angle single-axis maneuvers of flexible spacecraft, paging by satellite. Consideration is given to space transportation, frequency-shaped large-angle maneuvers of flexible spacecraft, and in particular the Long March launcher, Ariane 5/Hermes, and computational methods for closed-loop control problems. C.D. Hotol. I.F.

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A87-25753 A87-28526 JAPANESE LABORATORY PROPOSAL INTERNATIONAL MODAL ANALYSIS CONFERENCE, 4TH, LOS TADAHICO INADA (National Space Development Agency of Japan, ANGELES, CA, FEB. 3-6, 1986, PROCEEDINGS. VOLUMES 1 & Paris, France) IN: Space Tech '86; Proceedings of the International 2 Conference, Geneva, Switzerland, May 14-16, 1986 . London, Conference sponsored by Union College. Schenectady, NY, Union Online International, Ltd., 1986. p. 21-31. College, 1986. Vol. 1, 850 p.; vol. 2, 911 p. For individual items Japanese participation in the Space Station Phase B study is see A87-28527 to A87-28584. concentrated on the experimental module, which is attached to Techniques and applications of structural modal analysis and the core module from one side, and other facilities, which are testing are examined in reviews and reports. Topics covered include attached to the other side. The basic principles for participation experimental case histories, analytical methods, structural-dynamics and detailed configuration of the module are described. Author modifications, linking analysis and tests, and techniques for rotating machinery. Consideration is given to substructuring, structure A87-25976 modeling, processing modal data, analysis of nonlinear structures, AEROSPACE APPLICATIONS CONFERENCE, STEAMBOAT FEM analysis, noise acoustics, vehicle design, transducers and SPRINGS, CO, FEB. 1-8, 1986, DIGEST instrumentation, and design methods. T.K. Conference sponsored by IEEE. New York, Institute of Electrical and Electronics Engineers, Inc., 1986, 359 p. For individual items see A87-25977 to A87-26000. The present conference considers topics concerning the projected NASA Space Station's systems, digital signal and data processing applications, and space science and microwave A87-29401 applications. Attention is given to Space Station video and audio SPACE COMMERCE '86; PROCEEDINGS OF THE subsystems design, clock error, jitter, phase error and differential INTERNATIONAL CONFERENCE AND EXHIBITION ON THE time-of-arrival in satellite communications, automation and robotics COMMERCIAL AND INDUSTRIAL USES OF OUTER SPACE, in space applications, target insertion into synthetic background MONTREUX, SWITZERLAND, JUNE 16-20, 1986 scenes, and a novel scheme for the computation of the discrete VIVECA C. OTT, ED. Geneva, lnteravia Publishing Group, 1986, Fourier transform on a systolic processor. Also discussed are a 489 p. For individual items see A87-29402 to A87-29440. novel signal parameter measurement system employing digital Progress in the commercialization and industrialization in space signal processing, EEPROMS for spacecraft applications, a unique is assessed with emphasis on near- and medium-term concurrent processor architecture for high speed simulation of developments. Details of the history and status of lntelsat and dynamic systems, a dual polarization flat plate antenna, Fresnel other satellite-based telecommunications systems are explored, diffraction, and ultralinear TWTs for high efficiency satellite along with factors of importance for competing systems, DBS communications. O.C. systems, and the evolution of the lntelsat services. NASA, ESA and NASDA efforts to further space industrialization through the A87-27603 Space Station/COLUMBUS program are discussed in great detail. SPACE LOGISTICS SYMPOSIUM, lST, HUNTSVILLE, AL, MAR. Attention is also given to the encouragement the space agencies 24-26, 1987, TECHNICAL PAPERS are providing to private industries to identify materials processing Symposium sponsored by AIAA and Society of Logistics Engineers. and other technologies which have the potential for commercial New York, American Institute of Aeronautics and Astronautics, scale manufacturing in space. Spinoffs from space activities which 1987, 167 p. For individual items see A87-27604 to A87-27624. have had significant impacts for terrestrial industries are examined, Logistics problems and possible solutions are identified for as are potential and historically proven methods of attracting planned and proposed space, launch vehicle and ground support venture capital to the financing of space projects. The status and systems, services and capabilities. Systems engineering and prospects for international space law regulating space logistics planning techniques are identified for launching, retrieving commercialization are discussed. M.S.K. and repairing satellites and various free-flying platforms from the Orbiter and/or the Space Station. Alternative design approaches are explored for the construction, growth, maintenance and operation of the Space Station and SDI battle stations and ground support systems. Integrated ground support services are described as a necessary component that must be considered in the systems A87-29441 engineering of affordable, third generation of more-nearly fully AEROSPACE TESTING SEMINAR, 9TH, LOS ANGELES, CA, reusable manned and unmanned launch systems. Finally, several OCT. 15-17, 1985, PROCEEDINGS logistics analysis approaches, which must be applied at the Seminar sponsored by the Institute of Environmental Sciences inception of design studies, are delineated for inventory control, and Aerospace Corp. Mount Prospect, IL, Institute of Environmental launch and maintenance, and repair and refurbishment of future Sciences, 1986, 268 p. For individual items see A87-29442 to space systems such as the Hubble Space Telescope. M.S.K. A87-29471. Papers are presented on the qualification/acceptance program A87-27621# for the Hubble Space Telescope, launch vehicle platform and SPACE LOGISTICS SUPPORT TO MILITARY SPACE SYSTEMS high-energy upper stage acceptance testing, the integrated JOHN C. BAKER (bd Systems, Inc., Torrance, CA) and WILLIAM spacecraft automated test system, characteristics of MOROSOFF IN: Space Logistics Symposium, 1st, Huntsville, electromagnetic interference generated by arc discharging, and AL, Mar. 24-26, 1987. Technical Papers . New York, American strain gage selection and bonding techniques for application in a Institute of Aeronautics and Astronautics, 1987. p. 138-144. cryogenic-pyrotechnic environment. Topics discussed include a (AIAA PAPER 87-0694) design verification system for advanced aerospace engines, a Deficiencies in current space support capabilities have been Space Station propulsion system test bed, test and verification examined and compared to evolving infrastructure requirements, impact on commercial Space Station operations, cost effective both with and without SDI. The resulting needs are documented management of space venture risks, and automated microwave in the launch, on-orbit and C3 areas. Technology advances and testing of spacecraft. Consideration is given to vibration testing of methods of operation that will be required to bring space logistics large spacecraft; transfer-orbit-stage off-line processing; utilization, to an appropriate level so that military activity can become effective testing, and maintenance of multimission hardware; payload in space are identified and documented, and a 10 yr is presented. vibroacoustics for Shuttle peculiar environments; and automatic, Supportability is shown to be an important force multiplier for military integrated facility record systems for Shuttle processing at space systems. Author Vandenberg AFB. I.F.

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A87-29466# N87-10886# European Space Agency, Paris (France). UTILIZATION, TESTING AND MAINTENANCE OF PROCEEDINGS OF AN INTERNATIONAL CONFERENCE ON MULTlMlSSlON HARDWARE SPACECRAFT STRUCTURES G. K. JANES and R. L. RADCLIFFE (Martin Marietta Corp., Denver, W. R. BURKE, comp. Apr. 1986 433 p In ENGLISH and CO) IN: Aerospace Testing Seminar, 9th, Los Angeles, CA, Oct. FRENCH Conference held in Toulouse, France, 3-6 Dec. 1985 15-17, 1985, Proceedings . Mount Prospect, IL, Institute of (ESA-SP-238; ISSN-0379-6566; ETN-86-98078) Avail: NTlS HC Environmental Sciences, 1986, p. 206-210. A19/MF A01 The preflight testing, operation, and postflight inspection of the Spacecraft structural analysis, including dynamic analysis and Manned Maneuvering Unit (MMU)/Flight Support Station (FSS) tests, dynamical identification, and acoustics analysis; design are described. The procedures for testing and maintaining the engineering; and spacecraft construction materials were MMUIFSS, and the functions of the MMU Depot are examined. discussed. Examples revealing the preflight and postflight testing and ESA inspection of the MMU/FSS for various space missions are presented. Diagrams of the MMU and FSS are provided. I.F. N87-10945’# National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. PROCEEDINGS OF THE 2ND ANNUAL SCOLE WORKSHOP L. W. TAYLOR, JR., comp. Oct. 1986 268 p Workshop held A87-31112’# National Aeronautics and Space Administration, in Hampton, Va., 9-10 Dec. 1985 Washington, D.C. (NASA-TM-89048; NAS 1.1 5:89048) Avail: NTlS HC A1 2/MF SECOND AIAA/NASA USAF SYMPOSIUM ON AUTOMATION, A01 CSCL22B ROBOTICS AND ADVANCED COMPUTING FOR THE NATIONAL Proceedings of the Second Annual Spacecraft Control SPACE PROGRAM Laboratory Experiment (SCOLE) Workshop held at the NASA DALE MYERS (NASA, Washington, DC) AIAA, NASA, and USAF, Symposium on Automation, Robotics and Advanced Computing Langley Research Center, Hampton, Va., December 9 to 10, 1985 are presented. Author for the National Space Program, 2nd, Arlington, VA, Mar. 9-11, 1987. 4 p. (AIAA PAPER 87-1655) N87-10947# Oak Ridge National Lab., Tenn. An introduction is given to NASA goals in the development of PROTECTION OF SPACECRAFT FROM METEOROIDS AND automation (expert systems) and robotics technologies in the Space ORBITAL DEBRIS Station program. Artificial intelligence (AI) has been identified as A. P. FRAAS Mar. 1986 66 p a means to lowering ground support costs. Telerobotics will (Contract DE-AC05-840R-21400) enhance space assembly, servicing and repair capabilities, and (DE86-009996; ORNLITM-9904) Avail: NTlS HC A04/MF A01 will be used for an estimated half of the necessary EVA tasks. This report presents a review of information on the incidence The general principles guiding NASA in the design, development, of meteoroids and solid debris in orbital space, the damaging ground-testing, interactions with industry and construction of the effects of these materials, and the principles that may be used to Space Station component systems are summarized. The design protective shields for orbiting spacecraft. The report was telerobotics program has progressed to a point where a telerobot prepared as part of a current Oak Ridge National Laboratory effort servicer is a firm component of the first Space Station element to develop and evaluate conceptual designs of space power launch, to support assembly, maintenance and servicing of the systems. DOE Station. The University of Wisconsin has been selected for the establishment of a Center for the Commercial Development of N87-10956# Marconi Space Systems Ltd., Portsmouth Space, specializing in space automation and robotics. M.S.K. (England). MODERN CONTROL OF LARGE FLEXIBLE SPACECRAFT, ESA ASTP STUDY Final Report Paris ESA May 1985 272 p N87-10113 Centre National d’Etudes Spatiales, Toulouse (Contract ESA-5664/83-NL-BI; ESTEC-5352/83-NL-HP(SC)) (France). (BL-6206-ISSUE-2; ESA-CR(P)-2197; ETN-86-98083) Avail: NTlS PROCEEDINGS OF AN INTERNATIONAL CONFERENCE ON HC A12/MF A01 SPACE DYNAMICS FOR GEOSTATIONARY SATELLITES Stability control of large flexible spacecraft using bang-bang 1986 869 p In ENGLISH and FRENCH Conference held in nonlinear control based on Sturm’s theorem was investigated. A Toulouse, France, Oct. 1985 canonical model for preliminary tuning of the Sturm control law (ISBN-2-85428-149-7; ETN-86-98079) Avail: was derived. The damping matrix for the control law was studied. CEPADUES-Editions, 111 rue Nicolas-Vauquelin, 31 100 Toulouse, Use with one and two flexure modes per array axis; state estimation; France stationkeeping maneuver responses; effect of parameter Geostationary satellite mission analysis, attitude determination, mismatches; and effect of mode spillover were assessed. orbit determination, (onboard technology, low-thrust techniques, Comparisons with other techniques show that the Sturm controller station acquisition, stationkeeping) ground segments, and future is superior, particularly with respect to ability to reject orbital developments were discussed. correction disturbance. ESA ESA N87-11066# Messerschmitt-Boelkow-BlohmG.m.b.H., Ottobrunn (West Germany). Space Div. N87-10720*# National Aeronautics and Space Administration. OFFSET UNFURLABLE ANTENNA. PHASE 2A EXECUTIVE Goddard Space Flight Center, Greenbelt, Md. SUMMARY PROCEEDINGS OF THE 5TH ANNUAL USERS’ CONFERENCE Paris ESA Nov. 1985 34 p M. SZCZUR, ed. and E. HARRIS, ed. 1985 400 p Conference (Contract ESTEC-5206/82-NL-PB(SC)) held at Greenbelt, Md., 4-6 Jun. 1985 (MBB-R-0200/3069-R; ESA-CR(P)-2199; ETN-86-98085) Avail: (NASA-CP-2399; NAS 1.552399) Avail: NTlS HC A17/MF A01 NTlS HC AO3/MF A01 CSCL 09B A 4.5 m radial rib reflector was designed for the 4 GHz lntelsat The Transportable Applications Executive (TAE) was conceived mission. The reflector was redesigned for the M-Sat 2-beam in 1979. It was proposed to be a general purpose software coverage requirements, resulting in a 5 m dia, 850 MHz offset executive that could be applied in various systems. The success reflector. It features a radial carbon fiber rib concept where foldable of this concept and of TAE was demonstrated. Topics included: main ribs and intermediate ribs tension a gold plated molybdenum TAE current status; TAE development; TAE applications; and UNlX mesh to the required surface contour. The accuracy is varied by emp hasis. B.G. applying different numbers of ribs (e.g., 16 for 850 MHz or 30 for

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12 GHz) and mesh fastening points. The electrical performance N87-11838*# National Aeronautics and Space Administration. criteria used to establish the acceptable mechanical tolerances is Lewis Research Center, Cleveland, Ohio. that the level of the gore lobes generated by the ribs remains at EFFECT OF HARD PARTICLE IMPACTS ON THE ATOMIC least 30 dB below the main beam peak under all orbital OXYGEN SURVIVABILITY OF REFLECTOR SURFACES WITH conditions. ESA TRANSPARENT PROTECTIVE OVERCOATS D. A. GULINO 1986 22 p Proposed for presentation at the 25th Aerospace Sciences Meeting, Reno, Nev. 12-15 Jan. 1987; sponsored by the American Institute of Aeronautics and N87-11717'# National Aeronautics and Space Administration. Astronautics Langley Research Center, Hampton, Va. (NASA-TM-88874; E-3281; NAS 1.15:88874) Avail: NTlS HC RECENT EXPERIENCES IN MULTIDISCIPLINARY ANALYSIS AO2/MF A01 CSCL 106 AND OPTIMIZATION, PART 1 Silver mirror samples with protective coatings were subjected J. SOBIESKI, comp. 1984 517 p Symposium held in Hampton, to a stream of 27 microns alumina particles to induce pinhole Va., 24-26 Apr. 1984 defects. The protective coating consisted of a layer of aluminum (NASA-CP-2327-PT-1; NAS 1.55:2327-PT-l) Avail: NTlS HC dioxide over silver followed by a layer of silicon dioxide over the A22/MF A01 CSCL 01C alumina. Samples were prepared on both graphite-epoxy composite Papers presented at the NASA Symposium on Recent and fused quartz substrates. After exposure to the hard particle Experiences in Multidisciplinary Analysis and Optimization held at stream, the samples were exposed to an oxygen plasma NASA Langley Research Center, Hampton, Virginia April 24 to environment in a laboratory plasma asher. The effects of both the 26, 1984 are given. The purposes of the symposium were to hard particles and the oxygen plasma were documented by both exchange information about the status of the application of reflectance measurements and scanning electron microscopy. The optimization and associated analyses in industry or research results indicated that oxidative damage to the silver reflecting layer laboratories to real life problems and to examine the directions of continues beyond that of the erosively exposed silver. Oxidative future developments. Information exchange has encompassed the undercutting of the silver layer and graphite-epoxy substrate following: (1) examples of successful applications; (2) attempt and continues in undamaged areas through adjacent, particle damaged failure examples; (3) identification of potential applications and defect sites. This may have implications for the use of such mirrors benefits; (4) synergistic effects of optimized interaction and in a space station solar dynamic power system. Author trade-offs occurring among two or more engineering disciplines and/or subsystems in a system; and (5) traditional organization of N87-13167*# McDonnell-Douglas Astronautics Co., Houston, a design process as a vehicle for or an impediment to the progress Tex. in the design methodology. ADVANCED EVA SYSTEM DESIGN REQUIREMENTS STUDY Final Technical Report Jan. 1986 248 p (Contract NAS9-17299) N87-11750'# National Aeronautics and Space Administration. (NASA-CR-171942; NAS 1.26:171942; MDC-W0072) Avail: NTlS Langley Research Center, Hampton, Va. HC A1 1/MF A01 CSCL 05H RECENT EXPERIENCES IN MULTIDISCIPLINARY ANALYSIS Design requirements and criteria for the Space Station AND OPTIMIZATION, PART 2 Advanced Extravehicular Activity System (EVAS) including crew J. SOBIESKI, comp. 1984 509 p Symposium held in Hampton, enclosures, portable life support systems, maneuvering propulsion Va., 24-26 Apr. 1984 systems, and related extravehicular activity (EVA) support (NASA-CP-2327-PT-2; L-15830; NAS 1.55:2327-PT-2) Avail: equipment were defined and established. The EVA mission NTlS HC A22/MF A01 CSCL 01C requirements, environments, and medical and physiological The papers presented at the NASA Symposium on Recent requirements, as well as opertional, procedures, and training issues Experiences in Multidisciplinary Analysis and Optimization held at were considered. B.G. NASA Langley Research Center, Hampton, Virginia, April 24 to 26, 1984 are given. The purposes of the symposium were to N87-13466'# Draper (Charles Stark) Lab., Inc., Cambridge, exchange information about the status of the application of Mass. optimization and the associated analyses in industry or research FORMATIONKEEPING OF SPACECRAFT VIA DIFFERENTIAL laboratories to real life problems and to examine the directions of DRAG M.S. Thesis future developments. C. L. LEONARD 1 Jul. 1986 159 p Prepared for Massachusetts Inst. of Tech., Cambridge (Contract NAS9-17560) (NASA-CR-171939; NAS 1.26:171939; CSDL-T-920) Avail: NTlS N87-11833# Dornier-Werke G.m.b.H., Friedrichshafen (West HC AOWMF A01 CSCL 22A Germany). The use of differential drag in the formationkeeping of spacecraft DOCKING MECHANISMS TECHNOLOGY STUDY Final Report is examined. In many future space missions one satellite will be Paris ESA Nov. 1984 70 p required to fly in a specific position with respect to another satellite; (Contract ESA-5195/82-NL-BI) this action is referred to as formationkeeping. In this study, (ESA-CR(P)-2273; ETN-86-98138) Avail: NTlS HC A04/MF A01 differential drag is the difference in drag between the two satellites. A zero impact docking concept, where the attitude orbit control Reasons to use differential drag as an actuator for formationkeeping system (AOCS) of the chaser spacecraft performs a close-up include the avoidance of jet plume impingement effects on closely maneuver within the range of the latching subassembly, is spaced satellites and possible fuel savings. The equations of proposed. The AOCS-controlled closure is a feasible solution of relative motion between the two satellites are derived and a the last meter problem taking typical European rendezvous and mathematical transformation is made to reduce the docking (RVD) mission scenarios into account. The European formationkeeping problem to the simultaneous solution of a double standard docking interface is characterized by the prism seats on integrator and a harmonic oscillator. A two part control law is the chaser and the handles on the target. The servicing concept developed that simultaneously and dependently solves cases being fits well within the modular docking mechanism subsystem driven to a target position; two different simulations are used. The approach with minimum interface problems. The latching concept validity of assumptions made in the derivation of the control law giving high modularity and adaptability can be tailored to the specific is examined in the comparison of similar test cases run through mission needs without changing the baseline. A minimum of RVD different simulations. The control law developed can drive a satellite equipment has to be furnished additionally to existing chaser from an initial position to a target position and maintain the satellite capabilities to perform the RVD last-meter-approach. ESA at that location. Author

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N87-13989'# Hamilton Standard, Hartford, Conn. Space and N87-14374*# National Aeronautics and Space Administration. Sea Systems Dept. Goddard Space Flight Center, Greenbelt, Md. DEVELOPMENT OF A PRE-PROTOTYPE POWER ASSISTED PROCEEDINGS OF THE SMRM DEGRADATION STUDY GLOVE END EFFECTOR FOR EXTRAVEHICULAR ACTIVITY WORKSHOP Final Report 1985 351 p Workshop held in Greenbelt, Md., 9-10 May 1985 1986 26 p (NASA-TM-89274; REPT-408-SMRM-79-0001; NAS 1.1 5:89274) (Contract NAS9-17020) Avail: NTlS HC Al6/MF A01 CSCL 228 (NASA-CR-171940; NAS 1.26:171940; SVHSER-10630) Avail: The proceedings of the Solar Maximum Repair Mission NTlS HC AO3/MF A01 CSCL 05H Degradation Study Workshop, held at the Goddard Space Flight The purpose of this program was to develop an EVA power Center in Greenbelt, Maryland on May 9 to 10, 1985 are contained. tool which is capable of performing a variety of functions while at The results of tests and studies of the returned Solar Maximum the same time increasing the EVA crewmember's effectiveness Mission hardware and materials are reported. Specifically, the by reducing hand fatigue associated with gripping tools through a workshop was concerned with the effects of four years' exposure pressurized EMU glove. The Power Assisted Glove End Effector to a low-Earth orbit environment. To provide a background for the (PAGE) preprototype hardware met or exceeded all of its technical reported findings, the summary includes a short description of the requirements and has incorporated acoustic feedback to allow Solar Maximum Mission and the Solar Maximum Repair Mission. the EVA crewmember to monitor motor loading an'd speed. If this tool is to be developed for flight use, several issues need to be addressed. These issues are listed. Author N87-14375*# National Aeronautics and Space Administration. Goddard Space Flight Center, Greenbelt, Md. REPORTON SMRM CIP MAIN ELECTRONICS BOX COMPONENT N87-14359# MATRA Espace, Paris-Velizy (France). AND MATERIALS DEGRADATION EVALUATIONS RENDEZVOUS AND DOCKING (RVD) GUIDANCE SIMULATION R. E. DAVIS ln its Proceedings of the SMRM Degradation Study PROGRAM, RIDER 2 Final Report C. PAUVERT and R. WORSWICK Paris, France ESA Jan. Workshop p 33-40 1985 1986 212 p Prepared in cooperation with Logica Ltd., London, Avail: NTlS HC A16/MF A01 CSCL 228 The history of the Main Electronics Box (MEB), a description England (Contract ESA-5347/83-NL-BI(SC)) of the the assembly, and handling conditions following the Solar (MATRA-EPT/DT/VTO68/012; ESA-CR(P)-2238; ETN-86-98116) Maximum Repair Mission are contained. B.G. Avail: NTlS HC AlO/MF A01 Propellant sloshing and structural flexibility were added to the RVD Simulation Program (now called RVD Guidance Simulator). The performance of the modified program for realistic mission N87-14394# European Space Agency, Paris (France). configurations and docking conditions was evaluated. The basic PROCEEDINGS OF AN INTERNATIONAL SYMPOSIUM ON structure of the RVD Guidance Simulator (RVD GS) is kept, but FLUID DYNAMICS AND SPACE to save computing time, a basic two body (chaser+target) version W. R. BURKE, comp. Aug. 1986 205 p Symposium held in of the program was developed, rather than a three body version Rhode-Saint-Genese, Belgium, 25-26 Jun. 1986; organized by ESA, including a dummy Earth, previously used to overcome numerical and the Von Karman Inst. for Fluid Dynamics problems. Simulations provide sets of typical docking conditions (ESA-SP-265; ISSN-0379-6566; ETN-87-98893) Avail: NTlS HC in terms of spacecraft relative position, velocity, attitude, and AlO/MF A01 attitude rate for various geometric, dynamic, and control Reentry aerothermodynamics; rocket engines; spacecraft configurations. Worst case parameters are derived from the environments; and fluid dynamic experiments in space were simulations as typical initial conditions to the Docking Simulation discussed. Program. ESA ESA

N87-14364# SATCOM International, Paris (France). ANALYSIS OF RENDEZVOUS AND DOCKING IN N87-14423'# National Aeronautics and Space Administration. GEOSTATIONARY EARTH ORBIT. RIDER TO COMPARISON OF Lewis Research Center, Cleveland, Ohio. FUTURE COMMUNICATIONS SPACE SEGMENT CONCEPTS THE SURVIVABILITY OF LARGE SPACE-BORNE REFLECTORS Final Report UNDER ATOMIC OXYGEN AND MICROMETEOROID IMPACT C. COUGNET, J. M. AUBERTIN, P. LEBOUAR, B. GOVIN, A. D. A. GULINO 1987 18 p Presented at the 25th Aerospace AYOUN, and M. CALDICHOURY Toulouse, France Matra Sciences Meeting, Reno, Nev., 12-15 Jan. 1987; sponsored by Espace Sep. 1982 164 p AlAA (Contract ESA-4818/81-NL-MD) (NASA-TM-88914; E-3338; NAS 1.1 5:88914) Avail: NTlS HC (DM51-C/PL/FL/0099.82; ESA-CR(P)-2011-VOL-2; A02/MF A01 CSCL 21H ETN-87-98644) Avail: NTlS HC AOB/MF A01 Solar dynamic power system mirrors for use on space station Geostationary rendezvous homing, final approach, and docking and other spacecraft flown in low Earth orbit (LEO) are exposed phases were analyzed. The target is assumed to be a linear to the harshness of the LEO environment. Both atomic oxygen telecommunication platform composed of a service module and and micrometeoroids/space debris can degrade the performance several payload modules; when operating, the platform must not of such mirrors. Protective coatings will be required to protect be disturbed by the rendezvous and docking (RVD) operations. A oxidizable reflecting media, such as silver and aluminum, from period of time compatible with the orientation of the solar arrays atomic oxygen attack. Several protective coating materials have is allocated each day for the final approach and docking phase. been identified as good candidates for use in this application. The homing phase and final approach are analyzed with simulations The durability of these coating/mirror systems after pinhole defects which propose a nominal strategy to meet the constraints and have been inflicted during their fabrication and deployment or requirements, and to reuse as much as possible hardware already through micrometeoroid/space debris impact once on-orbit is of implemented on board. The analysis of docking phase is performed concern. Studies of the effect of an oxygen plasma environment in terms of performance and requirements, and results in the on protected mirror surfaces with intentionally induced pinhole definition of docking mechanism concepts. Block diagram of the defects have been conducted at NASA Lewis and are reviewed. RVD is compared to the reference scenario; the applicability of It has been found that oxidation of the reflective layer and/or the the scenario to ESAS platform and specific RVD hardware are substrate in areas adjacent to a pinhole defect, but not directly discussed. ESA exposed by the pinhole, can occur. Author

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N87-15028# Committee on Commerce, Science, and N87-16027'# Jet Propulsion Lab., California Inst. of Tech., Transportation (U.S. Senate). Pasadena. REPORT OF THE NATIONAL COMMISSION ON SPACE SENSOR TECHNOLOGY FOR ADVANCED SPACE MISSIONS Washington GPO 1986 53 p Hearing before the Subcommittee N. M. NERHEIM and R. P. DEPAULA In NASA. Langley Research on Science, Technology and Space of the Committee on Center NASAIDOD ControVStructures Interaction Technology, Commerce, Science and Transportation, 99th Congress, 2nd 1986 p 207-219 NOV. 1986 Session, 22 Jul. 1986 Avail: NTlS HC A23/MF A01 CSCL 148 (S-HRG-99-954; GPO-64-727) Avail: Subcommittee on Science, The capability and applications of two sensors, Spatial, Technology and Space High-Accuracy, Position-Encoding Sensor (SHAPES) and Fiber The proposed agenda for the civilian space program for the Optics Rotation Sensor (FORS), for advanced missions are next 20 years and beyond was discussed. The National Commission discussed. The multiple target, 3-D position sensing capability of on Space proposed a broad, long-range, pioneering mission which SHAPES meets a critical technology need for many developing includes: exploration and development of the space frontier; applications. A major milestone of the SHAPES task was completed advancing science, technology, and enterprise; and building on schedule on May 30, 1986, by demonstrating simultaneous institutions and systems that make acessible vast resources and ranging to eight moving targets at a rate of 10 measurements per support human settlement beyond Earth orbit, from the highlands second. The range resolution to static target was shown to be 25 of the Moon to the plains of Mars. To accomplish this mission, microns. SHAPES scheduled technology readiness will support the three mutually-supportive thrusts are outlined: advancing scientific sensor needs of a number of early users. The next phase in the understanding of the planet Earth, the solar system, and the development of SHAPES is to incorporate an angular measurement universe; exploring, prospecting, and settling the solar system; CCD to provide the full 3-dimensional sensing. A flight unit design and stimulating space enterprise. B.G. and fabrication can be complete by FY89. FORS, with its significant improvement over present technology in lifetime, performance, weight, power, and recurrent cost, will be an important technology for future space systems. Technology readiness will be demonstrated with a FORS brassboard with fully integrated IO chips by FY88. The unique capability of miniature remote sensing N87-15259*# National Aeronautics and Space Administration. heads, connected to a central system, will open up new areas in Langley Research Center, Hampton, Va. control and stability of large space structures. This application SPACE SPIDER CRANE Patent Application requires additional study. Author IAN 0. MACCONOCHIE, inventor (to NASA), JACK E. PENNINGTON, inventor (to NASA), CHARLES F. BRYAN, JR., N87-16321'# National Aeronautics and Space Administration. inventor (to NASA), MARTIN M. MIKULAS, JR., inventor (to NASA), Lewis Research Center, Cleveland, Ohio. and REBECCA KINKEAD, inventor (to NASA) 30 Sep. 1986 L. THE 20TH AEROSPACE MECHANICS SYMPOSIUM 18 P May 1986 316 p Symposium held in Cleveland, Ohio, 7-9 May (NASA-CASE-LAR-13411-1SB; NAS 1.71:LAR-13411-1; 1986; sponsored by NASA, the California Inst. of Tech. and US-PATENT-APPL-SN-913432) Avail: NTlS HC A02/MF A01 LMSC CSCL 84G (NASA-CP-2423-REV; E-2904; NAS 1.55:2423-REV) Avail: NTlS A space spider crane for the movement, placement, and/or HC A14/MF A01 CSCL 20K assembly of various components on or in the vicinity of a space Numerous topics related to aerospace mechanisms were structure is described. As permanent space structures are utilized discussed. Deployable structures, electromagnetic devices, by the space program, a means will be required to transport cargo tribology, hydraulic actuators, positioning mechanisms, electric and perform various repair tasks. A space spider crane comprising motors, communication satellite instruments, redundancy, a small central body with attached manipulators and legs fulfills lubricants, bearings, space stations, rotating joints, and this requirement. The manipulators may be equipped with constant teleoperators are among the topics covered. pressure gripping end effectors or tools to accomplish various repair tasks. The legs are also equipped with constant pressure gripping end effectors to grip the space structure. Control of the N87-16338*# Sperry Corp., Phoenix, Ariz. Space Systems Div. space spider crane may be achieved either by computer software SPACE STATION ROTARY JOINT MECHANISMS or a remotely situated human operator, who maintains visual contact GLEN W. DRlSKlLL In NASA. Lewis Research Center The 20th via television cameras mounted on the space spider crane. One Aerospace Mechanics Symposium p 241-251 May 1986 possible walking program consists of a parallel motion walking Avail: NTlS HC A14/MF A01 CSCL 131 The mechanism which will be used on the space station to program whereby the small central body alternatively leans forward position the solar arrays and radiator panels for Sun pointing and and backward relative to end effectors. NASA Sun avoidance is described. The unique design features will be demonstrated on advanced development models of two of the joints being fabricated under contract to NASA-MSFC. Author

N87- 16366# Air Force Wright Aeronautical Labs., N87-16014*# National Aeronautics and Space Administration. Wright-Patterson AFB, Ohio. Langley Research Center, Hampton, Va. DAMPING 1986 PROCEDURES, VOLUME 2 Summary Report, NASNDOD CONTROUSTRUCTURES INTERACTION TECHNOL- Feb. 1984 - Feb. 1986 OGY, 1986 E. D. PINSON, D. W. NICHOLSON, M. G. PRASAD, R. H. LIN, ROBERT L. WRIGHT, comp. Nov. 1986 549 p Conference and B. K. WADA May 1986 614 p held in Norfolk, Va., 18-21 Nov. 1986; sponsored by NASA Langley (AD-A173950; AFWAL-TR-86-3059-VOL-2) Avail: NTlS HC Research Center and AFWAL A99/MF A01 CSCL 20K (NASA-CP-2447-PT-1; L-16242-PT-1; NAS 1.5512447-PT-1) Individual conference papers are presented. Some of the titles Avail: NTlS HC A23/MF A01 CSCL 228 include: Damping Characteristics of the Solar Array Flight ControVstructures interactions, deployment dynamics and Experiment; Resonant Shift Modal Testing Method for Viscous system performance of large flexible spacecraft are discussed. Damping Coefficient Estimation; Prediction of Spacecraft Damping; Spacecraft active controls, deployable truss structures, deployable On Orbit Flexible Body Parameter Identification for Space Station; antennas, solar power systems for space stations, pointing control Design and Analysis of the PACOSS Representative System; systems for space station gimballed payloads, computer-aided Robust Control Design for Vibration Suppression of Large Space design for large space structures, and passive damping for flexible Structures; Active Augmentation of a Passively Damped structures are among the topics covered. Representative Large Space System; Active Control for Vibration

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Damping; A New Approach to Modeling Linear Viscoelastic stiffness. Applications include controlling the final angular aperture Damping for Space Structures; Expertimental Investigations Into of deployable antennas, e.g., the petals of the FIRST antenna. Passive and Active Control Using Space Realized Techniques; For this case, main requirements are: minimum angular step 0.001 Material Damping in Aluminum and Metal Matrix Materials; Material arc min; total angular range 2.6 arc min; torsional stiffness 900,000 Damping in Space Structures; Specific Damping Capacity of Metal Nm/ rad. ESA Matrix Composites in Tension Tension Fatigue; Response Suppression in Composite Sandwich Shells; Prediction of Material Damping of Laminated Polymer Matrix Composites; The Influence of Fiber Length and Fiber Orientation on Damping and Stiffness N87-17036' National Aeronautics and Space Administration. of Polymer Composite Materials; A Review of the Damping Lyndon 6. Johnson Space Center, Houston, Tex. Mechanisms in Advanced Fiber Reinforced Plates; Damping SUN SHIELD Patent Measurements by Hilbert Transform on Composite Materials; and ARTHUR M. FRANK, inventor (to NASA), SlLVlO F. DERESPINIS, A Comparison Among Damping Coefficients on Several Aerospace inventor (to NASA), and JOHN MOCKOVCIAK, JR., inventor (to Composite Materials. GRA NASA) 20 Jan. 1987 8 p Filed 12 Aug. 1985 Supersedes N86-20803 (24 - 11, p 1783) N87-16662# Executive Office of the President, Washington, D.C. (NASA-CASE-MSC-20162-1; US-PATENT-4,637,447; AERONAUTICS AND SPACE REPORT OFTHE PRESIDENT: 1985 US-PATENT-APPL-SN-764805; US-PATENT-CLASS-160-265; ACTIVITIES US-PATENT-CLASS-160-23R; US-PATENT-CLASS-244-121 ; US-PATENT-CLASS-244-158R; US-PATENT-CLASS-135-903; 1986 132p US-PATENT-CLASS-296-100) Avail: US Patent and Trademark Avail: NTlS HC A07/MF A01 Office CSCL 131 The achievements of aeronautics and space programs in the A shading device which is capable of compactly storing a flexible United States for 1985 are summarized in the areas of shade on a biased, window shade type spring roller is disclosed. communications; Earth atmosphere, environment, and resources; It is controlled to deliver the shade selectively to either its operative space science; space transportation; commercial use of space; shading or compact storage orientation. space tracking and data systems; space station; and aeronautics Official Gazette of the US Patent and Trademark Office and space research and technology. The achievements of each of the following organizations are described: National Aeronautics and Space Administration, Department of Defense, Department of Commerce, Department of Energy, Department of the Interior, N87-17656'# National Aeronautics and Space Administration. Department of Agriculture, Federal Communications Commission, Lewis Research Center, Cleveland, Ohio. Department of Transportation, Environmental Protection Agency, RESEARCH AND TECHNOLOGY Annual Report, 1986 National Science Foundation, Smithsonian Institution, Department 1986 103 p of State, Arms Control and Disarmament Agency, and United States (NASA-TM-88868; NAS 1.1 5:88868) Avail: NTlS HC AO6/MF Information Agency. Appendices provide historical information on A01 CSCL05A launches, satellites, manned and unmanned spacecraft, and federal The research and technology accomplishments of the NASA budgets for aeronautical and astronautical activities. J.P.B. Lewis Research Center are summarized for the fiscal year 1986, the 45th anniversary year of the Center. Five major sections are presented covering: aeronautics, aerospace technology, space N87-16944# Contraves Italiana, Rome. communications, space station systems, and computational CONTRAVES' ANTENNA TIP HINGE MECHANISM FOR technology support. A table of contents by subjects was developed SELENIA SPAZIOS 20/30 GHZ ANTENNA to assist the reader in finding articles of special interest. Author D. STELLA, F. MORGANTI (Selenia S.p.A., Rome, Italy), and G. NIELSEN (European Space Agency. European Space Research and Technology Center, ESTEC, Noordwijk (Netherlands) In ESA Proceedings of the Second ESA Workshop on Mechanical N87-17810# Toronto Univ. (Ontario). Inst. for Aerospace Technology for Antennas p 185-194 Aug. 1986 Studies. Avail: NTlS HC A12/MF A01 COMBINED ORBIT/ATTITUDE DETERMINATION FOR A mechanism which can deploy a folded tip of an antenna in LOW-ALTITUDE SATELLITES orbit, the Antenna Tip Hinge Mechanism (ATHM) was developed. PAUL WINCHESTER CHODAS Dec. 1986 275 p The ATHM consists of two hinges, each near the edge of the (UTIAS-320; ISSN-0082-5255; AD-6109229L) Avail: NTlS HC antenna main body and tip interface. Following a command, the A12/MF A01 antenna tip is released and spiral springs drive the antenna tip to Orbit and attitude determination are studied as a single its end position, where latches secure the tip in place. No damping combined estimation problem, and the coupling between the orbit or any form of energy dissipation is provided for, other than that and attitude dynamics is included. The focus is on missions with which is caused by friction within the system. Two ATHM's, one large spacecraft in low-altitude Earth orbits. The orbit and attitude at each end of the antenna, enable a 20/30 GHz multibeam motions are coupled by the gravitational forces and torques and antenna to fit in the Ariane 4 shroud. This mechanism can, with the aerodynamic forces and torques, which are the dominant minor modifications, be used to deploy a multitude of different environment effects for the class of missions under consideration. systems, provided that they are not too fragile to withstand the A computer simulation of the combined orbit and attitude deceleration loads that occur at the end of deployment. ESA determination problem, including the coupled orbit and attitude equations of motion, was implemented. Two combinations of N87-16946# Sener, SA., Madrid (Spain). measurement types are studied: ground tracking with onboard star A SENER MECHANISM: FINE ADJUSTMENT MECHANISM FOR observations, and onboard tracking of known landmarks combined THE FAR INFRARED AND SUBMILLIMETER SPACE with star observations. The effect of the dynamic orbit-attitude TELESCOPE (FIRST) (F F F) coupling on the position and attitude estimates was studied. It is F. DELCAMPO. J. DELTORO, and J. RIVACOBA In ESA shown that the inclusion of the dynamic coupling improves the Proceedings of the Second ESA Workshop on Mechanical position and attitude estimates substantially. Using covariance Technology for Antennas p 205-210 Aug. 1986 analysis techniques, it is demonstrated that the attitude Avail: NTlS HC A12/MF A01 uncertainties are unrealistically small without coupling, and that A mechanism for obtaining very fine variations of the relative this lead to divergence in the attitude estimate. The use of process angular position of two surfaces having a common hinge axis is noise to prevent this divergence in the attitude estimate is studied. presented. The mechanism introduces no backlash, by using flexing A process noise model which includes some of the coupling effects elements for articulations. It can be designed for very high torsional is also applied to the problem. Author

74 10 GENERAL

N87-17820' National Aeronautics and Space Administration, N87-19814# Societe Nationale Industrielle Aerospatiale, Cannes Washington, D.C. (France). Div. Systems Balistiques et Spatiaux. SPACE STATION SYSTEMS A CONTINUING BIBLIOGRAPHY THE CONCENTRATION PRINCIPLE APPLIED TO SPACEBORNE WITH INDEXES (SUPPLEMENT 3) SOLAR ARRAYS. APPLICATION TO THE COORBITING Jan. 1987 205 p PLATFORM MISSION: STUDIES SYNTHESIS (NASA-SP-7056(03); NAS 1.21 :7056(03)) Avail: NTlS HC A10 R. LAGET Paris, France ESA 27 Jan. 1986 46 p CSCL 22A (Contract ESA-5978/84-NC-PB(SC)) This bibliography lists 780 reports, articles and other documents (SNIAS-975-CA/CG; ESA-CR(P)-2291-VOL-l; ETN-87-99482) introduced into the NASA scientific and technical information Avail: NTlS HC AOB/MF A01 system between January 1, 1986 and June 30, 1986. Its purpose Studies that led to selection of the distributed concentration is to provide helpful information to the researcher, manager, and biplane concept for the solar cell generator to be flown on the designer in technology development and mission design according coorbiting platform mission, and the major characteristics of such to system, interactive analysis and design, structural and thermal a spaceborne solar array are summarized. It is concluded that analysis and design, structural concepts and control systems, there is not a considerable interest in concentration either for electronics, advanced materials, assembly concepts, propulsion, array area reduction or cost reduction, although improvements of and solar power satellite system. The coverage includes documents 15% for both domains are feasible. Only predevelopment activities that define major systems and subsystems, servicing and support to verify concentrator performances and system studies to assess requirements, procedures and operations, and missions for the respective importance of cost and area saving may increase the current and future space station. Author level of interest of concentrator solar arrays for this kind of mission. ESA

N87-20057'# Jet Propulsion Lab., California Inst. of Tech., Pasadena. N87-17821'# National Aeronautics and Space Administration. LARGE STRUCTURES AND TETHERS WORKING GROUP Langley Research Center, Hampton, Va. G. MURPHY, H. GARRET, U. SAMIR, A. BARNET, J. RAIlT, PROCEEDINGS OF THE 3RD ANNUAL SCOLE WORKSHOP J. SULLIVAN, and 1. KATZ ln its Space Technology Plasma LAWRENCE W. TAYLOR, JR., comp. Jan. 1987 457 p Issues in 2001 p 6-11 1 Oct. 1986 Workshop held in Hampton, Va., 17-18 Nov. 1986; sponsored by Avail: NTlS HC A20/MF A01 CSCL 228 NASA Langley Research Center and California Univ., Los The Large Structures and Tethers Working Group sought to Angeles clarify the meaning of large structures and tethers as they related (NASA-TM-89075; NAS 1.1589075) Avail: NTlS HC A20/MF to space systems. Large was assumed to mean that the A01 CSCL22B characteristic length of the structure was greater than one of such Topics addressed include: modeling and controlling the relevant plasma characteristics as ion gyroradius or debey length. Spacecraft Control Laboratory Experiment (SCOLE) configurations; Typically, anything greater than or equal to the Shuttle dimensions slewing maneuvers; mathematical models; vibration damping; was considered large. It was agreed that most large space systems gravitational effects; structural dynamics; finite element method; that the tether could be better categorized as extended length, distributed parameter system; on-line pulse control; stability area, or volume structures. The key environmental interactions augmentation; and stochastic processes. were then identified in terms of these three categories. In the following Working Group summary, these categories and the related interactions are defined in detail. The emphasis is on how increases in each of the three spatial dimensions uniquely determine the interactions with the near-Earth space environment. Interactions with the environments around the other planets and the solar N87-17838"# McDonnell-Douglas Astronautics Co., Houston, wind were assumed to be similar or capable of being extrapolated Tex. from the near-Earth results. It should be remembered in the ADVANCED EVA SYSTEM DESIGN REQUIREMENTS STUDY, following that the effects on large systems do not just affect specific EXECUTIVE SUMMARY Final Technical Report technologies but will quite likely impact whole missions. Finally, Jan. 1986 45 p the possible effects of large systems on the plasma environment, (Contract NAS9-17299) although only briefly discussed, were felt to be of potentially great (NASA-CR-171960; NAS 1.26:171960; MDC-W0072) Avail: NTlS concern. Author HC A03lMF A01 CSCL 228 Design requirements and criteria for the space station advanced N87-20071*# Science Applications International Corp., McLean, Extravehicular Activity System (EVAS) including crew enclosures, Va. Plasma Physics Div. portable life support systems, maneuvering propulsion systems, TECHNICAL ISSUES IN THE CONDUCT OF LARGE SPACE and related EVA support equipment were established. The EVA PLATFORM EXPERIMENTS IN PLASMA PHYSICS AND mission requirements, environments, and medical and physiological GEOPLASMA SCIENCES requirements, as well as operational, procedures and training issues EDWARD P. SZUSZCZEWICZ ln JPL, Space Technology Plasma were considered. B.G. Issues in 2001 p 225-236 1 Oct. 1986 Avail: NTlS HC A2O/MF A01 CSCL 201 Large, permanently-manned space platforms can provide exciting opportunities for discoveries in basic plasma and geoplasma sciences. The potential for these discoveries will depend N87-18583'# Science Applications International Corp., very critically on the properties of the platform, its subsystems, Schaumberg, 111. Advanced Planning and Analysis Div. and their abilities to fulfill a spectrum of scientific requirements. SATELLITE SERVICING PRICE ESTIMATION INSTRUCTION With this in mind, the planning of space station research initiatives BOOKLET and the development of attendant platform engineering should Jan. 1987 47 p allow for the identification of critical science and technology issues (Contract NAS9-17207) that must be clarified far in advance of space station program (NASA-CR-171967; NAS 1.26:171967; SAIC-87/1515; implementation. An attempt is made to contribute to that process, SAIC-1-120-7784215) Avail: NTlS HC AOS/MF A01 CSCL 22A with a perspective that looks to the development of the space The results of a brief study to develop a possible methodology station as a permanently-mannedSpaceborne Ionospheric Weather for estimating the price to non-US. Government users for satellite Station. The development of this concept requires a synergism of servicing are documented. B.G. science and technology which leads to several critical design

75 10 GENERAL issues. To explore the identification of these issues, the development of the concept of an Ionospheric Weather Station will necessarily touch upon a number of diverse areas. These areas are discussed. Author

N87-20079'# California Univ., San Diego, La Jolla. Center for Astrophysics and Space Science. CONTROLLING AND MONITORING THE SPACE-STATION PLASMA INTERACTION: A BASELINE FOR PERFORMING PLASMA EXPERIMENTS AND USING ADVANCED TECHNOLOGY Abstract Only ELDEN C. WHIPPLE and RICHARD C. OLSEN (Alabama Univ., Huntsville) ln JPL, Space Technology Plasma Issues in 2001 p 310 1 Oct. 1986 Avail: NTlS HC A20/MF A01 CSCL 228 The size, complexity, and motion of space station through the Earth's environmental plasma means that there will be a large, complicated interaction region, involving a sheath, wake, charging of surfaces, induced electric fields, secondary emission, outgassing with ionization, etc. This interaction will necessarily be a factor in carrying out and interpreting plasma experiments and in the use of certain technologies. Attention should be given ahead of time to: (1) monitoring this interaction so that it is well described; (2) implifying the interaction by appropriate design and construction of the spacecraft and by appropriate planning of technology use; and (3) controlling the interaction by both active and passive means. Plasma emitters for modifying and controlling the spacecraft charge should be placed in several locations. Portable electrostatic shields could be deployed around noisy sections of the spacecraft in order to carry out sensitive experiments. A particle umbrella could be raised to deflect the ram ions and neutrals in order to provide a controlled environment. These interactions are briefly discussed. Author

76 SUBJECT INDEX

TECHNOLGY FOR LARGE SPACE SYSTEMS /ABibliography (Supplement 17) OCTOBER 1987

Typical Subject Index Listing

Experimental study of active vibration control AEROSPACE INDUSTRY IAD-At731441 p 41 N87-17845 Space commerce '86; Proceedings of the International SUBJECT HEADING ACTUATORS Conference and Exhibition on the Commercial and Effect of sensor and actuator errors on static shape Industrial Uses of Outer Space, Montreux. Switzerland, control for large space structures p 29 A8727948 June 16-20. 1986 p 69 A87-29401 Large wheel actuators definition study --- spacecraft Aerospace Testing Seminar, 9th. Los Angeles. CA. Oct. control t 5-1 7, 1985. Proceedings p 69 A87-29441 I TELDIX-15-020-880I p 33 N87-11834 AEROSPACE SCIENCES F Static deflection control of flexible beams by International Symposium on Space Technology and piezo-electric actuators Science. 14th. Tokyo, Japan, May 27-June 1. 1984. I NASA-CR-179947I p 34 N87-13788 Proceedings p 66 A87-18201 Distributed control for COFS 1 p 36 N87-16043 AEROSPACESYSTEMS The 20th Aerospace Mechanics Symposium Aerospace Computer Security Conference, 2nd. I NASA-CP-2423-REV] p 73 N87-16321 McLean. VA, December 2-4. 1986. Technical Papers Proof-mass actuator placement strategies for regulation p 67 A87-18852 of flexure during the SCOLE slew p 40 N87-17830 Optimization of closed loop eigenvalues. Maneuvering. Regulation of the SCOLE configuration vibration control and structurelcontrol design iteration for p 41 N87-17833 flexible spacecraft The SCOLE design challenge p 10 N87-17836 (AD-A1727161 p 34 N87-15263 Optimum vibration control of flexible beams by piezo-electric actuators Mast flight system beam structure and beam structural I NASA-CR-180209I p 42 N87-18880 performance p 17 N87-I6031 ADAPTIVE CONTROL MAST flight system dynamic performance p 35 N87-16032 The subject heading is a key to the subject content Adaptive control techniques for large space structures I AD-At 73083 I p 38 N87-16871 Passively damped loints for advanced space of the document The title is used to provide a Adaptive control of a flexible structure structures description of the subject matter When the title is p 39 N87-17449 IAD-Al749141 p 42 N87-19435 insufficiently descriptive of the document content, ADHESIVE BONDING Large structures and tethers working group the title extension is added, separated from the International Week on Bonding and Joining p 75 N87-20057 Technologies. 1st, Bordeaux. France. April 15-18, 1986, title by three hyphens The (NASA or AIAA) acces- AEROSPACE TECHNOLOGY TRANSFER Selected Papers p 67 A87-20144 Space Station beyond IOC; Proceedings of the sion number and the page number are included in Behavioural analysis of adhesive-bonded structural Thirty-second Annual International Conference. Los each entry to assist the user in locating the abstract joints in space vehicles p 16 A87-20148 Angeles. CA. November 6. 7, 1985 -.. Initial Operational Adhesive bonding of aerospace materials - Surface Capability p 65 A87-15376 in the abstract section If applicable, a report characterization of metallic adherends number is also included as an aid in identifying Space Station evolution - The aerospace technology p 51 A87-20149 impact the document Under any one subject heading, the Debonding analysis of thermally stressed I AAS PAPER 85-456 I p 1 A87-15380 fiber-reinforced composite malerials p 52 N87-10933 accession numbers are arranged in sequence with Technologies lor affordable access to space ADHESIVES I IAF PAPER 86-4421 p 2 A87-16096 the AlAA accession numbers appearing first Effects of thermal cycling on the mechanical and physical properties of a space qualified epoxy adhesive Space Station - NASA's greatest challenge p 19 A87-20082 p2 A87-16399 A AERODYNAMIC DRAG AEROTHERMODYNAMICS Formationkeeping of spacecraft via differential drag Proceedings of an International Symposium on Fluid ACGENERATORS I NASA-CR-1719391 p 71 N87-13466 Dynamics and Space Design of a superconducting alternator for space based AERODYNAMIC LOADS [ ESA-SP-2651 p 72 N87-14394 power generation p 43 A87-18144 Combined orbitlattitude determination for low-altitude AGREEMENTS The Space Station - United States proposal and ACCESS CONTROL satellites Proceedings of the 5th Annual Users' Conference [ UTIAS-320 I p 74 N87-17810 implementation p 1 A87-14969 INASA-CP 2399 I p 70 N87 10720 AERODYNAMICS AIRCRAFT CONSTRUCTION MATERIALS International Symposium on Space Technology and ACCIDENTS Activities report in materials and construction --- Science, 14th. Tokyo, Japan, May 27-June 1. 1984. Hearings before the Subcommittee on Space Science aerospace structures Proceedings p 66 A87-18201 [ISSN-Ot74-39101 p 54 N87-13589 and Applications of the Committee on Science and AERONAUTICAL ENGINEERING Technology, 99th Congress 2nd Session. No 132. 25. AIRCRAFT DESIGN Aeronautics and space report of the President: 1985 27 February. 11 13 20 March 10 April 1986 Volume Recent Experiences in Multidisciplinary Analysis and 9 activities p 74 N87-16662 2 Optimization. part 1 [GPO 61.7771 p7 N87-12402 Research and technology I NASA-CP-2327-PT-1I p 71 N87-11717 INASA-TM-88868 j p 74 N87-17656 ACOUSTIC EXCITATION Recent Experiences in Multidisciplinary Analysis and AEROSPACE ENGINEERING Comparison of multiple input random and sine excitation Optimization. part 2 Aerospace Applications Conference, Steamboat [ NASA-CP-2327-PT-2I p 71 N87-11750 methods for aerospace structures --- spacecraft vibration Springs. CO. Feb. 1-8. 1986. Digest p 69 A8725976 AIRCRAFT STRUCTURES models p 12 A87 28552 Second AlAAlNASA USAF Symposium on Automation. Activities report in materials and construction --- Prediction and correlation of structural response in Robotics and Advanced Computing for the National Space acoustic chambers .--large space structures aerospace structures Program [ ISSN-0174-39101 p 54 N87-I3589 p 20 N87-10907 1 AlAA PAPER 87-16551 p 70 A87-31112 AIRGLOW ACTIVE CONTROL Mast flight system beam structure and beam structural Spacecraft glows from surface-catalyzed reactions Improving the active vibrational control of large space performance p 17 N87-16031 p 43 A87-I7368 structures through structural modifications Aeronautics and space report of the President: 1985 ALGORITHMS [ IAF PAPER 86-204 I p 26 A87-15932 activities p 74 N87-16662 MAST flight system dynamic performance A slewing control experiment for flexible structures Adaptive control techniques for large space structures p 35 N87-16032 p 27 A87-17761 [AD-A173083] p 38 N87-16871 ALTERNATING CURRENT On optimal passive and active control of precision AEROSPACE ENVIRONMENTS Radiation from large space structures in low earth orbit spacecran structures p 31 N87-10891 Studies of erosion of solar max samples of Kapton and with induced ac currents Distributed active control of large flexible space Teflon p 55 N87-14384 [AIM PAPER 87-06121 p 68 A87-22738 structures Proceedings of an International Symposium on Fluid ALUMINUM ALLOYS [NASA-CR-t79941] p 33 N87-13476 Dynamics and Space Fabrication of a carbon fibrelaluminium alloy composite Active Control Evaluation for Spacecraft (ACES) ( ESA-SP-2651 p 72 N87-14394 under microgravity p 48 A87-11384 p34 N87 16019 Space spider crane The welding of aluminum alloys. A new technology in The 15 meter hoop-column antenna dynamics Test and [ NASA-CASE-LAR-1341I-lSBI p 73 N87-I5259 space application p 56 N87-17056 analysis p35 N87-16025 Tribological properties of polymer films and solid bodies ALUMINUM COATINGS Multidisciplinary analysis of actively controlled large in a vacuum environment Preliminary results of SMM exposed aluminized Kapton flexible spacecraft p 37 N87-16045 [ NASA-TM-889661 p 57 N87-17906 and silvered Teflon p 55 N87-14389

A- 1 ALUMINUM GRAPHITE COMPOSITES SUBJECT INDEX

ALUMINUM GRAPHITE COMPOSITES APPENDAGES AUTOMATION Effects of thermal cycling on graphie-fiber-reinforced Dynamic analysis of satellites with deployable hinged Space station automation; Proceedings of the Meeting, 6061 aluminum appendages Cambridge, MA. September 17. 18. 1985 [ NASA-TP-26121 p 52 N87-10184 [AIAA PAPER 87-00201 p 27 A87-22364 [SPIE-580] p 64 A87-13705 Metallurgical characterizationof the interfaces and the APPROPRIATIONS The role of automation and robotics in space stations damping mechanisms in metal matrix composites National Aeronautics and Space Administration p 58 A87-13706 [ADA1734701 p 57 N87-17863 p6 N87-10774 Space missions for automation and robotics ANTENNA COMPONENTS National Aeronautics and Space Administration technologies (SMART) program p 58 A87-13707 Composite space antenna structures: Properties and Authorization Act, 1987 p6 N87-10775 The system approach for applying artificial intelligence environmental effects National Aeronautics and Space Administration to Space Station automation p 64 A87-13708 [ NASA-TM-88859] p 39 N87-16880 p 7 N87-15908 An introduction to the concept of robot factors and its ANTENNA DESIGN application to Space Station automation The ESAIMBB unfurlable mesh antenna development APPROXIMATION Alternative approximation concepts for space frame p 58 A87-13712 for mobile services Remotely manipulated and autonomous robotic welding synthesis p 19 A87-18940 [ IAF PAPER 66-27] p2 A87-15818 fabrication in space p 59 A87-13714 S band 3.5-m-diameter fan rib type deployable mesh ARABSAT The role of expert systems on Space Station ARABSAT solar generator concept and in orbit antenna for satellite use p 4 A87-25758 [ IAF PAPER 86-28] p 11 A87-15819 performance p 43 A87-18075 AUTONOMY Concept of tension activated cable lattice antenna ARCHITECTURE (COMPUTERS) Robotics concepts for the US. Space Station [IAF PAPER 86.2061 p 15 A87-15934 Software architecture for manufacturing and space [AAS PAPER 85.6661 p 60 A87-18486 Antenna system alternatives for Data Relay Satellites robotics with multiple steerable beams [AIAA PAPER 87-16871 p 12 A87-31121 [IAF PAPER 86-3491 p 43 A87-16041 ARTIFICIAL INTELLIGENCE B Offset unfurlable antenna. Phase 2A: Executive 1986 American Control Conference, 5th, Seattle, WA, summary --- Intelsat. M-Sat June 16-20, 1986. Proceedings. Volumes 1. 2. 8 3 BALLISTIC MISSILES [ MBB-R-0200/3069-R] p 70 N87-11066 p 64 A87-13301 Space vehicle design --- French book Unified controllstructure design and modeling The system approach for applying artificial intelligence p 11 A87-10092 research to Space Station automation p 64 A87-13708 BAYES THEOREM [ NASA-CR-1799481 p 33 N87-13478 The role of expert systems on Space Station Component testing for dynamic model verification Study of frequency selective systems. Part 1: Preliminary p4 A87-25758 p 32 N87-11765 investments on shapes and lattices; software ARTIFICIAL SATELLITES BEAMS (SUPPORTS) developments. Part 2: Interfacing of Politecnico FSS Development of the Lens Antenna Deployment On the Orbiter based deployment of flexible members programs with MATRA reflector antenna software. Part Demonstration (LADD) shuttle-attachedflight experiment [AAS PAPER 85-6731 p 16 A87-18489 3: Application to MACS phase 2 TX antenna (MATRA) p 7 N87-16022 An explicit expression for the tangent-stiffness of a --- satellite antennas Aeronautics and space report of the President: 1985 finitely deformed 3-D beam and its use in the analysis of [ANT/NTEA/04.85] p 13 N87-13626 activities p74 N87-16662 space frames p 19 A87-20247 Development of the 15 meter diameter hoop column ASSEMBLING On the dynamics of flexible beams under large overall antenna Assembly of thermoelastic continuous elements motions - The plane case. I, II [ NASA-CR-40381 p 17 N87-14366 [IAF PAPER 86.2071 p 59 A87-15935 [ASME PAPER 86-WA/APM-41I p 28 A87-23212 L-band antennas for regional mobile communication ASTRODYNAMICS Wave-absorbing controllers for a flexible beam satellites p 47 N87-15377 The dynamics and control of a space platform connected p 28 A87-23986 Mechanical and control study of a 7 m offset unfurlable to a tethered subsatellite p 25 A87-14074 Design, construction and utilization of a space station tracking antenna p 39 N87-16926 Dynamics formulation and simulation of multi-body assembled from 5-meter erectable struts Development of a 2.8 m offset antenna reflector using space structures [ NASA-TM-890431 p 6 N87-11827 inflatable. space-rigidized structures technology [IAF PAPER 86.2381 p 26 A87-15957 Static deflection control of flexible beams by p8 N87-16927 Dynamic analysis of satellites with deployable hinged piezo-electricactuators Study on solid surface, deployable antenna reflector --- appendages [NASA-CR-I79947 ] p 34 N87-13788 satellite antenna p8 N87-16928 [AIAA PAPER 87-00201 p 27 A87-22364 Mobile remote manipulator system for a tetrahedral Analysis of high precision composite sandwich antennas ASTRONAUT TRAINING truss --- spacecraft antennas p 56 N87-16929 Advanced EVA system design requirements study, [ NASA-CASE-MSC-20985-11 p61 N87-15260 Dielectric support structures for Spacecraft antenna executive summary COFS 1 research overview p8 N87-16029 feeds p 17 N87-16931 [NASA-CR-171960] p 75 N87-17838 Description of the Mast Flight System Design of a low distortion shared aperture reflector -.- ASTRONAUTICS p8 N87-16030 satellite antenna p 14 N87-16934 Space Congress, 23rd. Cocoa Beach. FL, April 22-25, Mast flight system beam structure and beam structural Development of lightweightdimensionally stable carbon 1986. Proceedings p 63 A87-10026 performance p 17 N87-16031 MAST flight system dynamic performance fiber composite antenna reflectors for the INSAT-I Space exploitation and utilization; Proceedings of the p 35 N87-16032 satellite p 56 N87-16936 Symposium, Honolulu, HI, December 15-19. 1985 p 66 A87-18451 MAST flight system operations p 8 N87-16033 Giotto spacecraft high gain antenna mechanical design Development and use of a linear momentum exchange and development p 18 N87-16938 Perspective on non-U.S. presentations at the 37th Congress of the International Astronautical Federation device p 36 N87-16041 Development status of the ERS-I SAR antenna - October 4-1 1. 1986, Innsbruck, Austria Estimation and control of distributed models for certain p9 N87-16939 p 67 A87-21975 elastic systems arising in large space structures ANTENNAFEEDS ASTRONOMICAL OBSERVATORIES [AD-A175019] p 38 N87-16872 Dielectric support structures for spacecraft antenna Large space observatories of the 2tst century Optimum vibration control of flexible beams by feeds p 17 N87-16931 [AIAA PAPER 87.06361 p4 A87-22751 piezo-electricactuators ANTENNA RADIATION PATTERNS Dynamic analysis of the large deployable reflector [ NASA-CR-180209I p 42 N87-18880 Study of frequency selective systems. Part 1: Preliminary [NASA-TM-89056] p 37 N87-16050 BOOMS (EQUIPMENT) investments on shapes and lattices; software ASTRONOMICAL TELESCOPES Pultrusion process development for long space boom developments. Part 2: Interfacing of Politecnico FSS Large optics technology; Proceedings of the Meeting, models p60 A87-20083 programs with MATRA reflector antenna software. Part San Diego. CA. August 19-21, 1985 Boom potential of a rotating satellite in sunlight 3: Application to MACS phase 2 TX antenna (MATRA) [SPIE-571] p 63 A87-10997 p68 A87-24198 --- satellite antennas ltek optical technology in manufacturing and The effect of the non-uniform stress distribution in the [ANT/NTEA104.85] p 13 N87-13626 metrology p 64 A87-11008 blankets of single and twin boom solar array panels upon ANTENNAS ATTITUDE CONTROL their modal characteristics p 32 N87-10904 Effect of sensor and actuator errors on static shape Nonlinear attitude control of elastic spacecraft-antenna Development of a continuous manufacturing method for control for large space structures p 29 ~87-27948 system p 25 A87-13433 a CFRP collapsible tube mast NASA/DOD Control/Structures InteractionTechnology, Attitude control expenment for flexible spacecraft [AERE-G-3898] p 54 N87-13572 1986 p 27 A87-18320 Design and development of a telescopic axial boom [NASA-CP-2447-PT-I] p 73 N87-16014 Numerical and experimental evaluation of poles and p 14 N87-16322 Deployable truss structure advanced technology system zeros for large flexible space structures Space station erectable manipulator placement system P 22 N87-16021 p 27 A87-18322 [NASA-CASE-MSC-21096-1] p 62 N87-18596 COFS 2: 3-D dynamics and controls technology Local output-feedback control for large flexible space structures p 27 A87-18323 BORON OXIDES P 35 N87-16035 Li corrosion resistant glasses for headers in ambient Surface control system for the 15 meter hoop-column Flexibility control of solar battery arrays. II - Vibration and attitudecontrol based on state estimation of differential temperature Li batteries antenna p 37 N87-16047 p 33 N87-12802 Robust multivariable controller design for flexible solar cell sensors p 45 A87-22968 Efficient modal analysis of damped large space BOUNDARY[DE86-013754] VALUE PROBLEMS spacecraft P 37 N87-16048 structures p 28 A87-23995 Issues in modeling and controlling the SCOLE ANTIMISSILE DEFENSE AURORAL ZONES configuration p 39 N87-17822 Solar power satellite concept revisited Spacecraft charging in the auroral plasma: Progress Optimal torque control for SCOLE slewing maneuvers p4 A87-22771 toward understanding the physical effects involved p 40 N87-17823 ANTIREFLECTION COATINGS p 48 N87-20080 Finite element model of SCOLE laboratory Effect of hard particle impacts on the atomic oxygen AUTOMATIC CONTROL configuration p 14 N87-17828 survivability of reflector Surfaces with transparent Software architecture for manufacturing and space Model reference control of distributed parameter protective overcoats robotics systems: Application to the SCOLE problem [AIAA PAPER 87-0104] p 45 A87-22417 [AIAA PAPER 87-16871 p 12 A87-31121 p 40 N87-17829 A-2 SUBJECT INDEX COMPUTERIZED SIMULATION

BOX BEAMS CHEMICAL REACTIONS Composite space antenna structures: Properties and Dynamic testing of a two-dimensional box truss beam A high flux source of energetic oxygen atoms for material environmental effects [ NASA-CR-40391 p 34 N87-I5262 degradation studies p 52 A87-27936 [ NASA-TM-888591 p 39 N87-16880 BRACKETS SSM atomic oxygen reactions on Kapton and silverized Analysis of high precision composite sandwich antennas Locking hinge Teflon p 55 N87-14388 --- spacecraft antennas p 56 N87-16929 [ NASA-CASE-MSC-21056-11 p 62 N87-18595 Preliminary results of SMM exposed aluminized Kapton Effects of curing stresses on composite structures p 56 N87-16930 BRAKES (FOR ARRESTING MOTION) and silvered Teflon p 55 N87-14389 CHEMILUMINESCENCE Development of a lest procedure and facility for the Seamless metal-clad fiber-reinforced organic matnx Spacecraft glows from sudace-catalyzedreactions investigation of a Canadarm joint brake anomaly composite structures and process for their manufacture p 59 A87-15191 p 43 A87-17368 [ NASA-CASE-LAR-13562-1 I p 57 N87-18613 CIRCUIT BOARDS Thermoviscoelasticcharacterization and analysis of fiber BROMINE Thermoplastic-basedcomposites with low CTE for space composite space structures Properties and potential applications of brominated structures and circuit board applications [AD-A1750241 p 58 N87-19457 P-100 carbon fibers p 51 A87-23702 p 49 A87-13097 COMPUTATION BUCKLING CLADDING Comparison of methods for the calculation of thermal Optimization of a truss member Seamless metal-clad fiber-reinforced organic matrix contact resistance of the first Brazilian satellite [ IAF PAPER ST-86-17 I p 15 A87-16145 composite structures and process for their manufacture [ INPE-3864-TDLf2171 p21 N87-12596 Buckling and nonlinear response Of imperfect [ NASA-CASE-LAR-13562-1] p 57 N87-18613 The identificationof a distributed parameter model for three-leggedtruss columns p 19 A87-30296 COHERENTRADAR a flexible structure Analysis of long thin-walled lubes --- large space Application of Spaceborne Distributed [NASA-CR-1781991 p 13 N87-14059 structures p 20 N87-10895 AperturefCoherent Array Processing (SDAICAP) COMPUTATIONAL GRIDS technology to active and passive microwave remote A four node Marguerre element for non-linear shell sensing p 47 N87-17277 analysis p 30 A8740545 C COLLISION AVOIDANCE COMPUTER AIDED DESlGN Multiarm collision avoidance using the potential-field Hope for simulating flexible spacecraft CABLES approach p 59 A87-13715 p 11 A87-17146 Finite-element thermal-structural analyses of a Collisional probability in space and the debris 1986 LECEC stability and transient modeling of a large cable-stiffenedorbiting antenna p 19 A87-25687 environment in future p66 A87-18247 spacecraft power system p66 A87-18114 CALCIUM OXIDES COLLISIONAL PLASMAS Engineering and software interfacing for thermal. Li corrosion resistant glasses for headers in ambient ELF generation in the lower ionosphere via collisional structural and anitude control related with spacecraft temperature Li batteries parametric decay p 25 A87-14941 p 21 N87-10928 [ DE86-0137541 p 33 N87-12802 COLLOCATION Recent Experiences in Multidisciplinary Analysis and CANTILEVER PLATES Adaptive control of a flexible structure Optimization. part 1 p 39 N87-17449 Estimation and control of distributed models for certain [NASA-CP-2327-PT-II p 71 N87-11717 elastic systems arising in large space structures COLUMNS (SUPPORTS) Recent Experiences in Multidisciplinary Analysis and [AD-A175019] p 38 N87-16872 Buckling and nonlinear response of imperfect Optimization. part 2 three-legged truss columns p 19 A8740296 [ NASA-CP-2327-PT-21 p 71 N87-11750 CAPACITORS COMMERCIAL SPACECRAFT IDEAS A multidisciplinary computer-aidedconceptual Sensors for a system to control the liquid flow into an Communications spacecraft p 5 A87-30891 design system for spacecraft p 13 N87-11761 evaporation cold plate of a two-phase heal transport COMMONALITY Microcomputerdesign and analysis of the cable catenary system for large spacecraft Cost reduction on large space systems through large space antenna system p 13 N87-11762 [NLR-TR-86001-Ul p 23 N87-19442 commonality Thermal analysis of radiometer containers for the 122m CARBON FIBER REINFORCED PLASTICS [AIM PAPER 87-05851 p4 A87-22721 hoop column antenna concept Design and manufacturing aspects of tubular carbon COMMUNICATION [ NASA-TM-890261 p 21 N87-11966 fibre compositeftilanium bonded joints Research and technology Computer-aided design and distributed System p 50 A87-16163 [ NASA-TM-888681 p 74 N87-17656 technology development for large space structures The K1-K2 interactionfor matrix splining in unidirectional COMMUNICATION NETWORKS p 14 N87-16042 laminates of carbon fiber reinforced epoxy Digital networks and their evolution - Space and Multidisciplinary analysis of actively controlled large p 52 N87-10932 terrestrial systems; Proceedings of the Thirty-third flexible spacecraft p37 N87-16045 Development of a continuous manufacturing method for International Congress on Electronics and Twenty-sixth Preliminary findings for integrated modeling and a CFRP collapsible lube mast InternationalMeeting on Space, Rome, Italy. Mar. 18-20, simulation of directed energy weapons [AERE-G-3898] p 54 N87-13572 1986 p 68 A87-24701 [DE86-011636] p 10 N87-17846 CARBON FIBERS COMMUNICATION SATELLITES COMPUTER GRAPHICS Fabricationof a carbon fibrefaluminiumalloy composite Antenna system alternatives for Data Relay Satellites Space station thnllers unfold at Draper Lab under microgravity p 48 A87-11384 with multiple steerable beams p 11 A87-21257 Properties and potential applications of brominated [IAF PAPER 86-3491 p 43 A87-I6041 Microcomputer design and analysis of the cable catenary P-100 carbon fibers p 51 A87-23702 Space Tech '86; Proceedings of the International large space antenna system p 13 N87-11762 Effects of thermal cycling on graphie-fiber-reinforced Conference. Geneva, Switzerland, May 14-16. 1986 COMPUTER INFORMATION SECURITY 6061 aluminum p 68 A8725751 Aerospace Cornpuler Security Conference. 2nd. [ NASA-TP-26121 p 52 N87-10184 Communications spacecraft p 5 A87-30891 McLean. VA. December 2-4, 1986. Technical Papers CASES (CONTAINERS) Communications technology p 46 A8740893 p 67 A87-18852 Thermal analysis of radiometer containers for the 122m Experience on the Olympus modal survey test COMPUTER NETWORKS hoop column antenna concept p6 N87-10919 Proceedings of the 5th Annual Users' Conference [NASA-TM-89026] p 21 N87-11966 Design and development of a telescopic axial boom [ NASA-CP-23991 p 70 N87-10720 CASSEGRAIN ANTENNAS p 14 N87-16322 COMPUTER PROGRAMS S band 3.5-m-diameter fan rib type deployable mesh COMPARISON Distributed control for COFS 1 p 36 N87-16043 antenna for satellite use Comparison of methods for the calculation of thermal Passively damped joints for advanced space [IAF PAPER 86-28] p 11 A87-I5819 contact resistance of the first Brazilian satellite structures Study on solid surface. deployable antenna reflector .-- [INPE-3864-TDLf217] p 21 N87-12596 [ AD-AI 749141 p 42 N87-19435 satellite antenna p 8 N87-16928 COMPLEX SYSTEMS A unified approach to computer analysis and modeling CATALYTIC ACTIVITY Architecture and design process for complex systems: of spacecraft environmental interactions Spacecraft glows from surface-catalyzed reactions Space Station - A case study p 12 A87-25978 p 14 N87-20066 p43 A87-17368 COMPOSITE MATERIALS COMPUTER SYSTEMS DESIGN CENTRIFUGES Holographic non-destructive testing for COmpOSile Aerospace Computer Security Conference, 2nd. Passive damping augmentation for flexible structures materials used in aerospace p 51 A87-19805 McLean, VA. December 2-4, 1986. Technical Papers p 36 N87-16044 International Week on Bonding and Joining p 67 A87-18852 CHARGECOUPLEDDEVICES Technologies, 1st, Bordeaux, France, April 15-18. 1986, COMPUTER SYSTEMS PROGRAMS Advanced opto-electronical sensors for autonomous Selected Papers p 67 A87-20144 Engineering and software interfacing for thermal. Rendezvous-/Dockingand proximity operations in space A method of studying the behavior of composite structural and anitude control related with spacecraft p 44 A87-19707 materials in simulated space environments p 21 N87-10928 CHEMICAL ANALYSIS p 53 N87-10940 Dynamics and Control Analysis Package (DCAP): An Analysis of micrometeorite material captured by the solar Damping 1986 procedures, Volume 2 automated analysis and design tool for structural control max satellite p 55 N87-14385 [AD-AI 739501 p 73 N87-16366 of space structures p 39 N87-16947 Examination of returned solar-max surfaces for COMPOSITE STRUCTURES Engineering and software interfacing for thermal. impacting orbital debris and meteoroids Fabrication of a Space Station composite telralrUSS structural and dynamic control related with spacecraft p 55 N87-14386 model p 49 A87-13159 activities p 22 N87-16948 Analysis of normal and transparent silver Teflon Stress and deformation analysis of thermally loaded light COMPUTERIZED SIMULATION p 55 N87-14391 weight composite struCtureS Modeling and simulation of large scale space systems Degradation studies of SMRM Teflon [IAF PAPER 86-2121 p 18 A87-15939 Strategic planning implications p 56 N87-14392 Use of graphitefepoxy composites in Spacecraft [ IAF PAPER 86-4531 p2 A87-16105 CHEMICAL AlTACK structures - A case study p 50 A87-19342 Hope for simulating flexible spacecraft Degradation studies of SMRM Teflon Tele-X antenna module structure qualification program p 11 A87-17146 p 56 N87-14392 p 21 N87-10924 A consideration of atomic oxygen interactions with the CHEMICAL COMPOSITION Composites design handbook for space structure Space Station p 43 A87-17836 Analysis of micrometeorite material captured by the solar applications. Executive summary 1986 LECEC stability and transient modeling of a large max satellite p 55 N87-14385 [ ESA-CR(P)-2196] p 54 N87-10982 spacecraft power system p 66 A87-18114 A-3 CONCENTRATORS SUBJECT INDEX

Space station thrillers unfold at Draper Lab Proceedings of an International Conference on Space CONTROL SYSTEMS DESIGN p 11 A87-21257 Dynamics for Geostationary Satellites A laboratory experiment in ControVstructureinteraction Use of support simulation modeling techniques in the [ ISBN-2.85428-149-71 p 70 N87-10113 --- for flexible spacecraft p 24 A87-13392 development of logistics support concepts for SDI orbital Proceedings of an International Conference on Slew maneuver control of the Spacecraft Control plalforms and constellations Spacecraft Structures Laboratory Experiment (SCOLE) p 24 A87-13393 [AIAA PAPER 87.06901 p 12 A8727617 [ESA-SP-2381 p 70 N87-10886 Decentralized Control experiments on NASA's flexible Identification. applications, and dynamic analysis of Recent Experiences in Multidisciplinary Analysis and grid p 24 A87-13394 nonlinear spacecraft components p 30 A87-28558 Optimization, part 1 Design of robust failure detection filters Rendezvous and dockina-. IRVD) .- auidance simulation [NASA-CP-2327-PT-lI p 71 N87-11717 p 24 A87-13395 program, rider 2 Proceedings of the SMRM Degradation Study Nonlinear attitude control of elastic spacecraft-antenna [MATRA-EPT/DT/VT068/012] p 72 N87-14359 Workshop system p 25 A87-13433 Combined orbitlattitude determination for low-altitude [ NASA-TM-892741 p 72 N87-14374 Flexibility control of solar arrays based on state satellites Proceedings of an International Symposium on Fluid estimation by Kalman filtering p 26 A87-15450 [UTIAS-320] p 74 N87-17810 Dynamics and Space A slewing control experiment for flexible structures Evaluation of on-line pulse control for vibration [ ESA-SP-2651 p 72 N87-14394 p 27 A87-17761 suppression in flexible spacecraft p 41 N87-17834 NASAIDOD Control/Structures Interaction Technology, Control of solar battery arrays of spacecraft with The SCOLE design challenge p 10 N87-17836 1986 consideration of the structural flexibility Preliminary findings for integrated modeling and [ NASA-CP-2447-PT-11 p 73 N87-16014 p 44 A87-18319 Simulation of directed energy weapons The 20th Aerospace Mechanics Symposium Altitude control experiment for flexible spacecraft [DE86-011636] p 10 N87-17846 [ NASA-CP-2423-REVl p 73 N87-16321 p 27 A87-18320 CONCENTRATORS Damping 1986 procedures, volume 2 Numerical and experimental evaluation of poles and Application of replicated glass mirrors lo large [AD-A173950] p 73 N87-16366 system zeros for large flexible space structures segmented optical systems --- for space structures Proceedings of the 3rd Annual SCOLE Workshop p 27 A87-18322 p 63 A87-11003 [NASA-TM-890751 p 75 N87-17821 Local output-feedback control for large flexible space The concentration principle applied to spaceborne solar CONGRESSIONAL REPORTS structures p 27 A87-18323 arrays. Application to the coorbiting platform mission: National Aeronautics and Space Administration Optimal SlNCtural design with control gain norm Studies synthesis Authorization Act, 1987 p6 N87-10775 constraint [ SNIAS-975-CA/CG I p 75 N87-19814 National Aeronautics and Space Administration [AIAA PAPER 87-00191 p 11 A87-22363 CONFERENCES Authorization Act. 1987 Vibration control of nonlinear flexible structures Space Congress. 23rd. Cocoa Beach. FL. April 22-25, [H-REPT-99-829] p 6 N87-11640 [AIAA PAPER 87-00741 p 28 A8722396 1986, Proceedings p 63 A87-10026 National Aeronautics and Space Administration A sequential linear optimization approach for controller Large optics technology; Proceedings of the Meeting, Authorization Bill. 1986 design p 28 A87-23989 San Diego, CA. August 19-21, 1985 [H-REPT-99-829] p6 N87-11641 Decentralized control of multi-body spacecraft - A [SPIE-571] p 63 A87-10997 Hearings before the Subcommittee on Space Science numencal experiment International SAMPE Symposium and Exhibiton. 31s. and Applications of the Committee on Science and [AIAA PAPER 87-0018) p29 A8724902 Los Angeles, CA. April 7-10, 1986, Proceedings Technology, 99th Congress, 2nd Session, No. 132, 25, An analytical and experimental study of a control p64 A87-13051 27 February; 11, 13. 20 March; 9. 10 April, 1986, Volume system's sensitivity to structural modifications --- for 1986 American Control Conference, 5th. Seattle, WA. 2 vibration of large space structures p 30 A87-30294 June 18-20, 1986, Proceedings. Volumes 1, 2. 8 3 [GPO-61-7771 p 7 N87-12402 On optimal passive and active control of precision p 64 A87-13301 National Commission on Space report spacecraft structures p 31 N87-10891 Space station automation; Proceedings of the Meeting. [ GPO-63.1 431 p7 N87-12574 On a simple vibration control design for large space Cambridge, MA, September 17. 18, 1985 Report of the National Commission on Space structure models with uncertain parameters [SPIE-580] p64 A87-13705 [S-HRG-99-954] p 73 N87-15028 p 32 N87-10903 Space Station beyond IOC Proceedings of the National Aeronautics and Space Administration Proceedings of the 2nd Annual SCOLE Workshop Thirty-second Annual International Conference, Los p7 N87-15908 [NASA-TM-89048] p 70 N87-10945 Angeles, CA, November 6. 7, 1985 --.Initial Operational CONSTRAINTS Qualitative results for distributed systems with discrete Capability p 65 A87-15376 Optimal structural design with control gain norm and StiffneSs with application to control IECEC '86;Proceedings of the Twenty-first lntersociety constraint [AD-A168622] p 33 N87-11829 Energy Conversion Engineering Conference, San Diego, [AIAA PAPER 87-00191 p 11 A87-22363 Spacecraft Dynamics and Control Program at AFRPL CA, August 25-29, 1986. Volumes 1. 2, & 3 CONTACT RESISTANCE p34 N87-16017 p66 A87-18026 Comparison of methods for the calculation of thermal The 15 meter hoop-columnantenna dynamics: Test and Space exploitation and utilization; Proceedings of the contact resistance of the first Brazilian satellite analysis p35 N87-16025 Symposium, Honolulu, HI, December 15-19, 1985 [INPE-3864-TDL/217] p 21 N87-12596 Application of physical parameter identification to finite p 66 A87-18451 CONTINUUM MODELING element models p35 N87-16026 Aerospace Computer Security Conference. 2nd. Assembly of thermoelastic continuous elements COFS 1: Beam dynamics and control technology McLean. VA, December 2-4.1986, Technlcal Papers [IAF PAPER 86-2071 p 59 A87-15935 overview p35 N87-16028 p 67 A87-18852 Equivalent continuum analyses of large space trusses COFS 1 research overview p8 N87-16029 Reinforced Plastics/Composites Institute. Annual p 12 N87-10894 MAST flight system dynamic performance Conference. 41st. Atlanta, GA. January 27-31. 1986, Application of dynamic elements and continuum p 35 N87-16032 Preprint p 67 A87-20076 methods lo large space structures, volume 1 Conceptualdesign of pointing control systems for space [ED/82-362/RD-VOL-l p 22 N87-13484 station gimballed payloads p 36 N87-16037 International Week on Bonding and Joining I Application of dynamic elements and continuum System identification for modeling for control of flexible Technologies, 1st. Bordeaux, France, April 15-18, 1986, methods lo large space structures. volume 2 structures p36 N87-16040 Selected Papers p 67 A87-20144 [ ED/82-362/RD-VOL-2] p 34 N87-13485 Computer-aided design and distributed system Space nuclear power systems 1985: Proceedings of the CONTOURS technology development for large space structures Second Symposlum, Albuquerque, NM, Jan. 14-16, 1985. Digital image processing: Binary images p 14 N87-16042 Volumes 3 8 4 p 67 A87-21801 p 57 N87-18015 Passive damping augmentation for flexible structures Perspective on non4.S. presentations at the 37th CONTROL p 36 N87-16044 Congress Of the International Astronautical Federation - 1986 American Control Conference. 5th. Seattle, WA, Surface control system for the 15 meter hoop-column October 4-11. 1986. Innsbruck. Austria June 18-20, 1986. Proceedinas. Volumes 1. 2. 8 3 antenna p37 N87-16047 p 67 A87-21975 p64 A87-13301 Robust multivariable controller design for flexible Digilal networks and their evolution - Space and CONTROL CONFIGURED VEHICLES spacecraft p37 N87-16048 terrestrial SySlemS; Proceedings of the Thirty-third Synthesis of control laws for optimally designed large Stochastic modeling and control system designs of the International Congress on Electronics and Twenty-sixth space structures NASAlMSFC Ground Facility for large space Structures: International Meeting on Space, Rome, Italy. Mar. 18-20, [IAF PAPER 86.2461 p 26 A87-15963 The maximum entropy/optimal projection approach 1986 p68 A8724701 CONTROL EQUIPMENT p38 N87-16766 Space Station: Gateway to space manufacturing; Static deflection control of flexible beams by Adaptive control techniques for large space structures Proceedings of the Conference. Orlando, FL, Nov. 7, 8, piezo-electric actuators [AD-A1730831 p 38 N87-16871 1985 p68 A87-25451 [NASA-CR-l79947] p 34 N87-13788 Adaptive control of a flexible structure Space Tech '86; Proceedings of the International CONTROL MOMENT GYROSCOPES p 39 N87-17449 Conference, Geneva, Switzerland. May 14-16, 1986 Large wheel actuators definition study --- spacecraft Ground facility for large space structures dynamics and p 68 A87-25751 control control verification Aerospace Applications Conference. Steamboat [TELDIX-I 5-020-8801 p 33 N87-11834 [ NASA-TM-865581 p41 N87-18600 Springs, CO. Feb. 1-8, 1986. Digest p 69 A87-25976 CONTROL SIMULATION CONTROL THEORY Space Logistics Symposium, Ist, Huntsville. AL. Mar. A laboratory experiment in control/structure interaction Synthesis of control laws for optimally designed large 24-26. 1987. Technical Papers p 69 A87-27603 --- for flexible spacecraft p 24 A87-13392 space structures Decentralized control experiments on NASA's flexible [IAF PAPER 86-2461 p 26 A87-15963 International Modal Analysis Conference. 4th. Los Modern control of large flexible spacecraft. ESA ASTP Angeles. CA. Feb. 3-6, 1986. proceedings. Volumes 1 grid p 24 A87-13394 8 Ground facility for Large Space Structures dynamics and study 2 p 69 A87-28526 control verification p 31 A87-31095 [ BL-6206-ISSUE-21 p 70 N87-10956 Space commerce '86;Proceedings of the International CONTROL STABILITY Qualitative results for distributed systems with discrete Conference and Exhibition on the Commercial and Pointing. control. and stabilization of solar dynamic and stiffness with application lo control Industrial Uses of Outer Space, Montreux, Switzerland, System on a Space Station p 25 A87-13437 [AD-AI686221 p 33 N87-11829 June 16-20, 1986 p 69 A87-29401 An analytical and experimental study of a control Unified control/structure design and modeling Aerospace Testing Seminar. 9th, Los Angeles, CA. Oct. SYStem's sensitivity to structural modifications --- for research 15-17. 1985. Proceedings p 69 A87-29441 vibration of large space slructures p 30 A87-30294 [NASA-CR-I 799481 p 33 N87-13478 A-4 SUBJECT INDEX DYNAMIC RESPONSE

The I5 meter hoop-columnantenna dynamics: Test and CURING DIGITAL SYSTEMS analysis p 35 N87-16025 Effects of cunng stresses on composite structures Digital image processing: Binary images COFS 1: Beam dynamics and control technology p 56 N87-16930 p 57 N87-18015 overview p 35 N87-16028 CURVATURE DIMENSIONAL STABILITY Description of the Mast Flight System Two-dimensionalarticulated systems developable on a Space radiation effects on the dimensional stability of p8 N87-16030 single or double curvature surface p 58 A87-12285 a toughened epoxy graphite composite CYLINDRICAL SHELLS Multidisciplinary analysis of actively controlled large p 49 A87-11847 Influence of fiber onentation and boundary conditions flexible spacecraft P37 N87-16045 Design of a low distortion shared aperture reflector --- on the dynamic behaviorof a cylindricallytelescoping solar satellite antenna p 14 N87-16934 Robust multivariable controller design for flexible array (INTELSAT 6) p 32 N87-10925 spacecraft p 37 N87-16048 Development of lightweight dimensionally stable carbon The control theory of flexible and articulated fiber composite antenna reflectors for the INSAT-1 satellite p 56 N87-16936 spacecraft D [ AD-A1748801 p 42 N67-19434 DIRECT BROADCAST SATELLITES p 46 A67-30893 CONTROLLERS DAMPING Communications technology 1986 American Control Conference. 5th. Seattle, WA. Metallurgicalcharacterization 01 the interfacesand the DIRECTIONAL ANTENNAS June 18-20, 1986. Proceedings. Volumes 1. 2, 8 3 damping mechanisms in metal matrix composites Communications technology p 46 A87-30893 p 64 A87-13301 [AD-A173470] p 57 N87-17863 DISTRIBUTED PARAMETER SYSTEMS Vibration suppression of planar truss structures utilizing The control theory of flexible and articulated Parameter identification in distributed spacecraft uniform damping control p 25 A87-13458 spacecraft structures [AD-A174880] p 42 N87-19434 PAPER 85-6701 p 18 A87-18487 Wave-absorbing controllers for a flexible beam [AAS DATA BASES p 28 A87-23986 Qualitative results for distributed systems with discrete Multidisciplinary analysis of actively controlled large MAST flight system dynamic performance and stiffness with application to control flexible spacecraft p 37 N87-16045 p 35 N87-16032 [ AD-A1686221 p 33 N87-11829 DATA REDUCTION COFS 2: 3-D dynamics and controls technology Unified controllstructure design and modeling Passively damped joints for advanced space p35 N87-16035 research structures System identificationfor modeling for control of flexible [NASA-CR-I799481 p 33 N87-13478 [AD-A174914) p 42 N87-19435 structures p36 N87-16040 The identification of a distributed parameter model lor DATA STORAGE Development and use of a linear momentum exchange a flexible structure Multidisciplinary analysis of actively controlled large device p36 N87-16041 [NASA-CR-1781991 p 13 N87-14059 flexible spacecraft p 37 N87-16045 Distributed control for COFS 1 p 36 N87-16043 DATA TRANSMISSION Proceedingsof the 3rd Annual SCOLE Workshop Passive damping augmentation for flexible structures Antenna system alternatives for Data Relay Satellites [NASA-TM-89075] p 75 N87-17821 p 36 N87-16044 with multiple steerable beams On incorporatingdamping and gravity effects in models Analysis and simulation of the MAST (COFS-1 flight [ IAF PAPER 86-3491 p 43 A87-16041 of structural dynamics of the SCOLE configuration hardware) p 37 N87-16046 Multidisciplinary analysis of actively controlled large p 40 N87-17827 Surface control system for the 15 meter hoopcolumn flexible spacecraft p37 N87-16045 Model reference control of distributed parameter antenna p37 N87-16047 DECONTAMINATION systems: Application to the SCOLE problem Robust multivariable controller design for llexible Acoustic cleaning of large space structures p 40 N87-17829 spacecraft p 37 N87-16048 p46 A87-26060 Investigation of interactive structural and controller DYNAMIC CONTROL DECOUPLING synthesis for large spacecraft Wave-absorbing controllers for a flexible beam Automatic decoupling of flexible spacecraft slewng [AD-A172811 ] p 17 N87-16055 p 28 A87-23986 maneuvers p 24 A87-13431 A modified loop transfer recovery approach for robust Modal control 01 traveling waves in flexible structures DEGRADATION control of flexible structures p 39 N87-17029 p 29 A87-24552 Energetic oxygen atom material degradation studies CORROSION PREVENTION Decentralized control of multi-body spacecraft - A [AIAA PAPER 87-01051 p 51 A87-24919 Protection of solar array blankets from aftack by low numerical experiment A high flux source of energetic oxygen atoms for material earth orbital atomic oxygen p 45 A87-19874 [AIAA PAPER 87-00181 p 29 A87-24902 degradation studies p 52 A87-27936 CORROSION RESISTANCE Software architecture for manufacturing and Space Degradationstudies of SMRM Teflon Li corrosion resistant glasses for headers in ambient robotics p 56 N87-14392 temperature Li batteries [AIAA PAPER 87-16871 p 12 A87-31121 DEGREES OF FREEDOM [ DE66-0137541 p 33 N87-12802 Design and control of modular. kinematically-redundant Decentralized control of multi-body spacecraft A COST ANALYSIS - manipulators numerical experiment On the initiation of SPS development [AIAA PAPER 87.16941 p 61 A87-31122 [AIAA PAPER 87-00181 p 29 A8724902 p 1 A87-12086 A space station Structures and Assembly Verification MMU (Manned Maneuvering Unit) task simulator Fabrication of a Space Station composite tetratruss Experiment, SAVE [AD-A169552] p 13 N87-14370 model p 49 A87-13159 [NASA-TM-89004] p5 N87-10170 DELAMINATING Solar power satellite built of lunar materials Estimation and control 01 distributed models for certain The effects of radiation on the interlaminar fracture p68 A8725426 elastic systems arising in large space structures toughness of a graphitelepoxy composite COST REDUCTION [ AD-A17501 91 p38 N87-16872 p 50 A87-19122 Technologies for affordable access to space DYNAMIC MODELS DEPLOYMENT [IAF PAPER 86-4421 p2 A87-16096 Stabilizationof aclass of hybridsystems arislng in flexible Modeling and simulation of Spacecraft solar array Cost reduction on large space systems through spacec r a ft p 24 A87-12139 deployment p 26 A87-17760 commonality Dynamics formulation and simulation of multi-body On the Orbiter based deployment of flexible members [AIAA PAPER 87-05851 p 4 A8722721 space structures [AAS PAPER 85-6731 p 16 A87-18489 Front end logistics influence on space system hardware [IAF PAPER 86-2381 p 26 A87-15957 design Optimal control of component deployment for the space Identification, applicatins. and dynamic analysis of radiotelescope system [AIAA PAPER 87-06581 p5 A87-27605 nonlinear spacecraft components p 30 A87-28558 [AAS PAPER 85.6631 p 16 A87-18495 COSTS Component testing for dynamic model verification Deployment analysis of the Olympus Astromast and Satellite servicing price estimation instruction booklet p 32 N87-11765 companson with test measurements p 61 A87-31220 [NASA-CR-171967] p 75 N87-18583 The control theory of flexible and articulated COUPLED MODES Extendable retractable telescopic mast for deployable spacecraft A study of nodal coupling methods --- structural structures p8 N87-16323 [ AD-A1748801 p 42 N87-19434 analysis p 31 N87-10896 DESIGN ANALYSIS DYNAMIC RESPONSE Demonstration of modal synthesis on an experimental Satellite construction p 61 A8727454 Buckling and nonlinear response of imperfect structure and its application to large spacecraft Rationalising Space Station p5 A8727455 three-legged truss columns p 19 A8730296 p 20 N87-10912 Optimization of equivalent periodic truss structures Prediction and correlation of structural response in Optimization procedure to control the coupling of p 16 A8741175 acoustic chambers --- large space structures p 20 N87-10907 vibration modes in flexible space structures Recent Experiences in Multidisciplinary Analysis and Initial results from multiaxes transient testing flexible [NASA-TM-89115] p 41 N87-18879 Optimization, part 1 --- CRACK INITIATION [NASA-CP-2327-PT-lI p 71 N87-11717 spacecraft p 21 N87-10917 The K1-K2 interactionfor matrix splitting in unidirectional Influence of fiber orientation and boundary conditions DESIGN TO COST on the dynamic behavior of a cylindricallytelescoping solar laminates of carbon fiber reinlorced epoxy Cost reduction on large space systems through p 52 N87-10932 array (INTELSAT 6) p 32 N87-I0925 commonality Qualitative results for distributed Systems with discrete CRANES [AIAA PAPER 87-05851 p4 A87-22721 Space spider crane and stiffnesswith application to control [NASA-CASE-LAR-13411-lSB] p 73 N87-15259 DICHROISM [AD-A168622] - p 33 N87-11829 Thermomechanical characteristics of dichroic CREEP PROPERTIES A model for predicting thermomechanical response of Thermoviscoelasticcharacterization and analysis of fiber subreflectors --- satellite antennas p 22 N87-16952 large space structures composite space structures DIELECTRICS [ AD-A1729661 p 22 N87-15264 [AD-A175024] p 58 N87-19457 Analysis of the ion spot phenomenon on beam-charged Dynamic analysis of the large deployable reflector CRYOGENIC ROCKET PROPELLANTS dielectrics p 51 A87-21993 [ NASA-TM-890561 p 37 N87-16050 Evaluationof on-orbit cryogenic propellant depot options DIGITAL SIMULATION Wave dispersion mechanisms in large space for the orbital transfer vehicle p 63 A87-31133 Modeling and simulation of spacecraft solar array structures CRYSTAL GROWTH deployment p 26 A87-17760 [AD-A1739671 p 38 N87-16059 Overview of planned tests of space materials MMU (Manned ManeuveringUnit) task simulator Adaptive control techniques for large space structures p 56 N87-15990 [AD-A169552] p 13 N87-14370 [AD-A1730831 p 36 N87-16871

A-5 DYNAMIC STRUCTURAL ANALYSIS SUBJECT INDEX

Thermoviscoelasticcharacterization and analysis of fiber Engineenng and software interfacing for thermal, ELECTRIC DISCHARGES composite space structures structural and dynamic control related with spacecraft A severe spacecraft-charging event on SCATHA in [ AD-A1750241 p 58 N87-19457 activities p 22 N87-16948 September 1982 DYNAMIC STRUCTURAL ANALYSIS Space station systems A continuing bibliography with [AIAA PAPER 87-04751 p 45 A87-22659 Vibration data reduction for design, analysis and testing indexes (supplement 3) ELECTRIC MOTORS of spacecraft p 23 A87-10901 [ NASA-SP-7056(03)] p 75 N87-I7820 Distributed control for COFS 1 p 36 N87-16043 A procedurefor calculating the damping in multi-element Proceedings of the 3rd Annual SCOLE Workshop Space station rotary joint mechanisms space structures [NASA-TM-89075] p 75 N87-17821 p 73 N87-16338 [IAF PAPER 86-2031 p 26 A87-15931 On incorporatingdamping and gravity effects in models ELECTRIC POWER Improving the active vibrational control of large space of structural dynamics of the SCOLE configuration Space Station challenge - On-orbit assembly of a 75-kW structures through structuralmodifications p 40 N87-17827 power system p 59 A87-18148 [IAF PAPER 86-2041 p 26 A87-I5932 Expenmental study of active vibration control ELECTRIC POWER SUPPLIES On-orbit systems identification of flexible spacecraft [AD-A173144] p 41 N87-17845 IECEC '86; Proceedings of the Twenty-first lntersociety p 26 A87-16187 Passive stabilization for large space systems Energy Conversion Engineering Conference, San Diego, The effects of radiation on the interlaminar fracture [NASA-CR-40671 p 42 N87-19755 CA, August 25-29. 1986. Volumes 1. 2. 8 3 toughness of a graphitelepoxy composite DYNAMEAL SYSTEMS p 66 A87-18026 p A87-19122 50 On the stability of multiple parameter time-varying ELECTRIC POWER TRANSMISSION Response of discretized structures with elasto-plastic dynamic systems p 29 A87-27449 A concept of the Energy Storable Orbital Power Station deformation to non-stationary random excitation (ESOPS) p 28 A87-22831 [IAF PAPER 86-1491 p 42 A87-15898 On the dynamics of flexible beams under large overall E ELECTRICAL MEASUREMENT motions - The plane case. I, II Prediction of the electrical performance of Inttatabte [ASME PAPER 86-WAlAPM-411 p 28 A87-23212 EARTH OBSERVATIONS (FROM SPACE) Space RigidizedStructure (ISRS) offset antenna reflectors International Modal Analysis Conference. 4th. Los Lidar remote sensing from space: NASA's plans in the and correlation with RF measurements Angeles, CA. Feb. 3-6. 1986, Proceedings. Volumes 1 8 Earth sciences p6 N87-10265 p 47 N87-16943 2 p 69 A87-28526 EARTH ORBITAL ENVIRONMENTS ELECTRICAL PROPERTIES Modal analysis technique used in Germany for Space radiation effects on the dimensional stability of Electrically conductive organic polymers for advanced aerospace structures p 30 A8728544 a toughened epoxy graphite composite applications --- Book p 50 A87-18554 Comparison of multiple input random and sine excitation p 49 A87-11847 Electron-radiation effects on the ac and dc electrical methods for aerospace structures --- spacecraft vibration Antenna system alternatives for Data Relay Satellites properties and unpaired electron densities of three models p 12 A87-28552 with multiple steerable beams aerospace polymers p 51 A87-21992 Transient modal tuning --.for space structures [IAF PAPER 86-3491 p 43 A87-16041 Properties and potential applications of brominated p 30 A87-28578 A consideration of atomic oxygen interactions with the P-100 carbon fibers p 51 A87-23702 A four node Marguerre element for non-linear shell Space Station p 43 A87-17836 LEO high voltage solar array arcing response model analysis p 30 A87-30545 Protection of solar array blankets from attack by low [NASA-CR-180073] p 47 N87-16971 Deployment analysis of the Olympus Astromast and earth orbital atomic oxygen p 45 A87-19874 ELECTRO-OPTICS comparison with test measurements p 61 A87-31220 Radiation from large space structures in low earth orbit Advanced opto-electronical sensors for autonomous A Taylor-Galerkinfinite element algorithm for transient with induced ac currents Rendezvous-/Docking and proximity operations in space nonlinear thermal-structuralanalysts [AIAA PAPER 87-06121 p 68 A8742738 p 44 A87-19707 [NASA-CR-177064] p 20 N87-10406 A high flux source of energetic oxygen atoms for material ELECTRODYNAMICS A study of nodal coupling methods --- structural degradation studies p 52 A87-27936 System engineenng study of electrodynamic tether as analysis p 31 N87-10896 Oxidation-resistantreflective surfaces for solar dynamic a spaceborne generator and radiator of electromagnetic Effective modal parameters and truncation effects in power generation in near Earth orbit waves in the ULFlELF frequency band structural dynamics p 31 N87-10897 [NASA-TM-88865] p 54 N87-10960 [NASA-CR-180156] p 23 N87-16956 Computational methods in elastic periodic structures EARTH ORBITAL RENDEZVOUS ELECTROMAGNETIC WAVE TRANSMISSION analyses p 32 N87-10901 Navigation, guidance, rendez-vous and docking - Integrated structure electromagnetic optimization of Prediction and correlation of structural response in Activities carried out for Columbus by the flight operations large space antenna reflectors acoustic chambers --- large space structures organization [NASA-TM-89110] p 48 N87-18598 p 20 N87-10907 [IAF PAPER 86-09] p 65 A87-15808 ELECTRON BEAMS Demonstration of modal synthesis on an experimental EARTH ROTATION Effect of electron-beam radiation on graphite epoxy structure and its application to large spacecraft MMU (Manned Maneuverina Unit) task simulator composites p 49 A87-13071 p 20 N87-10912 [ AD-AI 695521 p 13 N87-14370 ELECTRON DENSITY (CONCENTRATION) A review of time domain modal test methods and ECCENTRICITY The interaction of small and large spacecraft wtth their applications --- space structures p 32 N87-I0915 Efficiency eccentricity control using continuous, environment p 10 N87-20064 Tele-X antenna module structure qualification program vectored thrusting for satellites with large arealmass ELECTRON FLUX DENSITY p 21 N87-10924 ratios p 63 N87-10151 Boom potential of a rotating satellite in sunlight Loads analysis for the Galileo spacecraft ECONOMIC ANALYSIS p 68 A87-24198 p 21 N87-10926 Factors influencing selection of space transportation ELECTRON IRRADIATION Dynamics of flexible mechanisms --- spacecraft options Effect of electron-beam radiation on graphite epoxy p 32 N87-I0938 [IAF PAPER 86-1081 p 65 A87-15871 composites p 49 A87-13071 A study of large space structures EIGENVALUES The electron irradiation test of thermal control material ILR468691 p 21 N87-11832 A procedure for calculatingthe damping in multi-element p 50 A87-18271 Application of dynamic elements and continuum space structures Degradation of spacecraft thermal shield materials by methods to large space structures, volume 1 [IAF PAPER 86-2031 p 26 A87-15931 irradiation of energetic particles p 18 A87-18273 [ED/82-362lRD-VOL-l] p 22 N87-13484 Optimization of closed loop eigenvalues: Maneuvering, The effects of radiation on the interlaminar fracture Application of dynamic elements and continuum vibration control and structurelcontrol design iteration for toughness of a graphitelepoxy composite methods to large space structures, volume 2 flsxible spacecraft p 50 A87-19122 [EDl82-362/RD-VOL-2 I p 34 N87-13485 [AD-AI 727161 p 34 N87-15263 Electron-radiation effects on the ac and dc electrical Dynamic testing of a two-dimensional box truss beam ELASTIC BARS properties and unpaired electron densities of three [ NASA-CR-40391 p 34 N87-15262 Free rotation of an elastic rod with an end mass aerospace polymers p 51 A87-21992 Development of the Lens Antenna Deployment p 28 A87-23213 ELECTRON PLASMA Demonstration (LADD) shuttle-attached flight experiment ELASTIC BENDING Plasma electron collection through biased slits in a p7 N87-16022 Estimation and control of distributed models for certain dielectric p 46 A87-31223 Application of physical parameter identification to finite elastic systems arising in large space structures ELECTRON RADIATION element models p 35 N87-16026 [AD-A1750191 p 38 N87-16872 The importance of accurate secondary electron yields COFS 1: Beam dynamics and control technology ELASTIC DEFORMATION in modeling spacecraft charging p 46 A87-27018 overview p 35 N87-16028 Shear deformationplate continua of large double layered Space radiation effects on the thermo-mechanical COFS 1 research overview p8 N87-16029 space structures p 16 A8728882 behavior of graphite-epoxy composites COFS 3: Multibody dynamics and control technology ELASTIC SYSTEMS p 51 A8727178 p 36 N87-I6036 Nonlinear attitude control of elastic spacecraft-antenna ELECTRONIC PACKAGING Multidisciplinary analysis of actively controlled large system p 25 A87-13433 Thermal analysis of radiometer containers for the 122m flexible spacecraft p 37 N87-16045 ELASTODYNAMICS hoop column antenna concept Dynamic analysis of the large deployable reflector On the dynamics of flexible beams under large overall [ NASA-TM-890261 p 21 NB7-11966 ENERGETIC PARTICLES [NASA-TM-89056] P 37 N87-16050 motions -The plane case. I, I1 Energetic oxygen atom material degradation studies Wave dispersion mechanisms in large space [ASME PAPER 86-WAlAPM-41I p 28 A87-23212 [AIAA PAPER 87-01051 p 51 A87-24919 structures ELASTOPLASTICITY Response of discretized structures with elasto-plastic A high flux source of energetic oxygen atoms for material [AD-A1739671 p 38 N87-16059 deformation to non-stationaryrandom excitation degradation studies p 52 A87-27936 Discrete mechanism damping effects in the solar array p 28 A87-22831 ENERGY CONVERSION flight experiment p 38 N87-16341 ELECTRIC BATTERIES IECEC '86; Proceedings of the Twenty-first Intersociety Simple approach for evaluating mechanical reflector Flexibility control of solar battery arrays. Ill - vibration Energy Conversion Engineenng Conference, San Diego. antenna distortions --- satellite antennas and attitude control with consideration of the dynamics CA, August 25-29. 1986. Volumes 1, 2. 8 3 p 39 N87-16942 of a reaction wheel as an actuator p 45 A87-22969 p 66 A87-18026 Dynamics and Control Analysis Package (DCAP): An Li corrosion resistant glasses for headers in ambient ENERGY CONVERSION EFFICIENCY automated analysis and design tool for structural control temperature LI batteries Structural concepts for large solar concentrators of space structures p 39 N87-16947 [DE86-013754] p 33 N87-12802 [IAF PAPER 86.2021 p 15 A87-15930 A-6 SUBJECT INDEX FIBER ORIENTATION

Optimizationof a microwave-beamenergy transmission EUROPEANSPACE AGENCY F channel p 46 A87-29753 Composites design handbook for space structure ENERGY DISSIPATION applications. Executive summaly FABRICATION Wave dispersion mechanisms in large space [ ESA-CR(P)-PI961 p 54 "37-10982 Fabrication of a Space Station composite tetratruss structures EUROPEAN SPACE PROGRAMS model p 49 A87-13159 [ AD-A1739671 p 38 N87-I6059 Space materials in Europe p 49 A87-13067 Remotely manipulated and autonomous robotic welding ENERGY SOURCES Advanced propulsion status In Western Europe fabrication in space p 59 A87-13714 On the initiation of SPS development [IAF PAPER 86.1721 p 63 A87-15913 Fundamentals and advances in the development of p 1 A87-I2086 International Symposium on Space Technology and remote welding fabrication systems p 49 A67-14312 ENERGY STORAGE Science. 14th. Tokyo, Japan, May 27-June 1. 1964. Large inflatable parabolic reflectors in space A concept of the Energy Storable Orbital Power Station Proceedings p 66 A67-18201 p 3 A87-19789 (ESOPS) The international Space Statlon takes shape FAILURE ANALYSIS [IAF PAPER 86.1491 p 42 A87-15898 p4 A87-24123 Design of robust failure detection filters The potential impact of new power system technology Possible areas of collaboration between DFVLR and p 24 A87-13395 on the design of a manned Space Station ISRO in the fields of structures and materials Proceedings of the SMRM Degradation Study p 44 A87-18342 p 56 N87-15252 Workshop ENERGYTECHNOLOGY EVAPORATIVE COOLING [ NASA-TM-89274] p 72 N87-14374 IECEC '86; Proceedings of the Twenty-first lntersociety Sensors for a system to control the liquid flow into an Report on SMRM CIP maln electronics box component Energy Conversion Engineering Conference, San Diego, evaporation cold plate of a two-phase heat transport and matenals degradation evaluations CA, August 25-29. 1986. Volumes 1, 2. 8 3 system for large spacecraft p 72 N87-14375 p 66 A87-I8026 [NLR-TR-86001-U] p 23 N87-19442 Results of examination of materials from the solar The USSR and space power plants EXPANDABLESTRUCTURES maximum recovery mission p 54 N87-14363 p 45 A87-25533 Development of a 'Hingeless Mast' and its FAILURE MODES ENERGY TRANSFER applications The KI-K2 interactionfor matrix splitting in unidirectional Optimizationof a microwave-beamenergy transmission [IAF PAPER 86-2051 p 15 A87-15933 laminates of carbon fiber reinforced epoxy channel p 46 A87-29753 Feasibility study of a low-temperature expandable p 52 N87-I0932 Development and use of a linear momentum exchange megawatt pulse power radiator p 66 A87-17841 FAULTTOLERANCE device p36 N87-16041 Simplex Mast . An extendible mast for space Failure-accommodating control of large flexible ENVIRONMENTAL MONITORING applications p3 A87-18242 spacecraft p 24 A87-13317 Application of Spaceborne Distributed Development of the 15 meter diameter hoop column Design of robust failure detection filters AperturelCoherent Array Processing (SDAICAP) antenna p 24 A87-I3395 technology to active and passive microwave remote [NASA-CR-4038] p 17 N87-14366 FEASIBILITY ANALYSIS sensing p 47 N87-17277 Evaluation of Pactruss design characteristics critical to New materials for spacecraft stability and damping: A ENVIRONMENTAL TESTS space station primary structure feasibility study A method of studying the behavior of composite [NASA-CR-178171] p 17 N87-16870 [AD-AI698261 p 54 N87-12601 materials in simulated space environments EXPANSION FEDERAL BUDGETS p 53 N87-10940 New materials for spacecraft stability and damping: A National Aeronautics and Space Administration EPOXY MATRIX COMPOSITES feasibility study p6 N87-10774 The KI-K2 interaction for matrix splitting in unidirectional [AD-A169826] p 54 N87-12601 National Aeronautics and Space Administration laminates of carbon fiber reinforced eDow EXPENDABLE STAGES (SPACECRAm Authorization Act, 1987 p6 N87-10775 p 52 N87-10932 Factors influencing selection of space transportation National Aeronautics and Space Administration EPOXY RESINS options Authorization Act, 1987 Effects of thermal cycling on the mechanical and [IAF PAPER 86-1081 p 65 A87-15871 [H-REPT-99-829] p6 N87-11640 physical properties of a space qualified epoxy adhesive EXPERIMENTATION National Aeronautics and Space Administration p 19 A87-20062 COFS 1 Guest Investigator Program Authorization Bill. 1986 Advanced composites for large Navy spacecraft p8 N87-16034 [ H-REPT-99-829] p6 N87-11641 p 56 N87-16015 Hearings before the Subcommittee on Space Science Distributed control for COFS 1 p 36 N87-16043 Seamless metal-clad fiber-reinforced organic matrix and Applications of the Committee on Science and composite structures and process for their manufacture EXPERT SYSTEMS Technology, 99th Congress, 2nd Session. No. 132, 25, [ NASA-CASE-LAR-13562-11 p 57 N87-18613 The role of expert systems on Space Station 27 February; 11. 13. 20 March; 9. 10 April, 1986. Volume EQUATIONS OF MOTION p 4 A87-25758 2 Nonlinear interfaces for acceleration-commanded Space Station - The use of expert systems for [GPO-61-777] p7 N87-12402 control of spacecraft and manipulators planning p4 A67-25759 National Commission on Space report p 25 A87-13494 EXTERNAL SURFACE CURRENTS [ GPO-63-1431 p 7 N87-12574 Dynamics formulation and simulation of multi-body The interaction of small and large spacecraft with their National Aeronautics and Space Administration space structures environment p 10 N87-20064 p7 N87-15908 [ IAF PAPER 86-2381 p 26 A87-15957 EXTRATERRESTRIAL ENVIRONMENTS Budget availability p 10 N87-17799 On the stability of multlple parameter lime-varymg Cleaning up our space act p5 A67-31208 FEEDBACKCONTROL dynamic systems p 29 A87-27449 EXTRATERRESTRIAL RADIATION Stabilizationof a class of hybridsystems arisingin flexible MMU (Manned Maneuvering Unit) task simulator Degradation of spacecraft thermal shield materials by spacecraft p 24 A87-12139 [AD-A169552] p 13 N87-14370 irradiation of energetic particles p 18 A87-16273 Local output-feedback control for large flexible space EQUIPMENT SPECIFICATIONS EXTRATERRESTRIALRESOURCES structures p 27 A87-18323 Equipment designs for Space Station EVA examined Space Station beyond IOC; Proceedings of the ODtimal structural desian with control aain norm p 11 A87-15196 Thirty-second Annual International Conference. Los constraint EROSION Angeles. CA. November 6, 7, 1985 Initial Operational [AlAA PAPER 87-00191 p 11 A8722363 Erosion studies on Solar Max samples --- Capability p 65 A87-15376 Flexibilitv control of solar battew arravs. Ill - vibration p 50 A87-19343 and attitude control with consideration of the dynamics Lunar-based power systems Studies of erosion of solar max samples of Kapton and of a reaction wheel as an actuator p 45 A87-22969 [IAF PAPER 86-5071 p 43 A87-I6132 Teflon p 55 N87-14384 Efficient modal analysis of damped large space ERROR ANALYSIS Solar power satellite built of lunar materials structures p 28 A8723995 Truncation error estimation of a spacecraft model with p 66 A87-25426 Modal space design for active vibration control of large a flexible appendage p 16 A87-18321 EXTRAVEHICULAR ACTIVITY flexible structures p 30 A8728537 ERRORS Equipment designs for Space Station EVA examined Rapid precise end point control of a wrist carried by a Effect of sensor and actuator errors on static shape p 11 A87-15196 flexible manipulator p 61 N87-10398 control for large space structures p 29 A87-27948 Space construction results .The EASEIACCESS flight Optimizationof closed loop eigenvalues Maneuvenng. Active Control Evaluation for Spacecraft (ACES) expenment vibration control and structurelcontrol design iteration for p34 N87-16019 [ IAF PAPER 86-26] p2 A87-15817 flexible spacecraft Mathematical modeling of SCOLE configuration with Cleaning up our space act p5 A87-31208 [ ADA17271 61 p 34 N87-15263 line-of-sight error as the output p 40 N87-17824 A space station Structures and Assembly Verification Passive damping augmentation for flexible structures ERS-1 (ESA SATELLITE) Experiment, SAVE p 36 N87-16044 Development status of the ERS-1 SAR antenna [ NASA-TM-89004] p5 N87-10170 Robust multivariable controller design for flexible p9 N87-16939 Advanced EVA system deslgn requirements study spacecraft p 37 N87-16048 Features and technologies of ERS-1 (ESA) and X-SAR [ NASA-CR-1719421 p 71 N87-13167 A modified loop transfer recovery approach for robust antennas p 9 N87-17152 control of flexible structures p 39 N87-17029 Development of a pre-prototype power assisted glove ESASPACECRAFT Control of SCOLE p 40 N87-17832 end effector for extravehicular activity The dynamical qualification of present and future Decentralized optimal control of large flexible [NASA-CR-171940] p 72 N87-13989 spacecraft structures p 30 A67-29368 structures ETCHING Advanced EVA system design requirements study, [DE66-013906] p41 N8716101 Studies of erosion of Solar masamples of Kapton and executive summary FIBER OPTICS Teflon p 55 N87-14384 [ NASA-CR-I719601 p 75 N87-17638 Improving radiation/ contamination tests --- satellite EULER BUCKLING Advanced EVA system design requirements study: coating degradation Optimizationof equivalent periodic truss structures EVASlspace station system interface requirements [CERT-419300/1-DERTS] p 54 N87-10954 p 16 A87-31175 [NASA-CR-171981] p 62 N67-20351 FIBER ORIENTATION EULER-LAGRANGE EQUATION EXTREMELY LOW RADIO FREQUENCIES Influence of fiber orientation and boundary conditions Slew maneuver dynamics of the Spacecraft Control ELF generation in the lower ionosphere via collisional on the dynamic behavior of a cylindrically telescoping solar Laboratory expenment p 40 N87-17825 parametric decay p 25 A87-14941 array (INTELSAT 6) p 32 N87-10925

A-7 SUBJECT INDEX

FIBER REINFORCED COMPOSITES Experimental study of active vibration control Spacecraft Dynamics and Control Program at AFRPL Reinforced Plastics/Composites Institute. Annual [AD-A173144] p 41 N87-17845 p 34 N87-16017 Conference, 41st. Atlanta, GA, January 27-31, 1986. Decentralized optimal control of large flexible Active Control Evaluation for Spacecraft (ACES) Preprint p 67 A87-20076 structures p 34 N87-16019 Debonding analysis of thermally stressed [ DE86-0139061 p 41 N87-18101 Deployable truss structure advanced technology fiber-reinforced composite materials p 52 N87-10933 FLEXIBLE SPACECRAFT p 22 N87-16021 Seamless metal-clad fiber-reinforced organic matrix Parametric study of stable optical references for large COFS 1: Beam dynamics and control technology composite structures and process for their manufacture flexible structures in space p 64 A87-11013 overview p 35 N87-16028 [ NASA-CASE-LAR-13562-11 p 57 N87-18613 Stabilizationof a class of hybrid systems arisingin flexible COFS 2: 3-D dynamics and controls technology FINANCE spacecraft p 24 A87-12139 p35 N87-16035 National Aeronautics and Space Administration COFS Multibody dynamics and control technology Failure-accommodating control of large flexible 3: Authorization Act, 1987 p 36 N87-16036 spacecraft p 24 A87-13317 [ H-REPT-99-8291 p6 N87-11640 System identification for modeling for control of flexible National Aeronautics and Space Administration A laboratory experiment in control/structureinteraction structures p 36 N87-16040 Authorization Bill, 1986 --- for flexible spacecraft p 24 A87-13392 Development and use of a linear momentum exchange [ H-REPT-99-8291 p6 N87-11641 Slew maneuver control of the Spacecraft Control device p 36 N87-16041 FINANCIAL MANAGEMENT Laboratory Experiment [SCOLE) p 24 A87-13393 Distributed control for COFS 1 p 36 N87-16043 National Aeronautics and Space Administration Design of robust failure detection fillers Multidisciplinaly analysis of actively controlled large p6 N87-10774 p 24 A87-13395 flexible spacecraft p37 N87-16045 FINITE ELEMENT METHOD Automatic decoupling of flexible spacecraft slewing Analysis and simulation of the MAST (COFS-1 flight Response of discretized structures with elasto-plastic maneuvers p 24 A87-13431 hardware) p37 N87-16046 deformation to non-stationary random excitation Nonlinear attitude control of elastic spacecraft-antenna Robust multivariable controller design for flexible p 28 A87-22831 system p 25 A87-13433 spacecraft p 37 N87-16048 Finite-element thermal-StNClUral analyses of a Flexibility control of solar arrays based on slate The 20th Aerospace Mechanics Symposium cable-stiffenedorbiting antenna p 19 A87-25687 estimation by Kalman filtering p 26 A87-15450 [ NASA-CP-2423-REV] p 73 N87-16321 A four node Marguerre element for non-linear shell Development of a 'Hingeless Mast' and its Description of the Spacecraft Control Laboratory analysis p 30 A87-30545 applications Experiment (SCOLE) facility A Taylor-Galerkinfinite element algorithm for transient [IAF PAPER 86-2051 p 15 A87-15933 [ NASA-TM-890571 p8 N87-16848 nonlinear thermal-structuralanalysis Dynamics formulation and simulation of multi-body Dynamics and Control Analysis Package (DCAP): An [NASA-CR-177064] p 20 N87-10406 space structures automated analysis and design tool for structural control Unified control/structure design and modeling [IAF PAPER 86.2381 p 26 A87-15957 of space structures p 39 N87-16947 research Instability of rotating blades in space A modified loop transfer recovery approach for robust [NASA-CR-1799481 p 33 N87-13478 [IAF PAPER 86-2421 p 65 A87-15959 control of flexible structures p 39 N87-17029 Application of dynamic elements and continuum On-orbit systems identification of flexible spacecraft Proceedings of the 3rd Annual SCOLE Workshop methods lo large space structures. volume 1 p 26 A87-16187 [ NASA-TM-89075] p 75 N87-17821 [ ED/82-362/RD-VOL-l] p 22 N87-13484 Hope for simulating flexible spacecraft Issues in modeling and controlling the SCOLE Application of dynamic elements and continuum p 11 A87-17146 configuration p 39 N87-17822 methods to large space structures, volume 2 A slewing control experiment for flexible structures Optimal torque control for SCOLE slewing maneuvers [ ED/82-362/RD-VOL-2] p 34 N87-13485 p 27 A87-17761 p 40 N87-17823 Application of physical parameter identification to finite Simplex Mast - An extendible mast for space Mathematical modeling of SCOLE configuration with element models p35 N87-16026 applications p 3 A87-18242 line-of-sighterror as the output p 40 N87-17824 Analysis and simulation of the MAST (COFS-1 flight Control of solar battery arrays of spacecraft with Slew maneuver dynamics of the Spacecraft Control hardware) p37 N87-16046 consideration of the structural flexibility Laboratory experiment p 40 N87-17825 Identification of large space structures on orbit p 44 A87-18319 Modeling and identification of SCOLE [ AD-AI 737561 p 14 N87-16058 Attitude control experiment for flexible spacecraft p 23 N87-17826 The Extendable Refractable Mast (ERM) thermal p 27 A87-18320 On incorporatingdamping and gravity effects in models analysis: A heal radiation case study via the finite element Truncation error estimation of a spacecraft model with of structural dynamics of the SCOLE configuration method p 22 N87-16949 a flexible appendage p 16 A87-18321 p 40 N87-17827 Modeling and identification of SCOLE Local output-feedback control for large flexible space Finite element model of SCOLE laboratory p 23 N87-17826 structures p 27 A87-18323 configuration p 14 N87-17828 Finite element model of SCOLE laboratory Dynamics of the orbiter based flexible members Model reference control of distributed parameter configuration p 14 N87-17828 p 27 A87-18324 systems: Application to the SCOLE problem FLEXIBILITY On the Orbiter based deployment of flexible members p 40 N87-17829 Sun shield [AAS PAPER 85-6731 p 16 A87-18489 Evaluation of on-line pulse control for vibration [NASA-CASE-MSC-20162-1] p 74 N87-17036 Large-angleslewing of flexible spacecraft suppression in flexible spacecraft p 41 N87-17834 FLEXIBLE BODIES [AAS PAPER 85-6741 p 27 A87-18490 Active stability augmentation of large space structures: Decentralized control experiments on NASA's flexible Frequency-shapedlarge-angle maneuvers A stochastic control problem p 41 N87-17835 grid p 24 A87-13394 [AIAA PAPER 87-01741 p 28 A8722462 The SCOLE design challenge p 10 N87-17836 Vibration suppression of planar truss structures utilizing Flexibility control of solar battery arrays. I1 - Vibration Description of the Spacecraft Control Laboratory uniform damping control p 25 A87-13458 and attitude control based on stale estimation of differential Expenment (SCOLE) facility p 10 N87-17837 Numencal and experimental evaluation of poles and solar cell sensors p45 A87-22968 Optimization procedure to control the coupling of system zeros for large flexible space structures Free rotation of an elastic rod with an end mass vibration modes in flexible space structures p 27 A87-18322 p 28 A87-23213 [NASA-TM-89115] p 41 N87-18879 Vibratton control of nonlinear flexibk structures A sequential linear optimization approach for controller The control theory of flexible and articulated [AIM PAPER 87-00741 p 28 A87-22396 design p 28 A87-23989 spacecraft On the dynamics of flexible beams under large overall Nonlinear attitude control of flexible spacecraft under [AD-A174880] p 42 N87-19434 motions - The plane case. I. II disturbance torque p 29 A8724049 FLEXING [ASME PAPER 86-WA/APM-411 p 28 A8723212 Effect of Sensor and actuator errors on static shape Rapid precise end point control of a wrist carried by a A flexible telerobotic system for space operations control for large space structures p 29 A87-27948 flexible manipulator p 61 N87-10398 p 60 A8743229 Modal space design for active vibration control of large Proof-massactuator placement strategiesfor regulation Wave-absorbing controllers for a flexible beam flexible structures p 30 A87-28537 of flexure during the SCOLE slew p 40 N87-17830 p 28 A87-23986 Modal analysis technique used in Germany for FLIGHT CONTROL Modal control of traveling waves in flexible structures aerospace structures p 30 A8728544 Flight Dynamics Laboratory overview p 29 A87-24552 Parameter optimization and attitude stabilization of a p7 N87-16018 Static deflection control of flexible beams by flexible spacecraft p 31 N87-10138 FLIGHT HAZARDS piezo-electric actuators Identification and control of struclures in space Cleaning up our space act p5 A8741208 [ NASA-CR-1799471 p 34 N87-13788 [NASA-CR-179811] p 31 N87-10172 FLIGHT OPERATIONS The identification of a distributed parameter model for Initial results from mulliaxes transient testing --- flexible Navigation. guidance, rendez-vous and docking a flexible structure - spacecraft p 21 N87-10917 Activities carried out for Columbus by the flight operations [ NASA-CR-1781991 p 13 N87-14059 Dynamics of flexible mechanisms --- spacecraft organization Optimization of closed loop eigenvalues: Maneuvering, p 32 N87-I0938 IlAF PAPER 86-09] p 65 A87-15808 vibration control and structure/conlrol design iteration for Proceedings of the 2nd Annual SCOLE Workshop FLIGHT TESTS flexible spacecraft [NASA-TM-89048I p 70 N87-10945 [ AD-A1727161 p 34 N87-15263 SDace construction results - The EASElACCESS fliaht Modern control of large flexible spacecraft, ESA ASTP e-riment Mast flight system beam structure and beam structural study [IAF PAPER 86-26] p2 A87-15817 performance p 17 N87-16031 [BL-6206-lSSUE-2] p 70 N87-10956 Development of the Lens Antenna Deployment MAST flight system dynamic pedormance Large flexible space structures: Some simple models Demonstration (LADD) shunle.attached flight experiment p35 N87-16032 [TW-269] p N87-10957 32 p 7 N87-I6022 InVeSligatiOn Of interactive Structural and controller Dual structural-control optimization of large space synthesis for large spacecraft structures p 33 N87-11766 MAST flight system Operations p 8 N87-16033 [AD-A172811] p 17 N87-16055 Distributed active control of large flexible space Discrete mechanism damping effects in the solar array Parametric investigation of factors influencing the Structures flight experiment p 38 N87-16341 mechanical behavior of large space structures [NASA-CR-179941] p 33 N87-13476 FLYWHEELS [AD-A172880] p 38 N87-16056 NASAIWD ControVStructuresInteraction Technology, Large wheel actuators definition study ... Spacecraft Adaptive control of a flexible structure 1986 control p 39 N87-17449 [NASA-CP-2447-PT-l] p 73 N87-16014 [TELDIX-I5-020-880 J p 33 N87.11834 SUBJECT INDEX INDIAN SPACE PROGRAM

FOLDING STRUCTURES Li corrosion resistant glasses for headers in ambient HEAT SHIELDING Development of deployable truss concept for space temperature Li balleries Results of examination of materials from the solar station p 16 N87-10923 [DE86-013754] p 33 N87-12802 maximum recovery mission p 54 N87-14383 Foldable self-erectingjoint GLOVES HEATTRANSFER [ NASA-CASE-MSC-20635-1] p 17 N87-14373 DevelODment of a we-DrotolVoe Dower assisted alove The influence of interstitial media on spacecraft thermal Extendable retractable telescopic mast for deployable end effector for extravehicular a&& control p 18 A87-18266 structures p8 N87-16323 [NASA-CR-1719401 p 72 N87-13989 HELICOPTERS GOALS Study on solid surface, deployable antenna reflector --- Recent Experiences in Multidisciplinary Analysis and National Cornmission on Space report satellite antenna p 8 N87-16928 Optimization. part 2 Contraves' antenna tip hinge mechanism for Selenia [ GPO-63.1431 p 7 N87-12574 [ NASA-CP-2327-PT-2I p 71 N87-11750 GRAPHTHEORY Spazio's 20/30 GHz antenna --- satellite antenna HIGH TEMPERATURE GASES Application of graph theory to the nonlinear analysis D 74 N87-16944 The influence of interstitialmedia on spacecranthermal of large space structures p 12 N87-10418 Sun shield control p 18 A87-18266 GRAPHITE [ NASA-CASE-MSC-20162-1] p 74 N87-17036 HIGH VOLTAGES Advanced composites for large Navy spacecraft FOOD PROCESSING High voltage solar array plasma protection techniques p 56 N87-16015 Space Station evolution - The aerospace technology --- for use on spacecraft p 45 A87-19878 GRAPHITE-EPOXY COMPOSITES impact High voltage system: Plasma interaction summary Space radiation effects on the dimensional stability of [AAS PAPER 85-4561 p 1 A87-15380 p 48 N87-20069 a toughened epoxy graphite composite FORECASTING HINGES National Commission on Space report p 49 A87-11847 Contraves' antenna tip hinge mechanism for Selenia Effect of electron-beam radiation on graphite epoxy [GPO-63-143] p7 N87-12574 Spazio's 20130 GHz antenna --- satellite antenna composites p 49 A87-13071 FORMAT p 74 N87-16944 The effects of radiation on the interlaminar fracture Proceedings of the 5th Annual Users' Conference Locking hinge toughness of a graphite/epoxy composite [NASA-CP-2399] p70 N87 10720 [NASA-CASE-MSC-21056-1] p 62 N87-18595 p 50 A87-19122 FORMATIONS Space station erectable manipulator placement Use of graphitelepoxy composites in spacecraft Formationkeeping of spacecraft via differential drag system structures A case study p 50 A87-19342 [NASA-CR-l71939] p 71 N87-13466 - [ NASA-CASE-MSC-21096-1] p 62 N87-18596 Space radiation effects on the thermo-mechanical FOUNDATIONS HOLOGRAPHIC INTERFEROMETRY behavior of graphite-epoxy composites Space station erectable manipulator placement Holographic non-destructive testing for composite p 51 A87-27178 system materials used in aerospace p 51 A87-19805 [NASA-CASE-MSC-21096-1] p62 N87-18596 Development of lightweightdimensionally stable carbon HOOP COLUMN ANTENNAS fiber composite antenna reflectors for the INSAT-1 FRACTURE MECHANICS Thermal analysis of radiometer containers for the 122m Debonding analysis of thermally stressed satellite p 56 N87-16936 hoop column antenna concept Seamless metal-clad fiber-reinforced organic matrix fiber-reinforcedcomposite matenals p 52 N87-10933 [ NASA-TM-890261 p21 N87-11966 composite structures and process for their manufacture FRACTURESTRENGTH Development of the I5 meter diameter hoop column The effects of radiation on the interlaminar fracture [NASA-CASE-LAR-t3562-1] p 57 N87-18613 antenna Protective coatings for composite tubes in space toughness of a graphite/epoxy composite [ NASA-CR-40381 p 17 N87-14366 applications p 50 A87-19122 The 15 meter hoop-column antenna dynamics: Test and [NASA-CR-178116] p 57 N87-18669 FRAMES analysis p35 N87-16025 GRAVITATIONAL EFFECTS Alternative approximation concepts for space frame HUBBLE SPACE TELESCOPE synthesis p 19 A87-18940 Proceedings of the 3rd Annual SCOLE Workshop Hubble Space Telescope - Dawn of the era of [ NASA-TM-890751 p 75 N87-17821 An explicit expression for the tangent-stiffness of a serviceable spacecraft On incorporating damping and gravity effects in models finitely deformed 3-0 beam and its use in the analysis of [IAF PAPER 86-20] p2 A87-15814 of structural dynamics of the SCOLE configuration space frames p 19 A87-20247 Acoustic cleaning of large space structures p 40 N87-17827 FREE FLIGHT p46 A87-26060 GRAVITATIONAL FIELDS MMU (Manned Maneuvering Unit) task simulator Design and analysis of a keel latch for use on the Hubble Parametric investigation of factors influencing the [ AD-A1695521 p 13 N87-14370 Space Telescope p 62 N87-16326 mechanical behavior of large space structures FREOUENCYRESPONSE HUMAN FACTORS ENGINEERING [AD-A172860] p 38 N87-16056 Computation of total response mode shapes using tuned Maner of ease --- optimization of man- and GROUND SUPPORT SYSTEMS frequency response functions p 30 A87-28569 machine-controlled spaceborne structural assembly Space Logistics Symposium, lst, Huntsville. AL. Mar. FURLABLEANTENNAS operations p 59 A87-13949 24-26. 1987. Technical Papers p 69 A87-27603 Offset unfurlable antenna Phase 2A Executive Advanced EVA system design requirements study Second AIAA/NASA USAF Symposium on Automation, summary --- Intelsat. M-Sal [ NASA-CR-1719421 p 71 N87-13167 Robtics and Advanced Computing for the NationalSpace [ MBB-R-0200/3069-R] p 70 N87-11086 HYDRAULIC EOUIPMENT Program Experience gained by sector model testing of an The 20th Aerospace Mechanics Symposium [AIM PAPER 87-16551 p 70 A87-31112 unfurlable meshlrib antenna p 14 N87-16925 [ NASA-CP-2423-REVl p 73 N87-16321 Mechanical and control study of a 7 m offset unfurlable GROUND TESTS HYGRAL PROPERTIES Space construction results The EASE/ACCESS flight tracking antenna p 39 N87-16926 - Performance characteristicsof composite materials experiment p 53 N87-10935 [ IAF PAPER 86-26] p2 A87-15817 G Utilization, testing and maintenance of multimission hardware p 70 A87-29466 I GALACTIC CLUSTERS Ground facility for Large Space Structures dynamics and The tidal velocity field in the Local Supercluster control verification p 31 A87-31095 IDENTIFYING p 23 A87-11159 GYROSCOPES Identificationof large space structures on orbit GALERKIN METHOD Sensor technology for advanced space missions [ AD-A1737561 p 14 N87-16058 A Taylor-Galerkin finite element algorithm for transient p 73 N87-16027 IMAGE ANALYSIS nonlinear !hemal-struc!ural analysis Parametnc study of stable optical references for large [NASA-CR-1770641 p20 N87-10406 flexible structures in space p64 A87-11013 GALILEO SPACECRAFT H IMAGE PROCESSING Spacecraft structural model improvement by modal test Proceedings of the 5th Annual Users' Conference results p 20 A87-31225 HARDWARE [ NASA-CP-23991 p 70 N87-10720 Loads analysis for the Galileo spacecraft Front end logistics influence on space system hardware Digital image processing Binary images p 21 N87-10926 design p 57 N87-18015 [AIAA PAPER 87-06581 p5 A8727605 GAS TUNGSTEN ARC WELDING IMAGE RESOLUTION The welding of aluminum alloys: A new technology in Proceedinas of the SMRM Deqradation Study Large space observatories of the 21st century space application p 56 N87-17056 Workshop [AIAA PAPER 87-06361 p 4 A87-22751 [ NASA-TM-89274 p 72 N87-14374 GEOSYNCHRONOUSORBITS I IMPACT DAMAGE Improving the irradiation plus Contamination tests. Report on SMRM CIP main electronics box component Erosion studies on Solar Max samples Prestudy 2: Successive inadiationsand synergics. Volume and materials degradation evaluations p 50 A87-19343 D 72 N87-14375 1: Tests and conclusions --- satellite coatings The SuNivability of large space-borne reflectors under HEAT FLUX [CERT-4193-VOL-3] p 53 N87-10951 atomic oxygen and micrometeoroid impact Analysis of rendezvous and docking in geostationary Companson of methods for the calculation of thermal [AIM PAPER 87-0341I p 52 A87-31300 Earth orbit. Rider to comparison of future communications contact resistance of the first Brazilian satellite The SuNivability of large space-borne reflectors under [ INPE-3864-TDL/2171 p 21 N87-12596 space segment concepts atomic oxygen and micrometeoroid impact [DM51-CI PLIFL/OO99.821 p72 N87-14364 HEAT PIPES [ NASA-TM-889141 p 72 N87-14423 GIMBALS Sensors for a system to control the liquid flow into an IMPACT RESISTANCE Conceptual design of pointing control systems for space evaporation cold plate of a two-phase heat transport Meteoroid and orbital debris protection concepts station gimballed payloads p36 N87-16037 system for large spacecrall [IAF PAPER 86-4191 p65 A87-16081 GlOlTO MISSION [ NLR-TR-86001-U 1 p 23 N87-19442 IN-FLIGHT MONITORING Giono spacecraft high gain antenna mechanical design HEAT PUMPS On-orbit systems identificationof flexible spacecran and development p 18 N87-16938 Thermal contrOl systems for spacecraft p 26 A87-16187 GLASS instrumentation p 19 A8741213 INDIAN SPACE PROGRAM Application of replicated glass mirrors to large HEAT RADIATORS Possible areas of collaboration between DFVLR and segmented optical systems --- for space structures Feasibility study of a low-temperature expandable ISRO in the fields of structures and materials D 63 A87-11003 megawan pulse power radiator p 66 A87-17841 P 56 N87-15252

A-9 INDIAN SPACECRAFT SUBJECT INDEX

INDIAN SPACECRAFT Japanese laboratory proposal p 69 A87-25753 Space construction results - The EASEIACCESS flight Solar array mechanisms for Indian satellites. APPLE, Overview of planned tests of space materials experiment IRS and INSAT-IITS p 56 N87-15990 1 IAF PAPER 66-26] p2 A87-15817 [IAF PAPER 86-1421 p 11 A87-15893 JAPANESESPACECRAFT A new structure toward high precision large antenna Modeling and simulation of spacecraft solar array A new structure toward high precision large antenna [ IAF PAPER 86-201] p 15 A87-15929 deployment p 26 A87-17760 [ IAF PAPER 86-201] p 15 A87-15929 Structural concepts for large solar concentrators INFLATABLE SPACECRAFT JOINTS (JUNCTIONS) [ IAF PAPER 66.2021 p 15 A87-15930 Large inflatable parabolic reflectors in space Design and manufacturing aspects of tubular carbon A procedurefor calculating the damping in multi-element ~3 A87-I9789 fibre compositeltitanium bonded joints space structures INFLATABLE STRUCTURES p 50 A87-16163 IlAF PAPER 86-2031 p 26 A87-15931 Development of a 2.8 m offset antenna reflector using Improving the active vibrational control of large space International Week on Bonding and Joining inflatable. space-rigidizedstructures technology structures through structural modifications Technologies. Ist, Bordeaux. France, April 15-16, 1986. p8 N67-16927 [IAF PAPER 66-2041 p 26 A87-15932 Selected Papers p 67 A87-20144 INFRARED ASTRONOMY Concept of tension activated cable lattice antenna The Large Deployable Reflector (LDR) report of the Experimental characterization of passively damped [IAF PAPER 66.2061 p 15 A87-15934 Science Coordination Group joints for space structures p 29 A87-25680 Nonlinear effects in thermal conduction problems of [ NASA-CR-1802351 p 10 N87-19310 Foldable self-erecting joint large space structures INFRARED RADIATION [ NASA-CASE-MSC-20635-11 p 17 N67-14373 [IAF PAPER 86-2081 p 18 A87-15936 Model for radiation contamination by outgassing from COFS 1 research overview p 8 N67-16029 Synthesis of control laws for optimally designed large space platforms The 20th Aerospace Mechanics Symposium space structures [AlAA PAPER 87-01021 p 67 A8722416 [ NASA-CP-2423-REV] p 73 N67-16321 [IAF PAPER 86-2461 p 26 A87-I5963 INFRARED TELESCOPES Space station rotary joint mechanisms Modeling and simulation of large scale space systems System concept for a moderate cost Large Deployable p 73 N87-16336 Strategic planning implications Reflector (LDR) p3 A87-16506 The control theory of flexible and articulated [IAF PAPER 86.4531 p2 A87-I6105 A Sener mechanism: Fine adjustment mechanism for spacecraft Moon for terrestrial energetics the Far Infrared and Submillimeter Space Telescope [AD-A1748801 p 42 N67-19434 [IAF PAPER 86-4561 p2 A87-16108 (FIRST) (F f F) p 74 N87-16946 Reduced modelingand analysis of large repetitive space Passively damped joints for advanced space The large deployable reflector: A NASA structures via continuum/discrete concepts structures submillimeter-infraredorbiting Observatory [IAF PAPER ST-66-08] [AD-AI7491 41 p 42 N67-19435 p 65 A87-I6141 p 9 N87-17571 Optimization of a truss member The Large Deployable Reflector (LDR) report of the [IAF PAPER ST-66-17] p 15 A87-16145 Science Coordination Group On-orbit systems identification of flexible spacecraft [NASA-CR-160235] p 10 N87-19310 K p 26 A87-16187 INSPECTION Engineering considerations for on-orbit welding The welding of aluminum alloys: A new technology in KALMAN FILTERS operations p 59 A87-I7401 space application p 56 N87-17056 Flexibility control of solar arrays based on state A slewing control experiment for flexible structures INTEGRATORS estimation by Kalman filtering p 26 A87-I5450 p 27 A87-I7761 Nonlinear interfaces for acceleration-commanded KAPTON (TRADEMARK) Path-constrainedrendezvous - Necessary and sufficient control of spacecraft and manipulators Degradation of spacecraft thermal shield materials by conditions p 66 A87-17834 p 25 A87-13494 irradiation of energetic particles p 18 A87-18273 Space Station challenge - On-orbit assembly of a 75-kW INTELSAT SATELLITES Electron-radiation effects on the ac and dc electrical power system p 59 A87-18148 Modeling and Simulation of spacecralt solar array properties and unpaired electron densities of three A basic study for divided modal survey of future large deployment p 26 A87-17760 aerospace polymers p 51 A67-21992 spacecraft p 27 A87-18241 Influence of fiber orientation and boundary conditions Studies of erosion of solar max samples of Kapton and 2D-Array mission - Two-dimensionallydeployable solar on the dynamic behavior of a cylindrically telescopingsolar Teflon p 55 N67-14364 cell array mission p 15 A87-18243 array (INTELSAT 6) p 32 N87-10925 SSM atomic oxygen reactions on Kapton and silverized Numerical and experimental evaluation of poles and Offset unfurlable antenna. Phase 2A: Executive Teflon p 55 N87-14368 system zeros for large flexible space structures summary Intelsat, M-Sat --- Preliminary results of SMM exposed aluminized Kapton p 27 A67-16322 [ MBB-R-0200/3069-R] p 70 N87-11066 and silvered Teflon p 55 N87-I4389 Local output-feedback control for large flexible space INTERACTIVE CONTROL KEELS Structures p 27 A87-16323 Optimization procedure to control the coupling of Design and analysis of a keel latch for use on the Hubble Parameter identification in distributed spacecraft vibration modes in flexible space structures Space Telescope p 62 N87-16326 structures [NASA-TM-891151 p 41 N87-18879 KINETIC ENERGY [MS PAPER 85-6701 p 18 A87-16487 INTERCALATION Slew maneuver dynamics of the Spacecraft Control Optimal control of component deployment for the space Properties and potential applications of brominated Laboratory experiment p 40 N87-17825 radiotelescope system P-100 carbon fibers p 51 A87-23702 [ AAS PAPER 85-6831 p 16 A87-18495 INTERFACIAL TENSION Alternative approximation concepts for space frame Metallurgical characterizationof the interlaces and the L synthesis p 19 A87-18940 damping mechanisms in metal matrix composites An explicit expression for the tangent-stiffness of a [AD-A1734701 p 57 N87-17663 LABORATORIES finitely deformed 3-D beam and its use in the analysis of INTERNALPRESSURE Flight Dynamics Laboratory overview space frames p 19 A87-20247 An estimate of the outgassing of space payloads and p7 N87-16018 Optimal structural design with control gain norm its gaseous influence on the environment Description of the Spacecraft Control Laboratory constraint p 48 A87-11355 Experiment (SCOLE) facility [AIM PAPER 87-00191 p 11 A87-22363 INTERNATIONAL COOPERATION [ NASA-TM-890571 p8 N87-16848 Dynamic analysis of satellites with deployable hinged The international Space Station takes shape LAMINATES appendages p 4 A67-24123 Space radiation effects on the thermo-mechanical [AIAA PAPER 87-00201 p 27 A87-22364 Japanese laboratory proposal p 69 A87-25753 behavior of graphite-epoxycomposites Optimizationof a truss member Extending the Space Station inlrastructure p 51 A87-27178 [AIAA PAPER 67-00731 p 16 A87-22395 p5 A87-28953 Shear deformationplate continua of large double layered Cost reduction on large space systems through Possible areas of collaboration between DFVLR and space structures p 16 A87-28882 commonality ISRO in the fields of structures and materials The K1-K2 interactionfor matrix splitting in unidirectional [AIAA PAPER 87-05851 p4 A67-22721 p 56 N87-15252 laminates of carbon fiber reinforced epoxy Radiation from large space structures in low earth orbit INTERPLANETARY SPACECRAFT p 52 N87-10932 with induced ac currents Space vehicle design --- French book Performance characteristics of composite materials [AIAA PAPER 87-06121 p68 A87-22738 p 11 A87-10092 p 53 N87-10935 Large space observatories of the 21st century ION IRRADIATION LAND MOBILE SATELLITE SERVICE [AIAA PAPER 67-06361 p4 A87-22751 Analysis of the ion spot phenomenon on beam-charged L-band antennas for regional mobile communication Flexibility control of solar battery arrays. II - Vibration dielectncs p 51 A87-21993 satellites p 47 N87-15377 and attitude control based on state estimationof differential IONOSPHERIC HEATING LAP JOINTS solar cell sensors p45 A87-22968 ELF generation in the lower ionosphere via collisional Behavioural analysis of adhesive-bonded structural A sequential linear optimization approach for controller parametric decay P 25 A87-14941 joints in space vehicles p 16 A87-20146 IONOSPHERIC SOUNDING design p 28 A87-23989 LARGESPACESTRUCTURES Efficient modal analysis of damped large space Dual-spacecraft measurements Of Vibration data reduction for design, analysis and testing plasrnasphere-ionospherecoupling p 67 A87-20055 structures p 26 A87-23995 of spacecraft p 23 A87-10901 Decentralized control of multi-body spacecraft A ITALIAN SPACE PROGRAM Application of replicated glass mirrors to large - numerical experiment The international Space Station takes shape segmented optical systems --- for space structures [AIM PAPER 87-00181 p 29 A87-24902 P 4 A87-24123 p 63 A87-11003 Parametric study of stable optical references for large Experimental characterization of passively damped flexible structures in space p64 A87-11013 joints for space structures p 29 A87-25660 J Two-dimenstonal articulated systems developable on a Finite-element thermal-structural analyses of a single or double curvature surface p 58 A87-12285 cable-stiffened orbiting antenna p 19 A87-25687 JAPANESE SPACE PROGRAM Failure-accommodating control of large flexible Acoustic cleaning of large space structures International Symposium on Space Technology and spacec r a fl p24 A87-13317 p 46 A87-26060 Science. 14th. Tokyo, Japan. May 27-June 1, 1984, Flexibility control of solar arrays based on state Effect of sensor and actuator errors on static shape Proceedings P 66 A87-18201 estimation by Kalman filteriy p 26 A87-15450 control for large space structures p 29 A87-27948 A-10 SUBJECT INDEX LONGERONS

Modal space design for active vibration control of large Application of physical parameter identificationto finite Decentralized optimal control of large flexible flexible structures p 30 A87-28537 element models p 35 N87-16026 structures Transient modal tuning --- for space structures Sensor technology for advanced space missions [DE86-013906] p 41 N87-18101 p 30 A87-28578 p 73 N87-16027 Integrated structure electromagnetic optimization of Shear deformationplate continua of large double layered COFS 1: Beam dynamics and control technology large space antenna reflectors space structures p 16 A87-28882 overview p 35 N87-16028 [NASA-TM-891IO] p 48 N87-18598 COFS 1 research overview p8 N87-16029 Extending the Space Station infrastructure Ground facility for large space structures dynamics and Description of the Mast Flight System p5 A87-28953 control verification p8 N87-16030 [ NASA-TM-865581 p41 N87-I8600 An analytical and experimental study of a Control Mast flight system beam structure and beam structural Optimization procedure to control the coupling Of system's sensitivity lo structural modifications for --- performance p 17 N87-16031 vibration modes in flexible space structures vibration of large space structures p 30 A87-30294 MAST flight system dynamic performance [NASA-TM-89115] p 41 N87-18879 Ground facility for Large Space Structures dynamics and p 35 N87-16032 Thermoviscoelastic characterizationand analysis of fiber control verification p 31 A87-31095 MAST flight system operations p 8 N87-16033 composite space Structures Deployment analysis of the Olympus Astromast and COFS 1 Guest Investigator Program [AD-A1750241 p 58 N87-19457 comparison with test measurements p 61 A87-31220 p 8 N87-16034 Passive stabilization for large space systems The survivability of large space-borne reflectors under COFS 3: Multibody dynamics and control technology [NASA-CR-40671 p 42 N87-I9755 atomic oxygen and micrometeoroid impact p36 N87-16036 Large structures and tethers working group [AlAA PAPER 87-0341I p 52 A87-31300 Development and use of a linear momentum exchange p 75 N87-20057 A space station Structures and Assembly Verification device p 36 N87-16041 Plasma interactions with large spacecraft Experiment SAVE Computer-aided design and distributed system p 48 N87-20063 [ NASA-TM-890041 p5 N87-10170 technology development for large space structures LASER APPLICATIONS Application of graph theory to the nonlinear analysis p 14 N87-16042 Lidar remote sensing from space: NASA's plans in the of large space structures p 12 N87-10418 Analysis and Simulation of the MAST (COFS-I flight Earth sciences p6 N87-10265 Equivalent continuum analyses of large space trusses hardware) p 37 N87-16046 Solar array flight dynamic experiment p 12 N87-10894 Surface control system for the 15 meter hoop-column [ NASA-TP-25981 p 7 N87-12581 Analysis of long thin-walled tubes --- large space antenna p 37 N87-16047 LASER WEAPONS structures p 20 N87-10895 Robust multivariable controller design lor flexible Preliminary findings for integrated modeling and On a simple vibration control design for large space spacecraft p 37 N87-16048 simulation of directed energy weapons structure models with uncertain parameters Dynamic analysis of the large deployable reflector [DE86-011636] p 10 N87-17846 p 32 N87-10903 [NASA-TM-89056] p 37 N87-16050 LATCHES Prediction and correlation of structural response in Investigation of interactwe structural and controller Design and analysis of a keel latch for use on the Hubble acoustic chambers --- large space structures synthesis for large spacecraft Space Telescope p 62 N87-16326 p 20 N87-10907 [AD-A17281I] p 17 N87-16055 LATTICES (MATHEMATICS) Demonstration of modal synthesis on an experimental Parametric investigation of factors influencing the Two-dimensional articulated systems developable on a structure and its application to large spacecraft mechanical behavior of large space structures single or double curvature surface p 58 A87-12285 p 20 N87-10912 [AD-A1728801 p38 N87-16056 LEAST SQUARES METHOD Initial results from multiaxes transient testing --- flexible Identificationof large space structures on orbit Component testing for dynamic model verification spacecraft p 21 N87-10917 [AD-A1737561 p 14 N87-16058 p 32 N87-11765 Dynamics of flexible mechanisms --- spacecraft Wave dispersion mechanisms in large space LENS ANTENNAS p 32 N87-10938 structures Development of the Lens Antenna Deployment Proceedings of the 2nd Annual SCOLE Workshop [AD-A173967] p38 N87-16059 Demonstration (IADD) shunle-attached flight experiment [ NASA-TM-890481 p 70 N87-10945 Damping 1986 procedures, volume 2 p7 N87-16022 Large flexible space structures: Some simple models [AD-A173950] p 73 N87-16366 LIAPUNOV FUNCTIONS [ Tw-269 I p 32 N87-10957 Stochastic modeling and control system designs of the Stabilization of a class of hybrid systems arising in flexible Microcornpuler design and analysis of the cable catenary NASAlMSFC Ground Facility for large space struclures: spacecraft p 24 A87-12139 large space antenna system p 13 N87-11762 The maximum entropy/optimal projection approach LIBRATION Qualitative results for distributed systems with discrete p38 N87-16766 Dynamics of the orbiter based flexible members and stiffness with application lo control Description of the Spacecraft Control Laboratory p 27 A87-18324 (AD-A1686221 p 33 N87-11829 Experiment (SCOLE] facility Dynamic analysis of satellites with deployable hinged A study of large space structures [ NASA-TM-890571 p8 N87-16848 appendages [LR468691 p 21 N87-11832 Evaluation of Pactruss desgn characteristicscntical to [AIM PAPER 87-00201 p27 A87-22364 Solar array flight dynamic experiment space station primary structure LIFE (DURABILITY) [ NASA-TP-25981 p7 N87-12581 [ NASA-CR-178171I p 17 N87-I6870 Effect of hard particle impacts on the atomic oxygen Distributed active control of large flexible space Adaptive control techniques for large space structures survivability of reflector surfaces with transparent structures [AD-A1730831 p 38 N87-16871 protective overcoats [NASA-CR-179941] p 33 N87-13476 Estimation and control of distributed models for certain [AIAA PAPER 87-01041 p 45 A8722417 Unified control/structure design and modeling elastic systems arising in large space structures Effect of hard particle impacts on the atomic oxygen research [ AD-AI 750191 p 38 N87-16872 survivability of reflector surfaces with transparent [ NASA-CR-1799481 p 33 N87-I3478 Dynamics and Control Analysis Package (DCAP): An protective overcoats Application of dynamic elements and continuum automated analysis and design tool for structural control [ NASA-TM-888741 p 71 N87-11838 methods lo large space structures, volume 1 of space structures p 39 N87-16947 LIFE SUPPORT SYSTEMS [ ED182-362/RD-VOL-I] p 22 N87-13484 A modified loop transfer recovery approach for robust Equipment designs for Space Station EVA examined Application of dynamic elements and continuum control of flexible structures p 39 N87-17029 pll A87-15196 methods to large space structures, volume 2 Combined orbillattitude determination for low-altitude Space Station evolution - The aerospace technology [ ED/82-362/RD-VOL-2] p 34 N87-13485 satellites impact Development of the 15 meter diameter hoop column [ UTIAS-3201 p 74 N87-17810 [AAS PAPER 85-4561 p 1 A87-15380 antenna Proceedings of the 3rd Annual SCOLE Workshop Advanced EVA system design requirements study [ NASA-CR-40381 p 17 N87-14366 [ NASA-TM-890751 p 75 N87-17821 [NASA-CR-171942) p 71 N87-13167 The Survivability of large space-borne reflectors under LINEAR PROGRAMMING Issues in modeling and controlling the SCOLE A sequential linear optimization approach for controller atomic oxygen and micrometeoroid impact configuration p 39 N87-17822 [ NASA-TM-889141 p 72 N87-14423 design p 28 A8723989 Optimal torque control for SCOLE slewing maneuvers Possible areas of collaboration between DFVLR and LINEAR QUADRATIC GAUSSIAN CONTROL p 40 N87-17823 ISRO in the fields of structures and materials Issues in modeling and controlling the SCOLE p 56 N87-15252 Mathematical modeling of SCOLE configuration wth configuration p 39 N87-17822 Space spider crane line-of-sighterror as (he output p 40 N87-17824 LOADS (FORCES) [NASA-CASE-IAR-l3411-lSB] p 73 N87-15259 Slew maneuver dynamics of the Spacecraft Control Evaluation of Pactruss design characteristics critical to Mobile remote manipulator system for a tetrahedral Laboratoty experiment p 40 N87-17825 space station primary structure truss Modeling and identification of SCOLE [ NASA-CR-I78171 ] p 17 N87-16870 [NASA-CASE-MSC-20985-1I p 61 N87-15260 p 23 N87-17826 LOCAL GROUP (ASTRONOMY) A model for predicting thermomechanical response of On incorporating damping and gravity effects in models The tidal velocity field in the Local Supercluster large space structures of structural dynamics of the SCOLE configuration p23 A87-11159 [AD-At 729661 p22 N87-15264 p 40 N87-I7827 LOCKING Locking hinge NASAIDODControllStructures InteractionTechnology, Finite element model of SCOLE laboratory 1986 configuration p 14 N87-17828 [ NASA-CASE-MSC-21056-1] p 62 N87-18595 LOGISTICS MANAGEMENT [NASA-CP-2447-PT-I] p 73 N87-16014 Model reference control of distributed parameter Spacecraft Dynamics and Control Program at AFRPL Use of support simulation modeling techniques in the systems: Application to the SCOLE problem development of logistics support concepts for SDI orbital p 34 N87-16017 p 40 N87-17829 Flight Dynamics Laboratory overview platforms and constellations Active stability augmentation of large space StruCtUreS: p7 N87-16018 [AIAA PAPER 87-06901 p 12 A87-27617 A stochastic control problem p 41 N87-17835 Active Control Evaluation for Spacecraft (ACES) LONG DURATION SPACE FLIGHT p 34 N87-16019 The SCOLE design challenge p 10 N87-17836 Mars landing mission: A structural approach Deployable truss structure advanced technology Description of the Spacecraft Control Laboratory p 23 N87-17783 p 22 N87-16021 Experiment (SCOLE) facility p IO N87-17837 LONGERONS The 15 meter hoop-column antenna dynamics: Ted and Experimental study of active vibration control Deployment analysts of the Olympus Aslromast and analysis p 35 N87-16025 [AD-A1731441 p 41 N87-17845 comparison with test measurements p 61 A87-31220

A-1 1 LOW GRAVITY MANUFACTURING SUBJECT INDEX

LOW GRAVITY MANUFACTURING Mars landing mission: A Structural approach Effects of thermal cycling on the mechanical and Overview of planned tests of space materials p 23 N87-17783 physical properties of a space qualified epoxy adhesive p 56 N87-15990 Budget availability p 10 N87-17799 p 19 A87-20082 LOW TEMPERATURE MANNED SPACECRAFT Behavioural analysis of adhesive-bonded structural Feasibility study of a low-temperature expandable The potential impact of new power System technology joints in space vehicles p 16 A87-20148 megawan pulse power radiator p 66 A87-17841 on the design of a manned Space Station Space radiation effects on the thermo-mechanical LOW WEIGHT p 44 A87-18342 behavior of graphite-epoxy composites Development of lightweight dimensionally stable carbon p 51 A87-27178 Aeronautics and space report Of the President: 1985 fiber composite antenna reflectors for the INSAT-I activities p 74 N87-16662 Development of a continuous manufacturing method for satellite p 56 N87-16936 a CFRP collapsible lube mast MANUFACTURING LOWER IONOSPHERE [AERE-G-3898] p 54 N87-13572 ltek optical technology in manufacturing and ELF generation in the lower ionosphere via collisional Composite space antenna structures: Properties and metrology p 64 A87-11008 parametric decay p 25 A87-14941 environmental effects LUMPED PARAMETER SYSTEMS Development of a continuous manufacturingmethod for [ NASA-TM-888591 p 39 N87-16880 On the stability of multiple parameter time-varying a CFRP collapsible lube mast METAL BONDING dynamic systems p 29 A8727449 [AERE-G-38981 p 54 N87-13572 Adhesive bonding of aerospace materials - Surface LUNARBASES MARITIME SATELLITES characterization of metallic adherends Compact SPS for lunar development -.-solar power S band 3.5-m-diameter fan rib type deployable mesh p 51 A87-20149 satellites antenna for satellite use METAL COATINGS [IAF PAPER 86-1561 p 2 A87-15904 [IAF PAPER 86-26] p 11 A87-15819 Seamless metal-clad fiber-reinforced organic matrix Moon for terrestrial energetics MARS (MANNED REUSABLE SPACECRAFT) Comwsite structures and process for their manufacture [IAF PAPER 86-4561 p2 A87-16108 Manned Mars mission Earth-To-Orbit (ETO) delivery and [NASA-CASE-LAR-13562-1] p 57 N87-18613 Lunar-based power systems orbit assembly of the manned Mars vehicle METAL MATRIX COMPOSITES [IAF PAPER 86-5071 p 43 A87-16132 p 9 N87-17746 Fabrication of a carbon fibre/aluminiumalloy composite LUNAR SOIL MARS (PLANET) under microgravity p 48 A87-11384 Solar power satellite built of lunar materials Manned Mars mission Earth-To-Orbit (ETO) delivery and Development of Space Station strut design p 68 A87-25426 orbit assembly of the manned Mars vehicle p 15 A87-11842 p 9 N87-17746 Effects of thermal cycling on graphie-fiber-reinforced Budget availability p 10 N87-17799 6061 aluminum M MARS LANDING [NASA-TP-2612] p 52 N87-10184 Mars landing mission: A structural approach Advanced composites for large Navy spacecraft MAGNETIC STORMS p 23 N87-17783 p 56 N87-16015 Dual-spacecraft measurements Of MARS SURFACE Damping 1986 procedures, volume 2 plasmasphere-ionosphere coupling p 67 A87-20055 A 21sl century nuclear power strategy for Mars [AD-A1739501 p 73 N87-16366 MAINTAINABILITY [IAF PAPER 86-3221 p 42 A87-16019 Metallurgical characterization of the interfaces and the Maintainability technology p 59 A87-15407 MASS DISTRIBUTION damping mechanisms in metal matrix composites MAINTENANCE Proof-mass actuator placement strategies for regulation [AD-A173470] p 57 N87-17863 Advanced EVA system design requirements study: of flexure during the SCOLE slew p 40 N87-17830 Seamless metal-clad fiber-reinforced organic matrix EVASlspace station system interface requirements MATERIALS SCIENCE composite structures and process for their manufacture [NASA-CR-171981] p N87-20351 62 International SAMPE Symposium and Exhibition, 31 st. [NASA-CASE-LAR-13562-1] p 57 N87-18613 MAN MACHINE SYSTEMS Los Angeles. CA. Apnl 7-10, 1986. Proceedings METAL SURFACES Matter of ease optimization of man- and --- p 64 A87-13051 The influence of interstitial media on spacecraft thermal machine-controlled spaceborne structural assembly Electrically conductive organic polymers for advanced control p 18 A87-18266 operations p 59 A87-13949 applications --- Book p 50 A87-18554 METEORITIC DAMAGE Robotics concepts for the U.S. Space Station Materials - The challenge of space p 50 A87-18867 Analysis of micrometeorite material captured by the solar [AAS PAPER 85-6661 p 60 A87-18486 MATERIALS TESTS max satellite p 55 N87-14385 MANAGEMENT METHODS Degradation of spacecraft thermal shield matenals by Examination of returned solar-max surfaces for NASA: The vision and the reality irradiation of energetic particles p 18 A87-18273 impacting orbital debris and meteoroids [OP-51 p 7 N87-15898 Holographic non-destruclive testing for composite p 55 N87-14386 MANEUVERS materials used in aerospace p 51 A87-I9805 Advanced EVA system design requirements study METEOROID HAZARDS MATHEMATICAL LOGIC [NASA-CR-I 71 9421 p 71 N87-13167 Protection of spacecraft from meteoroids and orbital Identificationof large space structures on orbit MANIPULATORS debris [AD-AI 737561 p 14 N87-16058 Nonlinear interfaces for acceleration-commanded [DE86-009996] p 70 N87-10947 MATHEMATICAL MODELS control of spacecraft and manipulators METEOROID PROTECTION Modeling and simulation of large scale space systems p 25 A87-13494 Protection of spacecraft from meteoroids and orbital Strategic planning implications Multiarm collision avoidance using the potential-field debris [IAF PAPER 86-4531 p2 A87-16105 approach p 59 A87-13715 [ DEB6-0099961 p 70 N87-10947 Qualitative results for distributed systems with discrete Research and development of a small-sized space METEOROIDS and stiffness with application lo control manipulator Meteoroid and orbital debris protection concepts [ AD-A168622 I p 33 N87-I1829 [AAS PAPER 85-6601 p 60 A87-18481 [IAF PAPER 86-4191 p 65 A87-16081 LEO high voltage solar array arcing response model A robotic system for dexterous tasks [NASA-CR-I800731 p 47 N87-16971 Protection of spacecraft from meteoroids and orbital p 60 A8725757 Proceedings of the 3rd Annual SCOLE Workshop debris Design and control of modular, kinematically-redundant [NASA-TM-89075] p 75 N87-17821 [DE86-009996] p 70 N87-10947 manipulators Mathematical modeling of SCOLE configuration with Examination of returned solar-max surfaces for [AIAA PAPER 87.16941 p 61 A87-31122 line-of-sighterror as the output p 40 N87-17824 impacting orbital debris and meteoroids Rapid precise end point control of a wrist carried by a Modeling and identificationof SCOLE p 55 N87-14386 flexible manipulator p 61 N87-I0398 p 23 N87-17826 METEOROLOGICAL PARAMETERS Development of a pre-prototype power assisted glove Model reference control of distributed parameter Lidar remote sensing from space: NASA's plans in the end effector for extravehicular activity systems: Application lo the SCOLE problem Earth sciences p6 N87-10265 [NASA-CR-171940] p 72 N87-13989 p 40 N87-17829 METROLOGY Space spider crane MATRIX METHODS ltek optical technology in manufacturing and [NASA-CASE-LAR-13411-lSBl p 73 N87-15259 Mobile remote manipulator system for a tetrahedral A study of nodal coupling methods --.structural metrology p64 A87-11008 tNSS analysis p 31 N87-10896 MICROCOMPUTERS Computational methods in elastic periodic structures [ NASA-CASE-MSC-20985-1] p 61 N87-15260 Microcomputer design and analystsof the cable catenary The 20th Aerospace Mechanics Symposium analyses p 32 N87-10901 large space antenna system p 13 N87-11762 MAXIMUM ENTROPY METHOD [ NASA-CP-2423-REVl p 73 N87-16321 MICROCRACKS Space station erectable manipulator placement Stochastic modeling and control system designs of the Debondmg analysls of thermally stressed system NASAIMSFC Ground Facility for large space structures: fiber-reinforcedcomposite materials p 52 N87-10933 The maximum entropy/optimal projection approach [NASA-CASE-MSC-21096-1] p N87-18596 MICROMETEORITES 62 p 38 N87-16766 MANNED MANEUVERING UNITS Analysis of micrometeorite material capturedby the solar MECHANICAL DEVICES Utilization. testing and maintenance of multimission max satellite p 55 N87-14385 Docking mechanisms technology study hardware p 70 A8729466 MICROSTRIP TRANSMISSION LINES MMU (Manned Maneuvering Unit) task simulator [ESA-CR(P)-2273] p 71 N87-11833 MECHANICAL DRIVES Rectenna composed of a circular microstrip antenna [AD-A1695521 p 13 N87-14370 p 46 A87-25700 Space station rotary joint mechanisms MANNED MARS MISSIONS p 73 N87-16338 MICROSTRUCTURE Manned Mars mission Earth-To-Orbit(ETO) deltvery and MECHANICAL ENGINEERING Metallurgical characterization of the interfaces and the orbit assembly of the manned Mars vehicle Docking mechanisms technology study damping mechanisms in metal matrix composites p9 N87-17746 [ESA-CR(P)-2273] p 71 N87-I1833 [AD-A173470] p 57 N87-17863 MANNED SPACE FLIGHT MECHANICAL PROPERTIES MICROWAVE ANTENNAS Aeronautics and space report of the President: 1985 Effect of electron-beam radiation on graphite epoxy Protective coating for the KU-band reflector --- in Space activities p74 N87-16662 composites p 49 A87-13071 Shuttle radar antenna p 49 A87-13098 Manned Mars mission Earth-To-Orbit(ETO) delivery and Reinforced PlasticslComposites Institute. Annual The ESA/MBB unfurlable mesh antenna development orbit assembly of the manned Mars vehicle Conference. 41st. Atlanta, GA. January 27-31, 1986. for mobile services p 9 N87-17746 Preprint p 67 A87-20076 [IAF PAPER 86-271 p2 A87-15818 A-12 SUBJECT INDEX OPTIMAL CONTROL

S band 3.5-m-diameter fan rib type deployable mesh Computationof total response mode shapes using tuned Hearings before the Subcommittee on Space Science antenna for satellite use frequency response functions p 30 A87-28569 and Applications of the Committee on Science and [IAF PAPER 86-28] p 11 A87-15819 Transient modal tuning --.for space structures Technology, 99th Congress. 2nd Session, No. 132, 25. MICROWAVE RADIOMETERS p 30 A87-28578 27 February; 11. 13, 20 March; 9, 10 April, 1986. Volume Development of mm-wave radiometer antenna reflector Spacecraft structural model improvement by modal test 2 --- satellite antennas p 47 N87-16941 results p 20 A87-31225 [ GPO-61-7771 p 7 N87-12402 MICROWAVE SENSORS Effective modal parameters and truncation effects in NASA: The vision and the reality Features and technologies of ERS-1 (ESA) and X-SAR structural dynamics p 31 N87-10897 [OP-5] p7 N87-15898 antennas p 9 N87-17152 The effect of the non-uniform stress distribution in the Aeronautics and space report of the President: 1985 MICROWAVE TRANSMISSION blankets of single and twin boom solar array panels upon activities p74 N87-16662 their modal characteristics p N87-10904 Compact SPS for lunar development --- solar power 32 NONDESTRUCTIVE TESTS Experience on the Olympus modal survey test satellites Holographic non-destructive testing for composite p6 N87-10919 [IAF PAPER 86-1561 p2 A87-15904 materials used in aerospace p 51 A87-19805 Microwave power transmission for use in space MODELS NONLINEAR EQUATIONS p 46 A87-27180 1986 American Control Conference. 5th. Seattle. WA. Nonlinear interfaces for acceleration-commanded Optimizationof a microwave-beamenergy transmission June 18-20, 1986. Proceedings. Volumes 1. 2, 8 3 control of spacecraft and manipulators channel p 46 A87-29753 p 64 A87-13301 p 25 A87-13494 MILITARY SPACECRAFT The identification of a distributed parameter model lor Controlling waste heal in military Spacecraft a flexible structure NONLINEAR FEEDBACK p 18 A87-15197 [NASA-CR-1781991 p 13 N87-14059 Control of SCOLE p 40 N87-17832 A preliminary logistics support concept for space-based Preliminary findings for integrated modeling and NONLINEAR SYSTEMS SDI assets Simulation of directed energy weapons Nonlinear attitude control of elastic spacecraft-antenna [AIAA PAPER 87-06891 p 61 A87-27616 [DE86-011636] p 10 N87-17846 system p 25 A87-13433 Use of support simulation modeling techniques in the MODULARITY Vibration control of nonlinear flexible structures development of logistics support concepts for SDI orbital Transient external loads or interface forces [AIAA PAPER 87-00741 p28 A87-22396 platforms and constellations reconstructed from structural response measurements --- Identification. applications. and dynamic analysis of [AIAA PAPER 87-06901 p 12 A87-27617 modular spacecraft p 20 N87-10910 nonlinear spacecraft components p 30 A87-28558 Space logistics support to military space systems MOMENTUM Buckling and nonlinear response of imperfect [AIAA PAPER 87.06941 p 69 A87-27621 Development and use of a linear momentum exchange three-legged truss columns p 19 A8740296 MILITARY TECHNOLOGY device p36 N87-16041 Application of graph theory to the nonlinear analysis MULTIBEAM ANTENNAS Maintainabilitytechnology p 59 A87-15407 of large space structures p 12 N87-10418 The ESAIMBB unfurlable mesh antenna development MILLIMETER WAVES Adaptive control techniques for large space structures for mobile services Development of mm-wave radiometer antenna reflector [AD-A1730831 D 38 N87-16871 [IAF PAPER 86-27] p2 A87-15818 --- satellite antennas p 47 N87-16941 . The control theory of flexible 'and arlkulated S band 3.5-m-diameter fan rib deployable mesh MIRRORS type spacecraft antenna for satellite use Large optics technology; Proceedings of the Meeting. [ AD-AI 748801 p 42 N87-19434 [IAF PAPER 86-28] p 11 A87-15819 San Diego. CA, August 19-21, 1985 NONLINEARITY [SPIE-571] p 63 A87-10997 Nonlinear effects in thermal conduction problems of Application of replicated glass mirrors lo large N large space structures segmented optical systems --- for space structures [IAF PAPER 86-2081 p 18 A87-15936 p 63 A87-11003 NUCLEAR ELECTRIC POWER GENERATION System concept for a moderate cost Large Deployable NASA PROGRAMS National Aeronautics and Space Administration The potential impact of new power system technology Reflector (LDR) p3 A87-18508 on the design of a manned Space Station Effect of hard particle impacts on the atomic oxygen p6 N87-10774 National Aeronautics and Space Administration p 44 A87-18342 survivability of reflector surfaces with transparent Space nuclear power systems 1985; Proceedings of the protective overcoats Authorization Act, 1987 p6 N87-10775 Spacecraft load, design and test philosophies Second Symposium, Albuquerque, NM. Jan. 14-16,1985. [AIAA PAPER 87-01041 p 45 A87-22417 Volumes 3 & 4 p 67 A87-21801 The survivability of large space-borne reflectors under p 6 N87-10922 Development of deployable truss concept for space NUMERICAL ANALYSIS atomic oxygen and micrometeoroid impact 1966 American Control Conference. 5th. Seattle. WA, [AIM PAPER 87-03411 p52 A87-31300 station p 16 N87-10923 National Aeronautics and Space Administration June 16-20, 1986, Proceedings. Volumes 1.2, & 3 Effect of hard particle impacts on the atomic oxygen p64 A87-13301 survivability of reflector surfaces with transparent Authorization Act. 1987 protective overcoats [H-REPT-99-829] p6 N87-11640 [ NASA-TM-886741 p 71 N87-11838 National Aeronautics and Space Administration 0 The SUNNability of large space-bome reflectors under Authorization Bill, 1986 atomic oxygen and micrometeoroidimpact [H-REPT-99-8291 p6 N87-11641 ON-LINE SYSTEMS [NASA-TM-88914] p 72 N87-14423 Report of the National Commission on Space System identification for modeling for control of flexible Dynamic analysis of the large deployable reflector [S-HRG-99-954] p 73 N87-15028 structures p36 N87-16040 [NASA-TM-89056] p 37 N87-16050 National Aeronautics and Space Administration Adaptive control techniques for large space structures MISSION PLANNING p7 N87-15908 [AD-A1730831 038 N87-16871 The Space Station program The large deployable reflector: A NASA OPTICAL EQUIPMENT [AAS PAPER 85-451I p I A87-15377 submillimeter-infraredorbiting Observatory Large optics technology, Proceedings of the Meeting. Space Station design for growth p9 N87-17571 San Diego, CA, August 19-21, 1985 [IAF PAPER 86-4611 p2 A87-16110 Budget availability p 10 N87-17799 [SPIE-571] p63 A87-10997 Space Stahon ~ The use of expert systems for It& optical technology in manufactunng and NASA SPACE PROGRAMS planning p4 A8725759 metrology p 64 A87-11008 Technical aspects of the United States Space Station Extending the Space Station infrastructure OPTICAL MEASUREMENT p 1 A87-10043 p5 A87-28953 lmorovina radiation/ contamination tests --- satellite Second AIAAINASA USAF Symposium on Automation. Getting back on track in space p 1 A87-14375 coating degradation Robotics and Advanced Computing for the National Space The Space Station . United States proposal and [CERT-419300/1-DERTS] p 54 N87-10954 Program implementation p 1 A87-14969 OPTICAL RADAR [AIM PAPER 87-16551 p 70 A8741112 Space Station beyond IOC, Proceedings of the Lidar remote sensing from space: NASA's plans in the MMU (Manned Maneuvering Unit) task simulator Thirty-second Annual Inlernational Conference, LoS Earth sciences p 6 N87-?0265 [AD-A1695521 p 13 N87-14370 Angeles, CA, November 6, 7, 1985 --.Initial Operational OPTIMAL CONTROL Satellite servicing Price estimation instruction booklet Capability p 65 A87-15376 Synthesis of control laws for optimally designed large [NASA-CR-171967] p 75 N87-18583 The Space Station program space structures MOBILE COMMUNICATION SYSTEMS [AAS PAPER 85-4511 p 1 A87-15377 [IAF PAPER 86-2461 p26 A87-15963 The ESAIMBB unfurlable mesh antenna development Space Station . NASA's greatest challenge Optimal control of component deployment for the space for mobile services p2 A87-16399 radiotelescope system [IAF PAPER 66-27] p2 A87-15818 International Symposium on Space Technology and [AAS PAPER 85-6831 p 16 A87-18495 Communications spacecraft p5 A8740891 Science, 141h, Tokyo, Japan, May 27-June 1, 1984. Frequency-shapedlarge-angle maneuvers MODAL RESPONSE Proceedings p 66 A87-18201 [AIAA PAPER 87.01741 p 28 A8722462 Efficient modal analysis of damped large space An analytical and experimental study 01 a control An overview of NASA's programs and plans system's sensitivity to structural modifications for structures p 28 A8723995 [AAS PAPER 85-6471 p3 A87-18453 -_- Modal control of traveling waves in flexible structures vibration of large space Structures p 30 A8740294 p 29 A8724552 Robotics concepts for the US. Space Station On optimal passive and active control of precision International Modal Analysis Conference. 4th, Los [AAS PAPER 85-6661 p 60 A87-18486 spacecraft struclures p 31 N87-10891 Angeles, CA. Feb. 3-6, 1986, Proceedings. Volumes 1 8 NASA Growth Space Station missions and candidate Qualitative results lor distributed systems with discrete 2 p 69 A87-28526 nuclearlsolar power systems p3 A87-21807 and stiffness with application to control Modal space design for active vibration control of large Second AIAAfNASA USAF Symposium on Automation. [AD-A168622] P 33 N87-11829 flexible structures p 30 A8728537 Robotics and Advanced Computing for the NationalSpace Optimizationof closed loop eigenvalues: Manewering. Modal analysis technique used in Germany for Program vibration control and structure/conlroldesign iteration for aerospace structures p 30 A8728544 [AIAA PAPER 87-16551 p 70 A87-31112 flexible spacecraft Comparison of multiple input random and sine excitation NASA's technology plans - Will technology be ready [AD-A1727161 p 34 N87-15263 methods for aerospace structures --- spacecraft vibration when we are Optimal torque control for SCOLE slewing maneuvers models p 12 A87-28552 [AIAA PAPER 87-16951 p5 A87-31123 p 40 N87-17823

A-13 OPTIMIZATION SUBJECT INDEX

Decentralized optimal COntrOl Of large flexible ORBITAL SERVICING OXIDATION structures Hubble Space Telescope - Dawn of the era of A consideration of atomic oxygen interactions with the [DE86-013906] P 41 N87-18101 seNiceable spacecraft Space Station p 43 A87-17836 Passive stabilization for large space systems [ IAF PAPER 86-20] p2 A87-15814 OXIDATION RESISTANCE [NASA-CR-40671 P 42 N87-19755 Engineering considerations for on-orbit welding Protection of solar array blankets from attack by low OPTIMIZATION operations p 59 A87-17401 earth orbital atomic oxygen p 45 A87-19874 Optimization of a truss member Research and development of a small-sized space Oxidation-resistant reflective surfaces for solar dynamic [IAF PAPER ST-66-17] P 15 A87-I6145 manipulator power generation in near Earth orbit Optimization of a truss member [AAS PAPER 85-6601 p 60 A87-18481 [ NASA-TM-888651 p 54 N87-10960 [AIAA PAPER 87-00731 P 16 A87-22395 Space station thrillers unfold at Draper Lab OXYGEN ATOMS Efficient optimization of space trusses p 11 A87-2t 257 A consideration of atomic oxygen interactions with the P 19 A87-22814 Space Station The role of robotics in space p 60 A87-25756 p 43 A87-17836 A sequential linear optimization approach for controller Protection of solar array blankets from attack by low A robotic system for dexterous tasks design P 28 A87-23989 earth orbital atomic oxygen p 45 A87-19874 Optimal spacecraft rotational maneuvers --- Book p 60 A87-25757 Energetic oxygen atom matenal degradation studies p 68 A87-24625 Space Logistics Symposium, 1st. Huntsville. AL. Mar [AIAA PAPER 87-01051 p 51 A87-24919 Optimization of equivalent periodic truss structures 24 26, 1987, Technical Papers p 69 A8727603 A high flux source of energetic oxygen atoms for material p 16 A87-31175 Use of support simulation modeling techniques in the degradation studies p 52 A8727936 Parameter optimization and attitude stabilization of a development of logistics support concepts for SDI orbital Studbes of erosion of solar max samples of Kapton and flexible spacecraft p 31 N87-10138 plattorms and constellations Teflon p 55 N87-14384 Recent Experiences in Multidisciplinary Analysis and [AIAA PAPER 87-06901 p 12 A87-27617 SSM atomic oxygen reactions on Kapton and silverized optimization, part 1 Space logistics support to military space systems Teflon p 55 N87-14388 [NASA-CP-2327-PT-t I p 71 N87-11717 [AIAA PAPER 87-06941 p 69 A8727621 Preliminary results of SMM exposed aluminized Kapton Recent Experiences in Multidisciplinary Analysis and Evaluationof on-orbit cryogenic propellant depot options and silvered Teflon p 55 N87-14389 Optimization, part 2 for the orbital transfer vehicle p 63 A87-31133 Analysis of normal and transparent silver Teflon [ NASA-CP-2327-PT-2I p 71 N87-11750 Proceedings oi the SMRM Degradation Study p 55 N87-14391 Dual structural-control optimization of large space Workshop Degradation studies of SMRM Teflon structures p 33 N87-11766 [NASA-TM-892741 p 72 N87-14374 p 56 N87-14392 Integrated structure electromagnetic OptimiZatiOn of large space antenna reflectors Report on SMRM CIP main electronics box component [NASA-TM-891IO] p 48 N87-18598 and materials degradation evaluations P Optimization procedure to control the coupling of p 72 N87-14375 vibration modes in flexible space structures ORBITAL SPACE STATIONS PARABOLIC REFLECTORS [NASA-TM-891151 p 41 N87-18879 Space constructible radiator on-orbit assembly Application of replicated glass mirrors to large ORBIT PERTURBATION p 58 A87-11359 segmented optical systems --- for space structures Efficiency eccentricity control using continuous. Two-dimensional articulated systems developable on a p 63 A87-11003 vectored thrusting for Satellites with large area/mass single or double curvature surface p 58 A87-12285 Large inflatable parabolic reflectors in space ratios p63 N87-10151 A conceDt of the Enerav_. Storable Orbital Power Station p3 A87-19789 ORBIT TRANSFER VEHICLES (ESOPS) Surface control system for the 15 meter hoop-column Evaluationof on-orbit cryogenic propellant depot options [IAF PAPER 86-1491 p 42 A87-15898 antenna p 37 N87-I6047 for the orbital transfer vehicle p 63 A87-31133 Space Station design for growth Development of a 2.8 m offset antenna reflector using ORBITAL ASSEMBLY [ IAF PAPER 86-461 ] p2 A87-16110 inflatable. space-rigidized structures technology Space constructible radiator on-orbit assembly Telescience in orbit p 3 A87-16930 p8 N87-16927 p 58 A87-11359 The international Space Station takes shape Design of a low distortion shared aperture reflector --- Matter of ease -- optimizat~on of man- and $14 A87-24123 satellite antenna p 14 N87-16934 machine-controlled spaceborne structural assembly Space Logistics Symposium, 1st. Huntsville, AL. Mar. Construcciones Aeronauticas S A. (CASA) large operations p 59 A87-13949 24-26. 1987, Technical Papers p 69 A87-27603 reflector antenna --- satellite antenna p 9 N87-16935 Space construction results - The EASEIACCESS flight A space station Structures and Assembly Verification Structural analysis, manufacturing and development experiment Experiment, SAVE status of large polarization sensitive dual-griddedreflectors [ IAF PAPER 86-26] p2 A87-15817 [ NASA-TM-890041 p5 N87-10170 --- satellite antenna p 22 N87-16937 Engineering considerations for on-orbit welding Lidar remote sensing from space: NASA's plans in the Development of mm-wave radiometer antenna reflector operations p 59 A87-17401 Earth sciences p6 N87-10265 --- satellite antennas p 47 N87-I6941 Space Station challenge - On-orbit assembly of a 75-kW Proceedings of the 5th Annual Users' Conference Simple approach for evaluating mechanical reflector power system p 59 A87-18148 [ NASA-CP-23991 p 70 N87-10720 antenna distortions -.-satellite antennas Research and development of a small-sized space National Aeronautics and Space Administration p 39 N87-16942 manipulator p6 N87-10774 The large deployable reflector: A NASA [AAS PAPER 85.6601 p 60 A87-18481 National Aeronautics and Space Administration submillimeter-infrared orbiting observatory A space station Structures and Assembly Verification Authorization Act, 1987 p 6 N87-10775 p9 N87-I7571 Experiment, SAVE Development of deployable truss concept for space PARALLEL PROCESSING (COMPUTERS) Hope for simulating flexible spacecraft [ NASA-TM-89004] p5 N87-10170 stati 0 n p 16 N87-10923 Design. construction and utilization of a space station HPSA: High Power Solar Array study ---Columbusspace p 11 A87-I7146 assembled from 5-meter erectable struts station PARAMETER IDENTIFICATION [NASA-TM-89043 1 p6 N87-It827 [BAE-TP-8071] p 47 N87-11352 Parameter identification in distributed spacecraft Space spider crane Advanced EVA system design requirements study structures [NASA-CASE-LAR-13411-lS~l p 73 N87-t5259 [NASA-CR-171942] p 71 N87-13167 [AAS PAPER 85.6701 p 18 A87-18487 Mobile remote manipulator system for a tetrahedral High power rigid solar array --- Columbus space The identification of a distributed parameter model for truss station a flexible structure [ NASA-CASE-MSC-20985-1] p 61 N87-15260 [SNIAS-917A-CA/CG] p 47 N87-13864 [NASA-CR-l78199] p 13 N87-14059 Dynamic analysis of the large deployable reflector National Aeronautics and Space Administration Application of physical parameter identification to finite [ NASA-TM-890561 p 37 N87-16050 p 7 N87-15908 element models p 35 N87-16026 Manned Mars mission Earth-To-Orbit (ETO) delivery and Evaluation of Pactruss design characteristics critical to PARAMETERIZATION Orbit assembly of the manned Mars vehicle space station primary structure Parameter optimization and attitude stabilization of a p9 N87-17746 [NASA-CR-178171] p 17 N87-16870 flexible spacecraft p 31 N87-10138 Telerobotic assembly of space station truss structure Research and technology Effective modal parameters and truncation effects in [NASA-CR-180239] p 62 N87-18984 [NASA-TM-88868] p 74 N87-17656 structural dynamics p 31 N87-10897 Advanced EVA system design requirements study, ORBITAL MANEUVERS On a simple vibration control design for large space Rendezvous and docking verification and in-orbit executive summary structure models with uncertain parameters demonstration [ NASA-CR-1719601 p 75 N87-17838 p 32 N87-10903 [IAF PAPER 86-07] p 65 A87-15806 Rendezvous and docking and space robotics proximity PARTICLE BEAMS ORBITAL MECHANICS operations Part 5: Executive summary Effect oi hard particle impacts on the atomic oxygen Proceedings of an International Conference on Space [ NLR-TR-85099-U] p 62 N87-19441 SuNiVability of reflector surfaces with transparent Dynamics for Geostationary Satellites Passive stabilization for large space systems [ NASA-CR-4067] p 42 N87-19755 protective overcoats IISBN-2-85428-1 49-7 ] p 70 N87-10113 [AlAA PAPER 87-01041 p 45 A8722417 Efficiency eccentricity control using continuous, Advanced EVA system design requirements study: Effect of hard particle impacts on the atomic oxygen vectored thrusting for satellites with large area/mass EVASlspace station system interface requirements survivability of reflector surfaces with transparent ratios p 63 N87-10151 [NASA-CR-171981] p 62 N87-20351 ORGANIC SEMICONDUCTORS protective overcoats Combined orbit/attitude determination for low-altitude [NASA-TM-88874] p 71 N87-11838 satellites Electrically conductive organic polymers for advanced applications --- Book p 50 A87-18554 PATENT APPLICATIONS [UTIAS-320] P 74 N87-17810 OUTGASSING Li corrosion resistant glasses for headers in ambient ORBITAL RENDEZVOUS An estimate of the outgassing of space payloads and temperature Li batteries Rendezvous and docking (RVDI guidance Simulation its gaseous influence on the environment [DE86-0137541 p 33 N87-12802 program, rider 2 p 48 A87-11355 [MATRA-EPT/DT/VTO68/0121 p 72 N87-14359 PATTERN RECOGNITION Model for radiation contamination by outgassing from Satellite motion analysis via laser reflector pattern MMU (Manned Maneuvering Unit) task simulator space platforms processing tor rendez-vous and docking 1 AD-At695521 p 13 N87- 14370 [AIAA PAPER 87-01021 p 67 A87-22416 [IAF PAPER 86-06] p 65 A87-15805 A-14 SUBJECT INDEX PULSE COMMUNICATION

PAYLOAD RETRIEVAL (STS) PLASMA DIAGNOSTICS POWER SUPPLY CIRCUITS On the Orbiter based deployment of flexible members Controlling and monitoring the space-station plasma Multimegawanpower distribution considerations [AAS PAPER 85-6731 p 16 A87-18489 interaction:A baseline for perlorming plasma experiments p 43 A87-18113 PAYLOADS and using advanced technology p 76 N87-20079 POWER TRANSMISSION Conceptual design of pointing control systems for space PLASMA DYNAMICS Microwave power transmission lor use in space station gimballed payloads p 36 N87-16037 Technical issues in the conduct of large space platform p 46 A87-27180 Satellite servicing price estimation instruction booklet experiments in plasma physics and geoplasma sciences PREDICTION ANALYSIS TECHNIOUES [ NASA-CR-I719671 p 75 N87-18583 p 75 N87-20071 Prediction and correlation of structural response in PLASMA INTERACTIONS acoustic chambers --- large space structures PERFORMANCE PREDICTION Plasma electron collection through biased slits in a p 20 N87-10907 In-orbit performance of Hughes HS 376 solar arrays dielectric p 46 A87-31223 p 44 A87-19872 PREDICTIONS Plasma interactions with large spacecraft 1986 American Control Conference, 5th. Seanle, WA. Prediction of the electrical performance of Inflatable p 48 N87-20063 June 18.20, 1986, Proceedings. Volumes 1, 2. 8 3 Space RigidizedStructure (ISRS) offset antenna reflectors The interaction of small and large spacecraft with their p 64 A87-13301 and correlation with RF measurements environment p 10 N87-20064 A model for predicting thermomechanical response of p 47 N87-16943 A unified approach lo computer analysis and modeling large space structures PERFORMANCE TESTS of spacecraft environmental interactions [AD-At 729661 p 22 N87-15264 Decentralized control experiments on NASA's flexible p 14 N87-20066 PROCEDURES grid p 24 A87-13394 High voltage system: Plasma interaction summary COFS 1 Guest Investigator Program International Modal Analysis Conference. 4th, Los p 48 N87-20069 p8 N87-16034 Angeles. CA. Feb. 3-6. 1986. Proceedings. Volumes 1 8 Technical issues in the conduct of large space platform PRODUCTDEVELOPMENT 2 p 69 A87-28526 experiments in plasma physics and geoplasma sciences Construcciones Aeronauticas S.A. (CASA) large Experience gained by sector model testing of an p 75 N87-20071 reflector antenna --- satellite antenna p 9 N87-16935 unfurlable meshlrib antenna p 14 N87-16925 Controlling and monitoring the space-station plasma Giotto spacecraft high gain antenna mechanical design PERIODIC VARIATIONS interaction. A baseline for performing plasma experiments and development p 18 N87-I6938 Computational methods in elastic periodic structures and using advanced technology p 76 N87-20079 PROJECT MANAGEMENT analyses p 32 N87-10901 Spacecraft charging in the auroral plasma: Progress National Aeronautics and Space Administration PERSONNEL MANAGEMENT toward understanding the physical effects involved Authorization Act, 1987 NASA: The vision and the reality p 48 N87-20080 [ H-REPT-99.8291 p6 N87-I1640 [OP-51 p 7 N87-15898 PLASMA SHEATHS National Aeronautics and Space Administration PERTURBATION THEORY Plasma electron collection through biased slits in a Authorization Bill. 1986 A procedure for calculatingthe damping in multi-element dielectric p 46 A87-31223 [ H-REPT-99.8291 p6 N87-I1641 space structures PLASMA WAVES NASA: The vision and the reality [ IAF PAPER 86-2031 p 26 A87-15931 Radiation from large space structures in low earth orbit [ OP-51 p7 N87-15898 PHOTODECOMPOSITION with induced ac currents PROJECT PLANNING Design improvement and radiation.contamination tests. [AIAA PAPER 87-06121 p 68 A87-22738 Modeling and simulation of large scale space systems Prestudv 1: Ultraviolet radiation acceleration. volume 1 --- PLASMASPHERE Strategic planning implications satellite design Dual-spacecraft measurements Of (IAF PAPER 86-4531 p2 A87-16105 [CERT-4193-VOL-I] p 53 N87-10949 plasmasphere-ionospherecoupling p 67 A87-20055 PROPELLANTSTORAGE Desian improvement and radiation contamination tests PLASTIC DEFORMATION Evaluationof on-orbit cryogenicpropellant depot options Prestudy 1: 'Ultraviolet radiation acceleration. Volume 2: Response of discretized structures with elasto-plastic for the orbital transfer vehicle p 63 A87-31133 Appendix, detailed results --- satellite coating deformation lo non-stationary random excitation PROPULSION SYSTEM CONFIGURATIONS [ CERT-4193-VOL-21 p 53 N87-10950 p 28 A87-22831 Advanced propulsion status in Western Europe Improving the irradiation plus contamination tests. PLATETHEORY [IAF PAPER 86-1721 p 63 A87-15913 Prestudy 2: Successive irradiationsand synergics. Volume Shear deformation platecontinuaof large double layered PROTECTIVE COATINGS 1: Tests and conclusions --- satellite coatings space structures p 16 A87-28882 Protectivecoating for the KU-band reflector --- in Space [ CERT-4193-VOL-31 p 53 N87-I0951 PLY ORIENTATION Shunle radar antenna p 49 A87-13098 Improving radiation plus contamination tests. Prestudy Space radiation effects on the thermo-mechanical Protection of solar array blankets from attack by low 2: Successive irradiations and synergics. Volume 2: behavior of graphite-epoxy composites earth orbital atomic oxygen p 45 A87-19874 Annexes. Annex 1: Detailed results. Annex 2: Control and p 51 A87-27178 Effect of hard particle impacts on the atomic oxygen improvement of optical measurements --- satellite POINTING CONTROL SYSTEMS survivability of reflector surfaces with transparent coatings Pointing. control. and stabilization of solar dynamic protective overcoats ( CERT-4193-VOL-4I p 53 N87-10952 system on a Space Station p 25 A87-13437 [AIAA PAPER 87-0104] p 45 A87-22417 PHOTOELECTRONS Spacecraft Dynamics and Control Program at AFRPL The survivability of large space-borne reflectors under Boom potential of a rotating satellite in sunlight p 34 N87-16017 atomic oxygen and micrometeoroidimpact [AlAA PAPER 87-0341] p 52 A87-31300 p 68 A87-24198 COFS 2: 3-D dynamics and controls technology PHYSICAL PROPERTIES p 35 N87-16035 Design improvementand radiation,contamination tests. Prestudy 1: Ultraviolet radiation acceleration.volume 1 --- Effects of thermal cycling on the mechanical and Conceptualdesign of pointing control systems for space satellite design physical properties of a space qualified epoxy adhesive station gimballed payloads p 36 N87-I6037 p 19 A87-20082 [CERT-4193-VOL-t1 p 53 N87-10949 POLITICS PHYSIOLOGY Design improvement and radiation conlamination tests. NASA The vision and the reality Advanced EVA system design requirements study Prestudy 1: Ultraviolet radiation acceleration. Volume 2: [OP-51 p 7 N87-15898 [ NASA-CR-I71 942 I p 71 N87-I3167 Appendix. detailed results --- satellite coating PIEZOELECTRIC CERAMICS POLYMER PHYSICS [CERT-4193-VOL-21 p 53 N87-10950 Static deflection control of flexible beams by Electrically conductive organic polymers for advanced Improving the irradiation plus contaminabon tests. piezo-electric actuators applications --- Bmk p 50 A87-I8554 Prestudy 2: Successive irradiationsand synergics. Volume [ NASA-CR-1799471 p 34 N87-13788 POLYMERIC FILMS 1: Tests and conclusions --- satellite coatings PIEZOELECTRICITY Tribological properties of polymer films and solid bodies [ CERT-4193-VOL-31 p 53 N87-10951 Optimum vibration control of flexible beams by in a vacuum environment Improving radiation plus contamination tests. Prestudy piezo-electric actuators [ NASA-TM-889661 p57 N87-17906 2: Successive irradiations and synergics. Volume 2: [ NASA-CR-I802091 p 42 N87-18880 POLYMERS Annexes. Annex 1: Detailed results. Annex 2: Control and PIPES (TUBES) Electron-radiation effects on the ac and dc electrical improvement of optical measurements --- satellite Design and manufacturing aspects of tubular carbon properties and unpaired electron densities of three coatings fibre composite/titanium bonded ioints aerospace polymers p 51 A87-21992 [CERT-4193-VOL-4] p 53 N87-10952 p 50 A87-16163 POSITION (LOCATION) Improving radiationlcontamination tests --- Satellite Seamless metal-clad fiber-reinforced organic matrix MMU (Manned Maneuvering Unit) task simulator coating degradation composite structures and process for their manufacture [AD-A1695521 p 13 N87-14370 [CERT-419300/1-DERTS] p 54 N87-10954 Oxidation-resistantreflective surfaces for solar dynamic [ NASA-CASE-LAR-13562-11 p 57 N87-18613 POSTFLIGHT ANALYSIS power generation in near Earth orbit Protective coatings for composite tubes in space Proceedings of the SMRM Degradation Study [ NASA-TM-88865 p 54 N87-10960 applications Workshop I [NASA-CR-l78lt61 p 57 N87-18669 [ NASA-TM-892741 p 72 N87-I4374 Effect of hard particle impacts on the atomic oxygen survivability of reflector surfaces with transparent PITCH (INCLINATION) Report on SMRM C/P main electronics box component Parametric study of stable optical references for large protective overcoats and materials degradation eValUatiOnS [NASA-TM-88874] p 71 N87-11838 flexible structures in space p64 A87-11013 p 72 N87-14375 Instability of rotating blades in space The survivability of large space-borne reflectors under Results of examination of malerials from the solar [ IAF PAPER 86-2421 p 65 A87-I5959 atomic oxygen and micrometeoroidimpact maximum recovery mission p 54 N87-14383 PLANE STRAIN [ NASA-TM-889141 p 72 N87-14423 On the dynamics 01 flexible beams under large overall POTENTIAL FIELDS Protective coatings for composite tubes in space motions - The plane case. I. II Multiarm collision avoidance using the potential-field applications [ASME PAPER 86-WA/APM-41] p 28 A87-23212 approach p 59 A87-13715 [NASA-CR-178116] p 57 N87-18669 PLASMA ARC WELDING POWER CONDITIONING PULSE COMMUNICATION The welding of aluminum alloys: A new technology in 1986 American Control Conference. 5th. Seanle. WA. Digital networks and their evolution - Space and space application p 56 N87-I7056 June 18-20. 1986. Proceedings. Volumes 1, 2, 8 3 terrestrial systems; Proceedings of the Thirty-third PLASMA CONDUCTIVITY p 64 A87-13301 International Congress on Electronics and Twenty-sixth The interaction of small and large spacecraft with their Multimegawatt power distribution considerations International Meeting on Space, Rome, Italy. Mar. 18-20, environment p 10 N87-20064 p 43 A87-18113 1986 p 68 A87-24701

A-15 PULTRUSION SUBJECT INDEX

Aerospace Applications Conference, Steamboat REENTRY VEHICLES REPEATERS Springs. CO. Feb. 1-8. 1986, Digest p 69 A8725976 Proceedings of an International Symposium on Fluid Communicationstechnology p 46 A87-30893 PULTRUSION Dynamics and Space REQUIREMENTS Pultrusion process development for long space boom [ESA-SP-2651 p 72 N87-14394 Advanced EVA system design requirements study models , p60 A87-20083 REFLECTANCE [NASA-CR-171942] p 71 N87-13167 Improving radiationlcontamination tests --- satellite Advanced EVA system design requirements study, coating degradation executive summary Q [ CERT-41930011-DERTSl p 54 N87-10954 [NASA-CR-1719601 p 75 N87-17838 REFLECTOR ANTENNAS RESEARCH ANDDEVELOPMENT QUALIFICATIONS Advanced propulsion status in Western Europe The dynamical qualification of present and future Protectivecoating for the KU-band reflector --- in Space [IAF PAPER 86.1721 p 63 A87-15913 spacecraft structures p 30 A87-29368 Shuttle radar antenna p 49 A87-13098 The ESAIMBB unfurlable mesh antenna development A 21st century nuclear power strategy for Mars QUALITY CONTROL [IAF PAPER 86-3221 p 42 A87-16019 Developmentof a continuous manufacturing method for for mobile services [ IAF PAPER 86-271 p2 A87-15818 National Aeronautics and Space Administration a CFRP collapsible tube mast Authorization Act, 1987 [AERE-G-38981 p 54 N87-13572 A new structure toward high precision large antenna [ H-REPT-99-829] p6 N87-11640 [IAF PAPER 86-201 I p 15 A87-15929 National Aeronautics and Space Administration R Antenna system alternatives for Data Relay Satellites Authorization Bill, 1986 with multiple steerable beams [H-REPT-99-829] p6 N87-11641 [IAF PAPER 86-3491 p 43 A87-16041 RADAR ANTENNAS Aeronautics and space report of the President: 1985 REFLECTORS Development status of the ERS-1 SAR antenna activities p 74 N87-I6662 Satellite motion analysis via laser reflector pattern p9 N87-16939 Research and technology processing for rendez-vous and docking RADIATION DAMAGE [ NASA-TM-888681 p 74 N87-17656 [IAF PAPER 86-06] p 65 A87-15805 Design improvement and radiation. contaminationtests RESEARCH FACILITIES Prestudy 1: Ultraviolet radiation acceleration, volume 1 --- System concept for a moderate cost Large Deployable Description of the Spacecraft Control Laboratory satellite design Reflector (LDR) p3 A87-I8508 Experiment (SCOLE) facility p 10 N87-17837 [CERT-4193-VOL-I] p 53 N87-10949 Oxidation-resistantreflective surfaces for solar dynamic RESEARCH MANAGEMENT Design improvement and radiation contamination tests. power generation in near Earth orbit The system approach for applying artificial intelligence Prestudy 1. Ultraviolet radiation acceleration. Volume 2: [ NASA-TM-888651 p 54 N87-10960 to Space Station automation p 64 A87-13708 Appendix, detailed results --- Satellite coating Composite space antenna structures: Properties and RESIDUAL STRESS [CERT-4193-VOL-2] p 53 N87-10950 environmental effects Effects of curing stresses on composite structures Improving the irradiation plus contamination tests. [ NASA-TM-888591 p 39 N87-16880 p 56 N87-16930 Prestudy 2: Successive irradiationsand synergics. Volume Developmentof lightweight dimensionally stable carbon RESONANT FREQUENCIES 1: Tests and conclusions --- Satellite coatings fiber composite antenna reflectors for the INSAT-I Efficient modal analysis of damped large space [CERT-4193-VOL-3] p 53 N87-10951 satellite p 56 N87-16936 structures p 28 A87-23995 Improving radiation plus contamination tests. Prestudy Thermomechanical characteristics of dichroic RETRACTABLE EQUIPMENT 2 Successive irradiations and synergics. Volume 2: subreflectors --- Satellite antennas p 22 N87-16952 The Extendable Refractable Mast (ERM) thermal Annexes. Annex 1: Detailed results. Annex 2: Control and The Large Deployable Reflector (LDR) report of the analysis: A heat radiation case study via the finite element improvement of optical measurements --- satellite Science Coordination Group method p 22 N87-16949 coatings [ NASA-CR-1802351 p 10 N87-19310 REUSABLESPACECRAFT [CERT-4193-VOL-4] p 53 N87-10952 REINFORCED PLASTICS Space vehicle design --- French book RADIATION EFFECTS Reinforced PlasticslComposites Institute. Annual p 11 A87-10092 Space radiation effects on the dimensional stability of Conference, 41st. Atlanta. GA, January 27-31, 1986. Factors influencing selection of space transportation a toughened epoxy graphite composite Preprint p 67 A87-20076 options p 49 A87-11847 REINFORCING FIBERS [IAF PAPER 86-108] p 65 A87-15871 Effect of electron-beam radiation on graphite epoxy Effects of thermal cycling on graphie-fiber-reinforced Utilization. testing and maintenance of multimission composites p 49 A87-13071 6061 aluminum hardware p 70 A87-29466 The effects of radiation on the interlaminar fracture [NASA-TP-2612] p 52 N87-10184 RIGID STRUCTURES toughness of a graphitelepoxy composite REINFORCING MATERIALS High power rigid solar array --- Columbus space p 50 A87-19122 Advanced composites for large Navy spacecraft station Electron-radiation effects on the ac and dc electrical p 56 N87-16015 [SNIAS-917A-CA/CG] p47 N87-13864 properties and unpaired electron densities of three RELIABILITY ANALYSIS MMU (Manned Maneuvering Unit) task simulator aerospace polymers p 51 A87-21992 The dynamical qualification of present and future [ AD-A1695521 p 13 N87-14370 Analysis of the ion spot phenomenon on beam-charged spacecraft structures p 30 A87-29368 ROBOTICS dielectrics p 51 A87-21993 RELIABILITY ENGINEERING 1986 American Control Conference, 5th, Seattle, WA, Space radiation effects on the thermo-mechanical Maintainabilitytechnology p 59 A87-15407 June 18-20, 1986, Proceedings. Volumes 1, 2, 8 3 behavior of graphite-epoxycomposites Design and verification activities and requirements for p 64 A87-13301 p 51 A87-27178 spacecraft structures p 20 N87-10890 The role of automation and robotics in space stations RADIATION PROTECTION REMOTE HANDLING p 58 A87-I3706 Sun shield Fundamentals and advances in the development of Space missions for automation and robotics [NASA-CASE-MSC-20162-1] p 74 N87-17036 remote welding fabrication systems p 49 A87-14312 technologies (SMART) program p 58 A87-13707 RADIATION SHIELDING Space spider crane An introduction to the concept of robot factors and its Degradation of spacecraft thermal shield materials by [NASA-CASE-LAR-13411-lSBl p 73 N87-15259 application to Space Station automation Mobile remote manipulator system for a tetrahedral irradiation of energetic particles p 18 A87-18273 p 58 A87-13712 truss High voltage solar array plasma protection techniques Multiarm collision avoidance using the potential-field [ NASA-CASE-MSC-20985-11 p 61 N87-15260 --- for use on spacecraft p 45 A87-19878 approach p 59 A87-13715 RADIATIVE HEAT TRANSFER REMOTE MANIPULATOR SYSTEM Robotics concepts for the U.S. Space Station The Extendable Refractable Mast (ERM) thermal Space constructible radiator on-orbit assembly [AAS PAPER 85.6661 analysis: A heat radiation case study via the finite element p 58 A87-1 1359 p 60 A87-18486 method p 22 N87-16949 Development of a test procedure and facility for the A flexible telerobotic system for space operations RADIO TELESCOPES investigation of a Canadarm joint brake anomaly p 60 A87-23229 Optimal control of component deployment for the space p 59 A87-15191 The role of robotics in space p 60 A87-25756 radiotelescope system REMOTE SENSING A robotic system for dexterous tasks [AAS PAPER 85.6831 p 16 A87-18495 Model for radiation contamination by outgassing from p 60 A8725757 Large inflatable parabolic reflectors in space space platforms Second AIAAINASA USAF Symposium on Automation, p3 A87-19789 [AIAA PAPER 87-01021 p 67 A87-22416 Robotics and Advanced Computingfor the NationalSpace A Sener mechanism: Fine adjustment mechanism for Application of Spaceborne Distributed Program the Far Infrared and Submillimeter Space Telescope AperturelCoherent Array Processing (SDAICAP) [AIAA PAPER 87.16551 p 70 A87-31112 (FIRST) (F f F) p 74 N87-16946 technology to active and passive microwave remote Software architecture for manufacturing and space The large deployable reflector: A NASA sensing p 47 N87-17277 robotics RENDEZVOUS submillimeter-infraredorbiting observatory [AIAA PAPER 87-16871 p 12 A87-31121 Rendezvous and docking Verification and in-orbit p9 N87-17571 Design and control of modular, kinematically-redundant demonstration RANDOM LOADS manipulators [IAF PAPER 86-07] p 65 A87-15808 Response of discretized structures with elasto-plastic [AlAA PAPER 87-16941 p 61 A87-31122 deformation to non-stationary random excitation RENDEZVOUS GUIDANCE Trajectory shaping rendezvous guidance Rapid precise end point control of a wrist carried by a p 28 A87-22831 flexible manipulator p 61 N87-10398 RANGEFINDING p 64 A87-13434 RENDEZVOUS SPACECRAFT Telerobotic assembly of space station truss structure Sensor technology for advanced space missions Satellite motion analysis via laser reflector pattern [ NASA-CR-1802391 p 62 N87-18984 p 73 N87-16027 processing for rendez-vous and docking Rendezvous and docking and space robotics proximity RECTENNAS [IAF PAPER 86-06] p 65 A87-15805 operations. Part 5. Executive summary Rectenna composed of a circular microstrip antenna RENDEZVOUS TRAJECTORIES [ NLR-TR-85099-U1 p 62 N87-19441 p 46 A87-25700 Path-constrainedrendezvous - Necessary and sufficient ROBOTS RED SHIFT conditions p 66 A87-17834 Development of a test procedure and facility for the The tidal velocity field in the Local Supercluster MMU (Manned Maneuvering Unit) task simulator investigation of a Canadarm joint brake anomaly p 23 A87-11159 [AD-A169552] D 13 N87-14370 p 59 A87-I5191 A-16 SUBJECT INDEX SLEWING

Research and development of a small-sized space Construcciones Aeronauticas S.A. (CASA) large SATELLITE SOLAR POWER STATIONS manipulator reflector antenna --- satellite antenna p 9 N87-16935 Compact SPS for lunar development --- solar power [AAS PAPER 85-6601 p 60 A87-18481 Developmentof lightweignt dimensionally stable carbon satellites Rapid precise end point control of a wrist carried by a fiber composite antenna reflectors for the INSAT-I [IAF PAPER 86-1561 p 2 A87-15904 flexible manipulator P 61 N87-10398 satellite p 56 N87-16936 Optimizationof a microwave-beamenergy transmission Robot system for dexterous tasks (for space Structural analysis, manufacturing and development channel p 46 A87-29753 applications) status of large polarizationsensitive dual-griddedreflectors SATELLITE TRACKING [ETN-86-985621 p 61 N87-15472 --- satellite antenna p 22 N87-16937 Mechanical and control study of a 7 m offset unfurlable Development status of the ERS-I SAR antenna ROBUSTNESS (MATHEMATICS) tracking antenna p 39 N87-16926 p9 N87-16939 1986 American Control Conference, 5th. Seattle, WA. SCALE MODELS Developmentof mm-wave radiometer antenna reflector June 18-20. 1986, Proceedings. Volumes 1, 2, & 3 Experience gained by sector model testing of an p 64 A87-I3301 --- satellite antennas p 47 N87-16941 unfurlable meshlrib antenna p 14 N87-I6925 Simple approach for evaluating mechanical reflector Design of robust failure detection fllterS antenna distortions --- satellite antennas SCATHA SATELLITE p 24 A87-13395 A severe spacecraft-charging event on SCATHA in p 39 N87-16942 An analytical and experimental study of a control Prediction of the electrical performance of Inflatable September 1982 system's sensitivity to structural modifications --- for Space Rigidized Structure (ISRS) offset antenna reflectors [AIAA PAPER 87.04751 p 45 A87-22659 vibration of large space structures p 30 A87-30294 and correlation with RF measurements Boom potential of a rotating satellite in sunlight Unified ControVstructure design and modeling p 47 N87-16943 p 68 A87-24198 research Contraves' antenna tip hinge mechanism for Selenia The importance of accurate secondary electron yields [NASA-CR-l79948] p 33 N87-13478 Spazio's 20130 GHz antenna --- satellite antenna in modeling spacecraft charging p 46 A87-27018 Robust multivariable controller design for flexible p 74 N87-16944 SCIENTISTS Spacecraft p 37 N87-I 6048 Thermomechanical characteristics of dichroic COFS 1 Guest Investigator Program A modified loop transfer recovery approach for robust subreflectors --- satellite antennas p 22 N87-16952 p8 N87-I6034 control of flexible structures p 39 N87-17029 Features and technologies of ERS-1 (ESA) and X-SAR SELF ERECTING DEVICES ROCKET ENGINES antennas p9 N87-17152 Foldable self-erecting joint Proceedings of an International Symposium on Fluid SATELLITE ATTITUDE CONTROL [ NASA-CASE-MSC-20635-1I p 17 N87-14373 Dynamics and Space Nonlinear attitude control of flexible spacecraft under Development of a 2.8 m offset antenna reflector using [ESA-SP-265] p 72 N87-14394 disturbance torque p 29 A87-24049 inflatable, space-rigidizedstructures technology Parameter optimization and attitude stabilization of a ROCKET LAUNCHERS p 8 N87-16927 flexible Spacecraft p 31 N87-10138 Space vehicle design --- French book SENSITIVITY p 11 A87-10092 SATELLITE COMMUNICATION Active Control Evaluation for Spacecraft (ACES) Digital networks and their evolution Space and RODS - p 34 N87-16019 terrestrial systems; Proceedings of the Thirtythird Free rotation of an elastic rod with an end mass SERIES EXPANSION p 28 A87-23213 International Congress on Electronics and Twenty-sixth Control of SCOLE p 40 N87-17832 International Meeting on Space, Rome, Italy. Mar. 18-20, ROLL SHADES 1986 p 68 A87-24701 Parametric study of stable optical references for large Sun shield flexible structures in space p 64 A87-11013 SATELLITE CONTROL [ NASA-CASE-MSC-20162-11 p 74 N87-17036 Efficiency eccentricity control using continuous, ROTARY STABILITY SHALLOW SHELLS vectored thrusting for satellites with large areahass Instability of rotating blades in space A four node Marguerre element for non-linear shell [ IAF PAPER 86-2421 p 65 A87-15959 ratios p 63 N87-10151 analysis p 30 A87-30545 Formationkeeping of Spacecraft via differential drag The control theory of flexible and articulated SHAPE CONTROL [NASA-CR-171939] p 71 N87-I3466 spacecraft Decentralized control experiments on NASA's flexible [AD-A1748801 p 42 N87-19434 SATELLITE DESIGN grid p 24 A87-13394 Satellite construction p 61 A87-27454 ROTATING BODIES Numerical and experimental evaluation of poles and Comparisonof multiple input random and sine excitation Space station rotary joint mechanisms system zeros for large flexible space structures p 73 N87-16338 methods for aerospace structures --- spacecraft vibration p 27 A87-18322 models p 12 A87-28552 Modal control of traveling waves in flexible structures Design improvement and radiation. contaminationtests. p 29 A87-24552 S Prestudy 1: Ultraviolet radiation acceleration, volume 1 .-- Effect of sensor and actuator errors on static shape satellite design control for large space structures p 29 A87-27948 SAFETY FACTORS [CERT-4193-VOL-I] p 53 N87-10949 Formationkeeping of spacecraft via differential drag Meteoroid and orbital debris protection concepts Design improvement and radiation contamination tests. [NASA-CR-1719391 p 71 N87-13466 [IAF PAPER 86-4191 p 65 A87-16081 Prestudy 1: Ultraviolet radiation acceleration. Volume 2: COFS 2: 3-D dynamics and controls technology SANDWICH STRUCTURES Appendix, detailed results -..satellite coating p 35 N87-16035 Analysis of high precision composite sandwich antennas [CERT-4193-VOL-2] p 53 N87-10950 Surface control system for the 15 meter hoop-column --- spacecraft antennas p 56 N87-16929 Improving the irradiation plus contamination tests. antenna p 37 N87-16047 SATELLITE ANTENNAS Prestudy 2: Successive irradiations and synergics. Volume Robust multivariable controller design for flexible The ESA1MBB unfurlable mesh antenna development 1: Tests and conclusions --.satellite coatings spacecraft p 37 N87-16048 for mobile services [CERT-4193-VOL-3] p 53 N87-10951 A modified loop transfer recovery approach for robust [IAF PAPER 66-27] p2 A87-15818 Improving radiation plus contamination tests. Prestudy control of flexible Structures p 39 N87-17029 S band 3.5-m-diameter fan rib type deployable mesh 2: Successive irradiations and synergics. Volume 2: SHEAR STRAIN antenna for satellite use Annexes. Annex 1' Detailed results. Annex 2: Control and Shear deformation plate continua of large double layered [ IAF PAPER 86-26] p 11 A87-15819 improvement of optical measurements --- satellite space structures p 16 A87-28882 A new structure toward high precision large antenna coatings SHELL THEORY [IAF PAPER 86-201I p I5 A87-15929 [CERT-4193-VOL-4] p 53 N87-I0952 A four node Marguerre element for non-linear shell Antenna system alternatives for Data Relay Satellites Improving radialionlconlamination tests --- satellite analysis p 30 A87-30545 with multiple steerable beams coating degradation SHOCK ABSORBERS [IAF PAPER 86.3491 p 43 A87-16041 [CERT-41930011-DERTS] p 54 N87-10954 Passive damping augmentation for flexible structures Free rotation of an elastic rod with an end mass Development of the Lens Antenna Deployment p36 N87-16044 p 28 A87-23213 Demonstration (LADD) shuttle-attached flight experiment SIGNAL GENERATORS Communications technology p 46 A87-30893 p 7 N87-I6022 System engineering study of electrodynamic tether as Tele-X antenna module structure qualification program SATELLITE GROUND SUPPORT a spaceborne generator and radiator of electromagnetic P 21 N87-10924 Use of support simulation modeling techniques in the waves in the ULF1ELF frequency band Offset unfurlable antenna. Phase 2A Executlve development of logistics support concepts for SDI orbital [NASA-CR-1801561 p 23 N87-16956 summary --- Intelsat. M-Sat platforms and constellations SIGNAL PROCESSING [ MBB-R-020013069-Rl p 70 N87-11066 [AIM PAPER 87-06901 p 12 A87-27617 Aerospace Applications Conference, Steamboat Study of frequency selective systems. Part 1: Preliminary SATELLITE OBSERVATION Springs, CO. Feb. 1-8. 1986. Digest p 69 A87-25976 investments on shapes and lattices; software Dual-spacecraft measurements Of SILVER developments. Part 2: Interfacing of Politecnico FSS plasmasphere-ionospherecoupling p 67 A87-20055 Effect of hard particle impacts on the atomic oxygen programs with MATRA reflector antenna software. Part SATELLITE POWER TRANSMISSION (TO EARTH) Survivability of reflector surfaces with transparent 3: Application to MACS phase 2 TX antenna (MATRA) Mwn for terrestrial energetics protective overcoats --- satellite antennas [ IAF PAPER 86-4561 p2 A87-16108 [ NASA-TM-88874I p 71 N87-11838 SIMULATION [ANTINTEA/04.851 p 13 N87-13626 SATELLITE ROTATION L-band antennas for regional mobile communication Ground taciiity for large space structures dynamics and Free rotation of an elastic rod with an end mass control verification satellites p 47 N87-15377 p 28 A87-23213 Experience gained by sector model testing of an [NASA-TM-86558] p41 N87-18600 unfurlable mesh1rib antenna p 14 N87-16925 Boom potential of a rotating satellite in sunlight SIMULATORS p 68 A87-24198 Mechanical and control study of a 7 m offset unfurlable Flight Dynamics Laboratory overview tracking antenna p 39 N87-16926 SATELLITE SOLAR ENERGY CONVERSION p7 N87-16018 Study on solid surface, deployable antenna reflector --- Modeling and simulation of spacecraft solar array Distributed control for COFS 1 p 36 N87-I6043 satellite antenna p 8 N87-I6928 deployment p 26 A87-17760 SLEWING Development of 30120 GHz satellite antenna In-orbit performance of Hughes HS 376 solar arrays Slew maneuver control of the Spacecraft Control structures p9 N87-16933 p 44 A87-I9872 Laboratory Experiment (SCOLE) p 24 A87-13393 Design of a low distortion shared aperture reflector --- Solar power satellite built of lunar materials Automatic decoupling of flexible spacecraft slewing satellite antenna p 14 N87-16934 p 68 A87-25426 maneuvers D 24 A87-13431

A-17 SOFTWARE ENGINEERING SUBJECT INDEX

A slewing control experiment for flexible structures LEO high voltage solar array arcing response model SPACE COMMERCIALIZATION p 27 A87-17761 [ NASA-CR-I80073 I p 47 N87-16971 Technologies for affordable access to space Large-angle slewing of flexible spacecraft SOLAR COLLECTORS [ IAF PAPER 86-442j p2 A87-16096 [AAS PAPER 85-6741 p 27 A87-18490 Structural concepts for large solar concentrators Space Station: Gateway to space manufacturing; Optimal torque control for SCOLE slewing maneuvers [IAF PAPER 86-2021 p 15 A87-15930 Proceedings of the Conference, Orlando, FL. Nov. 7, 8. 1985 p 68 A87-25451 p 40 N87-17823 SOLAR DYNAMIC POWER SYSTEMS Slew maneuver dynamics 01 the Spacecraft Control Pointing, control. and stabilization of solar dynamic Space commerce '86; Proceedings of the International Laboratory experiment p 40 N87-17825 system on a Space Station p 25 A87-I3437 Conference and Exhibition on the Commercial and Proofmass actuator placement strategies for regulation Industrial Uses of Outer Space, Montreux. Switzerland. Effect of hard particle impacts on the atomic oxygen June 16-20, 1986 p 69 A87-29401 of flexure during the SCOLE slew p 40 N87-17830 survivability of reflector surfaces with transparent Active damping of vibrations in SCOLE excited by National Aeronautics and Space Administration protective overcoats p6 N87-10774 slewing p 40 N87-17831 [AIAA PAPER 87-01041 p 45 A87-22417 National Commission on Space report Description of the Spacecraft Control Laboratory Oxidation-resistantreflective surfaces for solar dynamic Experiment (SCOLE) facility p 10 N87-17837 [ GPO-63.1 43 I p7 N87-12574 power generation in near Earth orbit Report of the National Commission on Space SOFTWARE ENGINEERING [ NASA-TM-888651 p 54 N87-10960 Proceedings of the 5th Annual Users' Conference [S-HRG-99-954] p 73 N87-15028 [ NASA-CP-23991 p 70 N87-10720 Effect of hard particle impacts on the atomic oxygen SPACE DEBRIS SuNivability of reflector surfaces with transparent SOFTWARE TOOLS Meteoroid and orbital debris protection concepts protective overcoats Proceedings of the 5th Annual Users' Conference [IAF PAPER 86-4191 p 65 A87-16081 [ NASA-TM-888741 p 71 N87-11838 [ NASA-CP-23991 p 70 N87-10720 Collisional probability in space and the debris A unified approach to computer analysis and modeling SOLARENERGY environment in future p 66 A87-18247 of spacecraft environmental interactions NASA Growth Space Station missions and candidate Cleaning up our space act p5 A87-31208 p 14 N87-20066 nuclear/solar power systems p 3 A87-21807 Protection of spacecraft from meteoroids and orbital SOLARARRAYS SOLAR GENERATORS debris Flexibility control of solar arrays based on state ARABSAT solar generator concept and in orbit [ DE86-0099961 p 70 N87-10947 estimation by Kalman filtering p 26 A87-15450 perlormance p 43 A87-18075 Analysis of micrometeoritematerial captured by the solar Solar array mechanisms for Indian satellites, APPLE. 20-Array mission - Two-dimensionallydeployable solar max Satellite p 55 N87-14385 IRS and INSAT-IITS cell array mission p 15 A87-18243 Examination of returned solar-max surfaces for [IAF PAPER 86-1421 p 11 A87-15893 Developmentof a lightened structure for the GSR3 solar impacting orbital debris and meteoroids Modeling and simulation of spacecraft solar array generator p 17 N87-10927 p 55 N87-14386 SPACE ENVIRONMENT SIMULATION deployment p 26 A87-17760 SOLAR MAXIMUM MISSION A method of studying the behavior of composite Solar arrays for Space Station and platforms Erosion studies on Solar Max samples materials in simulated space environments p 44 A87-18149 p A87-19343 50 p 53 N87-10940 20-Array mission - Two-dimensionally deployable solar Proceedings of the SMRM Degradation Study cell array mission p 15 A87-I8243 Design improvement and radiation, contamination tests. Workshop Prestudy 1: Ultraviolet radiation acceleration, volume 1 --- Control of solar battery arrays of spacecraft with [ NASA-TM-892741 p 72 N87-I4374 consideration of the structural flexibility satellite design p44 A87-18319 Report on SMRM CIP main electronics box component [CERT-4193-VOL-I] p 53 N87-10949 and matenals degradation evaluations Dynamics of the orbiter based flexible members Design improvement and radiation contamination tests. p 27 A87-18324 p 72 N87-14375 Prestudy 1: Ultraviolet radiation acceleration. Volume 2: In-orbit performance of Hughes HS 376 solar arrays Results of examination of materials from the solar Appendix, detailed results --- satellite coating p 44 A87-19872 maximum recovery mission p 54 N87-14383 [CERT-4193-VOL-2] p 53 N87-10950 High voltage solar array plasma protection techniques SOLAR POWER SATELLITES Improving radiation plus contamination tests. Prestudy --- for use on spacecraft p 45 A87-19878 On the initiation of SPS development 2: Successive irradiations and synergics. Volume 2: Flexibility control of solar battery arrays. II - Vibration p 1 A87-12086 Annexes. Annex 1: Detailed results. Annex 2: Control and and attitudecontrol based on state estimationof differential A concept of the Energy Storable Orbital Power Station improvement of optical measurements --- satellite solar cell sensors p 45 A87-22968 (ESOPS) coatings Flexibility control of solar battery arrays. 111 - vibration [IAF PAPER 86-1491 p 42 A87-15898 [CERT-4193-VOL-4] p 53 N87-10952 and attitude control with consideration of the dynamics Compact SPS for lunar development --- solar power Improving radiationlcontamination tests --- satellite of a reaction wheel as an actuator p 45 A87-22969 satellites coating degradation Deployment analysis of the Olympus Astromast and [IAF PAPER 86-1561 p 2 A87-15904 [ CERT-419300/1 -DERTS] p 54 N87-10954 comparison with test measurements p 61 A87-31220 Structural concepts for large solar concentrators SPACEERECTABLESTRUCTURES Plasma electron collection through biased slits in a [IAF PAPER 86.2021 p 15 A87-15930 20-Array mission - Two-dimensionallydeployable solar dielectric p 46 A8741223 Moon for terrestrial energetics cell array mission p 15 A87-I8243 Influence of fiber orientation and boundary conditions [ IAF PAPER 86-4561 p2 A87-16108 Alternative approximation concepts for space frame on the dynamic behavior of a cylindrically telescoping solar Lunar-based power systems synthesis p 19 A87-18940 array (INTELSAT 6) p 32 N87-I0925 [IAF PAPER 86-5071 p 43 A87-16132 Deployment analysis of the Olympus Astromast and HPSA: High Power Solar Array study ---Columbus space Solar power satellite concept revisited comparison with test measurements p 61 A87-31220 station p 4 A87-22771 A space station Structures and Assembly Verification [BAE-TP-80711 p 47 N87-I1352 Solar power satellite built of lunar materials Experiment, SAVE Solar array flight dynamic experiment p 68 A87-25426 [ NASA-TM-89004j p 5 N87-10170 [ NASA-TP-2598j p7 N87-12581 The USSR and space power plants Influence of fiber orientation and boundary conditions High power rigid solar array --- Columbus space p 45 A87-25533 on the dynamic behavior of a cylindrically telescoping solar station Rectenna composed of a circular microstrip antenna array (INTELSAT 6) p 32 N87-10925 [SNIAS-917A-CA/CG1 p 47 N87-13864 p 46 A87-25700 Design, construction and utilization of a space station Space station rotary joint mechanisms SOLAR RADIATION assembled from 5-meter erectable struts p 73 N87-16338 Instability of rotating blades in space [ NASA-TM-890431 p6 N87-11827 The Extendable Refractable Mast (ERM) thermal [ IAF PAPER 86-242j p 65 A87-15959 analysis: A heat radiation case study via the finite element Analysis of normal and transparent silver Teflon High power rigid solar array --- Columbus space method p 22 N87-16949 p 55 N87-14391 station [SNIAS-917A-CA/CG p 47 N87-13864 LEO high voltage solar array arcing response model Parametric investigation of factors influencing the 1 [NASA-CR-180073] p 47 N87-16971 mechanical behavior of large space structures Foldable self-erecting joint The concentration principle applied to spaceborne solar [AD-AI 72880 j p 38 N87-16056 [ NASA-CASE-MSC-20635-1I p 17 N87-14373 arrays. Application to the coorbiting platform mission: SOLAR RADIATION SHIELDING Development of a 2.8 m offset antenna reflector using Studies synthesis Sun shield inflatable, space-rigidizedstructures technology [SNIAS-975-CA/CGj p 75 N87-19814 [NASA-CASE-MSC-20162-11 p 74 N87-17036 p8 N87-I6927 High voltage system: Plasma interaction summary SOLAR REFLECTORS Prediction of the electrical performance of Inflatable p 48 N87-20069 The survivability of large space-borne reflectors under Space RigidizedStructure (ISRS) offset antenna reflectors SOLARBLANKETS atomic oxygen and micrometeoroid impact and correlation with RF measurements Protection of solar array blankets from attack by low [AIAA PAPER 87-03411 p 52 A87-31300 p 47 N87-16943 earth orbital atomic oxygen p 45 A87-19874 The SUNiVability of large space-borne reflectors under Space station systems: A continuing bibliography with atomic oxygen and micrometeoroid impact The effect of the non-uniform stress distribution in the indexes (supplement 3) [ NASA-TM-889141 p 72 N87-14423 blankets of single and twin boom solar array panels upon [ NASA-SP-7056(03)j p 75 N87-17820 their modal characteristics p 32 N87-10904 SOLID LUBRICANTS Space station erectable manipulator placement Tribological properties of polymer films and solid bodies Discrete mechanism damping effects in the solar array system in a vacuum environment [ NASA-CASE-MSC-21096-11 p 62 N87-18596 flight experiment p 38 N87-16341 [ NASA-TM-88966j p 57 N87-17906 Passively damped joints for advanced space SOLAR CELLS SOLID SURFACES 1986 LECEC stability and transient modeling of a large structures Study on solid surface, deployable antenna reflector --- [AD-A1749141 p 42 N87-19435 spacecraft power system p66 A87-18114 satellite antenna p8 N87-16928 The potential impact of new power system technology SPACEBASES SPACE EXPLORATION on the design of a manned Space Station A 21st century nuclear power strategy for Mars Getting back on track in space p 1 A87-14375 p 44 A87-18342 [IAF PAPER 86.3221 p 42 A87-16019 The Space Station program Flexibility control of solar battery arrays. II - Vibration SPACE COLONIES [AAS PAPER 85-4511 pl A87-15377 and attitude control based on state estimationof differential Report of the National Commission on Space Report of the National Cornmission on Space solar cell sensors P 45 A87-22968 [S-HRG-99-954j p 73 N87-15028 [ S-HRG-99.9541 p 73 N87-15028 SUBJECT INDEX SPACE STATIONS

SPACE FLIGHT Space station systems: A continuing bibliography with Space station automation; Proceedings of the Meeting. National Aeronautics and Space Administration indexes (supplement 3) Cambridge, MA, September 17, 18, 1985 Authorization Act. 1987 [ NASA-SP-7056(03)] p 75 N87-17820 [SPIE-580] p 64 A87-13705 [ H-REPT-99-8291 p6 N87-11640 Preliminary findings for integrated modeling and The role of automation and robotics in space stations Aeronautics and space report of the President: 1985 simulation of directed energy weapons p58 A87-13706 activities p 74 N87-16662 [DE86-011636] p 10 N87-17846 The system approach for applying artificial intelligence SPACE INDUSTRIALIZATION SPACE POWER REACTORS to Space Station automation p 64 A87-13708 Space Congress. 23rd. Cocoa Beach. FL. April 22-25. A 21sl centuty nuclear power strategy for Mars An introduction lo the concept of robot factors and its 1986. Proceedings p 63 A87-10026 [ IAF PAPER 86-3221 p 42 A87-16019 application to Space Station automation Space commerce '86; Proceedings of the International Design of a superconducting alternator for space-based p 58 A87-13712 Conference and Exhibition on the Commercial and power generation p 43 A87-18144 Matter of ease --- optimization of man- and Industrial Uses of Outer Space, Montreux, Switzerland. Space nuclear power systems 1985; Proceedings of the machine-controlled spaceborne structural assembly June 16-20. 1986 p 69 A87-29401 Second Symposium, Albuquerque, NM. Jan. 14-16, 1985. operations p 59 A87-13949 SPACE LABORATORIES Volumes 3 8 4 p 67 A87-21801 The Space Station - United States proposal and Japanese laboratory proposal p 69 A8725753 NASA Growth Space Station missions and candidate implementation p 1 A87-14969 SPACE LAW nuclear/solar power systems p3 A87-21807 Equipment designs for Space Station EVA examined The Space Station - United States proposal and SPACE PROCESSING pi1 A87-15196 implementation p 1 A87-14969 Fabrication of a carbon fibre/aluminium alloy composite Space Station beyond 1% Proceedings of the SPACE LOGISTICS under microgravily p 48 A87-11384 Thirty-second Annual International Conference, Los Space Logistics Symposium, Ist, Huntsville. AL. Mar. Overview of planned tests of space materials Angeles. CA. November 6, 7, 1985 --- Initial Operational 24-26. 1987, Technical Papers p69 A8727603 p 56 N87-15990 Capability p 65 A87-15376 Front end logistics influence on space system hardware SPACE PROGRAMS The Space Station program design Space exploitation and utilization; Proceedings of the [AAS PAPER 85-451 I p 1 A87-15377 [AIAA PAPER 87.06581 p5 A87-27605 Symposium, Honolulu, HI, December 15-19. 1985 Space Station evolution - The aerospace technology A preliminary logistics support concept for space-based p 66 A87-18451 impact SDI assets National Commission on Space report [AAS PAPER 85.4561 p 1 A87-15380 [AIAA PAPER 87.06891 p 61 A87-27616 [ GPO-63.1431 p 7 N87-12574 Navigation. guidance, rendez-vous and docking - Space logistics support lo military space systems Aeronautics and space report of the President: 1985 Activities carried out for Columbus by the llight operations [AIAA PAPER 87-06941 p 69 A87-27621 activities p 74 N87-16662 organization SPACE MAINTENANCE SPACERENDEZVOUS [IAF PAPER 66-09] p 65 A87-15808 Hubble Space Telescope - Dawn of the era of Path-constrainedrendezvous - Necessary and sufficient Space construction results - The EASElACCESS flight serviceable spacecraft conditions p 66 A87-17834 experiment [ IAF PAPER 86-20] p2 A87-15814 Advanced opto-electronical sensors for autonomous [ IAF PAPER 86-26] p2 A87-15817 Space station thrillers unfold a1 Draper Lab Rendezvous-/Docking and proximity operations in space Meteoroid and orbital debris protection concepts p 11 A87-21257 p 44 A87-19707 [IAF PAPER 86-4191 p 65 A87-16081 The role of robolics in space p 60 A87-25756 Analysis of rendezvous and docking in geostationary Space Station - NASA's greatest challenge Design and analysis of a keel latch for use on the Hubble Earth orbit. Rider lo comparison of future communications p2 A87-16399 Space Telescope p 62 N87-16326 space segment concepts A consideration of atomic oxygen interactions with the SPACE MANUFACTURING [ DM51-C/PL/FL/OO99.82] p 72 N87-14364 Space Station p 43 A87-17836 Remotely manipulated and autonomous robotic welding Rendezvous and docking and space robotics proximity Robotics concepts for the U.S. Space Station fabrication in space p 59 A87-13714 operations. Part 5: Executive summary [AAS PAPER 85.6661 p 60 A87-18486 Fundamentals and advances in the development of [ NLR-TR-85099-U1 p 62 N87-19441 Pultrusion process development for long space boom remote welding fabrication systems p 49 A87-14312 SPACE SHUTTLE ORBITERS models p 60 A87-20083 Space Station: Gateway 10 space manufacturing; Protective coating lor the KU-band reflector --- in Space Space station thnllers unfold at Draper Lab Proceedings of the Conference, Orlando, FL, Nov. 7, 8. Shunle radar antenna p 49 A87-13098 p 11 A8741257 1985 p 68 A87-25451 Development of a test procedure and facility for the A flexible telerobotic system for space operations Overview of planned tests of space materials investigation of a Canadarm joint brake anomaly p 60 A87-23229 p56 N87-15990 p 59 A87-15191 Space Station: Gateway to space manufacturing; SPACE MISSIONS On the Orbiter based deployment of flexible members Proceedings of the Conference. Orlando, FL. Nov. 7, 8. Space missions for automation and robotics [AAS PAPER 85-6731 p 16 A87-18489 1985 p68 A87-25451 technologies (SMART) program p 58 A87-13707 Energetic oxygen atom inaterial degradation studies Space Tech '86; Proceedings of the International Aerospace Testing Seminar. 9th, Los Angeles, CA. Oct. [AIAA PAPER 87-01051 p 51 A87-24919 Conference, Geneva, Swiherland. May 14-16. 1986 15-17. 1985. Proceedings p 69 A87-29441 Ground facility for large space structures dynamics and p 68 A8725751 Aeronautics and space report of the President: 1985 control venficalion Space Station - Designing the future activities p74 N87-16662 [ NASA-TM-885581 p 41 N87-18600 p4 A8725752 SPACE NAVIGATION SPACESHUTTLEPAYLOADS Japanese laboratory proposal p 69 A8725753 Navigation. guidance, rendez-vous and docking - Dynamics of the orbiter based flexible members The role of robotics in space p 60 A87-25756 Activities carried out for Columbus by the flight operations p 27 A87-18324 The role of expert systems on Space Station organization Solar array flight dynamic experiment p4 A87-25758 [IAF PAPER 66-09] p 65 A87-15808 [ NASA-TP-25981 p 7 N87-12581 Space Station - The use of expert systems for SPACE PLASMAS Ground facility for large space structures dynamics and planning p 4 A87-25759 High voltage solar array plasma protection techniques control verification Aerospace Applications Conference, Steamboat --- for use on spacecraft p 45 A87-19878 [ NASA-TM-865581 p 41 N87-18600 Springs, CO. Feb. 1-8. 1986. Digest p 69 A87-25976 Architecture and design process lor complex systems: Dual-spacecraft measurements 01 SPACESHUTTLES Space Station A case study p 12 A87-25978 plasmasphere-ionospherecoupling p 67 A87-20055 Hearings before the Subcommittee on Space Science - Plasma electron collection through biased slits in a Rationalising Space Station p 5 A8727455 and Applications of the Committee on Science and dielectric p 46 A8741223 Extending the Space Station infrastructure Technology. 99th Congress. 2nd Session, No. 132, 25, LEO high voltage solar array arcing response model p5 A87-28953 27 February; 11. 13. 20 March 9. 10 April, 1986. Volume Communications spacecraft p 5 A87-30891 [NASA-CR-180073] p 47 N87-16971 2 Software architecture for manufacturing and space Large structures and tethers working group [ GPO-61.7771 p 7 N87-12402 p 75 N87-20057 robotics The interaction of small and large spacecraft with their Descnption of the Mast Flight System [AIAA PAPER 87-16871 p 12 A87-31121 p8 N87-16030 environment p 10 N87-20064 Design, construction and utilization of a space station High voltage system: Plasma interactionsummary Discrete mechanism damping effects in the solar array assembled from 5-meter erectable struts p 48 N87-20069 flight experiment p 38 N87-16341 [ NASA-TM-890431 p 6 N87-11827 Technical issues in the conduct of large space platform SPACE STATION POWER SUPPLIES Mobile remote manipulator system for a tetrahedral experiments in plasma physics and geoplasma Sciences Space Station challenge. On-orbit assembly of a 75-kW INSS p 75 N87-20071 power system p 59 A87-18148 [ NASA-CASE-MSC-20985-11 p 61 N87-15260 Controlling and monitoring the space-station plasma Solar arrays for Space Station and platforms NASA/DOD Control/StructuresInteraction Technology, interaction: A baseline for performing plasma experiments p 44 A87-18149 1986 and using advanced technology p 76 N87-20079 NASA Growth Space Station missions and candidate [ NASA-CP-2447-PT-11 p73 N87-16014 Spacecraft charging in the auroral plasma: Progress nuclear/solar power systems p3 A87-21807 COFS 3: Multibcdy dynamics and control technology toward understanding the physical effects involved Solar power satellite concept revisited p 36 N87-16036 p 48 N87-20080 p4 A87-22771 Conceptual design 01 pointingcontrol systems for space station gimballed payloads p36 N87-16037 SPACE PLATFORMS SPACE STATIONS Passive damping augmentation for llexible structures The dynamics and control of a space platformconnected Technical aspects of the United States Space Station p36 N87-16044 lo a tethered subsatellite p 25 A87-14074 p 1 A87-10043 Solar arrays for Space Station and platforms The 20th Aerospace Mechanics Symposium Space vehicle design French book p 44 A87-18149 --. [ NASA-CP-2423-REVI p 73 N87-16321 p 11 A87-10092 Model for radiation contamination by outgassing from Space station rotary joint mechanisms space platforms Development of Space Station strut design p 73 N87-16338 [AIAA PAPER 87-01021 p 67 A87-22416 p 15 A87-11842 Space station systems: A continuing bibliography with Use of support simulation modeling techniques in the Fabrication of a Space Station composite tetratruss indexes (supplement 3) development of logistics support concepts for SDI orbital model p 49 A87-13159 [ NASA-SP-7056(03)1 p 75 N87-17820 platforms and constellations Trajectory shaping rendezvous guidance Locking hinge [AlAA PAPER 87-06901 p 12 A87-27617 064 A87-13434 [NASA-CASE-MSC-21056-1] p 62 N87-18595

A-19 SPACE STORAGE SUBJECT INDEX

Space station erectable manipulator placement Concept of tension activated cable lattice antenna Adhesive bonding of aerospace materials - Surface system [IAF PAPER 86-2061 p 15 A87-15934 characterization of metallic adherends [ NASA-CASE MSC-21096 1I p 62 N87 18596 Stress and deformation analysis of thermally loaded light p 51 A87-20149 Telerobotic assembly of space Station truss structure weight composite Structures Electron-radiation effects on the ac and dc electrical [ NASA-CR 1802391 p 62 N87-18984 [IAF PAPER 86-2121 p 18 A87-15939 properties and unpaired electron densities of three Technical issues in the conduct of large space platform Design and development Of a telescopic axial boom aerospace polymers p 51 A87-21992 experiments in plasma physics and geoplasma sciences p 14 N87-16322 Energetic oxygen atom material degradation studies p75 N8720071 Composite space antenna structures: Properties and [ AlAA PAPER 87-0105 I p 51 A87-24919 Controlling and monitoring the space-station plasma environmental effects Satellite construction p 61 A8727454 interaction A baseline for performing plasma experiments [ NASA-TM-88859I p 39 N87-I6880 Space technologies and materials: A look back and and using advanced technology p 76 N87-20079 Development of a 2.8 m Offset antenna reflector using future perspectives p 52 N87-10934 SPACE STORAGE inflatable. space-rigidized structures technology A method of studying the behavior of composite Evaluation of on-orbit cryogenic propellant depot options p 8 N87-16927 matenals in simulated space environments for the orbital transfer vehicle p63 A8731133 Analysis of high precision composite sandwich antennas p 53 N87-10940 SPACE SUITS --- spacecraft antennas p 56 N87-16929 New materials for spacecraft stability and damping: A Equipment designs for Space Station EVA examined Effects of curing stresses on composite structures feasibility study pi1 A8715196 p 56 N87-16930 [AD-A169826] p 54 N87-12601 SPACE TECHNOLOGY EXPERIMENTS Dielectric support Structures for spacecraft antenna Activities report in materials and construction --- Space station systems A continuing bibliography with feeds p 17 N87-16931 aerospace structures indexes (supplement 3) Giotto spacecraft high gain antenna mechanical design [ISSN-0174-3910] p 54 N87-13589 [NASA SP-7056[03)1 p 75 N87-17820 and development p 18 N87-I6938 Study of frequency selective systems. Part 1: Preliminary SPACE TOOLS A Sener mechanism: Fine adjustment mechanism for investments on shapes and lattices; software Development of a pre prototype power assisted glove the Far Infrared and Submillimeter Space Telescope developments. Part 2: Interfacing of Politecnico FSS end effector for extravehicular activity [FIRST) (F f F) p 74 N87-16946 programs with MATRA reflector antenna software. Part [ NASA-CR-I719401 p 72 N87 13989 The Extendable Refractable Mast (ERM) thermal 3: Application to MACS phase 2 TX antenna (MATRA) SPACE TRANSPORTATION analysis: A heat radiation case study via the finite element --- satellite antennas Factors influencing selection of space transportation method p 22 N87-16949 ANTlNTEAl04.851 p 13 N87-13626 options Integrated structure electromagnetic optimization of Possible areas of collaboration between DFVLR and [IAF PAPER 86-1081 p65 A87 15871 large space antenna reflectors ISRO in the fields of structures and materials Space Tech '86. Proceedings of the International [ NASA-TM-891101 p 48 N87-I8598 p 56 N87-15252 Conference Geneva, Switzerland May 14 16 1986 SPACECRAFT CHARGING Advanced composites for large Navy spacecraft p68 A8725751 The electron irradiation test of thermal control material p 56 N87-16015 NASA's technology plans - Will technology be ready p 50 A87-I8271 Damping 1986 procedures, volume 2 when we are Analysis of the ion spot phenomenon on beam-charged [ AD-AI 73950 1 p 73 N87-16366 [AlAA PAPER 87-16951 p5 A8731123 dielectrics p 51 A87-21993 The welding of aluminum alloys: A new technology in SPACE TRANSPORTATION SYSTEM A severe spacecraft-charging event on SCATHA in space application p 56 N87-17056 National Aeronautics and Space Administration September 1982 SPACECRAFT CONTAMINATION p6 N87-10774 [AIAA PAPER 87.04751 p 45 A87-22659 An estimate of the outgassing of space payloads and National Aeronautics and Space Administration Radiation from large space structures in low earth orbit its gaseous influence on the environment Authorization Act. 1987 p6 N87-10775 with induced ac currents p48 A87-11355 National Aeronautics and Space Administration [AIAA PAPER 87-06121 p 68 A87-22738 Model for radiation contamination by outgassing from p7 N87-15908 The importance of accurate secondary electron yields space platforms Satellite servicing price estimation instruction booklet in modeling spacecraft charging p 46 A87-27018 [AIAA PAPER 87-01021 p 67 A87-22416 [NASA CR3-17t967] p 75 N87 18583 Plasma electron collection through biased slits in a Acoustic cleaning of large space structures SPACE WEAPONS dielectric p 46 A87-31223 p 46 A87-26060 Multimegawatt power distribution considerations Plasma interactions with large spacecraft Plasma interactions with large spacecraft p43 A8718113 p 48 N87-20063 p 48 N87-20063 A preliminary logistics support concept for space-based A unified approach to computer analysis and modeling SPACECRAFTCONTROL SDI assets of spacecraft environmental interactions Failure-accommodating control of large flexible [AlAA PAPER 87 0889) p61 A8727616 p 14 N87-20068 spacecraft p 24 A87-13317 Space logistics support to military space systems Spacecraft charging in the auroral plasma: Progress A laboratory experiment in controllstructure interaction [AIAA PAPER 87 06941 p69 A8727621 toward understanding the physical effects involved --- for flexible spacecraft p 24 A87-13392 Preliminary findings for integrated modeling and p 48 N87-20080 Slew maneuver control of the Spacecraft Control simulation of directed energy weapons SPACECRAFT COMMUNICATION Laboratory Experiment (SCOLE) p 24 A87-13393 [DE86-011636] p10 N87 17846 Digital networks and their evolution - Space and Pointing. control, and stabilization of solar dynamic SPACEBORNE EXPERIMENTS terrestrial systems; Proceedings of the Thirty-third system on a Space Station p 25 A87-13437 Proceedings of an International Symposium on Fluid International Congress on Electronics and Twenty-sixth Nonlinear interfaces for acceleration-commanded Dynamics and Space International Meeting on Space, Rome, Italy. Mar. 18-20, control of spacecraft and manipulators [ ESA-SP-2651 p 72 N87-14394 1986 p 68 A87-24701 p 25 ~87.13494 Technical issues in the conduct of large space platform SPACECRAFT COMPONENTS Space station automation; Proceedings of the Meeting, experiments in plasma physics and geoplasma sciences Cost reduction on large space systems through Cambridge. MA. September 17, 18. 1985 p 75 N87 20071 commonality [SPIE-5801 p 64 A87-13705 SPACEBORNE LASERS [AIAA PAPER 87.05851 p 4 A87-22721 The dynamics and control of a space platform connected Satellite motion analysis via laser reflector pattern New materials for spacecraft stability and damping: A to a tethered subsatellite p 25 A87-14074 processing for rendez-vous and docking feasibility study Improving the active vibrational control of large space [IAF PAPER 86-06] p 65 A87-15805 [AD-A169826] p 54 N87-12601 structures through structural modifications Advanced opto-electronical sensors for autonomous Robot system for dexterous tasks (for space [IAF PAPER 86.2041 p 26 A87-15932 Rendezvous-/Docking and proximity operations in space applications) Attitude control experiment for flexible spacecraft p44 A8719707 [ETN-86-98562] p 61 N87-I5472 p 27 A87-18320 SPACEBORNEPHOTOGRAPHY SPACECRAFT CONFIGURATIONS Large-angle slewing of flexible spacecraft Advanced opto-electronical sensors for autonomous Dynamics formulation and simulation of multi-body [AAS PAPER 85.6741 p 27 A87-I8490 Rendezvous-/Docking and proximity operations in space space structures Frequency-shaped large-angle maneuvers p 44 A87-19707 [IAF PAPER 86-2381 p 26 A87-I5957 [AIAA PAPER 87-01741 p 28 A87-22462 SPACEBORNETELESCOPES Space Station design for growth Nonlinear attitude control of flexible spacecraft under Telescience in orbit p3 A87-16930 [ IAF PAPER 86-461 ] p2 A87-I6110 disturbance torque p 29 A87-24049 Optimal control of component deployment for the space Space Station - NASA's greatest challenge Optimal spacecraft rotational maneuvers --- Book radiotelescope system p2 A87-16399 p 68 A87-24625 [AAS PAPER 85-6831 p 16 A87-18495 NASA Growth Space Station missions and candidate Decentralized control of multt-body spacecraft - A System concept for a moderate Cost Large Deployable nuclearlsolar power systems p3 A87-21807 numerical experiment Reflector (LDR) p3 A8718508 Rationalising Space Station p5 A8727455 [AIAA PAPER 87-00181 p 29 A87-24902 Large inflatable parabolic reflectors in space Mars landing mission: A structural approach Ground facility for Large Space Structures dynamics and p3 A8719789 p 23 N87-17783 control verification p 31 A87-31095 Regulation of the SCOLE configuration Large space observatories of the 21 st century Proceedings of the 2nd Annual SCOLE Workshop p 41 N87-I7833 [AIM PAPER 87.06361 p4 A87-22751 [ NASA-TM-890481 p 70 N87-10945 SPACECRAFT CONSTRUCTION MATERIALS A Sener mechanism Fine adlustment mechanism for Modern control of large flexible spacecraft, ESA ASTP the Far Infrared and Submillimeter Space Telescope Space materials in Europe p 49 A87-13067 Materials - The challenge of space p 50 A87-18867 study (FIRST) (F f F) p 74 N87 16946 Use of graphitelepoxy composites in spacecraft [ BL-6206-ISSUE-21 p 70 N87-10956 The large deployable reflector A NASA Large wheel actuators definition study --- spacecraft submillimeter-infrared orbiting observatory structures - A case study p 50 A87-I9342 Erosion studies on Solar Max samples control p9 N87 17571 p 50 A87-I9343 [TELDIX-I 5-020-880I p 33 N87-I1834 SPACECRAFTANTENNAS Holographic non-destructive testing for composite NASAIDOD ControllStructures Interaction Technology, Protective coating for the KU-bandreflector in Space --- materials used in aerospace p 51 A87-19805 1986 Shuttle radar antenna p 49 A87 13098 Effects of thermal cycling on the mechanical and [ NASA-CP-2447-PT-I] p 73 N87-16014 Nonlinear attitude control of elastic spacecraft antenna physical properties of a space qualified epoxy adhesive Spacecraft Dynamics and Control Program at AFRPL system p 25 A87-13433 p 19 A87-20082 p 34 N87-16017 A-20 SUBJECT INDEX SPACECRAFT POWER SUPPLIES

Flight Dynamics Laboratory overview A basic study for divided modal survey of future large SPACECRAFT GUIDANCE p7 N87-16018 spacecraft p 27 A87-18241 Navigation. guidance, rendez-vous and docking - Active Control Evaluation for Spacecraft (ACES) The potential impact of new power system technology Activities carried out for Columbus by the flight operations p 34 N87-16019 on the design of a manned Space Station organization The 15 meter hoop-columnantenna dynamics: Test and p 44 A87-18342 [IAF PAPER 86-09] p 65 A87-15808 analysis p 35 N87-16025 The international Space Station takes shape Rendezvous and docking (RVD) guidance simulation Application of physical parameter identification to finite p 4 A87-24123 program, rider 2 Space Tech '86; Proceedings of the International element models p 35 N87-16026 [MATRA-EPT/DT/vT068/012] p 72 N87-14359 Conference. Geneva, Switzerland, May 14-16. 1986 Sensor technology for advanced space missions SPACECRAFTINSTRUMENTS p 68 A8725751 An estimate of the outgassing of space payloads and p 73 N87-16027 Space Station - Designing the future COFS 1: Beam dynamics and control technology its gaseous influence on the environment p 4 A8725752 p 48 A87-11355 ovetview p 35 N87-16028 Front end logistics influence on space system hardware Thermal control systems for spacecraft COFS 1 research overview p8 N87-16029 design instrumentation p 19 A87-31213 COFS 1 Guest Investigator Program [AIAA PAPER 87-06581 p5 A8727605 p8 N67-16034 Spacecraft Structural model improvement by modal test The 20th Aerospace Mechanics Symposium [ NASA-CP-2423-REVl p 73 N87-16321 COFS 2: 3-0 dynamics and controls technology results p 20 A87-31225 p 35 N87-16035 Spacecraft load, design and test philosophies SPACECRAFT LUBRICATION COFS 3: Multibody dynamics and control technology p6 N87-10922 Tribological properties of polymer films and solid bodies p 36 N87-16036 Engineering and software interfacing for thermal, in a vacuum environment Conceptual design of pointing control systems for space structural and attitude control related with spacecraft [ NASA-TM-889661 p 57 N87-17906 station gimballed payloads p 36 N87-16037 p 21 N87-10928 SPACECRAFT MAINTENANCE Computer-aided design and distributed system IDEAS A multidisciplinary computer-aided conceptual Space constructible radiator on-orbit assembly technology development for large space structures design system for spacecraft p 13 N87-11761 p 58 A87-11359 p 14 N87-16042 Dual structural-control optimization of large space Utilization, testing and maintenance of multimission Passive damping augmentation for flexible structures structures p 33 N87-11766 hardware p 70 A8729466 p 36 N87-16044 Design, construction and utilization of a space station SPACECRAFTMANEUVERS Multidisciplinary analysis of actively controlled large assembled from 5-meter erectable struts Slew maneuver control of the Spacecraft Control flexible spacecraft p 37 N87-16045 [ NASA-TM-890431 p 6 N87-11827 Laboratory Experiment (SCOLE) p 24 A87-13393 Description of the Spacecraft Control Laboratory NASA/DOD ControllStructuresInteraction Technology, Automatic decoupling of flexible spacecraft slewing Experiment (SCOLE) facility 1986 maneuvers p 24 A87-13431 [NASA-TM-69057] p8 N87-16848 [ NASA-CP-2447-PT-I ] p 73 N87-I6014 Large-angle slewing of flexible spacecraft Dynamics and Control Analysis Package (DCAP): An Advanced composites for large Navy spacecraft [AAS PAPER 85-6741 p 27 A87-18490 automated analysis and design tool for structural control p 56 N87-16015 Frequency-shapedlarge-angle maneuvers of space slructures p 39 N87-16947 Active Control Evaluation for Spacecraft (ACES) [AIAA PAPER 87-01741 p 28 A87-22462 Engineering and software interfacing for thermal, p 34 N87-16019 Optimal spacecraft rotational maneuvers --- Book structural and dynamic control related with spacecraft Analysis and simulation of the MAST (COFS-I flight p 68 A8724625 activities p 22 N67-16948 hardware) p37 N87-16046 Identification and control of structures in space Proceedingsof the 3rd Annual SCOLE Workshop [ NASA-CR-179811] p 31 N87-10172 Controlling and monitoring the space-slation plasma [ NASA-TM-890751 p 75 N87-17821 SPACECRAFT MODELS interaction:A baseline for perlorming plasma experiments Issues in modeling and controlling the SCOLE 1986 LECEC stability and transient modeling of a large and using advanced technology p 76 N87-20079 configuration p 39 N87-I7822 spacecraft power system p66 A87-18114 Optimal torque control for SCOLE slewing maneuvers SPACECRAFT DOCKING Truncation error estimation of a spacecraft model with p 40 N87-17823 Satellite motion analysis via laser reflector pattern a flexible appendage p 16 A87-I8321 Mathematical modeling of SCOLE configuration with processing for rendez-vous and docking Spacecraft structural model improvement by modal test line-of-sight error as the output p 40 N87-17824 [IAF PAPER 86-06] p 65 A87-I5805 results p 20 A87-31225 Slew maneuver dynamics of the Spacecraft Control Rendezvous and docking verification and in-orbit Demonstration of modal synthesis on an experimental Laboratory experiment p 40 N87-17825 demonstration structure and its application to large spacecraft Modeling and identification of SCOLE [IAF PAPER 86-07] p 65 A87-15806 p 20 N87-I0912 p 23 N87-17826 Navigation, guidance, rendez-vous and docking - Experience on the Olympus modal survey test Finite element model of SCOLE laboratory Activities carried out for Columbus by the ilight operations p6 N87-10919 configuration p 14 N87-17828 organization Large flexible space structures: Some simple models Model reference control of distributed parameter [IAF PAPER 86-09] p 65 A87-15808 [TW-2691 p 32 N87-10957 systems: Application to the SCOLE problem Advanced opto-electronica sensors for autonomous Component testing for dynamic model verification p 40 N87-17829 Rendezvous-/Docking and proximity operations in space p 32 N87-11765 Proof-massactuator placement strategiesfor regulation p 44 A87-19707 Dual structural-control optimization of large space of flexure during the SCOLE slew p 40 N87-I7830 Rendezvous and docking (RVD) guidance simulation structures p 33 N87-11766 Active damping of vibrations in SCOLE excited by program, rider 2 Active Control Evaluation for Spacecraft (ACES) slewing p 40 N87-17831 [MATRA-€PT/DT/~O68/012] p 72 N87-14359 p34 N87-16019 Estimationand control of distributed models for certain Control of SCOLE p 40 N87-17832 Analysis of rendezvous and docking in geostationary Regulation of the SCOLE configuration elastic systems arising in large space structures Earth orbit. Rider to comparison of future communications p 41 N87-17833 [ AD-A 17501 9 ] p 38 N87-16872 space segment concepts Evaluation of on-line pulse control for vibration Engineering and software interfacing for thermal, [OM51-C/PL/FL/OO99.82] p72 N87-14364 suppression in flexible spacecraft p 41 N87-17834 slruclural and dynamic control related with Spacecraft Active stability augmentation of large space structures: Rendezvous and docking and space robotics proximity activities p 22 N87-16948 A stochastic control problem p 41 N87-17835 operations. Part 5: Executive summary The control theory of flexible and articulated [ NLR-TR-85099-Ul p 62 N87-19441 The SCOLE design challenge p 10 N67-17836 spacecraft Description of the Spacecraft Control Laboratory SPACECRAFT DOCKING MODULES [AD-A174680: p 42 N87-19434 Experiment (SCOLE) facility p 10 N87-17837 Docking mechanisms technology study SPACECRAFT MODULES Ground facility for large space structures dynamics and [ ESA-CR(P)-22731 p 71 N87-11833 Extending the Space Station infrastructure control verification SPACECRAFT ELECTRONIC EQUIPMENT p5 A8728953 [ NASA-TM-865581 p 41 N87-18600 Design of a superconductingalternator for space-based SPACECRAFT MOTION SPACECRAFT DESIGN power generation p 43 A87-18144 Satellite motion analysis via laser reflector pattern Space vehicle design --- French book SPACECRAFT ENVIRONMENTS processing for rendez-vous and docking p 11 A87-10092 An estimate of the outgassing of space payloads and [ IAF PAPER 88-06] p 65 A87-15805 Vibration data reduction for design. analysis and testing its gaseous influence on the environment Instability of rotating blades in space of spacecraft p23 A87-10901 p 48 A87-11355 [ IAF PAPER 86-2421 p 65 A87-15959 Development of Space Station strut design Erosion studies on Solar Max samples Optimal spacecraft rotational maneuvers --- Book p 15 A87-11842 p 50 A87-I9343 p68 A8724625 Development of a 'Hingeless Mast' and its The control theory of flexible and articulated Combined orbit/altitude determination for low-altitude applications spacecraft satellites [IAF PAPER 86.2051 p 15 A87-15933 [AD-AI748801 p 42 N87-19434 [ UTIAS-3201 p 74 N87-17810 Modeling and simulation of large scale space systems SPACECRAFT POWER SUPPLIES The interaction of small and large spacecraft with their Solar array mechanisms for Indian satellites. APPLE, Strategic planning implications environment p 10 N87-20064 [ IAF PAPER 66-4531 p2 A87-16105 IRS and INSAT-IITS Reduced modelingand analysis of large repetitive space A unified approach to computer analysis and modeling [IAF PAPER 86-1421 p 11 A87-15893 structures via continuumldiscrete concepts of spacecraft environmental interactions Spacecraft 2000 - The challenge of the future p 14 N87-20066 [IAF PAPER ST-86-06] p 65 A87-16141 p 3 A87-18064 Design and manufacturing aspects of tubular carbon High voltage system: Plasma interaction summary ARABSAT solar generator concept and in orbit fibre composite/litanium bonded joints p 48 N87-20069 performance p 43 A87-18075 p 50 A67-16163 SPACECRAFT EQUIPMENT Multimegawatt power distribution considerations Spacecraft 2000 - The challenge of the future A robotic system for dexterous tasks p 43 A87-18113 p3 A87-18064 p 60 A8725757 1986 LECEC stability and transient modeling of a large International Symposium on Space Technology and Design and control of modular. kinematically-redundant spacecraft power system p 66 A87-18114 Science, 14th, Tokyo, Japan, May 27-June 1. 1984. manipulators Design of a superconductingalternator for space-based Proceedings p 66 A87-18201 [AIAA PAPER 87-16941 p 61 A87-31122 power generation p 43 A87-18144

A-2 1 SPACECRAFT PROPULSION SUBJECT INDEX

Space Station challenge - On-orbit assembly of a 75-kW Dynamic analysis of SatelliteS with deployable hinged SPACETENNAS power system p59 A87-I8148 appendages A new structure toward high precision large antenna High voltage solar array plasma protection techniques [ AIAA PAPER 87-0020 I p 27 A87-22364 llAF PAPER 86-201 1 p 15 A87-I5929 --- for use on spacecraft p 45 A87-19878 Efficient optimization of space trusses Finite-element thermal-structural analyses of a Space nuclear power systems 1985: Proceedings of the p 19 A87-22814 cable-stiffened orbiting antenna p 19 A87-25687 Second Symposium. Albuquerque, NM. Jan. 14-16, 1985. Flexibility control of solar battery arrays. 111 - vibration Microcomputer design and analysis 01 the cable catenaly Volumes 3 8 4 p 67 A87-21801 and attitude control with consideration of the dynamics large space antenna system p 13 N87-11762 Microwave power transmission for use in space of a reaction wheel as an actuator p 45 A87-22969 A modified loop transfer recovery approach for robust p 46 A87-27180 Wave-absorbing controllers for a flexible beam control of flexible structures p 39 N87-17029 Protection of spacecraft from meteoroids and orbital p 28 A87-23986 SPRINGS (ELASTIC) debris Identification, applications. and dynamic analysis of Locking hinge [DE86-0099961 p 70 N87-10947 nonlinear spacecraft components p 30 A87-28558 [NASA-CASE-MSC-21056-1] p 62 N87-18595 HPSA. High Power Solar Array study --- Columbus space Computation of total response mode shapes using tuned SPUTTERING station frequency response functions p 30 A87-28569 The 20th Aerospace Mechanics Symposium [ BAE-TP-8071I p 47 N87-I 1352 Substructure coupling of analytical and test models for [ NASA-CP-2423-REVl p 73 N87-16321 High power rigid solar array --- Columbus space an experimental structure p 19 A87-28577 STABILITY AUGMENTATION station Transient modal tuning --- for space structures Active stability augmentation of large space structures: [SNIAS-917A-CAICG I p 47 N87-13864 p 30 A87-28578 A stochastic control problem p 41 N87-I7835 The concentration principle applied to spaceborne Solar The dynamical qualification of present and future STARTRACKERS arrays Application to the coorbiting platform mission: spacecraft structures p 30 A87-29368 Parametric study of stable optical references for large Studies synthesis Effects of thermal cycling on graphie-fiber-reinforced flexible structures in space p 64 A87-11013 [SNIAS-975-CAlCG] p 75 N87-19814 6061 aluminum STATE ESTIMATION SPACECRAFT PROPULSION [ NASA-TP-26121 p 52 N87-10184 Flexibility control of solar arrays based on state Advanced propulsion status in Western Europe Proceedings of an International Conference on estimation by Kalman filtering p 26 A87-15450 [IAF PAPER 86-1721 p 63 A87-15913 Spacecraft Structures STATIC DEFORMATION SPACECRAFT RADIATORS [ ESA-SP-2381 p 70 N87-10886 Static deflection control of flexible beams by Space constructible radiator on-orbit assembly Design and verification activities and requirements for piezo-electric actuators p 58 A87-11359 spacecraft structures p 20 N87-I0890 [ NASA-CR-1799471 p 34 N87-13788 Feasibility study of a low-temperature expandable On optimal passive and active control of precision STATIONKEEPING megawatt pulse power radiator p 66 A87-17841 spacecraft structures p 31 N87-10891 Formationkeeping of spacecraft via differential drag SPACECRAFTRECOVERY Damping representation related to spacecraft structural 1 NASA-CR-171939 p 71 N87-13466 Satellite servicing price estimation instruction booklet design p 31 N87-10898 STATISTICAL ANALYSIS [NASA-CR-l719671 p 75 N87-18583 Transient external loads or interface forces Component testing for dynamic model verification SPACECRAFT RELIABILITY reconstructed from structural response measurements --- p 32 N87-11765 Aerospace Testing Seminar, 9th. Los Angeles. CA. Oct. modular spacecraft p 20 N87-I0910 STIFFNESS MATRIX 15-17, 1985. Proceedings p 69 A87-29441 Structural system identification using single and An explicit expression for the tangent-stiffness of a SPACECRAFT SHIELDING multiaxial vibration test data --- spacecraft structures finitely deformed 3-D beam and its use in the analysis of Meteoroid and orbital debris protection concepts p 20 N87-I0911 space frames p 19 A8720247 [IAF PAPER 86-4191 p 65 A87-16081 A review of time domain modal lest methods and Modeling and identification of SCOLE Degradation of spacecraft thermal shield materials by applications --- space structures p 32 N87-I0915 p 23 N87-17826 irradiation of energetic particles p 18 A87-18273 Spacecraft load, design and test philosophies STOCHASTIC PROCESSES Energetic oxygen atom material degradation studies p 6 N87-I0922 1986 American Control Conference. Sth, Seattle. WA. [AIM PAPER 87-01051 p 51 A87-24919 Tele-X antenna module structure qualification program June 16-20, 1986. Proceedings. Volumes 1. 2. 8 3 A high flux source of energetic oxygen atoms for material p 21 N87-I0924 p 64 A87-13301 degradation studies p 52 A87-27936 Loads analysis for the Galileo spacecraft Stochastic modeling and control system designs of the Protection of spacecraft from meteoroids and orbital p 21 N87-10926 NASAIMSFC Ground Facility for large space structures: debris Development of a lightened structure for the GSR3 solar The maximum enlropyloptimal projection approach [DE86-009996] p 70 N87-I0947 generator p 17 N87-10927 p 38 N87-16766 SPACECRAFT STABILITY Composites design handbook for space structure Active stability augmentation of large space structures: Stabilization of aclass of hybrid systemsarising in flexible applications. Executive summary A stochastic control problem p 41 N87-17835 spacecraft p 24 A87-12139 [ ESA-CR(P)-2196] p 54 N87-10982 STOWAGE (ONBOARD EQUIPMENT) Pointing. control, and stabilization of solar dynamic Development of the Lens Antenna Deployment Locking hinge system on a Space Station p 25 A87-13437 Demonstration (LADD) shuttle-attached flight experiment [NASA-CASE-MSC-21056-11 p 62 N87-18595 Dynamics of the orbiter based flexible members p7 N87-16022 STRAIN ENERGY METHODS p 27 A87-I8324 COFS 1 Guest Investigator Program Shear deformation plate continua of large double layered Dynamic analysis of satellites with deployable hinged p 8 N87-16034 space structures p 16 A87-28882 appendages COFS 2: 3-D dynamics and controls technology STRATEGY [AIAA PAPER 87-00201 p 27 A87-22364 p 35 N87-I6035 Modeling and simulation of large scale space systems Ground facility for Large Space Structures dynamics and Identification of large space structures on orbit Strategic planning implications control verification p 31 A87-31095 [AD-A173756] p 14 N87-16058 [IAF PAPER 86.4531 p2 A87-16105 Modern control of large flexible spacecraft, ESA ASTP Extendable retractable telescopic mast for deployable STRESS ANALYSIS study structures p8 N87-16323 Stress and deformation analysis of thermally loaded light [BL-6206-ISSUE-2] p 70 N87-10956 Damping 1986 procedures, volume 2 weight composite structures New materials for spacecraft stability and damping: A [AD-A173950 I p 73 N87-16366 [IAF PAPER 86.2121 p 18 A87-15939 feasibility study Engineering and software interfacing for thermal, Behavioural analysis of adhesive-bonded structural [AD-A169826] p 54 N87-12601 structural and dynamic control related with spacecraft joints in space vehicles p 16 A87-20148 Passive damping augmentation for flexible structures activities p 22 N87-I6948 Buckling and nonlinear response of imperfect p 36 N87-16044 The welding of aluminum alloys: A new technology in three-legged truss columns p 19 A87-30296 The control theory of flexible and articulated space application p 56 N87-17056 Performance characteristics of composite materials spacecraft Experimental study of active vibration control p 53 N87-10935 [AD-AI74880 I p 42 N87-19434 [AD-AI731441 p 41 N87-17845 Effects of curing stresses on composite structures SPACECRAFTSTRUCTURES Thermoviscoelasticcharacterization and analysis of fiber p 56 N87-16930 Development of Space Station strut design Composite space structures STRESS CONCENTRATION p 15 A87-11842 [AD-A: 750241 p 58 N87-19457 The effect of the non-uniform stress distribution in the Thermoplastic-basedcomposites with low CTE for space SPACECRAFT SURVIVABILITY blankets of single and twin boom solar array panels upon structures and circuit board applications Collisional probability in space and the debris their modal characteristics p 32 N87-10904 p 49 A87-13097 environment in future p 66 A87-18247 STRESS INTENSITY FACTORS Development of a 'Hingeless Mast' and its SPACECRAFTTEMPERATURE The K1-K2 interaction for matrix splitting in unidirectional applications Space constructible radiator on-orbit assembly laminates of carbon fiber reinforced epoxy [IAF PAPER 86-2051 p 15 A87-15933 p 58 A87-11359 p 52 N87-10932 Stress and deformation analysis of thermally loaded light Controlling waste heat in military spacecraft weight composite structures STRUCTURAL ANALYSIS p 18 A87-15197 Reduced modeling and analysis of large repetitive space [IAF PAPER 86-2121 P 18 A87-15939 Feasibility study of a low-temperature expandable Spacecraft glows from surface-catalyzedreactions structures via continuumldiscrete concepts megawatt pulse power radiator p 66 A87-I7841 [ IAF PAPER ST-86-08] p 65 A87-16141 P 43 A87-17368 The influence of interstitial media on spacecraft thermal Feasibility study of a low-temperature expandable Efficient optimization of space trusses control p 18 A87-I8266 p 19 A87-22814 megawatt pulse power radiator p 66 A87-17841 SPACECRAFT TRACKING Finite-element thermal-structural analyses of a Simplex Mast - An extendible mast for space Combined orbitlanltude determination for low-altitude applications p3 A87-18242 satellites cable-stiffened orbiting antenna p 19 A87-25687 Parameter identification in distributed spacecraft [UTIAS-3201 p 74 N87-17810 Substructure coupling of analytical and lest models for structures SPACECRAFT TRAJECTORIES an experimental structure p 19 A87-28577 [AAS PAPER 85.6701 P 18 A87-18487 Trajectory shaping rendezvous guidance Application of graph theory to the nonlinear analysis PultruSiOn process development for long space boom p 64 A87-13434 of large space structures p 12 N87-10418 models P 60 A87-20083 SPACELAB Proceedings of an International Conference on Behavioural analysis of adhesive-bonded structural The welding of aluminum alloys: A new technology in Spacecraft Structures joints in space vehicles p 16 A87-20148 space application p 56 N87-I7056 [ ESA-SP-238I p 70 N87-10886

A-22 SUBJECT INDEX SYSTEM IDENTIFICATION

Equivalent continuum analyses of large space trusses STRUCTURAL RELIABILITY SUBMILLIMETER WAVES p 12 N87-10894 Behavioural analysis of adhesive-bonded structural The large deployable reflector A NASA Debonding analysis of thermally stressed joints in space vehicles p 16 A87-20148 submillimeter-infraredorbiting observatory fiber-reinforced composite materials p 52 N87-10933 The dynamical qualification of present and future p 9 N87-17571 Performance characteristics of composite materials spacecraft structures p 30 A87-29368 SUNLIGHT p 53 N87-10935 STRUCTURAL STABILITY Boom potential of a rotating satellite in sunlight Qualitative results for distributed systems with discrete p 68 A87-24198 IDEAS A multidisciplinary computer-aided conceptual and stiffness with application to control design system for spacecraft p 13 N87-11761 Sun shield [AD-A168622] p 33 N87-11829 Parametric investigation of factors influencing the [NASA-CASE-MSC-20162-1I p 74 N87-17036 Protective coatings for composite tubes in space SUPERCONDUCTIVITY mechanical behavior of large space structures applications [AD-A1728801 p 38 N87-16056 Design of a superconductingalternator for space-based [NASA-CR-t78116] p 57 N87-18669 power generation p 43 A87-18144 Analysis of high precisioncomposite sandwich antennas STRUCTURAL STRAIN SUPERHIGH FREQUENCIES --- spacecraft antennas p 56 N87-16929 Metallurgical characterization of the interfaces and the Protective coating for the KU-band reflector in Space Structural analysis, manufacturing and development damping mechanisms in metal matrix composites --- Shuttle radar antenna p 49 A87-13098 status of large polarizationsensitive dual-gridded reflectors [AD-A173470] p 57 N87-17863 --- satellite antenna p 22 N87-16937 STRUCTURAL VIBRATION Development of 30120 GHz satellite antenna structures p9 N87-16933 Proof-massactuator placement strategies for regulation Vibration suppression of planar truss structures utilizing of flexure during the SCOLE slew p 40 N87-17830 uniform damping control p 25 A87-13458 Features and technologies of ERS-1 (ESA) and X-SAR Active damping of vibrations in SCOLE excited by A procedure for calculatingthe damping in multi-element an1 en n a s p9 N87-17152 slewing p 40 N87-17831 space structures SUPPORT SYSTEMS Space logistics support to military space systems STRUCTURAL DESIGN [IAF PAPER 86-2031 p 26 A87-15931 [AIAA PAPER 87-06941 p 69 A87-27621 Improving the active vibrational control of large space A basic study for divided modal sulvey of future large structures through structural modifications spacecraft p 27 A87-18241 SUPPORTS [ IAF PAPER 86.2041 p 26 A87-15932 Control of solar battery arrays of spacecraft with Extendable retractable telescopic mast for deployable consideration of the structural flexibility structures p8 N87-16323 Optimization of a truss member p 44 A87-18319 Dielectric support structures for spacecraft antenna [ IAF PAPER ST-86-17 1 p 15 A87-16145 Dynamics of the orbiter based flexible members feeds p 17 N87-16931 Design and manufacturing aspects of tubular carbon p 27 A87-18324 SURFACE DISTORTION fibre compositeItitanium bonded joints Pultrusion process development for long space boom Simple approach for evaluating mechanical reflector p 50 A87-16163 models p 60 A87-20083 antenna distortions --- satellite antennas Alternative approximation concepts for space frame Optimal structural design with control gain norm p 39 N87-16942 synthesis p 19 A87-18940 constraint SURFACE FINISHING Optimization of a ~NSS member [AIM PAPER 87-00191 p It A87-22363 Adhesive bonding of aerospace materials - Surface [AIAA PAPER 87-00731 p 16 A87-22395 Vibration control of nonlinear flexible structures characterization of metallic adherends Modal space design for active vibration control of large [AIAA PAPER 87-00741 p 28 A87-22396 p 51 A87-20149 flexible structures p 30 A87-28537 Flexibility control of solar battery arrays. Ill - vibration SURFACE GEOMETRY Modal analysis technique used in Germany for and attitude control with consideration of the dynamics Two-dimensionalarticulated systems developable on a aerospace structures p 30 A87-28544 of a reaction wheel as an actuator p 45 A87-22969 single or double curvature surface p 58 A87-12285 An analytical and experimental study of a control On the dynamics of flexible beams under large overall SURFACE PROPERTIES system's sensitivity to structural modifications --- for motions . The plane case. I, II Adhesive bonding of aerospace materials - Surface vibration of large space structures p 30 A87-30294 [ASME PAPER 86-WA/APM-41] p 28 A87-23212 characterization of metallic adherends Proceedings of an International Conference on International Modal Analysis Conference, 4th, Los p 51 A87-20149 Spacecraft Structures Angeles. CA. Feb. 3-6, 1986. Proceedings. Volumes 1 8 Comparison of methods for the calculation of thermal [ ESA-SP-2381 p 70 N87-10888 2 p 69 A87-28526 contact resistance of the first Brazilian satellite [ INPE-3864-TDL/217] p 21 N87-12596 Design and verification activities and requirements for Comparison of multiple input random and sine excitation SURFACE REACTIONS spacecraft structures p 20 N87-10890 methods for aerospace structures --- spacecraft vibration A consideration of atomic oxygen interactions with the Damping representation related to spacecraft structural models p 12 A87-28552 design p 31 N87-10898 Space Station p 43 A87-17836 Computationof total response mode shapes using tuned Spacecraft load, design and test philosophies Energetic oxygen atom material degradation studies frequency response functions p 30 A87-28569 p6 N87-10922 [AIAA PAPER 87-01051 p 51 A87-24919 Development of deployable truss concept for space An analytical and experimental study of a control SURVIVAL station p 16 N87-10923 system's sensitivity to structural modifications --- for The survivability of large space-borne reflectors under Composites design handbook for space structure vibration of large space structures p 30 A87-30294 atomic oxygen and micrometeoroid impact applications. Executive summary On a simple vibration control design for large space [AlAA PAPER 87-03411 p 52 A87-31300 1 ESA-CR(P)-PI961 p 54 N87-10982 structure models with uncertain parameters The sulvwability of large space-borne reflectors under Recent Experiences in Multidisciplinary Analysis and p 32 N87-10903 atomic oxygen and micrometeoroid impact Optimization, part 1 Prediction and correlation of structural response in [ NASA-TM-889141 p 72 N87-14423 [ NASA-CP-2327-PT-t ] p 71 N87-11717 acoustic chambers --- large space structures SYNCHRONOUS PLATFORMS A study of large space structures p 20 N87-10907 Analysis of rendezvous and docking in geostationary [ LR468691 p 21 N87-11832 Structural system identification using single and Earth orbit. Rider to comparison of future communications Dielectric support structures for spacecraft antenna multiaxial vibration test data .-.spacecraft structures space segment concepts feeds p 17 N87-I6931 p 20 N87-10911 [DM5l-CIPL/FL/OO99.82] p72 N87-14364 Development of 30120 GHz satellite antenna Wave propagation and dynamics of lattice structures The concentration pnnciple applied to spaceborne solar structures p 9 N87-16933 [AD-At 703161 p 33 N87-13479 arrays. Application lo the coorbiting platiorm mission: Advanced EVA system design requirements study. Studies synthesis The 15 meter hoop-columnantenna dynamics: Test and [ SNIAS-975-CAICG] p 75 N87-19814 executive summary analysis p 35 N87-16025 [ NASA-CR-1719601 p 75 N87-17838 SYNCHRONOUS SATELLITES Description of the Mast Flight System STRUCTURAL DESIGN CRITERIA In-orbit performance of Hughes HS 376 solar arrays p 8 N87-I6030 Optimal structural design with control gain norm p 44 A87-19872 constraint MAST flight system dynamic performance Proceedings of an International Conference on Space [AlAA PAPER 87-00191 p 11 A87-22363 p 35 N87-16032 Dynamics for Geostationary Satellites A study of large space structures COFS 2: 3-D dynamics and controls technology [ ISBN-2-85428-149-71 p 70 N87-10113 [LR46869] p 21 N87-11832 p 35 N87-16035 SYNTHETIC APERTURERADAR Unified control/structure design and modeling Passive damping augmentation for flexible structures Development status of the ERS-1 SAR antenna research p 36 N87-16044 p 9 N87-16939 [ NASA-CR-1799481 p 33 N87-13478 Robust multivariable controller design for flexible Features and technologies of ERS-1 (ESA) and X-SAR Evaluation of Pactruss design characteristics critical to spacecraft p 37 N87-16048 antennas p 9 N87-17152 space station primary structure Wave dispersion mechanisms in large space SYNTHETIC APERTURES Application of Spaceborne Distributed [NASA-CR-178171] p 17 N87-16870 structures Advanced EVA system design requirements study: [ AD-A1739671 p 38 N87-16059 AperlureICoherent Array Processing (SDAICAP) EVASIspace station system interface requirements technology to active and passive microwave remote Discrete mechanism damping effects in the solar array sensing p 47 N87-17277 [NASA-CR-171981I p 62 N87-20351 flight experiment p 38 N87-16341 STRUCTURAL ENGINEERING SYNTHETIC ARRAYS Experimental study of active vibration control Investigation of interactive structural and controller Application of Spaceborne Distributed [AD-A173144] p 41 N87-17845 synthesis for large spacecraft Aperture/Coherent Array Processing (SDAICAP) [AD-A172811I p 17 N87-16055 Optimum vibration control of flexible beams by technology to active and passive microwave remote STRUCTURALMEMBERS piezo-electric actuators sensing p 47 N87-17277 Assembly of thermoelastic continuous elements [ NASA-CR-1802091 p 42 N87-18880 SYSTEM EFFECTIVENESS [ IAF PAPER 86.2071 p 59 A87-15935 STRUCTURAL WEIGHT In-orbit performance of Hughes HS 376 solar arrays New materials for spacecraft stability and damping: A Stress and deformationanalysis of thermally loaded light p 44 A87-19872 feasibility study weight composite Structures SYSTEM IDENTIFICATION [ AD-At 698261 p 54 N87-12601 [IAF PAPER 86-2121 p 18 A87-15939 On-orbit systems identification of flexible spacecraft Investigation of interactive structural and controller STRUTS p 26 A87-16187 synthesis for large spacecraft Development of Space Station strut design Transient modal tuning --- for space structures [AD-A172811] p 17 N87-16055 p 15 A87-11842 D 30 A87-28578

A-23 SYSTEMS ANALYSIS SUBJECT INDEX

Spacecraft structural model improvement by modal test Analysis of normal and transparent Silver Teflon THERMAL INSULATION results p 20 A87-31225 p 55 N87-14391 SSM atomic oxygen reactions on Kapton and silverized Structural system identification using single and Degradation studies of SMRM Teflon Teflon p 55 N87-14388 multiaxial vibration test data --- spacecraft structures p 56 N67-14392 THERMAL PROTECTION p 20 N87-10911 TELEOPERATORS The influence of interstitial media on spacecraft thermal MAST flight system operations p 8 N87-16033 An introduction to the Concept of robot factors and its control p 18 A87-18266 COFS 3: Multibody dynamics and control technology application to Space Station automation Thermaianalysis of radiometer containers for the 122m p 36 N87-16036 p 58 A87-13712 hoop column antenna concept System identification for modeling for control of flexible Remotely manipulated and autonomous robotic welding [ NASA-TM-89026] p 21 N87-11966 structures p 36 N87-16040 fabrication in space p 59 A87-13714 Results of examination of materials from the solar Computer-aided design and distributed system maximum recovery mission p 54 N87-14383 A flexible telerobotic system for space operations technology development for large space structures THERMAL STABILITY p 60 A87-23229 p 14 N87-16042 Deslgn of a low distortion shared aperture reflector --- SYSTEMS ANALYSIS Telerobotic assembly of space station truss structure satellite antenna p 14 N87-16934 The system approach for applying artificial intelligence [ NASA-CR-1802391 p 62 N87-I8984 THERMAL STRESSES to Space Station automation p 64 A87-13708 TEMPERATURE CONTROL Stress and deformationanalysis of thermally loaded light SYSTEMS ENGINEERING Controlling waste heat in military spacecraft weight composite structures Space Station - The use of expert systems for p 18 A87-15197 [ IAF PAPER 86.2121 p 18 A87-15939 planning p 4 A87-25759 The influence of interstitial media on spacecraft thermal Debonding analysis of thermally stressed Architecture and design process for complex systems: control p 18 A87-18266 fiber-reinforced composite materials p 52 N87-10933 Space Station - A case study p 12 A87-25978 Thermal control systems for spacecraft Parametric investigation of factors influencing the Robot system for dexterous tasks (for space instrumentation p 19 A87-31213 mechanical behavior of large space structures applications) Engineering and software interfacing for thermal. [AD-A1728801 p 38 N87-16056 [ ETN-86-985621 p 61 N87-15472 structural and dynamic control related with spacecraft THERMODYNAMIC EOUlLlBRlUM NASAIDOD ControllStructuresInteraction Technology, activities p 22 N87-16948 Nonlinear effects in thermal conduction problems of 1986 Sensors for a system to control the liquid flow into an large space structures [ NASA-CP-2447-PT-1] p 73 N87-16014 evaporation cold plate of a two-phase heal transport [IAF PAPER 86.2081 p 18 A87-15936 Passive damping augmentation for flexible structures system for large spacecraft THERMODYNAMIC PROPERTIES p 36 N87-16044 [ NLR-TR-86001-U] p 23 N87-19442 Comparison of methods for the calculation of thermal SYSTEMS INTEGRATION TEMPERATUREEFFECTS contact resistance of the first Brazilian satellite MAST flight system operations p 8 N87-16033 Performance characteristics of composite materials [ INPE-3864-TDL12171 p21 N87-12596 Preliminary findings for integrated modeling and p 53 N87-10935 Thermomechanical characteristics of dichroic simulation of directed energy weapons TEST EQUIPMENT subreflectors _-- satellite antennas p 22 N87-16952 [DE86-0116361 p 10 N87-17846 Aerospace Testing Seminar, 9th. Los Angeles, CA. Oct. THERMODYNAMICS Advanced EVA system design requirements study: 15-17, 1985, Proceedings p 69 A87-29441 On the initiation of SPS development EVASlspace station system interface requirements Utilization. testing and maintenance of multimission p 1 A87-12086 [NASA-CR-171981] p 62 N87-20351 hardware p 70 A87-29466 A model for predicting thermomechanical response of SYSTEMS STABILITY TEST FACILITIES large space structures Stabilizationof a class of hybrid systemsarisingin flexible The electron irradiation test of thermal control material [AD-At 729661 p 22 N87-15264 spacecraft p 24 A87-12139 p 50 A87-18271 THERMOELASTICITY On the stability of multiple parameter time-varying Description of the Spacecraft Control Laboratory Assembly of thermoelastic continuous elements dynamic systems p 29 A87-27449 Experiment (SCOLE) facility [ IAF PAPER 86-2071 p 59 A87-15935 [NASA-TM-89057] p 8 N87-16848 THERMOPLASTIC RESINS TETHERED SATELLITES Thermoplastic-basedcomposites with low CTE for space T The dynamics and control of aspace platform connected Structures and circuit board applications to a tethered subsatellite p 25 A87-14074 p 49 A87-13097 TAYLOR SERIES System engineering study of electrodynamic tether as THERMOVISCOELASTICITY A Taylor-Galerkinfinite element algorithm for transient a spaceborne generator and radiator of electromagnetic Thermoviscoelasticcharacterization and analysis of fiber nonlinear thermal-structuralanalysis waves in the ULFIELF frequency band composite space structures [NASA-CR-177064] p 20 N87-10406 [NASA-CR-1801561 p 23 N87-16956 [AD-A175024] p 58 N87-19457 TECHNOLOGICAL FORECASTING TETHERLINES Large space observatories of the 21st century THIN WALLED SHELLS Large structures and tethers working group [AIAA PAPER 87.06361 p 4 A87-22751 A four node Marguerre element for non-linear shell p 75 N87-20057 TECHNOLOGY ASSESSMENT analysis p 30 A87-30545 THERMAL ANALYSIS Space missions for automation and robotics Analysis of long thin-walled tubes --- large space Finite-element thermal-structural analyses of a technologies (SMART) program p 58 A87-13707 structures p 20 N87-10895 cable-stiffened orbiting antenna p 19 A87-25687 Fundamentals and advances in the development of THREE DIMENSIONAL BODIES A Taylor-Galerkin finite element algorithm for transient remote welding fabrication systems p 49 A87-14312 An explicit expression for the tangent-stiffness of a nonlinear thermal-structuralanalysis Maintainabilitytechnology p 59 A87-15407 finitely deformed 3-D beam and its use in the analysis of [NASA-CR-l77064] p 20 N87-10406 The international Space Station lakes shape space frames p 19 A87-20247 Debonding analysis of thermally stressed p4 A87-24123 fiber-reinforced composite materials p 52 N87-10933 THRUSTVECTORCONTROL Digital networks and their evolution - Space and IDEAS A multidisciplinary computer-aided conceptual Efficiency eccentricity control using continuous, terrestrial systems; Proceedings of the Thirty-third design system for spacecraft p 13 N87-11761 vectored thrusting for satellites with large arealmass International Congress on Electronics and Twenty-sixth Thermal analysis of radiometer containers for the 122m ratios p63 N87-10151 International Meeting on Space, Rome, Italy. Mar 18-20. hoop column antenna concept TIME FUNCTIONS 1986 p68 A87-24701 [ NASA-TM-890261 p 21 N87-11966 A review of time domain modal test methods and Communicationsspacecraft p 5 A87-30891 The Extendable Refractable Mast (ERM) thermal applications --- space structures p 32 N87-10915 NASA's technology plans - Will technology be ready analysis: A heat radiation case study via the finite element TIME SERIES ANALYSIS when we are method p 22 N87-16949 Application of physical parameter identification to finite [AIM PAPER 87-16951 p 5 A87-31123 THERMAL CONDUCTIVITY element models p 35 N87-16026 Sensors for a system to control the liquid flow into an Nonlinear effects in thermal conduction problems of TIMOSHENKO BEAMS evaporation cold plate of a two-phase heal transport large space structures Optimization of equivalent periodic truss structures system for large spacecraft [IAF PAPER 86.2081 p 18 A87-15936 p 16 A87-31175 [NLR-TR-86001-U] p 23 N87-19442 THERMAL CONTROL COATINGS TITANIUM The concentration principle applied to spaceborne solar The electron irradiation test of thermal control material Design and manufactunng aspects of tubular carbon arrays. Application to the cwrbiting platform mission: p 50 A87-18271 fibre compositeltitanium bonded joints Studies synthesis THERMAL CYCLING TESTS p 50 A87-16163 [SNIAS-975-CA/CG] p 75 N87-19814 Effects of thermal cycling on the mechanical and TOPOLOGY TECHNOLOGY UTILIZATION physical properties of a space qualified epoxy adhesive Digital image processing: Binary images Space Station evolution - The aerospace technology p 19 A87-20082 p 57 N87-18015 impact Effects of thermal cycling on graphie-fiber-reinforced TOROUE 6061 aluminum [AAS PAPER 85-4561 p 1 A87-15380 Optimal torque control for SCOLE slewing maneuvers Technologies for affordable access to space [NASA-TP-2612] p 52 N87-10184 p 40 N87-17823 [IAF PAPER 86-4423 p2 A87-16096 THERMAL DEGRADATION TORSIONAL VIBRATION Utilization. testing and maintenance of multimission Degradation of spacecraft thermal shield materials by irradiatlon of energetic particles p 18 A87-18273 Flexibility control of solar battery arrays. II - Vibration hardware p 70 A8729466 and anitude control based on state estimationof differential Space technologies and materials: A look back and THERMAL EXPANSION Thermoplastic-basedcomposites with low CTE for space solar cell sensors p 45 A87-22968 future perspectives p 52 N87-10934 Structures and circuit board applications TRACKING (POSITION) TEFLON (TRADEMARK) p 49 A87-13097 Solar array flight dynamic experiment Studies of erosion of solar max samples of Kapton and New materials for spacecraft stability and damping: A [ NASA-TP-25981 p7 N87-12581 Teflon p 55 N87-14384 feasibility study Space station rotary loint mechanisms SSM atomic oxygen reactionson Kapton and silverized [AD-A169826] p 54 N87-12601 p 73 N87-16338 Teflon p 55 N87-14388 Composite space antenna Structures: Properties and TRAJECTORY OPTIMIZATION Preliminary results of SMM exposed aluminized Kapton environmental effects Path-constrainedrendezvous - Necessary and sufficient and silvered Teflon p 55 N87-14389 [ NASA-TM-88859l p39 N87-16880 conditions p66 A87-17834 A-24 SUBJECT INDEX VISCOELASTIC DAMPING

TRANSFER FUNCTIONS Protective coatings for composite tubes in space Modal space design for active vibration control of large Numerical and experimental evaluation of poles and applications flexible structures p 30 A87-28537 system zeros for large flexible space structures [NASA-CR-178116] p 57 N87-18669 Modal analysis technique used in Germany for p 27 A87-18322 Telerobotic assembly of space station truss structure aerospace structures p 30 A87-28544 TRANSIENT HEATING [NASA-CR-180239] p 62 N87-18984 An analytical and experimental study of a control A Taylor-Galerkin finite element algorithm for transient TWO DIMENSIONAL BODIES system's sensitivity to structural modifications --- for nonlinear thermal-structural analysis Dynamic testing of a two-dimensional box truss beam vibration of large space structures p 30 A87-30294 [ NASA-CR-1770641 p 20 N87-10406 [ NASA-CR-40391 p 34 N87-15262 Identificationand control of structures in space TRANSIENT LOADS TWO PHASE FLOW [NASA-CR-179811] p 31 N87-10172 Transient external loads or interface forces Thermal control systems for spacecraft Qualitative results for distributed systems with discrete reconstructed from structural response measurements --- instrumentation p 19 A87-31213 and stiffness with application to control modular spacecraft p 20 N87-10910 Sensors for a system to control the liquid flow into an [AD-A168622] p 33 N87-11829 TRANSIENT RESPONSE evaporation cold plate of a two-phase heat transport NASAIDOD ControlIStructures Interaction Technology, Transient external loads or interface forces system for large spacecraft 1986 reconstructed from structural response measurements --- [NLR-TR-86001-U] p 23 N87-19442 [ NASA-CP-2447-PT-I ] p 73 N87-16014 modular spacecraft p 20 N87-10910 Development of the Lens Antenna Deployment Loads analysis for the Galileo spacecraft Demonstration (LADD) shuttle-attached flight experiment p 21 N87-10926 U p7 N87-16022 Passive damping augmentation for flexible structures The I5meter hoop-columnantenna dynamics: Test and U.S.S.R. SPACE PROGRAM p 36 N87-16044 analysis p 35 N87-16025 Multidisciplinary analysis of actively controlled large Getting back on track in space p 1 A87-14375 The USSR and space power plants Application of physical parameter identification to finite flexible spacecraft p 37 N87-16045 element models p 35 N87-16026 p 45 A87-25533 TRANSPARENCE COFS 1 research overview p8 N87-16029 ULTRAHIGH FREQUENCIES Analysis of normal and transparent silver Teflon Description of the Mast Flight System L-band antennas for regional mobile communication p 55 N87-14391 p8 N87-I6030 satellites p 47 N87-15377 TRANSPONDERS MAST flight system dynamic performance ULTRASONIC CLEANING Communicationstechnology p 46 A87-30893 p 35 N87-16032 Acoustic cleaning of large space structures TRAVELING WAVES Passive damping augmentation for flexible structures p 46 A87-26080 Modal control of traveling waves in flexible structures p 36 N87-16044 ULTRAVIOLET RADIATION p 29 A87-24552 Analysis and simulation of the MAST (COFS-1 flight Design improvement and radiation, contamination tests. TRENDS hardware) p 37 N87-I6046 Prestudy 1: Ultraviolet radiation acceleration. volume 1 --- Space technologies and materials: A look back and Robust multivariable controller design for flexible satellite design future perspectives p 52 N87-10934 spacecraft p 37 N87-16048 [CERT-4193-VOL-I] p 53 N87-10949 TRIBOLOGY Investigation of interactive structural and cont ro Ile r Design improvement and radiation contamination tests. The 20th Aerospace Mechanics Symposium synthesis for large spacecraft Prestudy 1: Ultraviolet radiation acceleration. Volume 2: [ NASA-CP-2423-REVl p 73 N87-16321 [AD-A172811] p 17 N87-16055 Appendix. detailed results --- satellite coating Tribologicalproperties of polymer films and solid bodies Discrete mechanism damping effects in the solar array 1 CERT-4193-VOL-2 p 53 N87-10950 in a vacuum environment I flight experiment p 38 N87-16341 Improving the irradiation plus contamination tests. [ NASA-TM-889661 p 57 N87-17906 Damping 1986 procedures, volume 2 Prestudy 2: Successive irradiationsand synergics. Volume TRUNCATION ERRORS [ AD-A173950 ] p 73 N87-16366 1: Tests and conclusions ---satellite coatings Truncation error estimation of a spacecraft model with On incorporatingdamping and gravity effects in models [CERT-4193-VOL-3I p 53 N87-10951 a flexible appendage p 16 A87-18321 of structural dynamics of the SCOLE configuration Improving radiation plus contamination tests. Prestudy Effective modal parameters and truncation effects in p 40 N87-17827 2: Successive irradiations and synergics. Volume 2: structural dynamics p 31 N87-10897 Active damping of Vibrations in SCOLE excited by Annexes. Annex 1: Detailed results. Annex 2: Control and TRUSSES slewing p 40 N87-17831 improvement of optical measurements satellite Fabncation of a Space Station composite tetratruss --- Evaluation of on-line pulse control for vibration coatings model p 49 A87-13159 suppression in flexible spacecraft p 41 N87-17834 [ CERT-4193-VOL-41 p 53 N87-10952 Vibration suppression of planar truss structures utilizing Expenmental study of active vibration control Preliminary results of SMM exposed aluminized Kapton uniform damping control p 25 A87-13458 [AD-A173144] p 41 N87-17845 and silvered Teflon p 55 N87-14389 Concept of tension activated cable lattice antenna Optimization procedure to control the coupling of UNMANNED SPACECRAFT [IAF PAPER 86-2061 p 15 A87-15934 vibration modes in flexible space structures Aeronautics and space report of the President: 1985 Optimization of a truss member [NASA-TM-89115] p 41 N87-I8879 activities p 74 N87-16662 [ IAF PAPER ST-86-171 p 15 A87-16145 Optimum vibration control of flexible beams by USER REQUIREMENTS Optimization of a truss member piezo-electric actuators Advanced EVA system design requirements study: [AIM PAPER 87-00731 p 16 A87-22395 [ NASA-CR-I802091 p 42 N87-18880 EVASlspace station system interface requirements Efficient optimization of space trusses Thermoviscoelasticcharacterization and analysisof fiber [NASA-CR-171981] p 62 N87-20351 p 19 A87-22814 composite space structures Buckling and nonlinear response of imperfect [AD-AI 750241 p 58 N87-19457 three-legged truss columns p 19 A87-30296 Passive stabilizationfor large space systems Optimization of equivalent periodic truss structures v [NASA-CR-4067] p 42 N87-19755 p 16 A87-31175 VARIABLE GEOMETRY STRUCTURES VIBRATION ISOLATORS Equivalent continuum analyses of large space trusses Simplex Mast - An extendible mast for space Synthesis of control laws for optimally designed large p 12 N87-10894 applications p3 A87-18242 space structures Development of deployable truss concept for space VELOCITY DISTRIBUTION [IAF PAPER 86.2461 p 26 A87-15963 station p 16 N87-10923 The tidal velocity field in the Local Supercluster Damping 1986 procedures, volume 2 Design. construction and utilization of a space station p23 A87-11159 [ ADA1739503 p 73 N87-16366 assembled from 5-meter erectable struts VIBRATION DAMPING Active damping of vibrations in SCOLE excited by [ NASA-TM-890431 p6 N87-11827 Vibration data reduction for design, analysis and testing slewing p 40 N87-17831 Mobile remote manipulator system for a tetrahedral of spacecraft p 23 A87-10901 VIBRATION MODE truss Vibration suppression of planar truss structures utilizing Modal analysis technique used in Germany for [ NASA-CASE-MSC-20985.11 p 61 N87-15260 uniform damping control p 25 A87-13458 aerospace structures p 30 A8728544 Dynamic testing of a two-dimensional box truss beam A procedurefor calculating the damping in multi-element Comparison of multiple input random and sine excitation [ NASA-CR-40391 p 34 N87-15262 space structures methods for aerospace structures --- spacecraft vibration NASAIDOD ControllStructures Interaction Technology, [ IAF PAPER 86-2031 p 26 A87-15931 models p 12 A87-28552 1986 Improving the active vibrational control of large space Computation of total response mode shapes using tuned [ NASA-CP-2447-PT-11 p 73 N87-16014 structures through structural modifications frequency response functions p 30 A87-28569 Deployable truss structure advanced technology [ IAF PAPER 88-2041 p 26 A87-15932 Transient modal tuning --- for space structures p 22 N87-16021 A slewing control experiment for flexible structures p 30 A87-28578 Application of physical parameter identification to finite p 27 A87-17761 Optimization procedure to control the coupling of element models p 35 N87-16026 Control of solar battery arrays of spacecraft with vibration modes in flexible space structures Mast flight system beam structure and beam structural consideration of the structural flexibility [ NASA-TM-891151 p 41 N87-18879 performance p 17 N87-16031 p 44 A87-18319 VIBRATION TESTS MAST flight system dynamic performance Vibration control of nonlinear flexible structures Vibration data reduction for design, analysis and testing p 35 N87-16032 [AIAA PAPER 87-00741 p 28 A8722396 of spacecraft p 23 A87-10901 MAST flight system operations p 8 N87-16033 Flexibility control of solar battery arrays. Ill - vibration Pultrusion process development for long space boom Surface control System for the 15 meter hoop-column and attitude control with consideration of the dynamics models p 60 A8720083 antenna p 37 N87-16047 of a reaction wheel as an actuator p 45 A87-22969 Identification, applications, and dynamic analysis of Wave dispersion mechanisms in large space nonlinear spacecraft components p 30 A87-28558 Wave-absorbing controllers for a flexible beam structures Structural system identification using single and p 28 A87-23986 [ADA1739671 p 38 N87-16059 multiaxial vibration test data --- spacecraft structures Evaluation of Pactruss design characteristics critical to A sequential linear optimization approach for controller p 20 N87-10911 space station primary structure design p 28 A87-23989 Experience on the Olympus modal survey test [ NASA-CR-1781711 p 17 N87-16870 Efficient modal analysis of damped large space p6 N87-10919 On incorporating damping and gravity effects in models structures p 28 A87-23995 VISCOELASTIC DAMPING of structural dynamics of the SCOLE configuration Experimental characterization of passively damped Damping representationrelated to Spacecraft structural p 40 N87-17827 joints for space structures p 29 A87-25680 design p 31 N87-10898

A-25 VLF EMISSION RECORDERS SUBJECT INDEX

I Damping 1986 procedures, volume 2 [AD-A1739501 p 73 N87-16366 VLF EMISSION RECORDERS ELF generation in the lower ionosphere via collisional paramelrtc decay p 25 A87-14941 W

WALKING MACHINES Space spider crane [NASA-CASE-lAR-l3411-lSB] p 73 N87-15259 I WASTE HEAT Controlling waste heat in military spacecraft 0 18 A87-15197 WAVE DISPERSION Wave propagation and dynamics of lanice structures [AD-A1703161 p 33 N87-13479 Wave dispersion mechanisms in large space structures [ AD-A1 739671 p 38 N87-16059 WAVE FRONT DEFORMATION System concept for a moderate cost Large Deployable Reflector (LDR) p3 A87-18508 WAVE GENERATION ELF generation in the lower ionosphere via collisional parametric decay p 25 A87-14941 WAVE PROPAGATION Wave propagation and dynamics of lanice structures [ AD-A1703161 p 33 N87-13479 System engineering study of electrodynamic tether as a spaceborne generator and radiator of electromagnetic waves in the ULFfELF frequency band [NASA-CR-l80156] p 23 N87-16956 Experimental study of active vibration control [ AD-A1731 441 p 41 N87-17845 WAVEGUIDE ANTENNAS Features and technologies of ERS-1 (ESA) and X-SAR anten n a s p 9 N87-17152 WEAPON SYSTEMS A oreliminarv.- loaistics suooort conceot,. for soace-based SDI Assets [AIAA PAPER 87-06891 p 61 A87-27616 WEAR Tribological properties of polymer films and solid bodies in a vacuum environment [NASA-TM-88966] p 57 N87 17906 WEATHER STATIONS Technical issues in the conduct of large space platform experiments in plasma physics and geoplasma sciences p 75 N87-20071 WEIGHT REDUCTION Optimization of a truss member [IAF PAPER ST-86-17] p 15 A87-16145 Efficient optimization of space trusses p 19 A87-22814 Development of a lightened structure for the GSR3 solar generator p 17 N87 10927 WEIGHTLESSNESS The control theory of flexible and articulated spacecraft [ AD-A1 748801 p 42 N87-19434 I WEIGHTLESSNESS SIMULATION Fabrication of a carbon fibrefaluminium alloy composite under microgravity p 48 A87-11384 WELD TESTS The welding of aluminum alloys A new technology in space application p 56 N87-17056 WELDED JOINTS The welding of aluminum alloys A new technology in space application p 56 N87-17056 WELDING Remotely manipulated and autonomous robotic welding I fabrication in space p 59 A87-13714 Fundamentals and advances in the development of remote welding fabrication systems p 49 A87 14312 Engineering considerations for on-orbit welding operations p 59 A87-17401 WEST GERMANY Possible areas of collaboration between DFVLR and ISRO in the fields of structures and materials I P 56 N87-15252

A-26 PERSONAL AUTHOR INDEX

TECHNOLOGY FOR LARGE SPACE SYSTEMS /A Bibliography (Supplement 77) OCTOBER 1987

Typical Personal Author Index Listing

AL-ABBASS, F. B Decentralized control experlrnents on NASAs flexible AUTHOR! PERSONAL grid p 24 A87-13394 BABCOCK, CHARLES D. ALARIO. J. P. Buckling and nonlinear response of imperfect Space constructible radiator on-orbit assembly three-legged truss columns p 19 A87-30296 IBAILEY. M. C. BAIER, H. p 58 A87-11359 Integrated structure electromagnetic optimization of ALBUGUES, F. On optimal passive and active control of precision large space antenna reflectors A method of studying the behavior of composite spacecraft structures p 31 N87-I0891 rINASA-TM-89110 I D 48 N87-18598 materials in simulated space environments BAIER, HORST p 53 N87-I0940 Identification. applications. and dynamic analysis of ALBUS. J. S. nonlinear spacecraft components p 30 A87 28558 Software archi!ecture for manufacturing and space BAILEY. JAMES P. robotics Analysis and Simulation of the MAST (COFS-1 flight IAlAA PAPER 87-1687 I p 12 A87-31121 hardware) p 37 N87-16046 BAILEY, M. C. ALFANO. S. Integrated structure electromagnetic optimization of MMU (Manned Maneuvering Unit) task simulator large space antenna reflectors 1 AD-A169552 I p 13 N87-14370 I NASA TM-89110 I p 48 N87-18598 ALLEN, D. H. BAILLIEUL, JOHN A model for predicting therrnomechanical response of The control theory of flexible and articulated Listings in this index are arranged alphabetically large space structures by personal author The title of the document pro- spacecraft IAD-AI729661 p 22 N87-15264 [AD-A1748801 p42 N87 19434 vides the user with a brief description of the subject ALLEN, JOHN L. BAINUM, P. M. matter The report number helps to indicate the COFS 1 Beam dynamics and control technology The dynamics and control of a space platform connected overview p 35 N87-16028 type of document listed (e g , NASA report, trans- to a tethered subsatellite p 25 A87-14074 ANDERSEN, G. C. Svnthesis of control laws for ODtimallv desianed laroe lation. NASA contractor report) The page and ac- Vibration suppression of planar truss structures utilizing space structures cession numbers are located beneath and to the uniform damping control p 25 A87.13458 I IAF PAPER 86-246) p 26 A87-15963 right of the title Under any one authors name the ANDERSSON, T. Space exploitation and utilization. Proceedinas of the accession numbers are arranged in sequence with Tele-X antenna module Structure qualification program Symposium. Honolulu, HI. December 15-19. 19i5 p 21 N87-10924 p 66 A87-18451 the AlAA accession numbers appearing first ANDRENUCCI, M. Optimal torque control for SCOLE slewing maneuvers Advanced propulsion status in Western Europe p 40 N87-17823 llAF PAPER 86.1721 p63 A87-I5913 BAINUM, PETER M. ANGELO, J. A., JR. Issues in modeling and controlling the SCOLE A A 21st century nuclear power strategy for Mars configuration p 39 N87-17822 1 IAF PAPER 86-322 I p 42 A@7-16019 BAIOCCHI, G. ADAMIAN, A. Advanced propulsion status in Western Europe ARDUINI. C. Unified controllstructure design and modeling 1 IAF PAPER 86-172 I p 63 A87-15913 Assembly of thermoelastic continuous elements research BAKER, JOHN C. I IAF PAPER 86-207 1 p 59 A87-15935 I NASA-CR-I79948 I p 33 N87-13478 Space logistics support to military space systems ADELI, HOJJAT Dynamics and Control Analysis Package (DCAP) An I AlAA PAPER 87-0694 1 p 69 A8727621 automated analysis and design tool for structural control Efficient optimization of space trusses BALAKRISHNAN, A. V. of space structures p 39 N87-16947 p 19 A8722814 Active stability augmentation of large space structures. Thermomechanical characteristics of dichroic ADELMAN, HOWARD M. A stochastic control problem p 41 N87-I7835 subreflectors p 22 N87-16952 Effect of sensor and actuator errors on static shape The SCOLE design challenge p 10 N87-17836 control for large space structures p 29 A87-27948 ARWSTRONG, ERNEST S. BALAS. M. Computer-aided design and distributed system Model reference control of distributed parameter Inlegrated structure electromagnetlc optimization of technology development for large space structures large space antenna reflectors systems Application to the SCOLE problem p 14 N87-16042 p 40 N87-17829 I NASA-TM-89110I p 48 N87-18598 Robust multivariable controller design for flexible BALMAIN. K. G. AGAPAKIS, J. E. spacecraft p 37 N87-16048 Analysis of the ion spot phenomenon on beam-charged Remotely manipulated and autonomous robotic welding dielectrics p 51 A87-21993 fabrication in space p 59 A87-I3714 ASTRACHAN, IRA R. Vibration control of nonlinear flexible structures BANERJEE. A. K. Fundamentals and rrdvances in the development of AlAA PAPER 87-0074 p 28 A87-22396 Moaeling and Simulation of spacecraft solar array remote welding fabrication systems p 49 A87-14312 I I ATLURI, S. N. deployment p 26 A87-I7760 AGGSON, T. L. An explicit expression for the tangent-stiffness of a BANHOUER, W. F. Boom potential of a rotating satellite in sunlight finitely deformed 3-D beam and its use in the analysis of Oxidation-resistant reflective surfaces for solar dynamic p 68 A87-24198 space frames p 19 A87-20247 power generation in near Earth orbit AGUILAR, L. I NASA-TM-88865 I p 54 N87-10960 Acoustic cleaning of large space structures ATZEI. A. BANING, G. Advanced propulsion status in Western Europe The welding of aluminum alloys A new technology in p46 A87-26060 IIAF PAPER 86-172 I p 63 A87-I5913 AGUIRRE, M. space application p 56 N87-I7056 AUBERTIN, J. M. Extendable retractable telescopic mast for deployable BANKE, E. A. Analysis of rendezvous and docking in geostationary structures p8 N87-16323 Optimization of a microwave-beam energy transmission Earth orbit. Rider to comparison of future communications AHL, ELVIN L., JR. channel p 46 A8729753 space segment concepts BANKS, E. A. Surface control system for the 15 meter hoopcolumn I DM51-C/PL/FL/0099 82 I p 72 N87-14364 antenna p 37 N87-I6047 Properties and potential applications of brominated AUCLAIR, J. M. P-I00 carbon fibers p 51 A8723702 AHMADIAN. MEHDl Dynamics of flexible mechanisms p 32 N87-10938 BANKS, BRUCE A. On the stability of multiple parameter time-varying AUTHIER, E. - Protection of solar array blankets from attack by low dynamic systems p 29 A87-27449 Large inflatable parabolic reflectors in space earth orbital atomic oxygen p 45 A87-19874 AHMED, N. U. p3 A87-19789 BANKS, H. T. Stabilization of a class of hybrid systems arising in flexible AYOUN. A. The identification of a distributed parameter model for spacecraft p 24 A87-12139 Analysis 01 rendezvous and docking in geostationary a flexible structure AKIBA, R. Earth orbit Rider to comparison of future communications I NASA-CR-178199I p 13 N87-14059 A concept of the Energy Storable Orbital Power Station space segment concepts BARBA, P. M. (ESOPS) I DM51-C/PL/FL/0099 821 p 72 N87-14364 Modeling and Simulation of spacecraft solar array [ IAF PAPER 86-1491 p 42 A87-15898 AZARBAYEJANI, A. deployment p 26 A87-17760 AKLE, W. Factors influencing selection of space transportation BARBONI, R. Microcomputer design and analysis 0' the cable catenary options Thermomechanical characteristics sf dichroic large space antenna system p 13 N87-11762 I IAF PAPER 86-108 I p 65 A87-15871 subreflectors p 22 N87-16952

B-1 BARGERON, C. B. PERSONAL AUTHOR INDEX

EARGERON, C. E. BLACK, D. C. Proceedings of an International Symposium on Fluid Erosion studies on Solar Max samples The role of automation and robotics in space stations Dynamics and Space p 50 A87-19343 p 58 A87-13706 [ESA SP-2651 p 72 N87-14394 Studies of erosion of solar max samples of Kapton and Telescience in orbit p3 A87-16930 BUSH, H. G. Teflon p55 N87 14384 ELELLOCH, P. A. Design. construction and utilization of a space station EARISA, 8. Unified controllstructure design and modeling assembled from 5-meter erectable struts Manned Mars mission Earth-To-Orbit(ETO) delivery and research [ NASA-TM-89043I p 6 N87-I1827 orbit assembly of the manned Mars vehicle [ NASA-CR-I799481 p 33 "37-13478 BUSH, HAROLD G. p9 N87-17746 ELELLOCH, PAUL ANDREW Seamless metal-clad fiber-reinforced organic matrix A modified loop transfer recovery approach for robust EARNETT, A. composite Structures and process for their manufacture controL oi flexible structures p 39 N87-I7029 Large structures and tethers working group [NASA-CASE-MR-I3562-1 1 p 57 N87-18613 BLEVINS, CREED E. p 75 N87-20057 BUSH, J. Passivelv damped IOintS for advanced space EARRETT, J. L. Acoustic cleaning of large space structures structures Spacecraft glows from surface-catalyzed reactions p 46 A87-26060 [ AD-AI 74914 1 p 42 N87-19435 BUTLER. DAVID H. p 43 A87-17368 ELUCK, R. M. Surface control system for the 15 meter hoop-column EARTOLI, C. Development of Space Station Strut design Advanced propulsion status in Western Europe p 15 A87-11842 antenna p 37 N87-16047 [IAF PAPER 86-1721 p 63 A87-15913 BLUCK, RAYMOND M. BARTON, JOHN R. Seamless metal-clad fiber-reinforced organic matrix High voltage solar array plasma protection techniques composite structures and process for their manufacture C p 45 A87-I9878 [NASA-CASE-LAR-13562-11 p 57 N87-18613 EASSNER, H. BODE, J. CALDICHOURY, M. Advanced propulsion status in Western Europe Stress and deformation analysis of thermally loaded light Analysis of rendezvous and docking in geostationary [ IAF PAPER 86-1721 p 63 A87-15913 weight composite structures Earth orbit Rider to comparison of future communications space segment concepts EAUER, E. [IAF PAPER 86-2121 p 18 A87-15939 Meteoroid and orbital debris protection concepts EONTSEMA, J. [DM51 C/PL/FL/OO99 821 p 72 N87 14364 [IAF PAPER 86-4191 p 65 A87-16081 Large flexible space structures: Some simple models CALEDONIA, GEORGE E. EAUER, J. L. [TW-2691 p 32 N87-10957 Energetic oxygen atom material degradation studies International SAMPE Symposium and Exhibition, 3tst, EOSSAVIT, A. [AIAA PAPER 87-01051 p5t A8724919 Los Angeles. CA, April 7-10. 1986, Proceedings Application of dynamic elements and continuum A high flux source of energetic oxygen atoms for material p 64 A87-13051 methods to large space structures. volume 1 degradation studies p 52 A87-27936 EM. A. [ED/82-362/RD-VOL-I] p 22 N87-13484 CALLESON, ROBERT E. Distributed active control of large flexible space Application of dynamic elements and continuum Dynamic analysis of the large deployable reflector structures methods to large space structures, volume 2 [NASA TM-89056 I p 37 N87-16050 [NASA-CR-179941] p 33 N87-I3476 [ ED/82-362/RD-VOL-Z] p 34 N87-13485 CALVERT, JOHN Optimum vibration control of flexible beams by EOSSI, J. A. Design and analysis of a keel latch for use on the Hubble piezo-electric actuators A laboratory experiment in control/structure Space Telescope p62 N87 16326 interaction p 24 A87-I3392 [NASA-CR 1802091 p 42 N87-18880 CARRUTH, M. R., JR. EOWEN, D. H. EAZ, A. M. Plasma electron collection through biased slits in a Developmentof a continuous manufacturingmethod for Static deflection control 01 flexible beams by dielectric p 46 A87-31223 piezo-electric actuators a CFRP collapsible tube mast CASSIDY, J. J. [NASA-CR-1799471 p 34 N87-13788 [ AERE-G-38981 p 54 N87-13572 A unified approach to computer analysis and modeling EEKEY, G. A. BOWLES, D. E. of spacecraft environmental interactbons Evaluation of on-line pulse control for vibration Space radiation effects on the dimensional stability of p 14 N87-20066 suppression in flexible spacecraft p 41 N87-17834 a toughened epoxy graphite composite EEKEY, I. p 49 A87-I 1847 CASTELLANI, A. Space construction results - The EASElACCESS flight BRACE, L. H. Thermomechanical characteristics of dichroic experiment Dual-spacecraft measurements Of subreflectors p 22 N87-16952 [IAF PAPER 86-26] p2 A87-15817 plasmasphere-ionospherecoupling p 67 A87-20055 CEEALLOS, D. C. EELVIN, W. KEITH BRAHNEY, J. H. Parameter optimization and anitude stabilization of a The 15 meter hoop-columnantenna dynamics Test and Controlling waste heat in military spacecraft flexible spacecraft p31 N87 10138 analysis p 35 N87-16025 p 18 A87-I5197 CECCONI, J. L. BENNETT, F. 0. ERANDHORST, H. W., JR. Space technologies and materials A look back and Evaluationof on-orbit cryogenic propellant depot options Spacecraft 2000 - The challenge of the future future perspectives p 52 N87-10934 for the orbital transfer vehicle p 63 A87-31133 p 3 A87-18064 CHAPPELL, C. R. EENNIGHOF, J. K. ERECKINRIDGE, J. 6. Dual spacecraft measurements Of Modal control of traveling waves in flexible structures System concept for a moderate cost Large Deployable plasmasphere-ionospherecoupling p 67 A87 20055 p 29 A87-24552 Reflector (LDR) p 3 A87-I8508 CHAREONNIER, M EENSON, R. C. Adhesive bonding of aerospace materials - Surface ERIEHL, D. Erosion studies on Solar Max samples characterizationof metallic adherends Technical aspects of the United States Space Station p 50 A87-19343 p 51 A8720149 p 1 A87-10043 Studies of erosion of solar max samples of Kapton and CHARRON, F. Teflon p 55 N87-14384 ERILLHART, RALPH Demonstration of modal synthesis on an experimental BENSON, SCOTT Computation of total responsemode shapes using tuned structure and its application to large spacecraft Use of support simulation modeling techniques in the frequency response functions p 30 A87-28569 p 20 N87-10912 development of logistics support concepts for SDI orbital ERONOWICKI, ALLEN J. CHARRON, FRANCOIS platforms and constellations Application of physical parameter identification to finite Substructure coupling of analytical and test models for IAlAA PAPER 87-0690) p 12 A87-27617 element models p 35 N87-16026 an experimental structure p 19 A87-28577 EERCAW, R. W. BROWN, N. CHASSERY, J. M. Spacecraft 2000 The challenge of the future Evaluationof on-orbit cryogenic propellant depot options Digital image processing Binary images p3 A87-18064 for the orbital transfer vehicle p 63 A87-31133 D57 N87 18015 BERGMANN, H. W. BRUMFIELD, M. LARRY CHEN, J. Performance characteristics of composite materials MAST flight system operations p 8 N87-I6033 1986 LECEC stability and transient modeling of a large p 53 N87-10935 ERUNNER, 0. SDacecraft power system D 66 A87-18114 EERNASCONI, C. M. Deployment analysis of the Olympus Astromast and CHEN. J.-C. Development of a 2 8 m offset antenna reflector using comparison with test measurements p 61 A87-31220 Spacecraft structural model improvementby modal test inflatable, space-rigidizedstructures technology results p 20 A87-31225 BRYAN, CHARLES F., JR. p8 N87-16927 CHEN, N. Prediction of the electrical perlormance of Inflatable Space spider crane [NASA-CASE-LAR-1341I-ISB] p 73 N87-I5259 Nonlinear interfaces for acceleration commanded Space Rigidized Structure (ISRS) offsetantenna reflectors control of spacecraft and manipulators EUCHHOU. G. and correlation with RF measurements F. p 25 A87-13494 Debonding analysis of thermally stressed P 47 N87-16943 CHIANG, W. W. fiber-reinforced composite materials p 52 N87-10933 BERTRAM, A. Rapid precise end point control of a wrist Carried by a Experience on the Olympus modal survey test EUDEN, D. flexible manipulator p 61 N87-10398 p6 N87-10919 A 2tst century nuclear power strategy for Mars CHIOU. W. C., SR. BERTRAM, AXEL [IAF PAPER 86-3221 p 42 A87-I6019 Space station automation, Proceedings of the Meeting. The dynamical qualification of present and future EURATTI, A. Cambridge. MA, September 17. 18. 1985 spacecraft structures P 30 A87-29368 Navigation. guidance, rendez-vous and docking - [SPIE-580] p64 A87 13705 BILBY, C. Activities carried out for Columbus by the flight operations An introduction to the concept of robot factors and its Modeling and simulation of large scale space systems organization application to Space Station automation Strategic planning implications [IAF PAPER 86-09] p 65 A87-I 5808 p 58 A87-13712 1 IAF PAPER 86.4531 p 2 A87-16105 BURKE. W. R. CHODAS, PAUL WINCHESTER EISWAS, S. K. Proceedings of an International Conference on Combined orbit/anitude determination for low-altitude Stabilizationof a classof hybrid systems arising in flexible Spacecraft Structures satellites spacecraft P 24 A87-12139 [ESA-SP-238] p 70 N87-I0886 [UTIAS-320] p 74 N87-17810 8-2 PERSONAL AUTHOR INDEX EGDALL, 1. M.

CHOW, L. C. D DONATO, L. Feasibility study of a low-temperature expandable Design of a low distortion shared aperture reflector megawatt pulse power radiator p 66 A87-17841 DAS, A. p 14 N67-16934 CHROSTOWSKI, J. D. Spacecraft Dynamics and Control Program at AFRPL DORROUGH, D. Component testing for dynamic model verification p 34 N87-16017 Robotics concepts for the U.S. Space Station [AAS PAPER 85-6661 p 60 A87-18486 p 32 N87-11765 DAS. S. DOWLATYARI CHUN, HON M. Solar array mechanisms for Indian satellites. APPLE, Application of dynamic elements and continuum Frequency-shapedlarge-angle maneuvers IRS and INSAT-IITS [AIAA PAPER 87-01741 p 28 A87-22462 [IAF PAPER 86-1421 p 11 A67-15893 methods to large space structures, volume 1 [ED/82-362/RD-VOL-I 1 p 22 N87-13484 DAUPHIN, J. CHUNG, S. V. Application of dynamic elements and continuum Space matenals in Europe p 49 A87-13067 Degradation studies of SMRM Teflon methods to large space structures, volume 2 p 56 N87-14392 DAVIDSON, R. [ ED/82-362/RD-VOL-21 p 34 N87-13485 CIFFONE, D. L Developmentof a continuous manufacturingmethod for DOWLATVARI, P. Space missions for automation and robotics a CFRP collapsible tube mast Equivalent continuum analyses of large space trusses technologies (SMART) program p 58 A87-13707 [AERE-G-36981 p 54 N87-13572 p 12 N87-10894 CLANTON, U. S. DAVIS, H. DRIES, G. A. Examination of returned solar-max surfaces for Modeling and simulation 01 large scale space systems Effects of thermal cycling on graphie-fiber-reinforced impacting orbital debris and meteoroids Strategic planning implications 6061 aluminum p 55 N87-14386 [IAF PAPER 86-4531 p2 A87-16105 [ NASA-TP-26121 p 52 N67-10184 CLAUDINON, E. DAVIS, L. DRISKILL, GLEN W. Rendezvous and docking verification and in-orbit MAST flight system dynamic performance Space station rotary joint mechanisms demonstration D 35 N87-16032 p 73 N87-16338 [IAF PAPER 86-07] p 65 A87-15806 DAVIS, R. E. DUBEL, J. F. CLAYTON, M. J. Report on SMRM C/P main electronics box component Fabrication of a Space Station composite tetratruss Parametric study of stable optical references for large and materials degradation evaluations model p 49 A87-13159 flexible structures in space p64 A87-11013 D 72 N87-14375 DUBOIS, J. CLINCKEMAILLIE, J. DAVIS, WILLIAM E. Equivalent continuum analyses of large space trusses p 12 N87-10894 Application of dynamic elements and continuum Advanced composites for large Navy spacecraft methods to large space structures, volume 1 p 56 N87-16015 Application of dynamic elements and continuum [ ED/62-362/RD-VOL-1] p 22 N87-13484 DE SANCTIS, C. methods to large space structures, volume 1 [ ED/82-362/RD-VOL-I ] p 22 N87-13484 Application of dynamic elements and continuum Large space observatories of the 21st century Application of dynamic elements and continuum methods lo large space structures. volume 2 [AIAA PAPER 87-06361 p 4 A87-22751 methods to large space structures. volume [ ED/82-362/RD-VOL-2] p 34 N87-13485 2 DE SMET, M.-A. [ ED/82-362/RD-VOL-21 p 34 N87-13465 Holographic non-destructive testing for composite COBUT, J. P. DUDECK. M. P. materials used in aerospace p 51 A87-19805 The Extendable Refractable Mast (ERM) thermal Deployable truss structure advanced technology analysis: A heat radiation case study via the finite element DECHAUMPHAI, P. p 22 N87-16021 method p 22 N87-16949 A Taylor-Galerkinfinite element algorithm for transient DUNAETZ, R. COHEN, H. A. nonlinear thermal-structuralanalysis International SAMPE Symposium and Exhibition, 31st. Boom potential of a rotating satellite in sunlight [NASA-CR-177064] p 20 N87-10406 Los Angeles. CA, April 7-10, 1986. Proceedings p 66 A87-24198 DECHAUMPHAI, PRAMDTE p 64 A87-13051 COLLADAV, R. S. Finite-element thermal-structural analyses of a DUNBAR, WILLIAM G. Technologies for affordable access to space cable-stiffened orbiting antenna p 19 A87-25687 High voltage solar array plasma protection techniques [ IAF PAPER 86-4421 p2 A67-16096 DEFOSSE, H. p 45 A87-19878 COLLADAY, RAYMOND S. Prediction and correlation of structural response in DUPAS, ALAIN acoustic chambers p 20 N87-I0907 NASA's technology plans - Will technology be ready The USSR and space power plants when we are DELCAMPO. F. p 45 A87-25533 [AIAA PAPER 87-16951 p 5 A87-31123 A Sener mechanism: Fine adjustment mechanism for DURSCH, HARRY W. the Far Infrared and Submillimeter Space Telescope Protective coatings for composite tubes in space COLLINS, EMMANUEL G. (FIRST) (F f F) p 74 N87-16946 Regulation of the SCOLE configuration applications p 41 N87-17833 DELIL, A. A. M. [NASA-CR-1781161 p 57 N67-18669 Sensors for a system to control the liquid flow into an DURVASULA, S. COMFORT, R. H. evaporation cold plate of a two-phase heat transport Dual-spacecraft measurements Of Vibration data reduction for design, analysis and testing system for large spacecraft of spacecraft p 23 A87-10901 plasmasphere-ionospherecoupling p 67 A87-20055 [ NLR-TR-6600 1 -U 1 p 23 N87-19442 DWVER, T. A. W., 111 COOGAN, CHARLES 0. DELTORO, J. Automatic decoupling of flexible spacecraft slewing Front end logistics influence on space system hardware A Sener mechanism: Fine adjustment mechanism lor maneuvers p 24 A67-13431 design the Far Infrared and Submillimeter Space Telescope [AIAA PAPER 67.06581 p 5 A67-27605 (FIRST) (F f F) p 74 N87-16946 Nonlinear interfaces for acceleration-commanded control of spacecraft and manipulators DENMAN, EUGENE COOMES, E. P. p 25 A87-13494 Design of a superconductingalternator for space-based Identification of large space structures on orbit DYER, J. E. power generation p43 A87-18144 [AD-A1737561 p 14 N87-16058 DENMAN, J. R. Deployable truss structure advanced technology COOPER, PAUL A. p22 N87-16021 Protective coating for the KU-band reflector Multidisciplinary analysis of actively controlled large p 49 A87-13098 flexible spacecraft p 37 N87-16045 DEPAULA. R. P. CORDERO. P. Sensor technology for advanced space missions E Development of mm-wave radiometer antenna D 73 N87-16027 reflector p 47 N87-16941 DERESPINIS. SlLVlO F. EASTEP, F. E. COTTS, D. B. Sun shieid Improving the active vibrational control of large space Electrically conductive organic polymers for advanced [ NASA-CASE-MSC-20162-1I p 74 N87-17036 structures through structural modifications applications p 50 A87-18554 DERYDER. L. J. [ IAF PAPER 86-2041 p 26 A87-15932 Optimal structural design with control gain norm COUGNET, C. A space station Structures and Assembly Verification Analysis of rendezvous and docking in geostationary Experiment. SAVE constraint [ NASA-TM-890041 p 5 N87-10170 p 11 A87-22363 Earth orbit. Rider lo comparison of luture communications [AIAA PAPER 87-00191 space segment concepts DIARRA, CHECK MODIBO EASTON, D. C. 0. [DM51-C/PL/FL/OO99.82] p72 N87-14364 Issues in modeling and controlling the SCOLE The ESA/MBB unfurlable mesh antenna development configuration p 39 N87-17822 for mobile services CRAIG, R. R. DILLON-TOWNES, L. A. [IAF PAPER 86-27] p 2 A67-15818 A study of nodal coupling methods p 31 N87-10896 Thermal analysis of radiometer containers for the 122m ECKER, J. A. CRAWLEY, E. F. hoop column antenna Concept Use of graphitelepoxy composites in spacecraft A procedurefor calculating the damping in multi-element [NASA-TM-89026] p 21 N87-11966 structures - A case study p 50 A87-19342 space structures DINER, A. ECKHARDT, K. [IAF PAPER 86-2031 p 26 A87-15931 System concept for a moderate cost Large Deployable Initial results from multiaxes transient testing CRISWELL, D. R. Reflector (LDR) p 3 A67-18508 p 21 N87-10917 DOANE. GEORGE B., 111 Lunar-basedpower systems EDGEMON, 0. DAVID [IAF PAPER 66-5071 p43 A87-16132 Developmentand use of a linear momentum exchange device p 36 N87-16041 Development and use of a linear momentum exchange CUCCIA, C. LOUIS device p 36 N87-16041 DODEL, H. Communicationstechnology p 46 A67-30893 Antenna system alternatives for Data Relay Satellites EDIGHOFFER, HAROLD H. CURRAN, R. J. with multiple steerable beams The 15 meter hoop-columnantenna dynamics Test and Lidar remote sensing from space: NASA's plans in the [IAF PAPER 86-3491 p 43 A87-16041 analysis p 35 N87-I6025 Earth sciences p 6 N87-I0265 DODGE, R. E., JR. EGDALL, 1. M. CYR, KELLEY J. Design of a superconductingalternator for space-based ltek optical technology in manufacturing and Budget availability p 10 N87-17799 power generation p 43 A87-18144 metrology p 64 A87-11006 B-3 EGGER, R. A. PERSONAL AUTHOR INDEX

EGGER. R. A. FISHER, SHALOM (MIKE) FUNK, J. G. Oxidation-resistantreflective surfaces for solar dynamic Proof-massactuator placement strategies for regulation The effects of radiation on the interlaminar fracture power generation in near Earth orbit of flexure during the SCOLE slew p 40 N87-17830 toughness of a graphitefepoxy composite [ NASA-TM-88865I p 54 N87-10960 FLETCHER, L. S. p 50 A87-19122 EGGERS, H. The influence of interstitial media on spacecrafl thermal FURNISS, T. The K1-K2 interactionfor matrix splitting in unidirectional control p 18 A87-18266 Space Station - NASA's greatest challenge laminates of carbon fiber reinforced epoxy FLOWERREE, RICHARD p 2 A87-16399 p 52 N87-10932 Use of support simulation modeling techniques in the FURNISS, TIM EDEN, M. development of logistics support concepts for SDI orbital RationalisingSpace Station p5 A87-27455 platforms and constellations Deployment analysis of the Olympus Astromast and FURUMOTO, N. [AIM PAPER 87.06901 p 12 A8727617 comparison with test measurements p 61 A87-31220 Modeling and simulation of spacecraft solar array FLOYD, MICHEL A. EL-GENK, MOHAMED S. deployment p 26 A87-17760 Investigation of interactive structural and controller Space nuclear power systems 1985; Proceedings of the FUSARO, ROBERT L. synthesis tor large spacecraft Second Symposium, Albuquerque, NM, Jan. 14-16, 1985. Tribologicalproperties of polymer films and solid bodies [AD-A172811] p 17 N87-16055 Volumes 3 8 4 p 67 A87-21801 in a vacuum environment FONG, 1. K. [ NASA-TM-88966I p 57 N87-17906 ELMS, R. V. Decentralized optimal control of large flexible Solar arrays for Space Station and platforms structures p 44 A87-18149 [ DE86-0139061 p 41 N87-18101 ELYADA, DOV FONTANA, ANTHONY G Buckling and nonlinear response of imperfect COFS 1 Guest Investigator Program GAEDKE, M. three-legged truss columns p 19 A87-30296 p8 N87-16034 Performance characteristics of composite materials ENDRES, NED M. FORDYCE. J. S. p 53 N87-10935 Composite space antenna structures: Properties and The potential impact of new power system technology GAIER, J. R. environmental effects on the design of a manned Space Station Properties and potential applications of brominated [ NASA-TM-888591 p 39 N87-I6880 p 44 A87-18342 P-100 carbon fibers p 51 A87-23702 ENGLER. E. E. FORDYCE, SAMUEL W. GAILLARD, F. Development of deployable truss concept for space Communications spacecraft p 5 A87-30891 Adhesive bonding of aerospace materials - Surface station p 16 N87-10923 FOSTER, N. characterizationof metallic adherends ENOMOT, J. A study of large space structures p 51 A8720149 Effect of electron-beam radiation on graphite epoxy [ LR468691 p 21 N87-11832 GALLAY, G. composites p 49 A87-13071 Dynamics of flexible mechanisms p 32 N87-10938 FOURNIER, RICHARD J. ENOMOTO, J. Vibration control of nonlinear flexible structures GALLOWAY, E. Degradation of Spacecraft thermal shield materials by [AIAA PAPER 87.00741 p 28 A87-22396 The Space Station - United States proposal and irradiation of energetic particles p 18 A87-18273 implementation p 1 A87-14969 FRAAS, A. P. GALUSKA, A. A. ESCOBAR, J. Protection of spacecrafl from meteoroids and orbital Analysis of normal and transparent silver Teflon Construcciones Aeronauticas S.A. (CASA) large debris p 55 N87-14391 reflector antenna p9 N87-16935 [ DE86-0099963 p 70 N87-10947 GARBA, J. A. ESTES, ROBERT D. FRANK, ARTHUR M. System engineering study of electrodynamic tether as Spacecraft structural model improvement by modal test Sun shield results p 20 A8731225 a spaceborne generator and radiator of electromagnetic [ NASA-CASE-MSC-20162-1] p 74 N87-17036 waves in the ULFIELF frequency band GARCIA, R. FRANZ, J. [NASA-CR-180156] p 23 N87-16956 Development of mm-wave radiometer antenna Design and manufacturing aspects of tubular carbon reflector p 47 N87-16941 EYLES, DON fibre compositeltitanium bonded joints GARRETT, H. Space station thrillers unfold at Draper Lab p 50 A87-16163 Large structures and tethers working group p 11 A87-21257 FRAUENBERGER, H. p75 N87-20057 Development of the Lens Antenna Deployment GATES, S. S. Demonstration (LADD) shuttle-attached flight experiment The identification of a distributed parameter model for F p7 N87-16022 a flexible structure FREELAND, R. E. [NASA-CR-178199] p 13 N87-14059 FAGNOUL, J. System concept for a moderate cost Large Deployable GAVEL, D. T. The Extendable Refractable Mast (ERM) thermal Reflector (LOR) p 3 A87-18508 Preliminary findings for integrated modeling and analysis A heat radiation case study via the finite element simulation of directed energy weapons method p 22 N87-16949 FREY, FRANCOIS A four node Marguerre element for non-linear shell [DE86-0116361 p 10 N87-17846 FALANGAS, E. T. analysis p 30 A87-30545 GEIER, E. Pointing. control, and stabilization of solar dynamic Analysis of long thin-walled tubes p 20 N87-I0895 system on a Space Station p 25 A87 13437 FRIEDENTHAL, M. J. Space Station beyond IOC; Proceedings of the GELB, STEVEN W. FAN, R. Thirty-second Annual International Conference, Los In-orbit performance of Hughes HS 376 solar arrays The dynamics and control of aspace platform connected Angeles, CA. November 6,7, 1985 p 65 A87-15376 p 44 A87-19872 to a tethered subsatellite p 25 A87-14074 GETZSCHMANN, A. FRISCH, BRUCE FARRELL, JAMES D. Rendezvous and docking verification and in-orbit Desian and control of modular kinematicallv-redundant Cleaning up our space act p 5 A87-31208 demonstration manipulators FRISCH, E. [ IAF PAPER 86-07J p 65 A87-15806 [AIAA PAPER 87.16941 p 61 A87-31122 Antenna system alternatives for Data Relay Satellites GEYSELAERS, H. FASOLD, D. with multiple steerable beams Engineering and software interfacing for thermal. Antenna system alternatives for Data Relay Satellites [IAF PAPER 86-3491 p 43 A87-16041 structural and anitude control related with spacecraft with multiple steerable beams FRISTROM, R. M. p 21 N87-I0928 [IAF PAPER 86.3491 p 43 A87-16041 Erosion studies on Solar Max samples GIBSON, J. S. FAYMON, K. A. p 50 A87-19343 Unified controllstructure design and modeling Spacecraft 2000 - The challenae of the future Studies of erosion of solar max samples of Kapton and research p3 A87-18064 Teflon p 55 N87-14384 [ NASA-CR-1799481 p 33 N87-13478 FEHSE. W. FRITSCHE, E. GINTY, CAROL A. Rendezvous and docking verification and in-orblt Influence of fiber orientation and boundary conditions Composite space antenna struciures: Properties and demonstration on the dynamic behavior of a cylindrically telescoping solar environmental effects [IAF PAPER 86-07] p 65 A87-I 5806 array (INTELSAT 6) p 32 N87-10925 [ NASA-TM-88859J p 39 N87-16880 FELICI, F. FUKUDA, T. GIRARD, A. Giotto spacecraft high gain antenna mechanical design Flexibility control of solar arrays based on state Effective modal parameters and truncation effects in and development p 18 N87-16938 estimation by Kalman filtering p 26 A87-15450 structural dynamics p 31 N87-10897 FELKAI. ROLAND GIRARO, F. Design and development of a telescopic axial boom Control of solar battery arrays of spacecraft with consideration of the structural flexibility Dynamics of flexible mechanisms p 32 N87-I0938 p 14 N87-16322 p 44 A87-18319 GLASER, H. FENNELL, J. F. Transient external loads or interface forces FUKUDA, TOSHIO A severe spacecraft-charging event on SCATHA in reconstructed from structural response measurements Flexibility control of solar battery arrays. II Vibration September 1982 - p 20 N87-10910 and attitude control based on state estimation of differential [AIAA PAPER 87-04753 p 45 A87-22659 GLASER, PETER E. solar cell sensors p 45 A87-22968 FEREBEE, M. J., JR. Solar power satellite concept revisited IDEAS A muliidisciplinary computer-aided conceptual Flexibility control of solar battery arrays. 111 - vibration p4 A87-22771 design system for spacecraft P 13 N87-11761 and attitude control with consideration of the dynamics Microwave power transmission for use in space FESTA, A. of a reaction wheel as an actuator p 45 A87-22969 p 46 A87-27180 Dynamics and Control Analysis Package (DCAP) An FULLER, STAN GLASS, M. automated analysis and design tool for structural control Mars landing mission: A structural approach 1986 LECEC stability and transient modeling of a large of space structures P 39 N87-16947 p 23 N87-17783 spacecraft power system p 66 A87-18114 FISCHER, GRAHME FUNAKI, M. GLINES, A. Telerobotic assembly of space Station truss structure The electron irradiation test of thermal control material Space Station challenge - On-orbit assembly of a 75-kW [ NASA-CR-I802391 P 62 N87-18984 p 50 A87-18271 power system p 59 A87-18148

6-4 PERSONAL AUTHOR INDEX HOWELL, J.

GLUCK, R. HAGER, R. W. HERAKOVICH, CARL T. Hope for simulating flexible spacecraft Space Station evolution - The aerospace technology Space radiation effects on the thermo-mechanical p 11 A87-17146 impact behavior of graphite-epoxy composites GOETTING, H. C. [AAS PAPER 85.4561 p 1 A87-15380 p 51 A87-27178 Performance characteristics of composite materials HAISLER, W. E. HERBIG, H. p 53 N87-10935 A model for predicting thermomechanical response of Experience gained by sector model testing of an GOLDHAMMER, LELAND J. large space structures unfurlable meshlrib antenna p 14 N87-16925 In-orbit performance of Hughes HS 376 solar arrays [AD-A172966] p 22 N87-15264 HERM. RONALD R. p 44 A87-19872 HALLAUER, WILLIAM L., JR. Model for radiation contamination by outgassing from GOMEZ, M. F. An analylical and experimental study of a control space plalforms A method of studying the behavior of composite system’s sensitivity lo structural modifications [AIAA PAPER 87-01021 p 67 A87-22416 materials in simulated space environments p 30 A87-30294 HERMAN, D. H. p 53 N87-10940 Experimental study of active vibration control Technical aspects of the United States Space Station GOTO, S. K. [ AD-A1731441 p 41 N87-17845 p 1 A87-10043 Multimegawan power distribution considerations HILBRANDT, E. HALM, R. p43 A87-18113 Damping representation related lo spacecraft structural Giono spacecraft high gain antenna mechanical design GOVIN, E. design p 31 N87-10898 and development p 18 N87-16938 Analysis of rendezvous and docking in geostationary HILL, H. Earth orbit. Rider lo comparison of future communications HAM, F. Development of the Lens Antenna Deployment space segment concepts MAST flight system dynamic performance Demonstration (LADD) shunle-attached flight experiment [DM5l-C/PL/FL/OO99.82] p72 N87-14364 p 35 N87-16032 p7 N87-16022 GOWARIKER, V. HARRIES, WYNFORD L. HILL, L. Possible areas of collaboration between DFVLR and Electron-radiationeffects on the ac and dc electrical Large inflatable parabolic reflectors in space ISRO in the fields of structures and materials properties and unpaired electron densities of three p 3 A87-19789 p 56 N87-15252 aerospace polymers p 51 A87-21992 HINDAWY, M. 1. GRAGLIA, R. D. HARRIS, E. Application of graph theory to the nonlinear analysis Dielectric support structures for spacecraft antenna Proceedings of the 5th Annual Users’ Conference of large space structures p 12 N87-10418 feeds p 17 N87-16931 [ NASA-CP-23991 p 70 N87-10720 HINNERS, N. W. GRANDHI, R. V. HARTFORD, J. The Space Station program Improving the active vibrational control of large space Perspective on non-US. presentations at the 37th [AAS PAPER 85-451] p 1 A87-15377 structures through structural modifications Congress of the International Astronautical Federation - HIRAKO, K. [IAF PAPER 86.2041 p A87-15932 26 October 4-1 1, 1986, Innsbruck, Austria Large-angle slewing of flexible spacecraft Optimal structural design with control gain norm p 67 A87-21975 [AAS PAPER 85.6741 p 27 A87-18490 constraint HASHIN, ZVI HISADA, Y. [AIAA PAPER 87-00191 p 11 A87-22363 Thennoviscoelastic characterizationand analysis of fiber Study on solid surface, deployable antenna reflector GRAZIANI, F. composite space structures p8 N87-16928 Computational methods in elastic periodic structures [AD-AI 750241 p 58 N87-19457 analyses p 32 N87-I0901 HASSELMAN, T. K. HOGGE, M. GREEN, BYRON D. Component testing for dynamic model verification The Extendable Refractable Mast (ERM) thermal A high flux source of energetic oxygen atoms for material p 32 N87-11765 analysis: A heal radiationcase studv nathe finite element degradation studies p 52 A87-27936 HASSELMAN, TIMOTHY method p 22 N87-16949 GREENBERG, H. S. Identificationof large space structures on orbit HOLL, SABINE Development of deployable truss concept for space [ AD-A1737561 p 14 N87-16058 The international Space Station takes shape station p 16 N87-10923 HASTINGS, D. E. p 4 A87-24123 GREGORY, W. H. Radiation from large space structures in low earth orbit HOLMES, A. M. C. Maner of ease p 59 A87-13949 with induced ac currents Development of Space Station strut design GRIFFIN, 0. H., JR. [AIAA PAPER 87.06121 p 68 A87-22738 p 15 A87-11842 Use of graphitelepoxy composites in spacecraft HATLEBERG, CLANCY J. HOUDEPPE, D. structures - A case study p 50 A87-19342 A preliminary logistics support concept for space-based Transient external loads or interface forces GRIMALDI, MARGARET E. SDI assets reconstructedfrom structural response measurements Space station erectable manipulator placement [AIAA PAPER 87-06891 p 61 A87-27616 p 20 N87-10910 system HAUG, E. HOOVER, MARK D. [ NASA-CASE-MSC-21096-11 p 62 N87-18596 Equivalent continuum analyses of large space trusses Space nuclear power systems 1985; Proceedings of the GRONET, M. J. p 12 N87-10894 Second Symposium. Albuquerque, NM. Jan. 14-16, 1985. Passive damping augmentation for flexible structures Application of dynamic elements and continuum Volumes 3 8 4 p 67 A87-21801 p 36 N87-16044 methods to large space structures. volume 1 HORI, M. Passive stabilization for large space systems [ED/82-362/RD-VOL-l] p 22 N87-13484 Fabrication of a carbon fibre/aluminiumalloy composite [NASA-CR-4067] p 42 N87-19755 Application of dynamic elements and continuum under microgravity p 48 A87-11384 GROSE. V. L. methods to large space structures. volume 2 HORNER. G. C. The system approach for applying artificial intelligence [ ED/82-362/RD-VOL-2] p 34 N87-13485 COFS 1 research overview p8 N87-16029 lo Space Station automation p 64 A87-13708 HAYDEN, J. H. GULDBERG, JENS Multimegawatt power distribution considerations HORNER, GARNETT C. Space Station - The use of expert systems for p 43 A87-18113 Analysis and simulation of the MAST (COFS1 flight planning p4 A87-25759 HEDGEPETH, J. M. hardware) p37 N87-16046 GULINO, D. A. Structural concepts for large solar concentrators HORTA, L. G. Oxidation-resistant reflective surfaces for solar dynamic [IAF PAPER 86-2021 p 15 A87-15930 A slewing control experiment for flexible structures power generation in near Earth orbit HEDGEPETH, JOHN M. p 27 A87-17761 [ NASA-TM-888651 p54 N87-10960 Evaluation of Pactruss design characteristics critical to HORTA, LUCAS 0. Effect of hard particle impacts on the atomic oxygen space station primary structure A sequential linear optimization approach for controller survivability of reflector surfaces with transparent [ NASA-CR-1781711 p 17 N87-16870 design p 28 A87-23989 protective overcoats HEFZY, MOHAMED SAMlR Analysis and simulation of the MAST (COFS-1 flight [ NASA-TM-888741 p 71 N87-11838 Shear deformation plate continua of large double layered hardware) p 37 N87-16046 The survivability of large space-borne reflectors under space structures p 16 A87-28882 HORWITZ, J. L. atomic oxygen and micrometeoroid impact HEIMEL, H. Dual-spacecraft measurements Of [ NASA-TM-889141 p 72 N87-14423 Large wheel actuators definition study plasmasphere-ionosphere coupling p 67 A8720055 GULINO, DANIEL A. [TELDIX-l5-020-8801 p 33 N87-11834 HOSHALL, C. H. Effect of hard particle impacts on the atomic oxygen HEINZE, H. SUNiVability Of reflector surfaces with transparent Studies of erosion of solar max samples of Kapton and Experience gained by sector model testing of an Teflon p 55 N87-14384 protective overcoats unfurlable mesh/rib antenna p 14 N87-16925 HOSOGAI, H. [AIAA PAPER 87-01041 p 45 A8722417 HELLER, JACK A. Control of solar battery arrays of spacecraft with The SUNNability of large space-borne reflectors under NASA Growth Space Station missions and candidate consideration of the structural flexibility atomic oxygen and micrometeoroid impact nuclear/solar power systems p 3 A87-21807 p 44 A87-18319 [AIAA PAPER 87-0341] p 52 A87-31300 HELLSTROM, E. E. GUSSENHOVEN. M. S. Li corrosion resistant glasses for headers in ambient HOSOKAI, H. Flexibility control of solar arrays based on state The importance of accurate secondary electron yields temperature Li batteries in modeling spacecraft charging p 46 ~87.27018 [D€86-0137541 p 33 N87-12802 estimation by Kalman filtering p 26 A87-15450 HELWIG, G. HOSOKAI, HlDEMl Analysis of high precision composite sandwich Flexibility control of solar battery arrays. II - Vibration H antennas p 56 N87-16929 and anitudecontrol based on slate estimation of differential HEMPSELL, C. M. solar cell sensors p45 A87-22968 HAFTKA, RAPHAEL T. Extending the Space Station infrastructure Flexibility control of solar battery arrays. Ill - vibration Effect of sensor and actuator errors on static shape p5 A87-28953 and anitude control with consideration of the dynamics control for large space structures p 29 A8727948 HENDRICKS, CARL L. of a reaction wheel as an actuator p 45 A8722969 An analytical and experimental study of a control Protective coatings for composite lubes in space HOWELL, J. system’s sensitlvity to structural modifications applications Large space ObSeNatOrieS of the 21st century p 30 A87-30294 [NASA-CR-178116] p 57 N87-18669 [AIAA PAPER 87-06361 P4 A87-22751

8-5 HSIA, WEI-SHEN PERSONAL AUTHOR INDEX

HSIA, WEI-SHEN JANES, G. K. KAMAL, OSAMA Stochastic modeling and control system designs of the Utilization. testing and maintenance of multimission Efficient optimization of space trusses NASAIMSFC Ground Facility for large space structures hardware p70 A87-29466 p 19 A87-22814 The maximum entropyloptimal prolection approach JAWORSKE, D. A. KAPLAN, M. S. p 38 N87-16766 Properties and potential applications of brominated Application of Spaceborne Distributed HUENERS, HORST P-100 carbon fibers p 51 A8723702 AperturelCoherent Array Processing (SDAICAP) The dynamical qualification of present and future JETTEUR, PHlLlPPE technology to active and passive microwave remote spacecraft structures p 30 A8729368 A four node Marguerre element for non-linear shell sensing p 47 N87-17277 analysis p 30 A8740545 HUETTMANN, H. J. KARLEN, JAMES P. Influence 01 fiber orientation and boundary conditions JHA, V. K. Design and control of modular, kinematically-redundant on the dynamic behavior of a cylindrically telescoping solar Design of a low distortion shared aperture reflector manipulators array (INTELSAT 6) p 32 N87-10925 p 14 N87-16934 [AIAA PAPER 87-16941 p 61 A87-31122 JHA, V. L KASAHARA. A. HUGHES, ROBERT 0. Demonstration 01 modal synthesis on an experimental Study on solid surface. deployable antenna reflector Conceptual design of pointing control systems for space structure and its application to large spacecraft station gimballed payloads p 36 N87-16037 p8 N87-16928 p20 N87-10912 KASHIWASE. T. HUMPHREYS, E. A. JHA. VIRENDRA K. Attitude control experiment for flexible spacecraft Thermoviscaelasticcharacterization and analysis of fiber Substructure coupling of analytical and test models for p 27 A87-18320 composite space structures an experimental structure p 19 A87-28577 KATZ, I. [ AD-A1750241 p 58 N87 19457 JOHNSON, R. R. Large structures and tethers working group HUNG, C. C. Development of Space Station strut design p 75 N87-20057 Properties and potential applications of brominated p 15 A87-11842 A unified approach to computer analysis and modeling P-100 carbon fibers p 51 A87-23702 JOHNSON, ROBERT R. of spacecraft environmental interactions HUNT, DAVID L. Seamless metal-clad fiber-reinforced organic matrix p 14 N87-20066 Comparison of multipleinput random and sine excitation composite structures and process for their manufacture KATZ, IRA methods for aerospace structures p 12 A87-28552 [ NASA-CASE-LAR-13562-1I p 57 N87-18613 The importance of accurate secondary electron yields Computationof total responsemode shapes using tuned JOHNSTON, 0. in modeling spacecraft charging p 46 A87-27018 frequency response functions p 30 A87-28569 Development of the Lens Antenna Deployment KAUFMAN, H. HUSSEY, J. Demonstration (LADD) shuttle-attachedflight experiment Model reference control of distributed parameter Space constructible radiator on-orbit assembly p7 N87-16022 systems: Application to the SCOLE problem p 58 A87-11359 JONES, 8. J. T. p 40 N87-17829 HYLAND, D. The tidal velocity field in the Local Supercluster KELLER, S. W. MAST llight system dynamic performance p 23 A87-11159 An overview of NASA's programs and plans p 35 N87-16032 JONES, BOBBIE L. [AAS PAPER 85-6471 p3 A87-18453 A preliminary logistics support concept for space-based KELLERMEIER. H. SDI assets The ESAtMBB unfurlable mesh antenna development I [AIAA PAPER 87-06891 p 61 A87-27616 for mobile services JONGEWARD, GARY [IAF PAPER 66-27] p2 A87-15818 The importance of accurate secondary electron yields IBRAHIM, A. M. KEROLA, DANA X. in modeling spacecraft charging p 46 A87-27018 Dynamics of the orbiter based flexible members In-orbit performance of Hughes HS 376 solar arrays JOSHI, S. M. p 27 A87-18324 p 44 A87-19872 Failure-accommodating control of large flexible KESSLER, D. J. On the Orbiter based deployment of flexible members spacecraft p 24 A87-13317 Examination of returned solar-max surfaces for [AAS PAPER 85.6731 p 16 A87-18489 Mathematical modeling of SCOLE configuration with impacting orbital debns and meteoroids IBRAHIM, S. R. line-of-sight error as the output p 40 N87-17824 p 55 N87-14386 A review of time domain modal test methods and JOSHI, SURESH M. KHOT, N. S. applications p 32 N87-10915 Computer-aided design and distributed system Improving the active vibrational control of large space IDO, Y. technology development for large space structures structures through structural modifications The electron irradiation test of thermal control matenal p 14 N87-16042 [IAF PAPER 86-2041 p 26 A87-15932 p 50 A87-18271 Robust multivariable controller design for flexible Optimal structural design with control gain norm IKEDA, K. spacecraft p 37 N87-16048 constraint Space exploitation and utilization. Proceedings of the JUANG, J.-N. [AIAA PAPER 87-00191 p 11 A87-22363 Symposium. Honolulu, HI, December 15-19, 1985 A slewing control experiment for flexible structures KIDA., T. p66 A87-18451 p 27 A87-17761 Dynamics formulation and simulation 01 multi-body IMAMURA, T. JUANG, JER-NAN space structures Degradation of spacecraft thermal shield materials by A sequential linear Optimization approach for controller [IAF PAPER 86.2381 p 26 A87-15957 irradiation of energetic particles p 18 A87 18273 design p 28 A87-23989 Numerical and experimental evaluation of poles and IYBERT, J. F. ldentilication of large space structures on orbit system zeros for large flexible space structures Effective modal parameters and truncabon effects in [ AD-AI 737561 p 14 N87-16058 p 27 A87-18322 structural dynamics p 31 N87-10897 JUANG, JES-NAN Local output-feedbackcontrol for large flexible space Frequency-shaped large-angle maneuvers INADA, TADAHICO structures p 27 A87-18323 [AIAA PAPER 87-01741 p A87-22462 Japanese laboratory proposal p 69 A8725753 28 Large-angle slewing of flexible spacecraft JUDD, D. INMAN, D. J. M. [AAS PAPER 85-8741 p27 A87-18490 A method of studying the behavior of composite Qualitative results for distributed systems with discrete KIMURA, H. materials in simulated space environments and stiffness with application to control Degradation of spacecraft thermal shield materials by p 53 N87-10940 [AD-A168622] p 33 N87-11829 irradiation of energetic particles p 18 A87-18273 INOUE, M. JUILLET, J. J. KINKEAD, REBECCA L Attitude control experiment for flexible spacecraft ARABSAT solar generator concept and in orbit Space spider crane performance p 43 A87-18075 p 27 A87-18320 [NASA-CASE-LAR-13411-lSB] p 73 N87-15259 IRACE, W. R. JUNKINS, JOHN KIRSCHKE, L. System concept for a moderate cost Large Deployable Identificationof large space structures on orbit The Kl-KZ interactionfor matrix splitting in unidirectional [AD-A1737561 p 14 N87-16058 Reflector (LDR) p 3 A87-18508 laminates of carbon fiber reinforced epoxy ITANAMI, T. JUNKINS, JOHN L. p 52 N87-10932 S band 3 5-m-diameter fan rib type deployable mesh A sequential linear optimization approach for controller KIRTLEY, J. L., JR. antenna for satellite use design p 28 A87-23989 Design of a superconducting alternator lor space-based [IAF PAPER 86-28] p 11 A87-15819 Optimal spacecraft rotational maneuvers power generation p 43 A87-18144 ITOH, KlYOHlKO p68 A8724625 KITAMURA..T. Rectenna composed of a circular microstrip antenna Optimization of closed loop eigenvalues: Maneuvering, Development of a 'Hingeless Mast' and its vibration control and structurelcontrol design iteration for p46 A87-25700 applications ITOH, Y. flexible spacecraft [IAF PAPER 86-2051 p 15 A87-15933 Study on solid surface, deployable antenna reflector [AD-A172716] p 34 N87-15263 KLEIN, M. p8 N87-16928 Engineering and software interfacing for thermal, IWAMOTO. K. structural and dynamic control related with spacecraft The electron irradiationtest of thermal control material K activities p 22 N87-16948 KLOMAN, ERASMUS H. p 50 A87-18271 KAI, T. IWATA, T. NASA The vision and the reality TNnCatiOn error estimation of a spacecraft model with [OP-5] p7 N87-15898 Research and development of a small sized space a flexible appendage p 16 A87-18321 manipulator KLUMPP, A. R. KAKAD, Y. P. [AAS PAPER 85-6601 p 60 A87-18481 Trajectory shaping rendezvous guidance Slew maneuver control of the Spacecraft Control p64 A87-13434 Laboratory Expenment (SCOLE) p 24 A87-13393 KNORR, M. J Slew maneuver dynamics of the Spacecraft Control Experience on the Olympus modal survey test Laboratory experiment p 40 N87-17825 p6 N87-10919 JAMISON, R. D. KAKITSUBO, Y. KO, K. Use of graphite/epoxy composites in spacecraft Simplex Mast - An extendible mast for space ELF generation in the lower ionosphere via collisional structures - A case study p 50 A87-19342 applications p3 A87-18242 parametric decay p 25 A87-14941

B-6 PERSONAL AUTHOR INDEX MAHEFKEY, E. 1.

KOCH, D. LARDNER, THOMAS J. LIWE, P. 8. Large space obseNatories of the 21st century Parametric investigation of factors influencing the The tidal velocity field in the Local Supercluster [AIAA PAPER 87-06361 p4 A8742751 mechanical behavior of large space structures p 23 A87-11159 KOFSKY, I. L. [AD-A1728801 p 38 N87-16056 LIN, JIGUAN GENE Spacecraft glows from surface-catalyzed reactions LAROSA, 1. Active damping of vibrations in SCOLE excited by p 43 A87-17368 Development of lightweightdimensionally stable carbon slewing p 40 N87-17831 KOITABASHI, M. fiber Composite antenna reflectors for the INSAT-I LIN, R. H. Degradation of spacecraft thermal shield materials by satellite p 56 N87-16936 Damping 1986 procedures, volume 2 irradiationof energetic particles p 18 A87-18273 LAUBE, H. [AD-AI 739501 p 73 N87-16366 KOLSCH, INGO Design and manufacturing aspects of tubular carbon LINDNER, D. K. Identification. applications, and dynamic analysis of fibre composite/titanium bonded joints Distributed control for COFS 1 p 36 N87-16043 nonlinear spacecraft components p 30 A87-28558 p 50 A87-16163 LINK, M. KONDOH, K. LEARY, TERRY Structural system identification using single and An explicit expression for the tangent-stiffness of a On incorporating damping and gravity effects in models multiaxial vibration test data p 20 N87-10911 finitely deformed 3-D beam and its use in the analysis of of structural dynamics of the SCOLE configuration LINTON, R. space frames p 19 A8720247 p 40 N87-17827 SSM atomic oxygen reactions on Kapton and silverized KOONS, H. C. LEBOUAR, Teflon p 55 N87-14388 A severe spacecraft-charging event on SCATHA in P. LONG, EDWARD R., JR. Analysis of rendezvous and docking in geostationary September 1982 Electron-radiationeffects on the ac and dc electrical Earth orbit. Rider lo comparison of future communications [AIAA PAPER 87.04751 p 45 A87-22659 properties and unpaired electron densities of three space segment concepts KOSUT, ROBERT L. aerospace polymers p 51 A87-21992 DM51-C/PL/FL/0099.82] p72 N87-14364 Adaptive control techniques for large space structures I LONG, SHEILA ANN T. [AD-AI73083 ] p 38 N87-16871 LEE, BETH Electron-radiation eflects on the ac and dc electrical KRECH, ROBERT H. Finite element model of SCOLE laboratory properties and unpaired electron densities of three Energetic oxygen atom material degradation studies configuration p 14 N87-17828 aerospace polymers p 51 A87-21992 [AIAA PAPER 87-01051 p 51 A87-24919 LEE, C. P. LOPEZ, G. A high flux source of energetic oxygen atoms for material HPSA High Power Solar Array study Development of mm-wave radiometer antenna degradation studies p 52 A87-27936 [ BAE-TP-8071] p 47 N87-11352 reflector p 47 N87-16941 KRIY, M. H. LEE, G. K. F. LU, s. c. Application of replicated glass mirrors lo large Nonlinear interfaces for acceleration-commanded Decentralized optimal control of large flexible segmented optical systems p 63 A87-11003 control of spacecraft and manipulators structures KUBIS, ANTHONY J., JR. p 25 A87-13494 [DE86-013906] p 41 N87-18101 Experimental study of active vibration control LEE, R. J. LUHMANN, H. J. [AD-A173144] p 41 N87-17845 Development of a continuous manufacturing method for Development status of the ERS-1 SAR antenna KUNKEL, B. a CFRP collapsible lube mast p9 N87-16939 Advanced opto-electronical sensors for autonomous [AERE-G-3898] p 54 N87-13572 LUKE, RICHARD T. Rendezvous-/Docking and proximity operations in space LEE, R. K. Architecture and design process for complex systems p 44 A87-19707 ltek optical technology in manufacturing and Space Station - A case study p 12 A87-25978 KURAL, M. H. metrology p 64 A87-11008 LUKICH, MICHAEL S. Development of Space Station strut design LEFEBVRE, J. D. Applicatlon of physical parameter identificatlonto finite p 15 A87-11842 Structural analysis, manufacturing and development element models p 35 N87-16026 KURIBAYASHI, Y. Status of large polarization sensitive dual-gridded LUM, H.. JR. Flexibility control of solar arrays based on slate reflectors p 22 N87-16937 Space missions for automation and robotics estimation by Kalman filtering p 26 A87-15450 technologies (SMART) program p 58 A87-13707 Control of solar battery arrays of spacecraft with LEGER, L J. consideration of the structural flexibility A consideration of atomic oxygen interactions with the LUMIA, R. Software architecture for manufacturing and space p 44 A87-18319 Space Station p 43 A87-17836 robotics KURIBAYASHI, YUTAKA LENZI, DAVID C. Flexibility control of solar battery arrays. II - Vibration Mast flight system beam structure and beam structural [AIAA PAPER 87.16871 p 12 A8741121 and attitudecontrol based on slate estimation of differential performance p 17 N87-16031 LUST, R. V. solar cell sensors p 45 A87-22968 LEONARD, C. L. Alternative approximation concepts for space frame KURIKI, K. Formationkeeping of spacecraft via differentialdrag synthesis p 19 A87-18940 On the initiation of SPS development [ NASA-CR-1719391 p 71 N87-13466 LUTZ, R. p 1 A87-12086 LEONARD, D. S. Advanced opto-electronical sensors for autonomous KURITZ, STEVEN P. Optimization of a truss member Rendezvous-/Docking and proximity operations in space Application of physical parameter identificationlo finite [IAF PAPER ST-86-17] p 15 A87-16145 p 44 A87-19707 element models p 35 N87-16026 LEONARD, DANIEL SHANE LYONS, MICHAEL 0. KUWAO, F. Optimization of a truss member Adaptive control techniques for large space structures A basic study for divided modal survey of future large [AIAA PAPER 87-00731 p 16 A8722395 [AD-A173083] p38 N87-16871 spacecraft p 27 A87-18241 LEONARD, P. M. KWAN, S. The Extendable Refractable Mast (ERM) thermal Acoustic cleaning of large space structures analysis: A heal radiation case study via the finite element M p 46 A87-26060 method p 22 N87-16949 LESOTA, S. K. MACCONE, C. Optimization of a microwave-beamenergy transmission Dynamics and Control Analysis Package (DCAP) An L channel p 46 A8729753 automated analysis and design tool for structural control LETCHWORTH, ROBERT of space structures p 39 N87-16947 LABRUYERE, G. COFS 3 Multibody dynamics and control technology MACCONOCHIE, IAN 0. Mechanical and control study of a 7 m offset unfurlable p 36 N87-16036 Space spider crane tracking antenna p 39 N87-16926 LEVI, MARK [NASA-CASE-LAR-13411-lSBl p 73 N87-15259 LAFRAMBOISE, J. G. The control theory of flexible and articulated MACHIDA. K. Spacecraft charging in the auroral plasma Progress spacecraft Research and development of a small-sized space toward understanding the physical effects involved [AD-A174880] p 42 N87-19434 manipulator p 48 N87-20080 LEWIS, J. S. [AAS PAPER 85-6601 p 60 A87-18481 LAGET, R. Gelling back on track in space p 1 A87-14375 MACKENZIE, C. W. The concentration principle applied to spacebome solar LEWIS, R. A. Development of a test procedure and facility for the arrays Application to the coorbiting plalform mission Gelling back on track in space p 1 A87-14375 investigationof a Canadarm joint brake anomaly Studies synthesis LI, FEIYUE p 59 A87-15191 Issues in modeling and controlling the SCOLE [SNIAS-975-CA/CG] p 75 N87-19814 MACKENZIE. J. D. configuration p 39 N87-17822 LAI, S. T. New materials for spacecraft stability and darnping A Optimal torque control for SCOLE slewing maneuvers Boom potential of a rotating satellite in sunlight feasibility study p 40 N87-17823 p 68 A8724198 [AD-A169826] p54 N87-12601 LIANG, R. H. LAJCZOK, M. Degradation studies of SMRM Teflon MAGNANI, PlERGlOVANNl Optimization of equivalent periodic truss structures p 56 N87-14392 A robotic system for dexterous tasks p 16 A8741175 LICATA, R. p 60 A8725757 LANGELAND, JENS On a simple vibration control design for large space Robot system for dexterous tasks (for space Space Station - The use of expert systems for structure models with uncertain parameters applications) planning p4 A87-25759 p 32 N87-10903 [ ETN-86-985621 p 61 N87-15472 LAPIERRE, H. LIEKE, M. MAHAMAD IBRAHIM, A. Demonstration of modal synthesis on an expenmental Antenna system alternatives for Data Relay Satellites Thermoplastic-basedcomposites with low CTE for space structure and its application to large spacecraft with multiple steerable beams structures and circuit board applications p 20 N87-10912 1 IAF PAPER 86-3491 p 43 A87-16041 p 49 A87-13097 LAPIERRE. HELENE LIGGElT, M. W. MAHEFKEY, E. T. Substructure coupling of analytical and test models for Evaluation of on-orbit cryogenic propellantdepot options Feasibility study of a low-temperature expandable an expenmental structure p 19 A8728577 for the orbital transfer vehicle D 63 A87-31133 megawall pulse power radiator p 66 A87-17841

8-7 MAIGRET, J.-P. PERSONAL AUTHOR INDEX

MAIGRET, J.-P. MAY, G. L. Improving the irradiation plus contamination tests. Behavioural analysis of adhesive-bonded structural Space exploitation and utilization; Proceedings of the Prestudy 2. Successive irradiations and synergics. Volume joints in space vehicles p 16 A87-20148 Symposium. Honolulu, HI, December 15-19. 1985 1 : Tests and conclusions p 66 A87-18451 [ CERT-4193-VOL-31 p 53 N87-10951 MALDOON, L. C. Protective coating for the KU-band reflector MAYNARD, NELSON C. Improving radiation plus contamination tests. Prestudy p 49 A87-13098 Plasma interactions with large spacecraft 2: Successive irradiations and synergics. Volume 2: p 48 N87-20063 Annexes. Annex 1: Detailed results. Annex 2: Control and MANDELL, M. J. MCCABE, S. J. improvement of optical measurements A unified approach to computer analysis and modeiing [ CERT-4193-VOL-4] p 53 N87-10952 of spacecraft environmental interactions Design of a superconducting alternator for space-based p 14 N87-20066 power generation p 43 A87-18144 MILLER, JAMES B. MCCAIN, H. Surface control system for the 15 meter hoop-column MANDELL, MYRON Software architecture for manufacturing and space antenna p 37 N87-16047 The importance of accurate secondary electron yields robotics MILLER, R. H. in modeling spacecraft charging p 46 A87-27018 [AlAA PAPER 87-16871 p 12 A87-31121 Factors influencing selection of space transportation MANHART, S. MCCRAY, MARK options Advanced opto-electronical sensors lor autonomous Use of support simulation modeling techniques in the [IAF PAPER 86-1081 p 65 A87-15871 Rendezvous-/Docking and proximity operations in space development of logistics support concepts for SDI orbital MILLER, R. K. p 44 A87-19707 platforms and constellations Structural concepts for large solar concentrators MANTELLI, M. B. H. [AIAA PAPER 87-06901 p 12 A87-27617 [ IAF PAPER 86-2021 p 15 A87-15930 Comparison of methods for the calculation of thermal MCELROY, P. M. Evaluation of on-line pulse control for vibration contact resistance of the first Brazilian satellite System concept for a moderate cost Large Deployable suppression in flexible spacecraft p 41 N87-17834 [ INPE-3864-TDL/217] p 21 N87-12596 Reflector (LDR) p 3 A87-18508 MILMAN, MARK MANTICA, P. G. MCGOWAN, PAUL E. System identification for modeling for control of flexible Study of frequency selective systems. Part 1: Preliminary COFS 3: Multibody dynamics and control technology structures p 36 N87-16040 investments on shapes and lattices: software p 36 N87-16036 MINGORI, 0. L. developments. Part 2: Interfacing of Politecnico FSS MCINTOSH, SAMUEL C., JR. Unified controllstructure design and modeling programs with MATRA reflector antenna software. Part Investigation of interactive structural and controller research 3: Application to MACS phase 2 TX antenna (MATRA) synthesis for large spacecraft [ NASA-CR-1799481 p 33 N87-I3478 [ANTINTEA/04.85] p 13 N87-13626 [AD-A172811 ] p 17 N87-16055 MINNICK, D. MARCHESE, P. MCKAY, D. S. Model reference control of distributed parameter The welding of aluminum alloys: A new technology in Analysis of micrometeorite material captured by the solar systems: Application to the SCOLE problem space application p 56 N87-17056 max satellite p 55 N87-14385 p 40 N87-17829 MARCHETTI, M. Examination of returned solar-max surfaces for MINOMO, M. Effects of curing stresses on composite structures impacting orbital debris and meteoroids S band 3.5-m-diameter fan rib type deployable mesh p 56 N87-16930 p 55 N87-14386 antenna for satellite use [ IAF PAPER 86-28] p 11 A87-15819 MARCO, J. MCKEIL, GORDON A new structure toward high precision large antenna Design improvement and radiation, contamination tests. Analysis of the ion spot phenomenon on beam-charged [IAF PAPER 86-201 p 15 A87-15929 Prestudy 1- Ultraviolet radiation acceleration, volume 1 dielectrics p 51 A87-21993 1 [CERT-4193-VOL-I ] p 53 N87-10949 Development of 30120 GHz satellite antenna MCNEIL, W. J. structures p 9 N87-16933 Design improvement and radiation contamination tests Boom potential of a rotating satellite in sunlight MIRTICH, MICHAEL J. Prestudy 1 : Ultraviolet radiation acceleration. Volume 2: p 68 A87-24198 Protection of solar array blankets from attack by low Appendix. detailed results MEINEL, A. 8. earth orbital atomic oxygen p 45 A87-19874 [CERT-4193-VOL-2] p 53 N87-10950 System concept for a moderate cost Large Deployable MISERENTINO, ROBERT Improving the irradiation plus contamination tests. Reflector (LDR) p 3 A87-18508 Pultrusion process development for long space boom Prestudy 2: Successive irradiations and synergics. Volume MEIROVITCH, L. models p 60 A87-20083 1: Tests and conclusions Parameter identification in distributed spacecraft MISHIMA, Y. [ CERT-4193-VOL-31 p 53 N87-10951 structures Fabrication of a carbon fibrelaluminium alloy composite Improving radiation plus contamination tests. Prestudy [AAS PAPER 85.6701 p 18 A87-18487 under microgravity p 48 A87-11384 2: Successive irradiations and synergics. Volume 2: Modal control of traveling waves in flexible structures MISRA, A. K. Annexes. Annex I: Detailed results. Annex 2: Control and p 29 A87-24552 On the Orbiter based deployment of flexible members improvement of optical measurements Identification and control of structures in space [AAS PAPER 85.6731 p 16 A87-18489 [CERT-4193-VOL-4] p 53 N87-10952 [NASA-CR-17981I I p 31 N87-10172 MISRA, MOHAN S. Improving radiation/contamination tests Modeling and identification of SCOLE Metallurgical characterization of the interfaces and the [CERT-419300/1-DERTS) p 54 N87-10954 p 23 N87-17826 damping mechanisms in metal matrix composites [AD-AI 734701 p 57 N87-17863 MARINOS, G. M. Control of SCOLE p 40 N87-17832 Passive damping augmentation lor flexible structures MITSUMA, H. p 36 N87-16044 MELTON, R. G. A basic study for divided modal survey of future large Decentralized control of multi-body spacecraft - A Passive stabilization for large space systems spacecraft p 27 A87-18241 numerical experiment [ NASA-CR-40671 p 42 N87-19755 MIURA, K. [AlAA PAPER 87-00181 p 29 A87-24902 MARSH, G. Development of a 'Hingeless Mast' and its Materials - The challenge of space p 50 A87-18867 MENYUK, C. R. applications MARTIN, J., 111 ELF generation in the lower ionosphere via collisional [IAF PAPER 86-2051 p 15 A87-15933 Decentralized control experiments on NASA's flexible parametric decay p 25 A87-14941 Concept of tension activated cable lattice antenna grid p 24 A87-13394 MERCIER, F. LlAF PAPER 86-2061 p 15 A87-15934 MARTIN, M. Prediction and correlation of structural response in Simplex Mast - An extendible mast for space Behavioural analysis of adhesive-bonded structural acoustic chambers p 20 N87-10907 applications p3 A87-18242 joints in space vehicles p 16 A87-20148 MESSAC, A. 2D-Array mission - Two-dimensionally deployable solar MARTINOVIC,ZORAN N. Dual structural-control optimization of large space cell array mission p 15 A87-18243 An analytical and experimental study of a control structures p 33 N87-11766 MIYAZAKI, Y. system's sensitivity to structural modifications METTLER, EDWARD The electron irradiation test of thermal control material p 30 A87-30294 System identification for modeling for control of flexible p 50 A87-18271 MARTY, D. structures p 36 N87-16040 MIZERA. P. F. Space vehicle design p 11 A87-10092 METZ, ROGER N. A severe spacecraft-charging event on SCATHA in MASRI, S. F. LEO high voltage solar array arcing response model September 1982 Evaluation of on-line pulse control for vibration [ NASA-CR-1800731 p 47 N87-16971 MOCKOVCIAK,[AIM PAPER JOHN,87-04751 JR. p 45 A87-22659 suppression in flexible spacecraft p 41 N87-17834 MIKULAS. M. M., JR. MASSONI, J. A. Sun shield Design, construction and utilization of a space station Space technologies and materials: A back and [ NASA-CASE-MSC-20162-11 p 74 N87-17036 look assembled from 5-meter erectable struts future perspectives p 52 N87-10934 MODI, V. J. [ NASA-TM-890431 p 6 N87-11827 MASUBUCHI, K. Dynamics of the orbiter based flexible members Remotely manipulated and autonomous robotic welding MIKULAS, MARTIN M., JR. p 27 A87-18324 fabrication in space p 59 A87-13714 Space spider crane On the Orbiter based deployment of flexible members Fundamentals and advances in the development of [NASA-CASE-UR-13411-lSB] p 73 N87-15259 [AAS PAPER 85-6731 p 16 A87-18489 remote welding fabrication systems p 49 A87-14312 MILKOVICH, SCOTT M. MONTGOMERY, R. C. MATIENZO, L. J. Space radiation effects on the thermo-mechanical Distributed control for COFS 1 p 36 N87-16043 Thermoplastic-basedcomposites with low CTE for space behavior of graphite-epoxy composites MOREL, D. E., JR. structures and circuit board applications p 51 A87-27178 Effects of thermal cycling on the mechanical and p 49 A87-13097 MILLAN. P. physical properties of a space qualified epoxy adhesive MATSUMOTO, K. Design improvement and radiation, contamination tests. p 19 A87-20082 Dynamics formulation and simulation of multi-body Prestudy 1: Ultraviolet radiation acceleration. volume 1 MORGAN, S. space structures [ CERT-4193-VOL-I ] p 53 N87-10949 Large space observatories of the 21st century [ IAF PAPER 86-2381 p 26 A87-15957 Design improvement and radiation contamination tests. [AIM PAPER 87-06361 p 4 A87-22751 MATSUSHITA. T. Prestudy 1: Ultraviolet radiation acceleration. Volume 2: MORGANTI. F. The electron irradiation test of thermal control material Appendix. detailed results Effects of curing stresses on composite structures P 50 A87-18271 [CERT-4193-VOL-2] p 53 N87-10950 p 56 N87-16930

8-8 PERSONAL AUTHOR INDEX PARK, J. J.

Contraves' antenna tip hinge mechanism for Selenia NICHOLSON, D. W. OLBERT, S. Spazio's 20130 GHz antenna p 74 N87-16944 Damping 1986 procedures, volume 2 Radiation from large space structures in low earth orbit MOROSOFF. WILLIAM 1 AD-AI 739501 p 73 N87-16366 with induced ac currents Space logistics support lo military space systems NIEDBAL, N. [AIAA PAPER 87-06121 p 68 A87-22738 [AIAA PAPER 87-06941 p 69 A87-27621 Modal analysis technique used in Germany for OLSEN, RICHARD C. MOSS, FRANK W. aerospace Structures p 30 A87-28544 Controlling and monitoring the space-station plasma A preliminarylogistics support concept for space-based NIELSEN, 0. interaction: A baseline for performing plasma experiments SDI assets COntraVeS' antenna tip hinge mechanism for Selenia and using advanced technology p 76 N87-20079 [AIM PAPER 87.06891 p 61 A87-27616 Spazio's 20130 GHz antenna p 74 N87-16944 OREFICE. M. MURAYAMA, K. NINOMIYA, K. Dielectric support structures for spacecraft antenna Effect of electron-beam radiation on graphite epoxy Satellite motion analysis via laser reflector pattern feeds p 17 N87-16931 composites p 49 A87-13071 processing for rendez-vous and docking ORTA, R. MURPHY, 0. Study of frequency selective systems. Part 1: Preliminary [IAF PAPER 86-06] p 65 A87-15805 Large structures and tethers working group investments on shapes and lanices; software NOMURA, T. p 75 N87-20057 developments. Part 2: Interfacing of Politecnco FSS Space exploitation and utilization. Proceedings of the MURPHY, GERARD programs with MATRA reflector antenna software. Part Symposium. Honolulu, HI, December 15-19, 1985 Satellite construction p 61 A87-27454 3: Application lo MACS phase 2 TX antenna (MATRA) p A87-18451 MUSALEM, A. 66 [ANTlNTEA/04.85] p 13 N87:13626 Model reference control of distributed parameter NORRIS, GREGORY A. Om,VIVECA C. systems Application lo the SCOLE problem Regulation of the SCOLE configuration Space commerce '86;Proceedings of the International p 40 N87-17829 p 41 N87-17833 Conference and Exhibition on the Commercial and MYERS, DALE NORRIS, M. A. Industrial Uses of Outer Space, Montreux. Switzerland, Second AlAAlNASA USAF Symposium on Automation. Parameter identification in distributed spacecraft June 16-20. 1986 p 69 A87-29401 Robotics and Advanced ComDutina.I for the National Soace structures OTTEN, T. Program [AAS PAPER 85.6701 p 18 A87-18487 MAST flight system dynamic perlormance [AlAA PAPER 87-16551 p70 A87-31112 Modeling and identificationof SCOLE p 35 N87-18032 MYERS. J. K. p 23 N87-17826 OTTERSTEDT, P. J. Multiarm collision avoidance using the potential-field Control of SCOLE p 40 N87-17832 Space constructible radiator on-orbit assembly approach p 59 A87-13715 NOZETTE, S. p 58 A87-11359 Modeling and simulation of large scale space systems OUALI, Y. Strategic planning implications Application of dynamic elements and continuum N [ IAF PAPER 86-4531 p2 A87-16105 methods to large space structures, volume 1 [ ED/82-362/RD-VOL-l] p 22 N87-13484 NAGATOMO, M. Application of dynamic elements and continuum International Symposium on Space Technology and 0 methods lo large space structures. volume 2 Science. 14th. Tokyo Japan, May 27-June 1. 1984, IED/82-362/RD-VOL-2] p 34 N87-13485 Proceedings p 66 A87-18201 OAKES, KEVIN F. 02, H. Collisional probability in space and the debris Dynamic analysis of satellites with deployable hinged Optimal structural design with control gain norm environment in future p 66 A87-18247 appendages constraint NAHRA, HENRY K. IAIAA PAPER 87-00201 p 27 A87-22364 [AlAA PAPER 87-00191 p 11 A87-22363 Protection of solar array blankets from anack by low OBRIEN, THOMAS P. OZGUNER, U. earth orbital atomic oxygen p 45 A87-19874 A preliminary logistics support concept for space-based Decentralized control experiments on NASA's flexible NAINIGER, JOSEPH J. SDI assets grid p 24 A87-13394 NASA Growth Space Station missions and candidate [AIAA PAPER 87.06891 p 61 A87-27616 nuclear/solar power systems p3 A87-21807 ODA, K. L NAIR, P. S. Degradation studies of SMRM Teflon P Vibration data reduction for design, analysis and testing p 56 N87-14392 of spacecrafl p 23 A87-10901 ODOM, PAT R. PACE, A. NAKATANI. 1. A preliminary logistics support concept for space-based Developmentof lightweightdimensionally stable carbon Satellite motion analysis via laser reflector pattern SDI assets fiber composite antenna reflectors for the INSAT-1 processing for rendez-vous and docking [AIM PAPER 8706891 p 61 A87-27616 satellite p 56 N87-16936 ODONNELL, I(. J. [IAF PAPER 86-06] p 65 A87 15805 PADULA, SHARON L. A procedurefor calculating the damping in multi-element NAKAYAMA, K. Integrated structure electromagnetic optimization of space structures Research and development of a small-sized space large space antenna reflectors [IAF PAPER 86.2031 p 26 A87-15931 manipulator [NASA-TM-891IO] p 48 N87-18598 OERY, H. [AAS PAPER 85-6601 p60 A87-18481 PAGANA, E. Transient external loads or interlace forces NAKAZAKI, K. Prediction the electrical performance of Inflatable reconstructed from structural response measurements of Effect of electron-beam radiation on graphite epoxy Space RigidizedStructure (ISRS) offset antenna reflectors p 20 N87-10910 composites p 49 A87-13071 and correlation with RF measurements OGAWA, YASUTAKA NASH, WILLIAM A. p 47 N87-16943 Rectenna composed of a circular microstrip antenna Parametric investigation of factors influencing the p 46 A87-25700 PAILLOUS. A. mechanical behavior of large space structures OHATA, K. A method of studying the behavior of composite [AD-A172880] p 38 N87-16056 A new Structure toward high precision large antenna materials in simulated space environments NATORI. M. [ IAF PAPER 86-201] p 15 A87-15929 p 53 N87-10940 Instability of rotating blades in space OHGANE, TAKE0 Design improvementand radiation, contaminationtests. [ IAF PAPER 86-2421 p 65 A87-I5959 Rectenna composed of a circular microstrip antenna Prestudy I: Ultraviolet radiation acceleration, volume 1 Simplex Mast - An extenaiDle mast for space p 46 A87-25700 [CERT-4193-VOL-1I p 53 N87-10949 applications p3 A87-18242 OHKAMI, Y. Design improvement and radiation Contamination tests. 2D-Array mission - Two-dimensionallydeployable solar Dynamics formulation and simulation of multi-body Prestudy 1: Ultraviolet radiation acceleration. Volume 2: cell array misson p 15 A87-18243 space structures Appendix, detailed results NATORI, M.. [IAF PAPER 136-2361 p 26 A87-15957 [CERT-4193-VOL-2] p 53 N87-10950 DeVelODment of a 'Hinaeless Mast' and its Truncation error estimation of a spacecrafl model with Improving the irradiation plus contamination tests. applications a flexible appendage p 16 A87-18321 Prestudy 2: Successive irradiationsand synergics. Volume IlAF PAPER 86-2051 p 15 A87-15933 Numencal and experimental evaluation of poles and 1: Tests and conclusions NAYFEH, ADNAN H. system zeros for large flexible space structures [CERT-4193-VOL-3] p 53 N87-10951 Shear deformationplate COntinUa of large double layered p 27 A87-18322 Improving radiation plus contamination tests. Prestudy space structures p 16 A87-28882 Local output-feedback control for large flexible space 2: Successive irradiations and synergics. Volume 2: NEIN, M. structures p 27 A87-18323 Annexes. Annex 1: Detailed results. Annex 2: Control and Large space observatories of the 21st century Large-angleslewing of flexible spacecrafl improvement of optical measurements [AAS PAPER 85-6741 p 27 A87-18490 [AIM PAPER 87-06361 p4 A87-22751 [ CERT-4193-VOL-41 p 53 N87-10952 OHTOMO, I. NEMAT-NASSER, S. Improving radiation/contamination tests S band 3.5-m-diameterfan rib type deployable mesh Instability of rotating blades in space [ CERT-419300/1-DERTSI p 54 N87-10954 antenna for satellite use PALMADESSO, P. [ IAF PAPER 86-2421 p 65 A87-15959 [IAF PAPER 86-26] p 11 A87-15819 ELF generation in the lower ionosphere via collisional NERHEIY, N. M. OKAMOTO, 0. parametric decay p 25 A87-14941 Sensor technology for advanced space missions Dynamics formulation and Simulation of multi-body p 73 N87-16027 space structures PANDEY, AJAY E. NGUYEN, C. C. [IAF PAPER 86.2381 p 26 A87-15957 Finite-element thermal-structural analyses of a Distnbuted active control of large flexible space Numerical and experimental evaluation of poles and cable-stiffened orbiting antenna p 19 A87-25687 structures system zeros for large flexible space structures PANOSSIAN, HAGOP V. [ NASA-CR-I79941 1 p 33 N87-13476 p 27 A87-18322 Modal space design for active vibration control of large NGUYEN, P. P. OKAZAKI. K. flexible structures P 30 A87-28537 Rendezvous and docking verification and in-orbit Development of a 'Hingeless Mast' and its PARK, J. J. demonstration applications Results of examination of materials from the solar [ IAF PAPER 66-07] p 65 A87-I 5806 [ IAF PAPER 86-2051 p 15 A87-15933 maximum recovery mission P 54 N87-I4383 PARK, K. C. PERSONAL AUTHOR INDEX

PARK, K. C. POTTER, A. E. ROCHE, A. Wave dispersion mechanisms in large space Examination of returned solar-max surfaces for Adhesive bonding of aerospace materials - Surface structures impacting orbital debris and meteoroids characterizataon of metallic adherends [AD-A173967] p 38 N87-16059 p 55 N87-14386 p 51 A87-20149 PARKER, L. W. PRASAD, M. G. ROEDER, J. L. Spacecraft charging in the auroral plasma: Progress Damping 1986 procedures, volume 2 A severe spacecraft-charging event on SCATHA in toward understandingthe physical effects involved [AD-AI739501 p 73 N87-16366 September 1982 p 48 N87-20080 PRINS, J. J. M. [AIAA PAPER 87.04751 p 45 A87-22659 Rendezvous and docking and space robotics proximity PASSERON, L. ROEDERER, A. operations. Part Executive summary Mechanical and control study of a 7 m offset unfurlable 5: L-band antennas for regional mobile communication tracking antenna p 39 N87-16926 [ NLR-TR-85099-Ul p 62 N87-19441 Satellites p 47 N87-15377 PASTORINO. M. PRITCHARD, E. B. ROMAND, M. Mechanical and control study of a 7 m offset unfurlable Space Station design for growth Adhesive bonding of aerospace materials - Surface tracking antenna p 39 N87-16926 [ IAF PAPER 86-461] p2 A87-16110 characterization of metallic adherends PAUVERT, C. PRONK, C. N. A. Rendezvous and docking (RVD) guidance simulation Rendezvous and docking and space robotics proximity p 51 A87-20149 program, rider 2 operations. Part 5: Executive summary ROSEN, 1. G. [MATRA-EPT/DT/VrOS8/012] p 72 N87-14359 [ NLR-TR-85099-UI p 62 N87-19441 The identification of a distributed parameter model for PEARSON, J. PRUCZ, JACKY a flexible structure Active Control Evaluation for Spacecraft (ACES) Experimental characterization of passively damped [NASA-CR-1781991 p 13 N87-14059 p 34 N87-16019 joints for space structures p 29 A87-25680 RUSSELL, R. A. PEEBLES, JAMES H. PRUCZ, JACKY C. A space station Structures and Assembly Verification Passively damped joints for advanced space Passively damped joints for advanced space Experiment, SAVE structures structures [ NASA-TM-890041 p5 N87-10170 [ AD-A1 749141 p 42 N87-19435 [ AD-A17491 41 p 42 N87-19435 RUTLEDGE, SHARON K. PELENC, L. PYLE, JON S. Protection of solar array blankets from attack by low ARABSAT solar generator concept and in orbit COFS 2: 3-0 dynamics and controls technology earth orbital atomic oxygen p 45 A87-I9874 performance p 43 A87-18075 p 35 N87-16035 High power rigid solar array [SNIAS-917A-CA/CGl p 47 N87-13864 S PELISCHEK, T. E. R Foldable self-erecting joint SABLE. C. RACHNIKOV, A. V. [ NASA-CASE-MSC-20635-1] p 17 N87-14373 Design improvementand radiation,contamination tests. Optimizationof a microwave-beamenergy transmission PENNINGTON, JACK E. Prestudy 1: Ultraviolet radiation acceleration, volume 1 channel p 46 A87-29753 Space spider crane [CERT-4193-VOL-l] p 53 N87-10949 [NASA-CASE-LnR-134ll-lSB] p 73 N87-15259 RADCLIFFE, R. L. Utilization. testing and maintenance of multimission Design improvement and radiation contamination tests. PERETTI, L F. Prestudy 1. Ultraviolet radiation acceleration. Volume 2: hardware p 70 A87-29466 Spacecraft structural model improvementby modal test Appendix, detailed results results p 20 A87-31225 RAITT, J. Large structures and tethers working group [CERT-4193-VOL-2] p 53 N87-10950 PERI, FRANK, JR. Improving the irradiation plus contamination tests. Surface control system for the 15 meter hoop-column p 75 N87-20057 RALLO, ROSEMARY A. Prestudy 2: Successive irradiationsand synergtcs. Volume antenna p 37 N87-16047 1: Tests and conclusions PETERSON, G. P. Description of the Spacecraft Control Laboratory Experiment (SCOLE) facility [CERT-4193-VOL-3] p 53 N87-10951 Thermal control systems for spacecraft Improving radiation plus contamination tests. Prestudy instrumentation p 19 A87-31213 [ NASA-TM-890571 p8 N87-16848 Description of the Spacecraft Control Laboratory 2: Successive irradiations and synergics. Volume 2: PFEIFER, K. Annexes. Annex 1: Detailed results. Annex 2: Control and Experiment (SCOLE) facility p 10 N87-17837 Stress and deformation analysis of thermally loaded light improvement of optical measurements weight composite structures RANEY. J. P. [CERT-4193-VOL-4] p 53 N87-10952 [IAF PAPER 663-2121 p 18 A87-15939 A space station Structures and Assembly Verification Experiment, SAVE SACH, E. D. PHILLIPS, T. E. Influence of fiber orientation and boundary conditions Erosion studies on Solar Max samples [ NASA-TM-890041 p 5 N87-10170 RATH, A. K. on the dynamic behavior of a cylindricallytelescoping solar p 50 A87-19343 array (INTELSAT 6) p 32 N87-I0925 Studies of erosion of solar may samples of Kapton and Analysis of long thin-walled tubes p 20 N87-10895 RAUPP. H. SACHS, WERNER Teflon p 55 N87-14384 The dynamical qualification of present and future PIMENTEL, K. D. Giotto spacecraft high gain antenna mechanical design and development p 18 N87-16938 spacecraft structures p 30 A87-29368 Preliminary findings for integrated modeling and SADIN, S. R. simulation of directed energy weapons REAU, J. P. Developmentof a lightened structure for the GSRB solar Technologies for affordable access to space [DE86-011636] p 10 N87-17846 [IAF PAPER 86-4421 p2 A87-16096 PINSON, E. D. generator p 17 N87-10927 REDDY, A. D. SAGALYN, RITA C. Discrete mechanism damping effects in the solar array Plasma interactions with large spacecraft flight experiment p 38 N87-16341 Experimental characterization of passively damped joints for space structures p 29 A87-25680 p 48 N87-20063 Damping 1986 procedures, volume 2 SAKAMAKI, M. [AD-AI739501 p 73 N87-16366 REDDY, A. S. S. R. Simplex Mast - An extendible mast for space PLAGNE, A. Issues in modeling and controlling the SCOLE applications p3 A87-18242 Developmentof a lightened structure for the GSRB solar configuration p 39 N87-17822 20-Array mission - Two-dimensionallydeployable solar generator p 17 N87-10927 REHFIELD, L. W. cell array mission p I5 A87-18243 PLOTARD, P. Experimental characterization of passively damped SAMBASIVA RAO, M. A method of studying the behavior of composite joints for space structures p 29 A87-25680 Vibration data reduction for design, analysis and testing matenals in simulated space environments REIMAN, A. of spacecraft p 23 A87-10901 p 53 N87-10940 ELF generation in the lower ionosphere via collisional SAMIR, U. POH. S. parametric decay p 25 A87-14941 Large structures and tethers working group Optimum vibration control of flexible beams by REISS, AMY C. p 75 N87-20057 piezo-electric actuators High voltage solar array plasma protection techniques SAMIR, URI [NASA-CR-180209] p 42 N87-18880 p 45 A87-19878 The interaction of small and large spacecraft with their PONTOPPIDAN, K. environment p 10 N87-20064 The ESAlMBB unfurlable mesh antenna development REYES, 2. SAN MARTIN, A. M. for mobile services Electrically conductive organic polymers for advanced applications p 50 A87-18554 Design of robust failure detection filters [IAF PAPER 86-27] P2 A87-15818 p 24 A87-13395 PONTOPPIDAN. KNUD RIES. HEIDI R. SANBORN, J. A. Simple approach for evaluating mechanical reflector Electron-radiation effects on the ac and dc electrical properties and unpaired electron densities of three Effects of thermal cycling on the mechanical and antenna distortions P 39 N87-16942 physical properties of a space qualified epoxy adhesive PONZI, U. aerospace polymers p 51 A87-21992 p 19 A87-20082 Dielectric support structures for spacecraft antenna RIVACOBA, J. SANDFORD, THADDEUS leers A Sener mechanism: Fine adjustment mechanism for P 17 N87-16931 Flight Dynamics Laboratory overview Thermomechanical characteristics of dichroic the Far Infrared and Submillimeter Space Telescope p7 N87-16018 (FIRST) (F f F) p 74 N87-16946 subreflectors P 22 N87-16952 SANGER, G. M. POSPlSlL, M. ROBERTSHAW, H. H. Large optics technology; Proceedings of the Meeting, Compact SPS for lunar development A slewing control expenment for flexible structures San Diego, CA. August 19-21, 1985 [IAF PAPER 86.1561 P 2 A87-15904 p 27 A87-17761 [SPIE-571] p 63 A87-10997 Moon for terrestrial energetics ROBINSON, 0. A. SANTINI, P. [IAF PAPER 86.4561 P2 A87-16108 Analysis of micrometeoritematerial captured by the solar Nonlinear effects in thermal conduction problems of POSPISILOVA, L max satellite p 55 N87-14385 large space structures Compact SPS for lunar development ROBLEE, J. W. [IAF PAPER 86.2081 p 18 A87-15936 [IAF PAPER 86-1561 P2 A87-15904 Preliminary findings for integrated modeling and SANTOS-MASON, B. Moon for terrestrial energetics Simulation of directed energy weapons Preliminary results of SMM exposed aluminized Kapton [IAF PAPER 86.4561 P2 A87-16108 [DE86-011636] p 10 N87-17846 and silvered Teflon p 55 N87-14389 B-10 PERSONAL AUTHOR INDEX SWANSON, P. N.

SATKIEWICZ, F. G. SGUBINI, S. SOILEAU. K. M. Studies of erosion of solar max Samples of Kapton and Computational methods in elastic penodic structures Path-constrainedrendezvous - Necessary and sufficient Teflon p 55 N87-14384 analyses p 32 N87-10901 conditions p66 A87-17834 SATO, K. Dielectric support structures for spacecraft antenna SOLMON, 0. Collisional probability in space and the debris feeds p 17 N87-16931 Manned Mars mission Earth-To-Orbit(ETO) delivery and environment in future p 66 A87-18247 Thermomechanical characteristics of dichroic orbit assembly of the manned Mars vehicle p9 N87-17746 SATO, S. subreflectors p 22 N87-16952 SONODA, K. Development of a 'Hingeless Mast' and its SHAH, T. K. Effect of electron-beam radiation on graphite epoxy applications Thermoplastic-based compositeswith low CTE for space composites p 49 A87-13071 [ IAF PAPER 86-2051 p 15 A87-15933 structures and circuit board applications SOROCKY, S. J. SATYANARAYANA, K. p 49 A87-13097 Synthesis of control laws for optimally designed large Demonstration of modal synthesis on an experimental SHEPARD, G. DUDLEY structure and its application to large spacecraft space structures Transient modal tuning p 30 A87-28578 [IAF PAPER 86-2461 p 26 A87-15963 p 20 N87-10912 SHIMOJI, S. SAW, K. C. SOROCKY. STEPHEN J. Degradation of spacecraft thermal shield materials by Reduced modeling and analysis of large repetitivespace Substructure coupling of analytical and test models for irradiation of energetic particles p 18 A87-18273 structures via continuumldiscreteconcepts an experimental structure p 19 A87-28577 [IAF PAPER ST-86-08] p 65 A87-16141 SHIPLEY, JOHN W. SOULE, SAM SCHAEFER, B. Description of the Mast Flight System Comparison of multiple input random and sine excitation Wave-absorbing controllers for a flexible beam p8 N87-16030 methods for aerospace structures p 12 A8728552 p 28 A87-23986 Mast flight system beam structure and beam structural SPARKS, DEAN SCHAFFAR. E. performance p 17 N87-16031 Finite element model of SCOLE laboratory Mechanical and control study of a 7 m offset unfurlable SHIRAKI, K. configuration p 14 N87-17828 tracking antenna p 39 N87-16926 A basic study for divided modal survey of future large STARKS, S. A. SCHAMEL, GEORGE spacec r a ft p 27 A87-18241 An introduction to the concept of robot factors and its An analytical and experimental study of a control SIDMAN, MICHAEL DAVID application to Space Station automation system's sensitivity to structural modifications Adaptive control of a flexible structure p 58 A87-13712 p 30 A87-30294 p 39 N87-17449 STAVRINIDIS, C. SCHLOEGEL, W. T. SIFFRE, J. Deployment analysis of the Olympus Astromast and Spacecraft Dynamics and Control Program at AFRPL Design improvement and radiation. contaminationtests. comparison with test measurements p 61 A87-31220 p34 N87-16017 Prestudy 1: Ultraviolet radiation acceleration, volume 1 Design and verification activities and requirements for SCHMID, M. [CERT-4193-VOL-l] p 53 N87-10949 spacecraft structures p20 N87-10890 Extendable retractable telescopic mast for deployable Design improvement and radiation contamination tests. Engineering and software interfacing for thermal, structures p8 N87-16323 Prestudy 1: Ultraviolet radiation acceleration. Volume 2: structural and dynamic control related with spacecraft SCHMIT, L. A. Appendix, detailed results activities p 22 N87-16948 Alternative approximation concepts for space frame [CERT-4193-VOL-21 p 53 N87-10950 STELLA, 0. synthesis p 19 A87-18940 Improving the irradiation plus contamination tests. Contraves' antenna tip hinge mechanism for Selenia SCHNEIDER, WILLIAM C. Prestudy 2 Successive irradiations and synergics. Volume Spazio's 20130 GHz antenna p 74 N87-16944 Mobile remote manipulator system for a tetrahedral 1: Tests and conclusions STENNE, E. truss [CERT-4193-VOL-3] p 53 N87-10951 The Extendable Refractable Mast (ERM) thermal [ NASA-CASE-MSC-20985-1I p 61 N87-15260 Improving radiation plus contamination tests. Prestudy analysis: A heat radiation case study via the finite element SCHOCK, R. W. 2: Successive irradiations and synergics. Volume 2: method p 22 N87-16949 Solar array flight dynamic experiment Annexes. Annex 1: Detailed results. Annex 2 Control and STERN, S. A. [ NASA-TP-25981 p7 N87-12581 improvement of optical measurements Path-constrainedrendezvous - Necessary and sufficient SCHOEDEL, H. J. [CERT-4193-VOL-4] p 53 N87-10952 conditions p 66 A87-17834 Giono spacecraft high gain antenna mechanical design SILVERBERG, L M. STEVENS, N. JOHN and development p 18 N87-16938 Vibration suppression of planar truss structures Utilizing High voltage system: Plasma interaction summary SCHRAMM, L. S. uniform damping control p 25 A87-13458 p 48 N87-20069 Analysis of micrometeoritematerial captured by the solar SIMO, J. C. STEWART, ERIC max satellite p 55 N87-14385 On the dynamics of flexible beams under large Overall On incorporatingdamping and gravity effects in models Examination of returned solar-max Surfaces for motions - The plane case. I, II of structural dynamics of the %OLE configuration impacting orbital debris and meteoroids [ASME PAPER 86-WAIAPM-411 D 28 A8723212 p 40 N87-17827 p 55 N87-14386 SINGH, R. P. STINSON, MELANIE SCHUESSLER, R. Dynamics and Control Analysis Package (DCAP): An Design and analysis of a keel latchfor use on the Hubble Features and technologies of ERS-1 (ESA) and X-SAR automated analvsis and design tool for structural control Space Telescope p 62 N87-16326 antennas p9 N87-17152 of space structures p 39 N87-16947 STONE, NOBIE H. SCHULTZ, R. A. SINGH, S. N. The interaction of small and large spacecraft with their Examination of returned solar-max surfaces for Nonlinear attitude control of elastic spacecraft-antenna environment p 10 N87-ZOO64 impacting orbital debris and meteoroids p 25 A87-13433 system STONIER, R. p 55 N87-14386 SINGH, SAHJENDRA N. Development of lightweight dimensionally stable carbon SCHUU, H. H. Nonlinear anitude control of flexible spacecraft under fiber composite antenna reflectors for the INSAT-I Large wheel actuators definition study disturbance torque p 29 A87-24049 satellite p 56 N87-16936 [TELDIX-15-020-880] p 33 N87-11834 SIPPEL, R. STUART, 0. G. SCHUSTER, J. R. Development status of the ERS-1 SAR antenna Factors influencing selection space transportation Evaluationof on-orbit cryogenic propellantdepot options p9 N87-16939 of options for the orbital transfer vehicle p 63 A87-31133 SIVO, JOSEPH [IAF PAPER 86-1081 p65 A87-15871 SCHWARTZ. H. J. Cornmunations technology p 46 A87-30893 The potential impact of new power system technology SKELTON, ROBERT E. STUCKEY. W. K. on the design of a manned Space Station Regulation of the SCOLE configuration Analysis of normal and transparent silver Teflon p 44 A87-18342 p 41 N87-17833 p 55 N87-14391 SCIACOVELLI, 0. SKULLNEY, W. E. STUIVER, W. Dynamics and Control Analysis Package (DCAP): An Use of graphitelepoxy composites in spacecraft Optimal control of component deployment for the space automated analysis and design tool for structural control structures - A case study p 50 A87-19342 radiotelescope system of space structures p 39 N87-16947 SLABINSKI, V. J. [AAS PAPER 85-6831 p16 A87-18495 SCIALDONE, J. J. Efficiency eccentricity control using continuous, SULLA, JEFF An estimate of the outgassing of space payloads and vectored thrusting for satellites with large arealmass Distributed control for COFS 1 p 36 N87-16043 its gaseous influence on the environment ratios p 63 N87-10151 SULLIVAN, 8. J. p 48 A87-11355 SLIMAK, L K. S. Thermoviscoelasticcharacterization and analysisof fiber SCOTT, A. DON Spacecraft Dynamics and Control Program at AFRPL composite space structures Dynamic analysis of the large deployable reflector p34 N87-16017 [AD-A1750241 p 58 N87-19457 [ NASA-TM-890561 p37 N87-16050 SLIWA, NANCY ORLANDO SULLIVAN, J. SEKIMOTO, S. A flexible telerohtic system for space operations Large structures and tethers working group A basic study for divided modal survey of future large p 60 A87-23229 p 75 N87-20057 spacecraft p 27 A87-18241 SLOGGETT, 0. R. SUN, C. T. SELVARAJ, 1. The role of expert systems on Space Station Identification of large space structures on orbit Solar array mechanisms for Indian satellites, APPLE, p4 A8725758 [ AD-A1737561 p 14 N87-16058 IRS and INSAT-IITS SOBIESKI, J. SUTTER, THOMAS R. [IAF PAPER 86.1421 p 11 A87-15893 Recent Expenences in Multidisciplinary Analysis and Multidisciplinary analysis of actively controlled large SENGER, K. H. Optimization, part 1 flexible spacecraft p 37 N87-16045 Debonding analysis of thermally stressed [ NASA-CP-2327-PT-1I p 71 N87-11717 fiber-reinforced composite materials p 52 N87-10933 Recent Experiences in Multidisciplinary Analysis and SUZUKI, 1. Fabricationof a cahnfibreIaluminium alloy composite SESAK, J. R. Optimization. part 2 under microgravity p 48 A87-11384 Passive damping augmentation for flexible structures [ NASA-CP-2327-PT-2I p 71 N87-11750 p36 N87-16044 SOGA, H. SWANSON, P. N. Passive stabilization for large space systems Large-angleslewing of flexible spacecraft System concept for a moderate cost Large Deployable [ NASA-CR-40671 p 42 N87-19755 [AAS PAPER 85-6741 p 27 A87-18490 Reflector (LDR) p3 A87-18508 B-11 SWANSON, PAUL N. PERSONAL AUTHOR INDEX

SWANSON, PAUL N. TODA, Y. VIGNERON, F. R. The large deployable reflector A NASA Research and development of a small-sized space Demonstration of modal synthesis on an experimental submillimeter-infrared orbiting observatory manipulator structure and its application to large spacecraft p 9 N87-17571 [AAS PAPER 85.6601 p 60 A87-18481 p 20 N87-10912 SYKES, G. F. TOLIVAR, A. F. VIGNERON, FRANK R. Space radiation effects on the dimensional stability of System concept for a moderate cost Large Deployable Substructure coupling of analytical and test models for a toughened epoxy graphite composite Reflector (LDR) p 3 A87-18508 an expenmental structure p 19 A87-28577 p 49 A87-11847 TOMPKINS, S. S. VISENTINE, J. T. The effects of radiation on the interlaminar fracture Effects of thermal cycling on graphie-fiber-reinforced A consideration of atomic oxygen interactions with the 6061 aluminurn toughness of a graphitelepoxycomposite Space Station p 43 A87-17836 [ NASA-TP-26121 p 52 N87-10184 p 50 A87-19122 VON ALT, C. TORRE, C. N. SYKES, GEORGE F. Fundamentals and advances in the development of Evaluation of on-orbitcryogenic propellantdepot options Space radiation effects on the thermo-mechanical remote welding fabrication systems p 49 A87-14312 for the orbital transfer vehicle p 63 A87-31133 behavior of graphite epoxy composites VON FLOTOW, A. H. TRENOUTH, J. M. p51 A8727178 Wave-absorbing controllers for a flexible beam Development of a test procedure and facility for the SZCZUR, M. p 28 A87-23986 investigationof a Canadarm joint brake anomaly Proceedings of the 5th Annual Users Conference VORBRUGG, H. p 59 A87-15191 [ NASA-CP-23991 p 70 N87-10720 The ESAlMBB unfurlable mesh antenna development TRIPATHI, V. for mobile services SZUSZCZEWICZ, EDWARD P. ELF generation in the lower ionosphere via collisional [IAF PAPER 86-27] p2 A87-15818 Technical issues in the conduct of large space platform parametric decay p 25 A87-14941 Experience gained by sector model testing of an experiments in plasma physics and geoplasma sciences TRUBERT, M. unfurlable meshlrib antenna p 14 N87-16925 p 75 N87-20071 Loads analysis for the Galileo spacecraft vu-auoc, L. p 21 N87-10926 On the dynamics of flexible beams under large overall TRUDELL, R. W. motions - The plane case I, II T Experimental characterization of passively damped [ASME PAPER 86-WAlAPM 411 p 28 A87-23212 joints for space structures p 29 A87-25680 TAKAHASHI, T. TRUDELL, RICHARD W. A basic study for divided modal survey of future large Passively damped joints for advanced space W spacecraft p 27 A87-18241 structures TAKANO, T. [ AD-At 749141 p 42 N87-19435 WADA. 8. K. A concept of the Energy Storable Orbital Power Station TSOU. J.-W. Spacecraft load, design and test philosophies (ESOPS) A laboratory experiment in controllstructure p6 N87-10922 [IAF PAPER 86-1491 p 42 A87-15898 interaction p 24 A87-13392 Damping 1986 procedures, volume 2 TALCOlT, RONALD C. TSUCHIYA, K. [AD-At 739501 p 73 N87-16366 Description of the Mast Flight System Attitude control experiment for flexible spacecraft WAGNER, R. p8 N87-16030 p 27 A87-18320 Development status of the ERS-1 SAR antenna TANAKA, K. Research and development of a small-sized space p9 N87-16939 An explicit expression for the tangent-stiffness of a manipulator Features and technologies of ERS-I (ESA) and X-SAR finitely deformed 3-D beam and its use in the analysis of [AAS PAPER 85.6601 p60 A87-18481 antennas p 9 N87-17152 space frames p 19 A87-20247 TSUTSUMI, Y. WAISS, R. D. TANAMACHI, T. Study on solid surface, deployable antenna reflector Cost reduction on large space systems through Satellite motion analysis via laser reflector pattern p8 N87-16928 cornm o n a I i ty processing for rendez-vous and docking TURNER, J. [AIM PAPER 87.05851 p4 A87-22721 [IAF PAPER 86-06] p 65 A87-15805 Dual structural-control optimization of large space WAITES, HENRY Structures p 33 N87-11766 TASCONE. R. Ground facilityfor Large Space Structures dynamics and TURNER, JAMES D. Study of frequency selective systems. Part 1: Preliminary control verification p 31 A87-31095 Frequency-shaped large-angle maneuvers investments on shapes and lattices; software Development and use of a linear momentum exchange developments. Part 2: Interfacing of Politecnico FSS [AIAA PAPER 87-01741 p 28 A87-22462 device p 36 N87-16041 Optimal spacecraft rotational maneuvers programs with MATRA reflector antenna software. Part Ground facility for large space structures dynamics and 3: Application to MACS phase 2 TX antenna (MATRA) p 68 A87-24625 control venficalion [ANT/NTEA/04.85] p 13 N87-13626 [ NASA-TM-865581 p41 N87-18600 TAYLOR, L W., JR. U WALDRON, R. D. On-orbit systems identification of flexible spacecraft Lunar-based power systems p 26 A87-16187 UHT, J. [IAF PAPER 86.5071 p 43 A87-16132 WALSH, JOANNE L. Proceedings of the 2nd Annual SCOLE Workshop Analysis of normal and transparent silver Teflon Analysis and simulation of the MAST (COFS-1 flight [NASA-TM-89048] p 70 N87-10945 p 55 N87-14391 hardware) p37 N87-16046 TAYLOR. LARRY UMEKAWA, S. Optimization procedure to control the coupling of On incorporating damping and gravity effects in models Fabrication of a carbon fibrelaluminiumalloy composite vibration modes in flexible space structures of structural dynamics of the SCOLE configuration under micrcgravity p 48 A87-11384 [ NASA-TM-89115] p 41 N87-18879 p 40 N87-17827 USHIROKAWA, A. WANG, C. Y. The SCOLE design challenge p IO N87-17836 2D-Array mission - Two-dimensionally deployable solar Free rotation of an elastic rod with an end mass TAYLOR, LAWRENCE W., JR. cell array mission p 15 A87-18243 p 28 A87-23213 Proceedings of the 3rd Annual SCOLE Workshop UY. 0. M. WANG, S. H. [ NASA-TM-890751 p 75 N87-17821 Studies of erosion of solar max samples of Kapton and Decentralized optimal control of large flexible THAMES, M. A. Teflon p 55 N87-14384 structures Decentralized control of multi-body spacecraft - A [DE86-0139061 p 41 N87-18101 numerical experiment WANG, Y. [AIAA PAPER 87-00181 p 29 A87-24902 v The identificationof a distributed parameter model for THOMPSON, JACK M., JR. a flexible structure Design and control of modular. kinematically-redundant VANDER VELDE, W. E. [ NASA-CR-1781991 p 13 N87-14059 manipulators Design of robust failure detection filters WARREN, J. L. [AIAA PAPER 87-16941 p 61 A87-31122 p 24 A87-13395 Examination of returned solar-max surfaces for THOMPSON, ROBERT VANDERVOORT, R. J. impacting orbital debris and meteoroids Space Station - Designing the future Dynamics and Control Analysis Package (DCAP): An p 55 N87-14386 p4 A87-25752 automated analysis and design tool for structural control WATKINS, R. D. THORNTON, E. A. of space structures p 39 N87-16947 Li corrosion resistant glasses for headers in ambient A Taylor-Galerkin finite element algorithm for transient VANSWIETEN, A. C. M. temperature Li batteries nonlinear thermal-structuralanalysis Engineering and software interfacing for thermal. [ DE86-0137541 p 33 N87-12802 WATSON, J. K. [ NASA-CR-1770641 p 20 N87-10406 structural and attitude control related with spacecraft Engineering considerations for on-orbit welding THORPE. T. p 21 N87-10928 operations p 59 A87-17401 Development of a continuous manufacturingmethod for VENABLES, J. D. WAlTS, L. A. a CFRP collapsible tube mast Thermoplastic-basedcomposites with low CTE for space Examination of returned solar-max surfaces for structures and circuit board applications [AERE-G-3898] p 54 N87-13572 impacting orbital debris and meteoroids p 49 A87-13097 THORTON, EARL A. p 55 N87-14386 VENKAYYA. V. 6. Finite-element thermal-structural analyses of a ,- WEAVER, LELLAND A. C. cable-stiffenedorbiting antenna p 19 A87-25687 Optimal structural design with control gain norm The role of robotics in space p 60 A87-25756 constraint TIZZI. S. WENDLER, BRUCE Effects of curing stresses on composite structures [AIAA PAPER 87-00191 p 11 A87-22363 Comparison of multiple input random and sine excitation p 56 N87-16930 VEST..~ C. E. methods for aerospace structures p 12 A87-28552 TO, C. W. S. Erosion studies on Solar Max samples WENTWORTH, S. J. Response of discretized structures with elasto-plastic p 50 A87-19343 Examination of returned solar-max surfaces for deformation to non-stationary random excitation Studies of erosion of solar max samples of Kapton and impacting orbital debris and meteoroids p 28 A87-22831 Teflon p 55 N87-14384 D 55 N87-14386 6-12 PERSONAL AUTHOR INDEX ZORGER, P. H.

WERTHEIMER, A. L YAHIL, A. Parametric study of stable optical references for large The tidal velocity field in the Local Supercluster flexible structures in space p 64 A87-11013 p 23 A87-11159 WESSELSKI, CLARENCE J. YAJIMA, N. Mobile remote manipulator system for a tetrahedral Flexibility control of solar arrays based on slate tNSS estimation by Kalman filtering p 26 A87-15450 [ NASA-CASE-MSC-20985-1I p 61 N87-15260 Control of solar battery arrays of spacecraft with Locking hinge consideration of the structural flexibility [NASA-CASE-MSC-21056-1I p 62 N87-18595 p 44 A87-18319 WESTPHAL M. YAJIMA. NOBUYUKI Development status of the ERS-1 SAR antenna Flexibility control of solar battery arrays. II - Vibration p9 N87-16939 and attitude control based on state estimation of differential WHIPPLE, ELDEN C. solar cell sensors p 45 A8722968 Controlling and monitoring the space-station plasma Flexibility control of solar battery arrays. 111 - vibration interaction: A baseline lor performing plasma experiments and attitude control with consideration of the dynamics and using advanced technology p 76 N87-20079 of a reaction wheel as an actuator p 45 A87-22969 WHITAKER, A. YAMADA, K. SSM atomic oxygen reactions on Kapton and silverized Anitude mntrol experiment for flexible spacecraft Teflon p 55 N87-14388 p 27 A87-18320 WHITE, CHARLES W. YAMAGUCHI, 1. Dynamic testing 01 a two-dimensional box truss beam Dvnamics formulation and simulation of multi-bodv [ NASA-CR-40391 p 34 N87-15262 space structures WHITE, LUTHER W. [IAF PAPER 86-2381 p 26 A87-15957 Estimation and control of distributed models for certain Numerical and experimental evaluation of des and elastic systems arising in large space structures system zeros for large flexible space structures [ AD-A17501 91 p 38 N87-16872 p 27 A87-18322 WICKMAN, L. A. Local output-feedback control for large flexible space Hubble Space Telescope - Dawn of the era of structures p 27 A87-18323 serviceable spacecraft Large-angle slewing of flexible spacecraft [ IAF PAPER 86-20] p2 A87-15814 [AAS PAPER 85-6741 p 27 A87-18490 WIE, 0. YAMANAKA, T. Modeling and simulation of spacecraft solar array Space exploitation and utilization; Proceedings of the deployment p26 A87-17760 Symposium, Honolulu, HI. Dscember 15-19. 1985 WIJKER, J. p 66 A87-18451 Engineering and software interfacing for thermal. YASAKA, T. structural and dynamic control related with spacecraft A new structure toward high precision large antenna activities p 22 N87-16948 [IAF PAPER 86-201 1 p 15 A87-15929 WIJKER, J. J. Development of 30120 GHz satellite antenna Engineering and software interfacing for thermal, structures p9 N87-16933 structural and attitude control related with spacecraft YOKAJTY, J. E. p 21 N87-10928 Feasibility study of a low-temperature expandable WILL, RALPH W. megawatt pulse power radiator p 66 A87-17841 A flexible telerobotic system for space operations YOKOTA, H. p 60 A87-23229 A concept of the Energy Storable Orbital Power Station WILLIAMS, J. H., JR. (ESOPS) Wave propagation and dynamics of lattice structures [IAF PAPER 86-1491 p 42 A87-15898 [AD-A170316] p 33 N87-13479 YOSHIMURA, S. WILLIAMS, JEFFREY P. Numerical and experimental evaluation of poles and Description of the Spacecraft Control Laboratory system zeros for large flexible space structures Experiment (SCOLE) facility p 27 A87-18322 [ NASA-TM-890571 p8 N87-16848 YOUNG, JOHN W. Finite element model 01 SCOLE laboratory Multidisciplinary analysis of actively controlled large configuration p 14 N87-17828 flexible spacecraft p 37 N87-16045 Description of the Spacecraft Control Laboratory YOUNG, STEPHEN J. Experiment (SCOLE) facility p 10 N87-17837 Model for radiation contamination by outgassing from WILLIAMS, TREVOR space plalforms Efficient mcdal analysis of damped large space [AIAA PAPER 87-01021 p 67 A87-22416 structures p 28 A8723995 YUEN, W. WILSON, MAYWOOD L. Active Control Evaluation for Spacecraft (ACES) Pultrusion process development for long space boom p34 N87-16019 models p 60 A87-20083 YURKOWICH, S. WOO, H. H. Decentralized control experiments on NASA's flexible Pointing. control, and stabilization of solar dynamic grid p 24 A87-13394 system on a Space Station p 25 A87-13437 WOODS, T. G. Advanced EVA system design requirements study: Z EVASlspace station system interface requirements [NASA-CR-171981] p 62 N87-20351 ZANARDO, A. WORSWICK, R. Two-dimensionalarticulated systems developable on a Rendezvous and docking (RVD) guidance simulation single or double curvature surface p 58 A87-12285 program, rider 2 ZICH, R. [MATRA-EPT/DT/Vl068/0121 p 72 N87-14359 Study of frequency selectivesystems. Part 1: Preliminary WRIGHT, J. R. investments on shapes and lattices; software The effect of the non-uniform stress distribution in the developments. Part 2: Interfacing of Politecnico FSS blankets of single and twin boom solar array panels upon programs with MATRA reflector antenna software. Part their modal characteristics p32 N87-10904 3 Application to MACS phase 2 TX antenna (MATRA) WRIGHT, ROBERT L [ANT/NTEAl04.85] p 13 N87-13626 NASAlDOD ControllStructuresInteraction Technology, ZOOK, n. A. 1986 Analysis of micrometeorite materialcaptured by the solar [ NASA-CP-2447-PT-11 p 73 N87-16014 max satellite p 55 N87-14385 COFS 1 Guest Investigator Program Examination 01 returned solar-max surfaces for p8 N87-16034 impacting orbital debris and meteoroids p 55 N87-14386 ZORGER, P. H. X Maintainabilitytechnology p 59 A87-15407

XU, D. M. On the Orbiter based deployment of flexible members [AAS PAPER 85-6731 p 16 A87-18489 Y

YAHAGI, H. Simplex Mast - An extendible mast for space applications p3 A87-18242

8-13 CORPORATE SOURCE INDEX

TECHNOLOGY FOR LARGE SPACE SYSTEMS /A Bibliography (Supplement 17) OCTOBER 1987

Typical Corporate Source Index Listing

Evaluation of Pactruss design characteristics critical to Colorado State Unlv., Fort Collins. space station primary structure Nonlinear interfaces for acceleration-commanded CORPORATE SOURCE [NASA-CR-178171I p 17 N87-16870 control of spacecraft and manipulators I Automatlx, Inc.. Burlington. Mass. p 25 A87-13494 Remotely manipulatedand autonomous robotic welding Colorado Univ., Boulder. fabrication in space p 59 A87-13714 Path-constrainedrendezvous. Necessary and sufficient conditions p 66 A87-17834 B Committee on Appropriations (US. Senate). I National Aeronautics and Space Administration p6 N87-10774 WngAeroapace Co., Soattle. Waah. Beljlng Inst. of Control Engineering (China). Protective coatings for composite tubes in space The dynamics and control 01 a space platform connected National Aeronautics and Space Administration appluatmns to a tethered subsatellite p 25 A87-14074 p 7 N87-I5908 rINASA-CA-178t16 I p57 N87-18669 Boeing Aerospace Co.. Seattle, Wash. Committee on Commerce, Science, and Transportation Protective Coatings for composite tubes in space (US. Senate). applications National Aeronautics and Space Administration [ NASA-CR-1781161 p 57 N87-18669 Authorization Bill. 1986 Boston Univ., Mass. [ H-REPT-99-829I p6 N87-11641 The control theory of flexible and articulated Report 01 the National Commission on Space spacecraft [S-HRG-99-954] p 73 N87-15028 I AD-AI 74880 I p 42 N87-19434 Committee on Science and Technology (US. House). British Aerospace Dynamics Group, Bristol (England). National Aeronautics and Space Administration HPSA: High Power Solar Array study Authorizalion Act. 1987 p6 N87-10775 I BAE-TP-8071I p 47 N87-11352 National Aeronautics and Space Administration British Aerospace Public Ltd. Co.. Bristol (England). Authorization Act. 1987 A study of large space structures IH-REPT-99-829 I p6 N87-11640 I LR46869 I p 21 N87.11832 Hearings before the Subcommitlee on Space Science Listings in this index are arranged alphabetically and Applications of the Committee on Science and by corporate source. The title of the document is Technology, 99th Congress. 2nd Session. No 132. 25. C 27 February. 11, 13. 20 March: 9. 10 April. 1986. Volume used to provide a brief description of the subject 2 matter. The page number and the accession California Univ., Los Angeles. [GPO-61-7771 p7 N87-12402 Alternative approximation concepts for space frame National Cornmission on Space report number are included in each entry to assist the synthesis p 19 A87-18940 (GPO-63-1431 p 7 N87-12574 user in locating the abstract in the abstract section. New malerials lor spacecraft stability and damping: A Communications Satellite Corp.. Washington, D.C. If applicable, a report number is also included as feasibility study Efficiency eccentricity control using continuous. [AD-A1698261 p 54 N87-12601 an aid in identifying the document. vectored thrusting for satellites with large arealmass Unified controllstructure design and modeling ratios p 63 N87-10151 research Construcciones Aeronauticas S.A., Madrid (Spain). 1 NASA-CR-1799481 p 33 N87-13478 Construcciones Aeronauticas S.A. (CASA) large A modified loop transfei recovery approach lor robust reflector antenna p9 N87-I6935 A control of flexible Structures p 39 N87-17029 Development of mm-wave radiometer antenna Active stability augmentation of large space structures. reflector p 47 N87-16941 A stochastic control problem p 41 N87-I7835 Acrltalla S.p.A.. Torlno (Italy). Contraves Corp.. Zurich (Switzerland). California Univ., San Diego. La Jolla. Development 01 a 2.8 m offset antenna reflector using The welding of aluminum alloys A new technology in Controlling and monitoring the space-station plasma space application p 56 N87 17056 inflatable. space-rigidizedstructures technology interaction: A baseline for performing plasma experiments p8 N87-16927 Alr Force Academy, Colo. and using advanced technology p 76 N87-20079 Contraves Italiana, Rome. MMU (Manned Maneuvering Unit) task Simulator Cambridge Research Associates, Mass. Contraves' antenna tip hinge mechanism lor Selenia IAD-Al69552) p 13 N87-14370 Frequency-shapedlarge-angle maneuvers Spazio's 20/30 GHz antenna p 74 N87-16944 Air Force Geophydcs Lab., Hanscorn AFB, Mass. lAlAA PAPER 87-01741 p 28 A87-22462 Control Research Corp., Lexington, Mass. Boom potential of a rotating satellite in sunlight Catholic Unlv. of Amerlca, Washington, D.C. Active damping of vibrations in SCOLE excited by p 68 A8724198 Distributed active control of large flexible space slewing p 40 N87-17831 Plasma interactions with large spacecraft structures p 48 N87-20063 [NASA-CR-179941I p 33 N87-13476 Alr Force Rocket Propulsion Lab., Edwards AFB. Calif. Static deflection control of flexible beams by D Spacecraft Dynamics and Control Program at AFRPL piezo-electric actuators p 34 N87-16017 I NASA-CR-179947I p 34 N87-13788 Deutsche Forschungs- und Versuchsanstalt fuer Luft- Air Force Wright Aeronautlcal Labs., Wrlght-Patterson Optimum vibration control 01 flexible beams by und Raumfahrt, Brunswick (West Germany). AFB, Ohlo. piezo-electric actuators Analysis of long thin walled tubes p 20 N87-10895 [ NASA-CR-180209 p 42 N87-18880 Flight Dynamics Laboratory overview I The K 1-K2 rnteractionfor matrix splitting in unidirectional p7 N87-16018 Centre d'Etudes et de Recherche de la Machlne-Outil, laminates of carbon fiber reinforced epoxy Saint-MartIn-d'Heres (France). p 52 N87-10932 Active Control Evaluation for Spacecraft (ACES) Performance characteristics of composite materials p 34 N87-16019 Digital image processing: Binary images p 57 N87-18015 p 53 N87-10935 Damping 1986 procedures. volume 2 Centre National dEtudes SpatlaIeI, Toulouse (France). Deutsche Forschungs- und Versuchsanstalt fuer Lult- [AD-A1739501 p 73 N87-16366 Proceedings of an InternationalConference on Space und Raumfahrt, Cologne (West Germany). Alabama Unlv., Huntsvllle. Dynamics for Geostationary Satellites Activities report in materials and construction Dual-spacecralt measurements Of [ ISBN-2.85428-149-71 p 70 N87-10113 IISSN-0174-39101 p 54 N87-13589 plasmasphere-ionospherecoupling p 67 A87-20055 Prediction and correlation of structural response in Deutsche Forschungs- und Versuchsanstalt fuer Luft- Stochastic modeling and control system designs of the acoustic chambers p 20 N87-I0907 und Raumfahrt, Goettingen (West Germany). NASAIMSFC Ground Facility for large space structures Centro Stud1 e Laborstori Telecomunicazioni, Turin Experience on the Olympus modal survey test The maximum entropyloptimal proiection approach (Italy). p6 N87-10919 p38 N87-16766 Prediction of the electrical performance of Inflatable Deutsche Forschungs- und Versuchsanstalt fuer Luft- Arnerlun Soclety of Clvil Englneen, New Yolk. Sfiace Rigidized Structure(ISRS) onset antenna reflectors und Raumfahrt, Oberpfaffenhofen (West Germany). Identification of large space structures on orbit and correlation with RF measurements Debonding analysis of thermally stressed [ AD-A1737561 p 14 N87-16058 p 47 N87-16943 fiber-reinforced composite materials p 52 N87-10933 Ametek, Inc.. Anaheim, Calif. Clnclnnatl Univ., Ohlo. Dornler-Werke G.m.b.H., Friedrichshafen (West Advanced composites for large Navy spacecraft Shear deformationplate continuaoflarge double layered Germany). p 56 N87-16015 space structures p 16 A8728882 On optimal passive and active control of precision Astro Aerospace Corp., Carpinterla. Cellf. Colby Coll., Waterville. Yslne. spacecraft structures p 31 N87-10891 Structural concepts for large solar concentrators LEO high voltage solar array arcing response model Damping representationrelated to spacecraft Structural [IAF PAPER 86-2021 p 15 A87-15930 [ NASA-CR-1800731 p 47 N87-16971 design p 31 N87-10898

c-1 Draper (Charles Stark) Lab., Inc., Cambridge, Mass. CORPORA TE SOURCE

Docking mechanisms technology study H Johns Hopklns Unlv., Laurel, Md. [ ESA-CR(P)-2273] p 71 N87-11833 Studies of erosion qf solar max samples of K&pton and Extendable retractable telescopic mast for deployable Hamllton Standard, Hartford, Conn. Teflon p 55 N87-14384 structures p8 N87-16323 Development of a pre-prototype power assisted glove Joint Publlcatlons Research Service, Arlington, Va. Analysis of high precision composite sandwich end effector for extravehicular activity Overview of planned tests of space matenals antennas p 56 N87-16929 [NASA-CR-1719401 p 72 N87-13989 p 56 N87-15990 Development status of the ERS-I SAR antenna Harris Corp., Melbourne, FIB. p 9 N87-16939 Development of the 15 meter diameter hoop column Features and technologies of ERS-1 (ESA) and X-SAR antenna K antennas p9 N87-17152 [NASA-CR-4038] p 17 N87-14366 Draper (Charles Stark) Lab., Inc., Cambridge. Mau. Ka..el Unhr. (Weat Germany). Harris Corp.. Palm Bay, Fla. Dual structural-control optimization of large space Structural System identification using single and Description of the Mast Flight System multiaxial vibration test data p 20 N87-10911 structures p 33 N87-11766 p8 N87-16030 Formationkeeping of spacecraft via differential drag Mast flight system beam structure and beam structural [NASA-CR-171939] p 71 N87-13466 performance p 17 N87-16031 L Howard Unlv., Washington, D. C. E The dynamics and control of a space platform connected Lawrence Livermore National Lab., Calif. to a tethered subsatellite p 25 A87-14074 Preliminary findings for integrated modeling and Engineering Mechanlcs Association, Inc., Palo Verde, Synthesis of control laws for optimally designed large simulation of directed energy weapons Calif. space structures [DE86-011636] p 10 N87-17846 Component testing for dynamic model verification [IAF PAPER 86-2461 p26 A87-15963 Decentralized optimal control of large flexible structures p 32 N87-11765 Issues in modeling and controlling the SCOLE [DE86-013906] p 41 N87-18101 Engineering System Internatlonal, Rungls (France). configuration p 39 N87-17822 Liege Unlv. (8elglum). Equivalent continuum analyses of large space trusses Optimal torque control for SCOLE slewing maneuvers p 12 N87-10894 The Extendable Refractable Mast (ERM) thermal p 40 N87-17823 Application of dynamic elements and continuum analysis: A heat radiation case study via the finite element methods to large space structures, volume I Hughes Alrcraft Co., El Sagundo, Callf. method p 22 N87-16949 [ ED/82-362/RD-VOL-I] p 22 N87-13484 International SAMPE Symposium and Exhibition, 31 st. Lockheed Mlulles and space Co., Palo Alto, Callf. Application of dynamic elements and continuum Los Angeles, CA. April 7-10, 1986. Proceedings Wave dispersion mechanisms in large space methods to large space structures, volume 2 p64 A87-13051 structures [ ED/82-362/RD-VOL-2] p 34 N87-13485 [AD-A173967] p38 N87-16059 Ern0 Raumfahrttechnlk G.m.b.H., Bremen (West Lockheed Ml~lle~and space Co., Sunnyvale, Callf. Germany). I Development of Space Station strut design Initial results from multiaxes transient testing p 15 A87-11842 p 21 N87-10917 Illlnols Unlv., Urbana. Passive damping augmentation for flexible structures Composites design handbook for space structure Automatic decoupling of flexible spacecraft slewing p36 N87-16044 applications. Executive summary maneuvers p 24 A87-13431 Discrete mechanism damping effects in the solar array [ ESA-CR(P)-2196] p54 N87-10982 Indian Space Research Organlzatlon, Trlvandrum. flight experiment p 38 N87-16341 European Space Agency, Paris (France). Possible areas of collaboration between DFVLR and Passive stabilization for large space systems Proceedings of an International Conference on ISRO in the fields of structures and matenals [ NASA-CR-40671 p 42 N87-19755 Spacecraft Structures p 56 N87-15252 Logice Ltd., London (England). [ ESA-SP-2381 p70 N87-10886 Instltuto de Pesqulaas Espaclala, s.0 Jose don Rendezvous and docking (RVD) guidance simulation Proceedings of an International Symposium on Fluid Campos (Brazil). program, rider 2 Dynamics and Space Parameter optimization and attitude stabilization of a [MATRA-EPT/DT/VrOS8/0121 p 72 N87-14359 [ ESA-SP-2651 p 72 N67-14394 flexible spacecraft p 31 N87-10138 London Unlv. (England). European Space Agency. European Space Research Comparison of methods for the calculation of thermal The effect of the non-uniform stress distribution in the and Technology Center, ESTEC, Noordwljk contact resistance of the first Brazilian satellite blankets of single and twin boom solar array panels upon (Netherlands). [INPE-3864-TDL/217] p 21 N87-12596 their modal characteristics p32 N87-10904 Design and verification activiiies and requirements for Integrated Syatema, Inc., Palo Alto, Calif. spacecraft structures p 20 N87-10890 Adaptwe control techniques for large space structures M L-band antennas for regional mobile communication [AD-A173083] p38 N87-16871 satellites p 47 N87-15377 Intespace, Toulouse (France). Giotto spacecraft high gain antenna mechanical design Marconl Space Systems Ltd., Portsmouth (England). Effective modal parameters and truncation effects in Modern control of large flexible spacecraft, ESA ASTP and development p 18 N87-16938 structural dynamics p 31 N87-10897 study Engineering and software interfacing for thermal, Iowa State Unlv. of Xlence end Technology, Amos. [ BL-6206-ISSUE-21 p 70 N87-10956 structural and dynamic control related with spacecraft Application of graph theory to the nonlinear analysis Martin Marietta Aerospace, Denver, Colo. activities p 22 N87-16948 of large space structures p 12 N87-10416 Gynamic testing of a two-dimensional box truss beam Executlve Office of the President, Washington, D. C. [ NASA-CR-40391 p 34 N87-15262 Aeronautics and space report of the President: 1985 Metallurgical characterization of the interfaces and the activities D74 N87-16662 J damping mechanisms in metal matrix composites [ADA1734701 p57 N87-17863 Jet Propulsion Lab., CalMornla Inst. of Tech., Massachusetts Inst. of Tech., Cambridge. F PaMdeM. Design of robust failure detection filters International SAMPE Symposium and Exhibition, 3131, p 24 A87-13395 Fabrlcb Itallana Apparecchl Radio S.p.A., Mllan. Los Angeles, CA. April 7-10, 1986, Proceedings Remotely manipulatedand autonomous robotic welding Robot system for dexterous tasks (for space p64 A87-13051 fabrication in space p 59 A87-13714 applications) Design of robust failure detection filters Fundamentals and advances in the development of [ETN-86-98562] p 61 N87-15472 p 24 A87-13395 remote welding fabrication systems p 49 A87-14312 Flight Mechanlca and Control, lnc., Harnpton, Va. Trajectory shaping rendezvous guidance A procedurefor calculating the damping in multi-element Gynamic analysis of satellites with deployable hinged p64 A87-13434 space structures appendages System concept for a moderate cost Large Deployable [IAF PAPER 86-2031 p 26 A87-15931 [AIAA PAPER 87-00201 p27 A87-22364 Reflector (LDR) p3 A87-18508 Radiation from large space structures in low earth orbit Footscray Inst. of Tech. (Australia). Spacecraft structural model improvement by modal test with induced ac currents On a simple vibration control design for large space results p 20 A87-31225 [AIAA PAPER 87-06121 p68 A87-22738 Structure models with uncertain parameters Spacecraft load, design and test philosophies Formationkeeping of spacecraft via differential drag p 32 N87-10903 p6 N87-10922 [NASA-CR-171939] p71 N87-13466 Loads analysis for the Galileo spacecraft Massachusetts Unlv., Amherat. p 21 N87-10926 Parametric investigation of factors influencing the G Unified controllstructure design and modeling mechanical behavior of large space structures research [AD-A1728801 p38 N87-16056 Genml DyMmka Corp., San Mego, Callf. [NASA-CR-179948] p 33 N87-13478 Matorlais Sciences Corp., Spring House, Pa. Evaluationof on-orbit cryogenic propellantdepot options Degradatlon studies of SMRM Teflon Thermoviscoelasticcharacterization and analysisof fiber for the orbital transfer vehicle p 63 A87-31133 p 56 N87-14392 composite space structures Deployable truss structure advanced technology Sensor technology for advanced space missions [AD-A175024] p 58 N87-19457 P22 N87-16021 p73 N87-16027 MATRA Espace, Paris-Vellzy (France). System identification for modeling for control of flexible Rendezvous and docking (RVD) guidance simulation General Electric Co., Phlledelphla, Pa. structures p36 N87-16040 Conceptualdesign of pointing control systems for space program, rider 2 The large deployable reflector: A NASA [MATRA-EPT/DT/VrO66/012] p 72 N87-14359 station gimballed payloads p36 N87-16037 submillimeter-infraredorbiting observatory YATRA Espace, Toulouse (France). Oroningum Rljksunlveraiteit (Netherlands). p9 N87-17571 Study of frequency selective systems. Part 1: Preliminary Large flexible space struclures: Some simple models The Large Deployable Reflector (LDR) report of the investments on shapes and lanices; software [TW-269] p 32 N87-10957 Science Coordination Group developments. Part 2: Interfacing of Politecnico FSS Grummn Aeroepace Corp., Bothpage, N.Y. [NASA-CR-180235] p 10 N87-19310 programs with MATRA reflector antenna software. Part Telerobotic assembly of space station truss structure Large structures and tethers working group 3: Application to MACS phase 2 TX antenna (MATRA) [NASA-CR-180239] p 62 N87-18984 p 75 N87-20057 [ANT/NTEA/04.85] p 13 N87-13626 c-2 ~~ ~ ~

CORPORA TE SOURCE NASA. Marshall Space Flight Center, Huntsville, Ala.

McDonnell-Douglas Aatronautlcs Co.. Houston, Tex. Analysis of normal and transparent silver Teflon COFS 1 research overview p8 N87-16029 Advanced EVA system design requirements study p 55 N87-14391 MAST flight system dynamic performance [NASA-CR-1719421 P 71 N87-13167 National Aeronautlcs and Space Admlnlstratlon. p 35 N67-16032 Advanced EVA system design requirements study, Lyndon 8. Johnson Space Center, Houston, lex. MAST flight system operations p 8 N87-16033 executive summary Path-constrained rendezvous. Necessary and sufficient COFS 1 Guest Investigator Program [ NASA-CR-171960] p 75 N87-17838 conditions p 66 A87-17834 p8 N87-16034 McDonnell-Douglas Astronautics Co., Huntington A consideration of atomic oxygen interactions with the COFS 2: 3-D dynamics and controls technology Beach, Calif. Space Station p 43 A87-17836 p 35 N87-16035 Passively damped joints for advanced space Foldable self-erecting joint COFS 3: Multibody dynamics and control technology structures [ NASA-CASE-MSC-20635-1] p 17 N87-14373 p 36 N87-16036 [ AD-A1 749141 p 42 N87-19435 Analysis of micrometeorite materialcaptured by the solar Computer-aided design and distributed system McDonnell-Douglas Astronautics Co., St. LOUIS, Mo. masatellite p 55 N87-14385 technology development for large space structures Examination of returned solar-max surfaces for Advanced EVA system design requirements study: p 14 N87-16042 impacting orbital debris and meteoroids EVASlspace station system interface requirements Distributed control for COFS 1 p 36 N87-16043 [NASA-CR-171981] p 62 N87-20351 p 55 N87-14386 Multidisciplinary analysis of actively controlled large Mobile remote manipulator system lor a tetrahedral flexible spacecraft p37 N87-16045 McIntosh Structural Dynamics, Inc., Pal0 Alto. Calif. truss Analysis and simulation of the MAST (COFS-1 flight Investigation of interactive structural and controller [ NASA-CASE-MSC-20985.11 p 61 N87-15260 hardware) p 37 N87-16046 synthesis for large spacecraft Sun shield [ADA172611I p 17 N87-16055 Surface control system for the 15 meter hoop-column [ NASA-CASE-MSC-20162-11 p 74 N87-17036 antenna p 37 N87-16047 Meascrschmltt-Boa(kow-Blohm/En~lcklungaprlng Budget availability p 10 N87-17799 Robust multivariable controller design for flexible Nord, Bremen (West Germany). Locking hinge spacecraft p 37 N87-16048 Design and development of a telescopic axial boom [ NASA-CASE-MSC-21056-11 p 62 N87-16595 Dynamic analysis of the large deployable reflector p 14 N87-16322 Space station erectable manipulator placement [ NASA-TM-890561 p 37 N87-16050 Mesaer~hmltt-BOeIkow-BlohmG.m.b.H., Munich (West system Description of the Spacecraft Control Laboratory Germany). [NASA-CASE-MSC-21096-1] p 62 N67-18596 Experiment (SCOLE) facility Experience gained by sector model testing of an National Aeronautics and Space Administration. [ NASA-TM-890571 p6 N87-16648 unfurlable rneshlrib antenna p 14 N87-16925 Langley Research Center, Hampton, Va. Proceedings of the 3rd Annual SCOLE Workshop Mesaerschmln-Boelkow-Blohm G.m.b.H., Ottobrunn Space radiation effects on the dimensional stability of [ NASA-TM-890751 p 75 N87-17821 (West Germany). a toughened epoxy graphite composite Mathematical modeling of SCOLE configuration with Influence of fiber orientation and boundary conditions p 49 A87-11847 line-of-sighterror as the output p 40 N87-17824 on the dynamic behavior of a cylindrically telescoping solar Failure-accommodating control of large flexible On incorporating damping and gravity effects in models array (INTELSAT 6) p 32 N87-10925 spacecraft p 24 A87-13317 of structural dynamics of the SCOLE configuration Offset unfurlable antenna. Phase 2A Executive Vibration suppression of planar truss structures utilizing p 40 N87-17827 summary uniform damping control p 25 A87-13458 Finite element model of SCOLE laboratory [ MBB-R-0200/3069-R1 p 70 N87-11066 Space Station design for growth configuration p 14 N87-17828 [IAF PAPER 86-461I p2 A87-16110 The SCOLE design challenge p 10 N87-17836 On-orbit systems identification of flexible spacecraft Description of the Spacecraft Control Laboratory N p 26 A87-16187 Experiment (SCOLE) facility p 10 N87-17837 A slewing control experiment for flexible structures Integrated structure electromagnetic optimization of National Academy of Public Admlnlatratlon, p 27 A87-17761 large space antenna reflectors Washington. D. C. The effects of radiation on the interlaminar fracture [NASA-TM-89110] p 48 N87-18598 NASA: The vision and the reality toughness of a graphitelepoxy composite Seamless metal-clad fiber-reinforced organic matrix [OP-5] p 7 N87-15898 p 50 A87-19122 composite structures and process for their manufacture National Aeronautics and Space Admlnlstratlon. Pultrusion process development for long space boom [NASA-CASE-LAR-13562-11 p 57 N87-18613 Washington, D.C. models p 60 A87-20083 Optimization procedure to control the coupling of Technical aspects of the United States Space Station Electron-radiationeffects on the ac and dc electrical vibration modes in flexible space structures p 1 A87-10043 properties and unpaired electron densities of three [NASA-TM-89115] p 41 N87-18879 The role of automation and robotics in space stations aerospace polymers p 51 A87-21992 National Aeronautics and Space Administration. Lewis p 58 A87-13706 Frequency-shapedlarge-angle manewers Research Center, Cleveland, Ohio. Space construction results - The EASE/ACCESS flight [AIAA PAPER 87.01741 p 28 A8722462 Spacecraft 2000 - The challenge of the future experiment A flexible telerobotic system for space operations p 3 A87-18064 [IAF PAPER 86-26] p2 A87-15817 p60 A8723229 The potential impact 01 new power system technology Technologies for affordable access to space A sequential linear optimization approach for controller on the design of a manned Space Station [IAF PAPER 66-4421 p2 A87-16096 design p 28 A87-23989 p 44 A87-18342 Telescience in orbit p3 A87-16930 Space radiation effects on the thermo-mechanical Protection of solar array blankets from attack by low An overview of NASA's programs and plans behavior of graphite-epoxy composites earth orbital atomic oxygen p 45 A87-19874 [AAS PAPER 85-6471 p 3 A87-18453 p 51 A87-27178 NASA Growth Space Station missions and candidate Communications technology p 46 A87-30893 Effect of s@nsorand actuator errors on static shape nuclearlsolar power systems p 3 A87-21807 Second AIAAINASA USAF Symposium on Automation, control for large space structures p 29 A87-27948 Effect of hard particle impacts on the atomic oxygen Roboticsand Advanced Computing for the NationalSpace A space station Structures and Assembly Verification survwabilitv of reflectlx surfaces with transparent Program Experiment. SAVE protective overcoats [AIAA PAPER 67-16551 p 70 A87-31112 [ NASA-TM-890041 p5 N87-10170 [AIM PAPER 87-01041 p 45 A87-22417 NASA's technology plans - Will technology be ready Effects of thermal cycling on graphie-fiber-reinforced Properties and potential applications of brominated when we are 6061 aluminum P-100.carbon fibers p 51 A8723702 [AIAA PAPER 87.16951 p5 A67-31123 [ NASA-TP-26121 p 52 N87-10184 The survivability of large space-borne reflectors under Lidar remote sensing from space: NASA's plans in the Proceedings of the 2nd Annual SCOLE Workshop atomic oxygen and micrometeoroid impact Earth sciences p6 N87-10265 [ NASA-TM-890481 p 70 N87-10945 [AIAA PAPER 87-03411 p52 A87-31300 Space station systems: A continuing bibliography with Recent Experiences in Multidisciplinary Analysis and Oxidation-resistant reflective surfaces lor solar dynamic indexes [supplement 3) Optimization, part 1 power generation in near Earth orbit [ NASA-SP-7056(03)1 p 75 N87-17620 [ NASA-CP-2327-PT-l ] p 71 N87-11717 [ NASA-TM-888651 p 54 N87-10960 National Aeronautics and Space Administration. Ames Recent Experiences in Multidisciplinary Analysis and Effect of hard particle impacts on the atomic oxygen Research Center, Moffett Field, Calif. Optimization. part 2 survivability of reflector surfaces with transparent Space missions for automation and robotics [ NASA-CP-2327-PT-21 p 71 N87-11750 protective overcoats technologies (SMART) program p 58 A87-13707 IDEAS A multidisciplinary computer-aided conceptual [ NASA-TM-888741 p 71 N87-11838 National Aeronautics and Space Admlnlatratlon. design system for spacecraft p 13 N87-11761 The survivability of large space-borne reflectors under Goddard Space Flight Center, Grwnbelt, Md. Design, construction and utilization of a space station atomic oxygen and micrometeoroid impact An estimate of the outgassing of space payloads and assembled lrom 5-meter erectable struts [ NASA-TM-889141 p 72 N87-14423 its gaseous influence on the environment [ NASA-TM-890431 p6 N87-11827 The 20th Aerospace Mechanics Symposium p 48 A87-11355 Thermal analysis of radiometer containers for the 122m [ NASA-CP-2423-REV] p 73 N87-16321 The Space Station program hoop column antenna concept Composite space antenna structures: Properties and [AAS PAPER 85-451 I p 1 A87-15377 [NASA-TM-89026] p 21 N87-11966 environmental effects Dual-spacecraft measurements Of The identification of a distributed parameter model for [ NASA-TM-888591 p 39 N87-16880 plasmasphere-ionospherecoupling p 67 A87-20055 a flexible structure Research and technology Boom potential of a rotating satellite in sunlight [NASA-CR-178199] p 13 N87-14059 [ NASA-TM-888681 p 74 N87-17656 p6E A87-24198 Preliminary results of SMM exposed aluminized Kapton Tribological properties of polymer films and solid bodies Proceedings of the 5th Annual Users' Conference and silvered Teflon p 55 N87-14389 in a vacuum environment [ NASA-CP-23991 p 70 N87-10720 Space spider crane [ NASA-TM-889661 p 57 N67-17906 Proceedings of the SMRM Degradation Study [NASA-CASE-u\R-13411-1S8] p 73 N87-15259 National Aeronautics and Space Administration. Workshop NASA/DOD Control/Structures InteractionTechnology, Marshall Space Flight Center, Huntsville, Ala. [ NASA-TM-892741 p 72 N87-14374 1986 Dual-spacecraft measurements 01 Report on SMRM CIP main electronics box component [NASA-CP-2447-PT-l] p 73 N87-16014 plasmasphere-ionospherecoupling p 67 A87-20055 and materials degradation evaluations The 15 meter hoop-columnantenna dynamics: Test and Large space observatones of the 21st century p 72 N87-14375 analysis p 35 N87-16025 [AIAA PAPER 87.06361 p 4 A8742751 Results of examination of materials from the solar COFS 1: Beam dynamics and control technology Ground facility lor Large Space Structures dynamcs and maximum recovery mission p 54 N87-14383 overview p 35 N87-16028 control verification D 31 A67-31095

c-3 National Aerospace Lab., Amsterdam (Netherlands). CORPORA TE SOURCE

Evaluationof on-orbitcryogenic propellant depot options A review of lime domain modal test methods and The concentration principleapplied to spaceborne solar for the orbital transfer vehicle p 63 A87-31133 applications p 32 N87-10915 arrays. Application to the coorbiting platform mission: Plasma electron collection through biased slits in a Studies synthesis dielectric p 46 A87-31223 [ SNIAS-975-CA/CG] p 75 N87-19814 Development of deployable truss concept for space P Societe Nationale lndustrielle Aerospatlale, Les station p 16 N87-10923 Mureaux (France). Solar array flight dynamic experiment Physical Sciences, Inc., Andover. Mass. Development of a lightenedstructure for the GSR3 solar [ NASA-TP-2598I p 7 N87-12581 Energetic oxygen atom material degradation studies generator p 17 N87-10927 SSM atomic oxygen reactions on Kapton and silverized [AIAA PAPER 87-01051 p 51 A87-24919 Mechanical and control study of a 7 m offset unfurlable Teflon p 55 N87-14388 A high flux source of energetic oxygen atoms for material tracking antenna p 39 N87-16926 Development of the Lens Antenna Deployment degradatlon studies p 52 A8727936 DemonsIration (LADD) shuttleattachedflight experiment Structural analysis. manufacturing and development Politecnico di Torlno (Italy). status of large polarization sensitive dual-gridded p7 N87-16022 Study of frequency selective systems Part 1 Preliminary reflectors p 22 N87-16937 Development and use of a linear momentum exchange investments on shapes and lanices. software device p 36 N87-16041 developments Part 2 Interfacing of Politecnico FSS Soclete Nationale Industrlelle Aerospatlale, Design and analysis of a keel latch for use on the Hubble programs with MATRA reflector antenna software Part Salnt-Medard-en-Jalles (France). Space Telescope p 62 N87-16326 3 Application to MACS phase 2 TX antenna (MATRA) A method of studying the behavior of composite Manned Mars mission Earth-To-Orbit(ETO) delivery and [ANT/NTEA/O4 851 p 13 N67-13626 materials in simulated space environments orbit assembly of the manned Mars vehicle p 53 N87-10940 p 9 N87-17746 Purdue Univ., West Lafayette, Ind. Regulation of the SCOLE configuration Spar Aerospace Ltd., Ste-Anne-de-Bellevue (Quebec). Mars landing mission: A structural approach p 41 N87-17833 Demonstration of modal synthesis on an expenmental p 23 N87-17783 structure and its applicationto large spacecraft Ground facility for large space structures dynamics and p 20 N87-10912 control verification [NASA-TM-86558] p 41 N87-18600 R Design of a low distortion shared aperture reflector p 14 N87-16934 The interaction of small and large spacecraft with their RADEX. Inc., Carllsle, Mass. Sperry Corp., Phoenix, Ark. environment p 10 N87-20064 Boom potential of a rotating satellite in sunlight Space station rotary joint mechanisms National Aerospace Lab., Amaterdam (Netherlands). p 68 A8724198 Rendezvous and docking and space robotics proximity p 73 N87-16338 Rensselaer Polytechnlc Inst., Troy, N.Y. operations. Part 5: Executive summary Model reference control of distributed parameter Stanford Univ.. Calif. [NLR-TR-85099-U] p 62 N87-19441 systems: Application to the SCOLE problem Rapid precise end point control of a wrist carried by a Sensors for a system to control the liquid flow into an p 40 N87-17829 flexible manipulator p 61 N87-10398 evaporation cold plate of a two-phase heal transport Ricerche e Progettl s.r.1.. Turin (Italy). Adaptive control of a flexible structure system for large spacecraft Dynamics and Control Analysis Package (DCAP): An p 39 N87-17449 [NLR-TR-86001-U] p 23 N87-19442 automated analysis and design tool for structural control State Unlv. of New York, Buffalo. Naval Research Lab., Washington. D. C. of space structures p 39 N87-16947 Application of Spaceborne Distributed Oualitalive results for distributed systems with discrete Rome Unlv. (Italy). and stiffness with application to control Aperture/Coherent Array Processing (SDA/CAP) Computational methods in elastic periodic structures technology to active and passive microwave remote [AD-AI 68622 I p 33 N87-11829 analyses p32 N87-10901 sensing p 47 N87-17277 Effects of curing stresses on composite structures Systems Science and Software, La Jolla, Calif. Proof-mass actuator placement strategies for regulation p 56 N67-16930 A unified approach to computer analysis and modeling of flexure during the SCOLE slew p 40 N87-17830 Thermomechanical characteristics of dichroic of spacecraft environmental interactions Nlppon Telegraph and Telephone Public Corp., subreflectors p 22 N87-16952 D 14 N87-20066 Yokoauka (Japan). Royal Netherlands Aircraft Factorles Fokker. Development of 30120 GHz satellite antenna Amsterdam. structures p9 N87-16933 Engineering and software interfacing for thermal, T North Carollna State Unlv., Raleigh. structural and anilude control related with spacecraft Vibration suppression of planar ~NSSstructures utilizing p 21 N87-10928 uniform damping control p 25 A87-13458 Technlsche Hochschule, Aachen (West Germany). North Carollna Univ., Charlotte. Transient external loads or interface forces Slew maneuver dynamics of the Spacecraft Control S reconstructedfrom structural response measurements Laboratory experiment p 40 N67-17825 p 20 N87-10910 Saab-Scania, Linkoplng (Sweden). Teldlx Luftfahrt-Ausrueatungs G.m.b.H., Heldelberg Tele-X antenna module structure qualificationprogram (West Germany). 0 p 21 N67-10924 Large wheel actuators definition study Sandla National Labs., Albuquerque, N. Mex. [TELDIX-15-020-880] p 33 N87-11834 Ridge Lab., Tenn. Oak National Li corrosion resistant glasses for headers in ambient Protection of Spacecraft from meteoroids and orbital Texas A&M Unlv., College Station. temperature Li baneries debris A sequential linear optimization approach for controller [ DE86-0137541 p 33 N87-12802 design p 28 A87-23989 [DE86-009996] p 70 N87-I0947 SATCOM Internatlonal, Parls (France). Offlce National detudes et de Recherche8 Optimization of closed loop eigenvalues: Maneuvering, Analysis of rendezvous and docking in geostationary Aerospatlales, Toulouse (France). vibration control and structurelcontrol design iteration for Earth oht. Rider to comparison of future communications Design improvement and radiation. contamination tests. flexible spacecraft space segment concepts Prestudy 1: Ultraviolet radiation acceleration, volume 1 [AD-A1727161 p 34 N87-15263 [DM5l-C/PL/FL/OO99.82] p 72 N87-14364 [CERT-4193-VOL-l p 53 N87-10949 I Science Appllcatlons International Corp., McLean, Va. A model for predicting thermomechanical response of Design improvement and radiation contamination tests. Technical issues in the conduct of large space plalform large space structures Prestudy 1: Ultraviolet radiation acceleration. Volume 2 experiments in plasma physics and geoplasma sciences [AD-A172966] p 22 N87-15264 Appendix, detailed results p 75 N87-20071 Texas Unlv., Austin. [CERT-4193-VOL-2] p N87-10950 53 Science Appllcatlona International Corp., Schaumberg, A study of ncdal coupling methods p 31 N87-10896 Improving the irradiation plus contamination tests. 111. Prestudy 2: Successive irradiations and synergics. Volume TlCRA Als, Copenhagen (Denmark). Satellite servicing price estimation instruction booklet 1: Tests and conclusions Simple approach for evaluating mechanical reflector [ NASA-CR-1719671 p 75 N87-18583 [CERT-4193-VOL-3 p 53 N87-10951 antenna distortions p 39 N87-16942 I Selenla S.p& Rome (Italy). Improving radiation plus Contamination tests. Prestudy Development of lightweight dimensionally stable carbon Toronto Univ. (Ontario). 2 Successive irradiations and synergics. Volume 2: fiber composite antenna reflectors for the INSAT-1 Combined orbit/anitude determination for low-altitude Annexes. Annex 1: Detailed results. Annex 2: Control and Satellite p 56 N87-16936 Satellites improvement of optical measurements Sener, S.A., Madrld (Spain). [UTIAS-320] p 74 N87-17810 [CERT-4193-VOL-4] p 53 N87-10952 Improving radiationlcontaminationtests A Sener mechanism: Fine adjustment mechanism for Toshlba Research and Development Center, Kawasakl the Far Infrared and Submillimeter Space Telescope (Japan). [CERT-419300/1 -DERTS] p 54 N87-10954 (FIRST) (F f F) p 74 N87-16946 Ohlo State Unlv.. Columbus. Study on solid surface, deployable antenna reflector Decentralized Control experiments on NASA's flexible Smlthsonlan Astrophysical Observatory, Cambridge, p 8 N87-16928 Mass. grid p 24 A87-13394 TRW Defense and Space Systems Group, Redondo Oklahoma Unlv., Norman. Large space observatories of the 21st century [AIAA PAPER 87.06361 p 4 A87-22751 Beach, Callf. Estimation and control of distnbuted models for certain Microcomputerdesign and analysis of the cable catenary elastic systems arising in large space structures System engineering study of electrodynamic tether as a spaceborne generator and radiator of electromagnetic large space antenna system p 13 N87-11762 [AD-A1750191 p 38 N87-16672 waves in the ULFIELF frequency band TRW, Inc., Redondo Beach, Calif. Old Domlnlon Unlv., Norfolk, Va. [NASA-CR-180156] p 23 N87-16956 Electron-radiationeffects on the ac and dc electrical Application of physical parameter identificationIO finite Soclete Berth et Cle, Plalslr (France). p N87-16026 properties and unpaired electron densities of three element models 35 DyMmics of flexible mechanisms p 32 N87-I0938 TRW Space Technology Labs., Redondo Beach. Calif. aerospace polymers p 51 A87-21992 SOClCte Natlonale lndustrlelle Aeroapatlale. Cannes Finite-element thermal-structural analyses of a (France). High voltage system: Plasma interaction summary p 48 N87-20069 cable-stiffenedorbiting antenna p 19 A87-25687 Space technologies and materials: A look back and A Taylor-Galerkinfinite element algorithm for transient future perspectives p 52 N87-10934 Turin Univ. (Italy). nonlinear thermal-structuralanalysis High power rigid solar array Dielectric support structures for spacecraft antenna [ NASA-CR-1770641 p 20 N87-10406 [SNIAS-917A-CA/CG] p 47 N87-13864 feeds p 17 N67-16931 c-4 CORPORA TE SOURCE York Univ., Toronto (Ontario). U

Unlted Kingdom Atomic Energy Authority, Hamell (England). Development of a continuous manufacturing method for a CFRP collapsible tube mast [AERE-G-3898] p 54 N87-13572 Unlversity of Southern California, Los Angeles. Structural concepts for large solar concentrators [IAF PAPER 86-2021 p 15 A87-15930 Evaluation of on-line pulse control for vibration suppression in flexible spacecraft p 41 N87-17834 V

Vlgyan Research Associates, Inc., Hampton, Va. Nonlinear attitude control of elastic spacecraft-antenna system p 25 A87-13433 Nonlinear anitude control of flexible spacecraft under disturbance torque p 29 A87-24049 Vlrglnla Polytechnic Inst. and State Unlv., Blacksburg. A slewing control experiment for flexible structures p 27 A87-17761 Parameter identification in distributed spacecraft structures [AAS PAPER 85-6701 p 18 A87-18487 Finite-element thermal-structural analyses of a cable-stiffenedorbiting antenna p 19 A87-25687 Space radiation effects on the thermo-mechanical behavior of graphite-epoxy composites p 51 A87-27178 Effect of sensor and actuator errors on static shape control for large space structures p 29 A8727948 An analytical and experimental study of a control system’s sensitivity to structural modifications p 30 A8730294 Identificationand control of structures in space [NASA-CR-l79811I p 31 N87-10172 Optimization of closed loop eigenvalues: Maneuvering, vibration control and structurelcontrol design iteration lor flexible spacecraft [ AD-A1727161 p 34 N87-15263 Modeling and identificationof SCOLE p 23 N87-17826 Control of SCOLE p 40 N87-17832 Experimental study of active vibration control [AD-A173144] p 41 N87-17845 W

WEA. Cambrldge, Mass. Wave propagation and dynamics of lanice structures [AD-A170316] p 33 N87-I3479 Woods Hole Oceanographic Institution, Mass. Fundamentals and advances in the development of remote welding fabrication systems p 49 A87-14312 Y

York Unlv., Toronto (Ontario). Spacecraft charging in the auroral plasma: Progress toward understanding the physical effects involved p 48 N87-20080

c-5 FOREIGN TECHNOLOGY INDEX

TECHNOLOGY FOR LARGE SPACE SYSTEMS /A Bibliography (Supplement 17) OCTOBER 1987

Typical Foreign Technology Index Listing

Substructure coupling of analytical and test models for Application of dynamic elements and continuum an experimental structure p 19 A87-28577 methods to large space structures. volume 1 Demonstration of modal synthesis on an expenmental I ED/82-362/RD-VOL-l I p 22 N87-13484 structure and its application to large spacecraft Application of dynamic elements and continuum COUNTRY OF p 20 N87-10912 methods to large space structures. volume 2 INTELLECTUAL Design of a low distortion shared aperture reflector I ED/82-362/RD-VOL-2 I p 34 N87-13485 FIN I I p 14 N87-169j4 Study of frequency selective systems Part 1 Preliminary Combined OrbitIattitude determination for low-altitude investments on shapes and lattices. software satellites developments Part 2 Interfacing of Politecnico FSS 1 UTIAS-3201 p 74 N87-17810 programs with MATRA reflector antenna software Part CZECHOSLOVAKIA 3 Application to MACS phase 2 TX antenna (MATRA) L Compact SPS for lunar development I ANTINTEAIOI 85 I p 13 N87 13626 AUSTRALIA IAF PAPER 86-156 p 2 A87-15904 I I High power rigid solar array On a simple vibration control design for large space Moon for terrestrial energetics ISNIAS-917A-CA/CG 1 p 47 N87-13864 structure models w:th uncertain parameters I IAF PAPER 86-4561 p2 A87-16108 r p 32 N87-10903 Rendezvous and docking (RVD) guidance simulation program, rider 2 D I MATRA-EPTIDTIVTO68/012] p 72 N87-14359 Analysis of rendezvous and docking in geostationary DENMARK Earth orbit Rider to comparison of future communications Space Station - The use of expert systems for space segment concepts planning p4 A8725759 IDM51 CIPLIFLIOO99 821 p 72 N87-14364 Simple approach for evaluating mechanical reflector Proceedings of an International Symposium on Fluid antenna distortions p39 N87 16942 Dynamics and Space I ESA-SP-265I p 72 N87-14394 Mechanical and control study of a 7 m offset unfurlable F tracking antenna p 39 N87-16926 FRANCE Structural analysis. manufacturing and development Listings in this index are arranged alphabetically Space vehicle design pll A8710092 status of large polarization sensitive dual-gridded by country of intellectual origin. The title of the Rendezvous and docking verification and in orbit reflectors p 22 N87-16937 document is used to provide a brief description of demonstration The welding of aluminum alloys A new technology in the subject matter. The page number and the ac- 1 IAF PAPER 86 07 I p 65 A87 15806 space application p 56 N87-17056 ARABSAT solar generator concept and in orbit Digital image processing Binary images cession number are included in each entry to assist perlormance p 43 A87-18075 p 57 N87-18015 the user in locating the citation in the abstract sec- Large inflatable parabolic reflectors in space The concentration principle applied to spaceborne solar tion. p 3 A87 19789 arrays Application to the coorbiting platform mission Behavioural analysis of adhesive-bonded structural Studies synthesis joints in space vehicles p 16 A8720148 I SNIAS-975-CAICG1 p 75 N87-19814 Adhesive bonding of aerospace materials Surface characterizationof metallic adherends p51 A8720149 The USSR and space power plants G A p45 A87 25533 GERMANY,FEDERAL REPUBLIC OF Proceedings of an Internationalconference on Space The ESA/MBB unfurlable mesh antenna development AUSTRALIA Dynamics for Geostationary Satellites for mobile services On a simple vibration control design for large space 1 ISBN 2 85428 149-71 p70 N87 10113 I IAF PAPER 86 27 I p2 A87 15818 structure models with uncertain parameters Proceedings of an International Conference on Stress and deformationanalysis of thermally loaded light p 32 N87-10903 Spacecraft Structures weight composite structures [ ESA SP 238 I p 70 N87 10886 [ IAF PAPER 86 212 I p 18 A87 15939 B Equivalent continuum analyses of large space trusses Antenna system alternatives for Data Relay Satellites p 12 N87-10894 with multiple steerable beams BELGIUM Effective modal parameters and truncation effects in IIAF PAPER 86.3491 p 43 A87-16041 Holographic non-destructive testing for composite structural dynamics p 31 N87-10897 Meteoroid and orbital debris protection concepts materials used in aerospace p 51 A87-19805 Prediction and correlation of structural response in [IAF PAPER 86 4191 p 65 A87-16081 The Extendable Refractable Mast (ERM) thermal acoustic chambers p20 N87 10907 Design and manufacturing aspects of tubular carbon analysis A heat radiation case study via the finite element Development of a lightened structure for the GSR3 solar fibre compositeltitanium bonded joints method p 22 N87-16949 generator p 17 N87-10927 p 50 A87-16163 BRAZIL Space technologies and materials A look back and Advanced opto-electronical sensors for autonomous Parameter optimization and allitude stabilization of a future perspectives p 52 N87-10934 Rendezvous {Docking and proximity operations in space flexible spacecraft p 31 N87-10138 Dynamics of flexible mechanisms p 32 N87-10938 p 44 A87-19707 Cohparison of methods for the calculation of thermal A method of studying the behavior Of composite Wave-absorbingcontrollers for a flexible beam contact resistance of the first Brazilian satellite materials in simulated space environments p 28 A87-23986 [ INPE-3864-TDLI2171 p21 N87-12596 p 53 N87 10940 The international Space Station takes shape p4 A87-24123 Design improvement and radiation contaminationtests Modal analysis technique used in Germany for Prestudy 1 Ultraviolet radiation acceleration. volume 1 C [CERT 4193-VOL-11 p 53 N87-10949 aerospace structures p 30 A87-28544 Identification. applications. and dynamic analysis of CANADA Design improvement and radiation contamination tests nonlinear spacecraft components p 30 A87-28558 Stabilizationof a class of hybridsystems arising in flexible Prestudy 1 Ultraviolet radiation acceleration Volume 2 The dynamical qualification of present and future spacecraft p 24 A87-12139 Appendix. detailed results spacecraft structures p30 A87-29368 [ CERT-4193-VOL-21 p 53 N87-10950 Development of a test procedure and facility for the On optimal passive and active control of precision investigation of a Canadarm joint brake anomaly Improving the irradiation plus contamination tests spacecraft structures p 31 N87-10891 p 59 A87-15191 Prestudy 2 Successiveirradiations and synergics Volume Analysis of long thin walled tubes p 20 N87-10895 Dynamics of ttw orbiter based flexible members 1 Tests and conclusions Damping representationrelated to spacecrafl structural p 27 A87-18324 [CERT-4193-VOL-3] p 53 N87-10951 design p 31 N87-10898 On the Orbiter based deployment of flexible members Improving radiation plus contamination tests Prestudy Translent external loads or interlace forces [AAS PAPER 85.6731 p 16 A87-18489 2 Successive irradiations and synergics Volume 2 reconstructed from structural response measurements Analysls of the on spot phenomenon on beamcharged Annexes Annex 1 Detailed results Annex 2 Control and p 20 N87-10910 dielectrics p 51 A87-21993 improvement of optical measurements Structural system identification using single and Response of discretized structures with elasto-plastic [CERT-4193-VOL-4] p 53 N87-10952 multiaxial vibration test data p 20 N87-10911 deformation to non-stauonaryrandom excitatnn Improving radiaton/contaminatlontests Initial results from multiaxes transent testig p 28 A87-22831 [CERT-419300/1-DERTS] p 54 N87-10954 p 21 N87-10917

D- 1 INDIA FOREIGN TECHNOLOGY INDEX

Experience on the Olympus modal survey test Contraves' antenna tip hinge mechanism for Selenia Engineering and software interfacing for thermal, p6 N87-10919 Spazio's 20130 GHz antenna p 74 N87-16944 structural and anitude control related with spacecraft Influence of fiber orientation and boundary conditions Dynamics and Control Analysis Package (DCAP) An p 21 N87-10928 on the dynamic behavior of a cylindricallytelescoping solar automated analysis and design tool for structural control Large flexible space structures: Some simple models array (INTELSAT 6) p 32 N87-10925 of space structures p 39 N87-16947 [TW-269] p 32 N87-10957 The Kl-K2 interactionfor matrix splittingin unidirectional Thermomechanical characteristics of dichroic L-band antennas for regional mobile communication laminates of carbon fiber reinforced epoxy subreflectors p 22 N87-16952 satellites p 47 N87-15377 p 52 N87-10932 Giotto spacecraft high gain antenna mechanical design Debonding analysis of thermally stressed and development p 18 N87-16938 fiber-reinlorcedcomposite materials p 52 N87-10933 J Engineering and software interfacing for thermal. Performance characteristics of composite materials Structural and dynamic control related with spacecraft p 53 N87-10935 activities p 22 N87-16948 JAPAN Rendezvous and docking and space robotics proximity Composites design handbook for space structure Fabrication of a carbon fibrelaluminium alloy composite applications. Executive summary under microgravity p 48 A87-11384 operations. Part 5: Executive summary [ESA-CR(P)-2196] p 54 N87-10982 [ NLR-TR-85099-UI p 62 N87-19441 On the initiation of SPS development Offset unfurlable antenna. Phase 2A Executive Sensors for a system lo control the liquid flow into an p 1 A87-12086 summary evaporation cold plate of a two-phase heal transport [ MBB-R-020013069-Rl p 70 N87-11066 Effect of electron-beam radiation on graphite epoxy system for large spacecraft Docking mechanisms technology study composites p 49 A87-13071 [ NLR-TR-86001-U] p 23 N87-19442 [ESA-CR(P)-2273] p 71 N87-11833 Flexibility control of solar arrays based on stale Large wheel actuators definition study estimation by Kalman filtering p 26 A87-15450 [TELDIX-15-020-8801 p 33 N87-11834 Satellite motion analysis via laser reflector panern S Activities report in materials and construction processing for rendez-vous and docking [ ISSN-0174-39101 p 54 N87-13589 [IAF PAPER 86-06] p 65 A87-15805 SPAIN Design and development of a telescopic axial boom S band 3.5-m-diameter fan rib type deployable mesh Construcciones Aeronauticas S.A. (CASA) large reflector antenna p9 N87-16935 p 14 N87-16322 antenna for satellite use Extendable retractable telescopic mast for deployable [ IAF PAPER 86-26] p 11 A87-15819 Development of mm-wave radiometer antenna structures p8 N87-16323 reflector p 47 N87-16941 A concept of the Energy Storable Orbital Power Station A Sener mechanism: Fine adjustment mechanism for Experience gained by sector model testing of an (ESOPS) unfurlable meshlrib antenna p 14 N87-16925 the Far Infrared and Submillimeter Space Telescope [IAF PAPER 86.1491 p 42 A87-15898 (FIRST) (F f F) p 74 N87-16946 Analysis of high precision composite sandwich A new structure toward high precision large antenna antennas p 56 N87-16929 SWEDEN [IAF PAPER 86-201] p 15 A87-15929 Tele-X antenna module structure qualification program Development status of the ERS-1 SAR antenna Development of a 'Hingeless Mast' and its D9 N87-16939 p 21 N87-10924 applications SWITZERLAND Features and technologies of ERS-1 (ESA) and X-SAR [IAF PAPER 86-2051 p 15 A87-15933 antennas p9 N87-17152 Space commerce '86; Proceedings of the lnternational Concept of tension activated cable lattice antenna Conference and Exhibition on the Commercial and [IAF PAPER 86-2061 p 15 A87-15934 Industrial Uses of Outer Space, Montreux. Switzerland, I Dynamics formulation and simulation of multi-body June 16-20. 1986 p 69 A87-29401 space structures A four node Marguerre element for non-linear shell INDIA [IAF PAPER 86-2381 p 26 A87-15957 analysis p 30 A87-30545 Vibration data reduction for design, analysis and testing Instability of rotating blades in space Development of a 2.8 m offset antenna reflector using of spacecraft p 23 A87-10901 [IAF PAPER 86-2421 p 65 A87-15959 inflatable, space-rigidized structures technology Solar array mechanisms for Indian satellites. APPLE, International Symposium on Space Technology and p 8 N87-16927 IRS and INSAT-IITS Science, 14th. Tokyo, Japan, May 27-June 1. 1984. [IAF PAPER 86-1421 p 11 A87-15893 Proceedings p 66 A87-18201 Possible areas of collaboration between DFVLR and A basic study for divided modal survey of future large U ISRO in the fields of structures and materials spacecraft p 27 A87-18241 p 56 N87-15252 Simplex Mast - An extendible mast for space U.S.S.R. INTERNATIONAL ORGANIZATION applications p3 A87-18242 Optimization of a microwave-beam energy transmission Space materials in Europe p 49 A87-13067 2D-Array mission - Two-dimensionally deployable solar channel p 46 A87-29753 Navigation. guidance, rendez-vous and docking - cell array mission p 15 A87-18243 UNITED KINGDOM Activities carried out for Columbus by the flight operations Collisional probability in space and the debris The tidal velocity field in the Local Supercluster organization environment in future p 66 A87-18247 p 23 A87-11159 [ IAF PAPER 86-09] p 65 A87-15808 The electron irradiationtest of thermal control matenal Space Station - NASA's greatest challenge Factors influencing selection of space transportation p 50 A87-18271 p2 A87-16399 options Degradation of spacecraft thermal shield materials by Materials - The challenge of space p 50 A87-18867 [IAF PAPER 86.1081 p 65 A87-15871 irradiation of energetic particles p 18 A87-18273 International Week on Bonding and Joining Deployment analysis of the Olympus Astromast and Control of solar battery arrays of spacecraft with Technologies, 1st. Bordeaux. France, April 15-18, 1986. comparison with test measurements p 61 A87-31220 consideration of the structural flexibility Selected Papers p 67 A87-20144 ISRAEL p 44 A87-18319 Efficient modal analysis of damped large space Buckling and nonlinear response of imperfect Anitude control experiment lor flexible spacecraft structures p 28 A87-23995 three-legged truss columns p 19 A87-30296 p 27 A87-18320 Solar power satellite built of lunar materials ITALY Truncation error estimation of a spacecraft model with p 68 A87-25426 Two-dimensional articulated systems developable on a a flexible appendage p 16 A87-18321 Space Tech '86: Proceedings of the International single or double curvature surface p 58 A87-12285 Numerical and experimental evaluation of poles and Conference. Geneva, Switzerland, May 14-16, 1986 Advanced propulsion status in Western Europe system zeros for large flexible space structures p 68 A87-25751 [IAF PAPER 86-1721 p 63 A87-15913 p 27 A87-18322 The role of robotics in space p 60 A87-25756 Assembly of thermmlastic continuous elements Local output-feedback control for large flexible space The role of expert systems on Space Station [IAF PAPER 86-2071 p 59 A87-15935 structures p 27 A87-18323 p4 A87-25758 Nonlinear effects in thermal conduction problems of Research and development of a small-sized space Satellite construction p 61 A87-27454 large space structures manipulator Rationalising Space Station p5 A8727455 [IAF PAPER 86.2081 p 18 A87-15936 [AAS PAPER 85-6601 p 60 A87-18481 Extending the Space Station infrastructure Digital networks and their evolution - Space and Large-angle slewing of flexible spacecraft p5 A87-28953 terrestrial systems; Proceedings of the Thirty-third [AAS PAPER 85-6741 p 27 A87-18490 The effect of the non-uniformstress distribution in the International Congress on Electronics and Twenty-sixth Flexibility control of solar battery arrays. II - Vibration blankets of single and twin boom solar array panels upon InternationalMeeting on Space, Rome, Italy, Mar. 18.20, and anitudecontrol based on stale estimation of differential their modal characteristics p 32 N87-10904 1986 p 68 A8724701 mlar cell sensors p 45 A87-22968 Modern control of large flexible spacecraft, ESA ASTP A robotic system for dexterous tasks Flexibility control of solar banery arrays. 111 - vibration study p60 A87-25757 and anitude control with consideration of the dynamics [BL-6206-ISSUE-2] p 70 N87-10956 Computational methods in elastic periodic structures of a reaction wheel as an actuator p 45 A87-22969 HPSA: High Power Solar Array study analyses p 32 N87-10901 Rectenna composed of a circular microstrip antenna [BAE-TP-8071I p 47 N87-11352 Robot system for dexterous tasks (for space p 46 A87-25700 A study of large space structures applications) Japanese laboratory proposal p 69 A87-25753 [ LR468691 p 21 N87-11832 [ ETN-86-985821 p 61 N87-15472 Overview of planned tests of space malerials Development of a continuous manufacturing method for Effects of curing stresses on composite structures D 56 N87-15990 a CFRP collapsible tube mast p 56 N87-16930 Study on solid surface, deployable antenna reflector [AERE-G-3898] p 54 N87-13572 Dielectric support structures for spacecraft antenna p8 N87-16928 feeds p 17 N87-16931 Development of 30120 GHz satellite antenna Development of lightweight dimensionallystable carbon Structures p 9 N87-16933 fiber composite antenna reflectors for the INSAT-1 satellite p 56 N87-16936 N Prediction of the electrical performance of Inflatable Space Rigidized Structure (ISRS) offset antenna reflectors NETHERLANDS and correlation with RF measurements Design and verification activities and requirements for p 47 N87-16943 spacecraft structures D 20 N87-10890

D-2 CONTRACT NUMBER INDEX

TECHNOLOGY FOR LARGE SPACE SYSTEMS /A Bibliography (Supplement 17) OCTOBER 1987

Typical Contract Number Index Listing

F49620 83-C-0018 P 38 N87-16059 505-33 53 12 P 71 N87-11750 F49620-83-C 0067 P 22 N87-15264 505-63-01 P 57 N87-17906 F49620-83-C 0092 P 33 N87-13479 505-90-21-01 P 13 N87-14059 N87-10184 F49620-83-C-0117 P 42 N87-19435 506-43-21 02 P 52 NAS9-17207 p75 N87-18583 506-43-21 P 57 N87-18669 F49620-83-K-0032 P A87-13494 25 506-43-41 01 P 48 N87-18598 N87-15263 P 34 N87-18879 N87-16055 P 41 F49620-84-C-0025 P 17 N87-11827 N87-19157 506-43-41 02 P6 F49620-85-C-0004 P 58 N87-16870 N87-17845 P 17 F49620-85-C-0024 P 41 N87-19755 N87-16871 P 42 F49620-85-C-0094 P 38 506 43 51-04 P 21 N87- 1 1966 MOESC 56460102 P 46 A87-25700 NUMBER P 17 N87-14366 NUMBER NAGW 21 P 26 A87-15931 506-46 11 01 P 70 N87-10945 NAGI 126 P 24 A87-13395 P 75 N87-17821 NAGI 224 P 30 A87-30294 506 46 21-01 P8 N87-16848 NAGI 225 D 18 A87-18487 N87-16050 Listings in this index are arranged alpha-numeri- N87-10172 506 49 31-01 P 37 P 31 506 62 23 P 34 N87-15262 NAG1-343 P 51 A87-27178 cally by contract number. Under each contract 542 06 11 01 P 73 N87-16014 NAG1-436 D 24 A87-13431 number. the accession numbers denoting docu- 679-40 00 P 39 N87-16880 P 25 A87-13494 ments that have been produced as a result of re- NAG1-464 P 41 N87-17835 search done under that contract are arranged in NAGI-517 P 13 N87-14059 ascending order with the AlAA accession numbers NAG3-576 P 47 N87-16971 NAG3495 P 68 A87-22738 appearing first . The accession number denotes the NAG5250 P 42 N87-18880 number by which the citation is identified in the NAG5-475 P 67 A87-20055 abstract section . Preceding the accession number NAG5-749 P 33 N87-13476 A87-20055 is the page number on which the citation may be NAG8-054 P 67 NAG8-058 P 67 A87-20055 found . NAG8-551 P 23 N87-16956 NASA ORDER L 91 188 B P 24 A87-13394 NASA ORDER 30429-D P 42 N87-18880 AF-AFOSR-0025-83 ...... p 38 N87-16056 NASA WORK ORDER 30429-D p 34 N87-13788 AF-AFOSR-0144-85 ...... p 42 N87-I9434 NASI-15763 P 17 N87-14366 AF-AFOSR-0221-83 ...... p 54 N87-12601 NASl -16854 P 57 N87-18669 AF-AFOSR-0242-82 ....p 33 N87-11829 NAS1-17070 P 13 N87-14059 AF-AFOSR-0271-84 ...... p 38 N87-16872 NASI-I7536 P 15 A87-15930 AF-AFOSR-83-0017 ...... p 29 A87-24552 P 17 N87-16870 AF-AFOSR-83-0361 ...... p 28 A87-23212 NASI 17551 P 34 N87-15262 AF-AFOSR-84-0020A ...... p 19 A87-20247 NASI-17660 P 15 A87-11842 AF-AFOSR-84-0342 ...... p 51 A87-21993 P 42 N87-19755 AF-AFOSR-84-0393 ...... p 13 N87-14059 NASI-17919 P 25 A87-13433 AF-AFOSR-84-0398 ...... p 13 N87-14059 P 29 A87-24049 CAN-DEPT-COMM-PI ST-36100-3-031 p 14 N87-16934 NAS1-18107 P 13 N87-14059 CNR-PSN-83-098 ...... p 58 A87-I2285 NAS7-918 P 20 A87-31225 DE-AC02-80ER-I0719 ...... p 23 A87-11159 P 33 N87- 13478 DE-AC04-76DP-00789 ...... p 33 N87-I2802 P 10 N87-19310 DE-AC05-840R-21400 ...... p 70 N87-10947 NAS7 938 P 51 A87-24919 ESA-4818181-NL-MD ...... p 72 N87-14364 P 52 A87-27936 ESA-5195/82-NL-BI ...... p 71 N87-11833 NASB 33982 P 67 A87-20055 ESA-5263/82-NL-GM ...... p 47 N87-16941 NASB 36612 P 63 A87-31133 ESA-5277/82-NL-PP ...... p 9 N87-16935 NAS9 17020 P 72 N87-13989 ESA-5279/82-F-RD(SC) ...... p 13 N87-13626 NAS9-17207 P 75 N87-18583 ESA-5347/83-NL-Bl(SC) ...... p 72 N87-14359 NAS9-17229 P 62 N87-18984 ESA-5664/83-NL-B1 ...... p 70 N87-10956 NAS9-17299 P 71 N87-13167 ESA-5978/84-NC-PB(SC) ...... p 75 N87- 19814 D 75 N87-17838 ESA-6060184 ...... ; ...... p 62 N87-19441 P 62 N87-20351 ESA-6064/84-NL-PB ...... p 47 N87-11352 NAS9-17560 P 71 N87-13466 ESTEC-5158/82-NL-PB(SC) ...... p 21 N87-10928 NGA-47-003-052 P 27 A87-22364 P 22 N87-16948 NIVR-1073 ...... P 23 N87-19442 ESTEC-5206/82-NL-PB(SC) ...... p 70 N87-11066 NSERC-A-2181 ...... p 27 A87-18324 P 14 N87-16925 NSERC-A-4140 ...... p 51 A87-21993 ESTEC-5209/82-NL-PB(SCl ...... p 12 N87- 10894 NSERC-A-7109 ...... p 24 A87-12139 P 22 N87-13484 NSERC-G-0662 ...... p 27 A87-18324 P 34 N87-13485 NSERC-67-1547 ...... p 16 A87-18489 ESTEC-5352/83-NL-HP(SC) ...... p 70 N87-10956 NSF ATM-83-00426 ...... p 67 A87-20055 ESTEC-5781/83-NL-AB ...... p 53 N87-10949 NSF ATM-85-06642 ...... p 67 A87-20055 P 53 N87-10950 NSF ECS-83-04968 ...... p 25 A87-13494 P 53 N87-10951 NSF ECS-85-16445 ...... p 24 A87-13431 P 53 N87-10952 NSF MCS-85-04316 ...... p 13 N87-14059 P 54 N87-10954 NSG-1185 ...... p 16 A87-28882 ESTEC-5816/84-NL-PB(SC) ...... p 54 N87-10982 NSG-1321 ...... p 20 N87-10406 ESTEC-5907/84-NL-AN(SC) ...... p 33 N87-11834 NSG-1490 ...... p 19 A87-18940 ESTEC-6061/84-NL-PB(SC) ...... p 47 N87-13864 N00014-82-M-0133 ...... p 25 A87-I4941 ESTEC-S106/84/NL/AN(SC) ...... p 54 N87-13572 N00014-84-C-0413 ...... p 57 N87-17863 FO4611-85-C-0092 ...... p 14 N87- 16058 N00024-85-C-5301 ...... p 50 A87-19343 FO4701-85-C-0086 ...... p 67 A87-22416 SNSF-2.353.0.84 ...... p 30 A87-30545 P 45 A87-22659 W-7405-ENG-48 ...... p 10 N87-17846 F19628-82-C-0081 ...... p 46 A87-27018 P 41 N87-18101 159-41-01-01-00 ...... p 10 N87-19310 F19628-83-K-0028 ...... p 48 N87-20080 480-51-13-01 ...... p 5 N87-10170 F33615-83-K-3205 ...... p 19 A87-20247 481-50-32 ...... p 54 N87-10960 F49620-82-K-0034 ...... p 59 A87-13715 P 71 N87-11838 F49620-83-C-0017 ...... p 29 A87-25680 P 72 N87-14423

E- 1 REPORT NUMBER INDEX

TECHNOLOGY FOR LARGE SPACE SYSTEMS /A Bibliography (Suppledent 17) OCTOBER 1987

Typical Report Number Index Listing AlAA PAPER 87-0019 P 11 A87-22363 # ESA CR(P) 2273 P 71 N87-11833 # AlAA PAPER 87 0020 P 27 A87-22364 * # ESA CR(P) 2291 VOL 1 P 75 N87-I9814 # AlAA PAPER 87 0073 P 16 A87-22395 # AlAA PAPER 87 0074 P 28 A87-22396 # ESA SP-238 P 70 N87-10886 # ESA SP-265 P 72 N87-14394 # AlAA PAPER 87-0102 P 67 A87-22416 # AlAA PAPER 87-0104 P 45 A8722417 ' # N87-11832 # AlAA PAPER 87-0105 P 51 A87-24919 # ETN 86-97949 P 21 N87-10886 # A87-22462 * # ETN 86 98078 P 70 AlAA FAPER 87-0174 P 28 N87-10113 # NASA-CR-171940 p 72 N87-13989 ' # AlAA PAPER 87 0341 P 52 A87-31300 * # ETN 86 98079 P 70 N87-I0982 # AlAA PAPER 87 0475 P 45 A87-22659 # ETN 86 98082 P 54 N87-I0956 A87-22721 # ETN 86 98083 P 70 # AlAA PAPER 87 0585 P4 N87-I1066 # A AA PAPER 87 0612 P 68 A87-22738 * # ETN 86 98085 P 70 N87-11352 # A87-22751 * # ETN 86 98086 P 47 AlAA PAPER 87-0636 P4 N87-13864 # A87-27605 # ETN-86-98087 P 47 AlAA PAPER 87-0658 P5 N87-10949 # AlAA PAPER 87-0689 P 61 A87-27616 # ETN-86 98105 P 53 N87-10950 # A87-27617 # ETN-86-98106 P 53 AlAA PAPER 87-0690 P 12 N87-10951 # A87-27621 # ETN-86 98107 P 53 Listings in this index are arranged alpha-numeri- AlAA PAPER 87-0694 P 69 N87-10952 # A8741112 * # ETN 86 98108 P 53 AlAA PAPER 87-1655 P 70 N87-14359 # cally by report number The page number indicates AlAA PAPER 87 1687 P 12 A87-31121 # ETN 86 981 16 P 72 ETN 86 981 23 N87-10954 # the page on which the citation is located The ac- AlAA PAPER 87 1694 P 61 A87-31122 # P 54 ETN 98138 P 71 N87-11833 # AlAA PAPER 87-1695 P5 A87-31123 * # 86 cession number demotes the number by which the ETN 86 98140 P 13 N87-13626 # citation is identified An asterisk (*) indicates that ETN 98144 P 33 N87-11834 # AIAA-87-0824-CP P 48 N87-18598 * # 86 the item is a NASA report A pound sign (#) indi- ETN-86 98150 P 22 N87-13484 # ETN-86 98151 P 34 N87-13485 # cates that the item is available on microfiche ANTINTEA104 85 P 13 N87-13626 # ETN-86-98280 P 54 N87-13589 # N87-10957 # ASME PAPER 86-WAIAPM-41 p 28 A87-23212 # ETN-86 98503 P 32 ETN-86-98562 P 61 N87-15472 # AAC-TN-1147-REV.A p 17 N87-16870 * # . ETN-87 98644 P 72 N87-14364 # BAE-TP 8071 P 47 N87-I1352 # ETN-87-98893 P 72 N87-14394 # A87-15377 * # AAS PAPER 85-451 PI ETN 87-99278 P 62 N87-19441 # A87-15380 # EL-62064SSUE 2 P 70 N87-I0956 # AAS PAPER 85-456 PI ETN-87-99281 P 23 N87-19442 # A87-18453 * # AAS PAPER 85-647 P3 ETN-87-99482 P 75 N87-19814 # AAS PAPER 85-660 P 60 A87-18481 # 68666169 P 32 N87-10957 # A87-18486 # 68679797 P 23 N87-19442 # AAS PAPER 85-666 P 60 GPO 58-629 ~6 N87-11640 # AAS PAPER 670 P 18 A87-18487 * # 85 GPO 61 777 P7 N87-12402 # A87-18489 # CERT 4193 VOL 1 P 53 N87-10949 # AAS PAPER 85-673 P 16 GPO 63 143 P7 N87-12574 # A87-18490 # SERT 4193 VOL-2 P 53 N87-10950 # AAS PAPER 85-674 P 27 GPO-64-727 P 73 N87-15028 # AAS PAPER 85-683 P 16 A87-18495 # CERT 4193 VOL 3 P 53 N87-10951 # CERT 4193 VOL 4 P 53 N87-10952 # H REPT 99 829 ~6 N87-11640 # N67-11829 # CERT 419300IFW1IT01 DERTS p 53 N87-10949 # AD A168622 P 33 H-REPT 99 829 ~6 N87-11641 # AD A169552 P 13 N87-14370 # CERT 419300/PR2/T01 DERTS p 53 N87-10951 # N87-12601 # CERT 419300I1 DERTS P 54 N87-10954 # AD-A169826 P 54 HL86/1252(C14) P 54 N87-13572 # AD-A170316 P 33 N87-13479 # N87-15263 # CONF 860899 1 P 41 N87-18101 # AD-A172716 P 34 HPSAIRPTI8071 P 47 N87-11352 # AD-A172811 P 17 N87-16055 # CONF 86091 13 1 P 10 N87-17846 # N87-16056 # AD-A172880 P 38 IAF PAPER ST-86-08 P 65 A87-16141 # N87-15264 CSDL T-920 P 71 N87-13466 * # AD-AI72966 P 22 # IAF PAPER ST-86 17 P 15 A87-16145 # AD-A173083 P 38 N87-16871 # DEIGEI006.85 ...... p 13 N87-13626 # AD-A1 73144 P 41 N87-17845 # IAF PAPER 86-06 ...... A87-15805 # AD-A173470 P 57 N87-17863 # IAF PAPER 86-07 ...... A87-15806 DE86-009996 ...... p 70 N87-10947 # # AD-A1 73756 P 14 N87-16058 # IAF PAPER 86-09 ...... A87-15808 DE86011636 ...... p 10 N87-17846 # # AD-A173950 P 73 N87-16366 # IAF PAPER 86-108 ...... A87-15871 # DE86013754 ...... p 33 N87-12802 # AD-A173967 P 38 N87-16059 # IAF PAPER 86-142 ...... A87-15893 # DE86-013906 ...... p 41 N87-18101 # AD-A174880 P 42 N87-19434 # IAF PAPER 86-149 ...... A87-15898 # AD-A174914 P 42 N87-19435 # IAF PAPER 86-156 ...... A87-I5904 # DM51-CIPLIFLI0099.82 ...... p 72 N87-14364 # AD-A175019 P 38 N87-16872 # IAF PAPER 86-172 ...... A87-15913 # AD-AI75024 P 58 N87-19457 # IAF PAPER 86-201 ...... A87-15929 # E-2904 ...... p 73 N87.16321 ' # IAF PAPER 86-202 ...... A87-15930 '# E-3225 ...... p 39 N87.16880 * # AD-6109229L ...... p 74 N87-17810 # IAF PAPER 86-203 ...... A87-15931 *# E-3268 ...... p 54 N87-10960 * # IAF PAPER 86-204 ...... A87-15932 # E-3281 ...... p 71 N87-11838 * # AERE-G-3898 ...... p 54 N87-13572 # IAF PAPER 86-205 ...... A87-15933 # E-3338 ...... p 72 N87-14423 * # IAF PAPER 86-236 ...... A87-15934 # E-3429 ...... p 57 N87-17906 * # AFOSR-86-0286TR ...... p 33 N87-11829 # IAF PAPER 86-207 ...... A87-15935 # AFOSR-86-0308TR ...... p 54 N87-12601 # IAF PAPER 86-208 ...... A87-15936 ED/82-362/RD-VOL-l p 22 N87-13484 # # AFOSR-86-0489TR ...... p 33 N87-13479 # ...... IAF PAPER 86-20 ...... A87-15814 ED/82-362/RD-VOL-2 ...... p 34 N87-13485 # # AFOSR-86-0858TR ...... p 38 N87-16056 # IAF PAPER 86-212 ...... A87-15939 # AFOSR-86-0884TR ...... p 22 N87-15264 # IAF PAPER 86-238 ...... A87-15957 ESA-CR(P)-ZOll-VOL-2 ...... p 72 N87-14364 # # AFOSR-86-0885TR ...... p 38 N87-16871 # IAF PAPER 86-242 ...... A87-15959 t ESA-CR(P)-2196 ...... p 54 N87-10982 # AFOSR-86-0900TR ...... p 17 N87-16055 # IAF PAPER 86-246 ...... p 26 A87-15963 * # ESA-CR(P)-2197 ...... p 70 N87-10956 # AFOSR-86-0905TR ...... p 34 N87-15263 # IAF PAPER 86-26 ...... p 2 A87-15817 * # ESA-CR(P)-2199 ...... p 70 N87-11066 # AFOSR-86-1003TR ...... p 41 N87-17845 # IAF PAPER 86-27 ...... p 2 A87-15818 # ESA-CR(P)-PZOl ...... p 47 N87-11352 # AFOSR-86-1007TR ...... p 38 N87-16059 # IAF PAPER 86-28 ...... p 11 A87-15819 # ESA-CR(P)-2202 ...... p 47 N87-13864 # AFOSR-86-2075TR ...... p 42 N87-19435 # IAF PAPER 86-322 ...... p 42 A87-16019 # ESA-CR(P)-2217-VOL-I ...... p 22 N87-13484 # AFOSR-86-2082TR ...... p 42 N87-19434 # IAF PAPER 86-349 ...... p 43 A87-16041 # ESA-CR(P)-2217-VOL-2 p 34 N87-13485 # AFOSR-86-21 11TR ...... p 58 N87-19457 # ...... IAF PAPER 86-419 ...... p 65 A87-16081 # ESA-CR(P)-2227-VOL-l p 53 N87-10949 # AFOSR-86-2193TR ...... p 38 N87-16872 # ...... IAF PAPER 86-442 ...... p 2 A87-16096 * # ESA-CR(P)-2227-VOL-2 p 53 N87-10950 # ...... IAF PAPER 86-453 ...... p 2 A87-16105 # ESA-CR(P)-2227-VOL-3 p 53 N87-10951 # AFRPL-TR-86-054 ...... p 14 N87-16058 # ...... IAF PAPER 86-456 ...... p 2 A87-16108 # ESA-CR(P)-2227-VOL-4 ...... p 53 N87-10952 # ESA-CR(P)-2238 ...... p 72 N87-14359 # IAF PAPER 86461 ...... p 2 A87-16110 * # AFWAL-TR-86-3059-VOL-2 ...... p 73 N87-16366 # ESA-CR(P)-2245 ...... p 54 N87-10954 # IAF PAPER 86-507 ...... p 43 A87-16132 # ESA-CR(P)-2265 ...... p 33 N87-11834 # AIMPAPER 87-0018 ...... p 29 A87-24902 # ESA-CR(P)-2271 ...... p 13 N87-13626 # CASE-86-71 ...... p 13 N87-14059 * #

F- 1 INPE-3864-TDLI217 REPORT NUMBER INDEX

INPE-3864-TDL/217 ...... p 21 N87-12596 # NASA-CASE-MSC-20162-1 ...... p 74 N87-17036 * # US-PATENT-APPL-SN-913432 ..... p 73 N87-I5259 * # NASA-CASE-MSC-20635-1 ...... p 17 N87-14373 * # US-PATENT-APPL-SN-921572 ..... p 57 N87-18613 * # ISBN-2-85428-149-7 ...... p 70 N87-10113 # NASA-CASE-MSC-20985-1 ...... p 61 N87-15260 * # US-PATENT-APPL-SN-924397 .._. p 62 N87-18595 # NASA-CASE-MSC-21056-1 ...... p 62 N87-18595 * # US-PATENT-APPL-SN-929865 ..... p 62 N87-18596 * # NASA-CASE-MSC-21096-1 ...... p 62 N87-18596 * # ISI-85 p 38 N87-16871 # ...... US-PATENT-CUSS-I35-903 ...... p 74 N87-17036 * # NASA-CP-2327-PT-1 ...... p 71 N87-11717 # US-PATENT-CLASS-I6-294 ...... p 17 N87-14373 * # ISSN-0082-5255 ...... p 74 N87-17810 # NASA-CP-2327-PT-2 ...... p 71 N87-11750 * # US-PATENT-CLASS-I6-370 ...... p 17 N87-14373 * # ISSN-0174-3910 ...... p 54 N87-13589 # NASA-CP-2399 ...... p 70 N87-10720 * # US-PATENT-CUSS-160-23R ...... p 74 N87-17036 * # ISSN-0379-6566 ...... p 70 N87-10886 # NASA-CP-2423-REV ...... p 73 N87-16321 * # US-PATENT-CLASS-160.265 ...... p 74 N87-17036 * # ISSN-0379-6566 ...... p 72 N87-14394 # NASA-CP-2447-PT-1 ...... P 73 N87-16014 * # US-PATENT-CLASS-244-121 ...... p 74 N87-17036 * # US-PATENT-CLASS-244-158R .... p 74 N87-17036 * # JPL-PUB-86-46 ...... p 10 N87-19310 * # NASA-CR-171939 ...... p 71 N87-13466 * # US-PATENT-CLASS-296-100 ...... p 74 N87-17036 * # NASA-CR-171940 ...... p 72 N87-13989 * # US-PATENT-CLASS-403-102 ...... p 17 N87-14373 * # JPL-9950-1206 ...... p 33 N87-13478 * # NASA-CR-171942 ...... p 71 N87-13167 * # US-PATENT-CLASS-403-119 ...... p 17 N87-14373 * # NASA-CR-171960 ...... p 75 N87-17838 * # US-PATENT-CLASS-403-146 ...... p 17 N87-14373 ' # L-15830 ...... p 71 N87-11750 * # NASA-CR-171967 ...... p 75 N87-18583 * # US-PATENT-CLASS-403.163 ...... p 17 N87-14373 * # L-16139 ...... p 52 N87-10184 * # NASA-CR-171981 ...... p 62 N87-20351 ' # US-PATENT-CLASS-403-85 ...... p 17 N87-14373 * # L-16242-PT-1 ...... p 73 N87-16014 * # NASA-CR-I77064 ...... p 20 N87-10406 * # NASA-CR-178116 ...... p 57 N87-18669 * # US-PATENT-4,615,637 ...... p 17 N87-14373 * # LMSC-F104499 ...... p 38 N87-16059 # NASA-CR-178171 ...... p 17 N87-16870 * # US-PATENT-4,637.447 ...... p 74 N87-17036 * # NASA-CR-178199 ...... p 13 N87-14059 * # LR46869 ...... p 21 N87-11832 # NASA-CR-179811 ...... p 31 N87-10172 * # USAFA-TR-86-2 ...... p 13 N87-14370 # NASA-CR-179941 ...... p 33 N87-13476 * # MATRA-EPT/DT/VT068/012 ...... p 72 N87-14359 # NASA-CR-179947 ...... p 34 N87-13788 * # UTIAS-320 ...... p 74 N87-17810 # NASA-CR-179948 ...... p 33 N87-13478 * # MBB-R-0200/3069-R ...... p 70 N87-11066 # NASA-CR-I80073 ...... p 47 N87-16971 * # NASA-CR-180156 ...... p 23 N87-16956 ' # MCR-85-605-ISSUE-4 ...... p 57 N87-17863 # NASA-CR-180209 ...... p 42 N87-18880 * # MCR-86-575 ...... p 34 N87-15262 * # NASA-CR-180235 ...... p 10 N87-19310 * # NASA-CR-180239 ...... p 62 N87-18984 * # MDC-H2334 ...... p 42 N87-19435 # NASA-CR-4038 ...... p 17 N87-14366 * # NASA-CR-4039 ...... p 34 N87-15262 * # MDC-WOO70 ...... p 62 N87-20351 * # NASA-CR-4067 ...... p 42 N87-19755 * # MDC-WOO72 ...... p 71 N87-13167 * # MDC-WOO72 ...... p 75 N87-17838 ' # NASA-SP-7056(03) ...... p 75 N87-17820 * #

MM-4875-86-16 ...... p 22 N87-15264 # NASA-TM-86558 ...... p 41 N87-18600 * # NASA-TM-88859 ...... p 39 N87-16880 * # MSC-TFR-1614/1505 ...... p 58 N87-19457 # NASA-TM-88865 ...... p 54 N87-10960 * # NASA-TM-88868 ...... p 74 N87-17656 * # NAS 1.1 5:86558 ...... p 41 N87-18600 * # NASA-TM-88874 ...... p 71 N87-11838 * # NAS 1.15:88859 ...... p 39 N87-16880 * # NASA-TM-88914 ...... p 72 N87-14423 * # NAS 1.1 5:88865 ...... p 54 N87-10960 * # NASA-TM-88966 ...... p 57 N87-17906 * # NAS 1.1 5:88868 ...... p 74 N87-17656 * # NASA-TM-89004 ...... p 5 N87-10170 * # NAS 1.15:88874 ...... p 71 N87-11838 * # NASA-TM-89026 ...... p 21 N87-11966 * # NAS 1.15:88914 ...... p 72 N87-14423 * # NASA-TM-89043 ...... p 6 N87-11827 * # NAS 1.1 5:88966 ...... p 57 N87-17906 * # NASA-TM-89048 ...... p 70 N87-10945 * # N87-10170 * # NASA-TM-89056 ...... p 37 N87-1M150 * # N87-11966 * # NASA-TM-89057 ...... p 8 N87-16848 * # N87-11827 * # NASA-TM-89075 ...... p 75 N87-17821 * # N87-10945 * # NASA-TM-89110 ...... p 48 N87-18598 * # N87-16050 * # NASA-TM-89115 ...... p 41 N87-18879 * # NAS 1.15:89057 ...... p 8 N87-16848 * # NASA-TM-89274 ...... p 72 N87-14374 * # NAS 1.15:89075 ...... p 75 N87-17821 * # NAS 1.15:89110 ...... p 48 N87-18598 * # NASA-TP-2598 ...... p 7 N87-12581 * # NAS 1.15:89115 ...... p 41 N87-18879 * # NASA-TP-2612 ...... p 52 N87-10184 * # NAS 1.15:89274 ...... p 72 N87-14374 * # NAS 1.21:7056(03) ...... p 75 N87-17820 ' # NLR-TR-85099-U ...... p 62 N87-19441 # NAS 1.26:171939 ...... p 71 N87-13466 * # NLR-TR-86001-U ...... p 23 N87-19442 # NAS 1.26171940 ...... p 72 N87-13989 * # NAS 1.26171942 ...... p 71 N87-13167 * # OP-5 ...... p7 N87-15898 # NAS 1.26:171960 ...... p 75 N87-17838 * # NAS 1.26:171967 ...... p 75 N87-18583 * # ORNL/TM-9904 ...... p 70 N87-10947 # NAS 1.26:171981 ...... p 62 N87-20351 * # NAS 1.26:177064 ...... p 20 N87-10406 # PS-4 ...... p 54 N87-10954 # NAS 1.26:178116 ...... p 57 N87-18669 * # NAS 1.26:178171 ...... p 17 N87-16870 * # REPT-408-SMRM-79-0001 ...... p 72 N87-14374 * # NAS 1.26:178199 ...... p 13 N87-14059 * # REPT-957114-3 ...... p 33 N87-13478 * # NAS 1.26:179811 ...... p 31 N87-10172 * # NAS 1.26:179941 ...... p 33 N87-13476 * # S-HRG-99-954 ...... p 73 N87-15028 # NAS 1.26:179947 ...... p 34 N87-13788 * # NAS 1.26:179948 ...... p 33 N87-13478 * # SAC-1-120-778-C15 ...... p 75 N87-18583 * # NAS 1.26:180073 ...... p 47 N87-16971 * # SAIC-87.'1515 ...... p 75 N87-18583 * # NAS 1.26180156 ...... p 23 N87-16956 * # NAS 1.26:180209 ...... p 42 N87-18880 * # SNIAS-917A-CAICG ...... p 47 N87-13864 # NAS 1.26:180235 ...... p 10 N87-19310 * # SNIAS-975-CA/CG ...... p 75 N87-19814 # NAS 1.26:180239 ...... p 62 N87-18984 * # NAS 1.264038 ...... p 17 N87-14366 * # SPIE-571 ...... p 63 A87-10997 # NAS 1.264039 ...... p 34 N87-15262 * # SPIE-580 ...... p 64 A87-13705 # NAS 1.264067 ...... p 42 N87-19755 * # N87-11717 * # SVHSER-10630 ...... p 72 N87-13989 * # N87-11750 * # NAS 1.55:2399 ...... p 70 N87-10720 * # TELDIX-15-020-880 ...... p 33 N87-11834 # NAS 1.55:2423-REV ...... p 73 N87-16321 * # P 73 N87-16014 ' # TR-86-1 ...... p 17 N87-16055 # NAS 1.60:2598 ...... p 7 N87-12581 ' # NAS 1.60:2612 ...... p 52 N87-10184 * # TW-269 ...... p 32 N87-10957 # N87-15259 * # N87-18613 * # UCRL-93765 ...... p 10 N87-17846 # NAS 1.71:MSC-20985-1 ...... p 61 N87-15260 * # UCRL-94993 ...... p 41 N87-18101 # NAS 1.71:MSC-21056-1 ...... p 62 N87-18595 * # NAS 1.71:MSC-21096-1 ...... p 62 N87-18596 * # US-PATENT-APPL-SN-588039 .._..p 17 N87-14373 ' # US-PATENT-APPL-SN-764805 .._..p 74 N87-17036 * # NASA-CASE-LAR-13411-1SB ...... p 73 N87-15259 * # US-PATENT-APPL-SN-786561 .._..p 33 N87-12802 # NASA-CASE-LAR-13562-1 ...... D 57 N87-18613 * # US-PATENT-APPL-SN-904134 .._..p 61 N87-15260 # ACCESSION NUMBER INDEX

OCTOBER 1987 TECHNOLOGY FOR LARGE SPACE SYSTEMS /A Bibliography (Supplement 77)

lrypical Accession Number Index Listing A87-18201 # p66 A87-25451 # p68 N87-10901 # p32 A87-I8241 # p27 A87-25533 # p45 N87-10903 # P32 A87-25680 # p29 A87-I8242 # p3 N87-10904 # p32 A87-25687 * # p 19 A87-18243 # p 15 N87-10907 # P20 ACCESSION A87-25700 # p46 N87-10910 # P20 NUMBER A87-18247 # p66 A87-25751 # p68 A87-18266 # p 18 N87-10911 # P 20 A87-25752 # p4 N87-10912 # P20 A87-18271 # p50 A87-25753 # p69 A87-18273 # PI8 N87-10915 # p32 N87-10184 '# p 52 A87-25756 # p60 N87-10917 # p21 A87-18319 # p44 A87-25757 # p60 - A87-18320 # p27 N87-10919 # p6 A87-25758 # p4 A87-18321 # p 16 N87-10922 # p6 A87-25759 # p 4 N87-10923 # PI6 A87-I8322 # p27 A87-25976 # p69 A87-18323 # p27 N87-10924 # p21 A87-25978 # p 12 N87-I0925 # p32 SPONSORED MICROFICHE NUMBER A87-18324 # p27 A87-26060 # p46 N87-10926 # p21 A87-18342 * # P 44 A87-27018 # p 46 +,+,A A87-18451 # p66 N87-I0927 # PI7 A87-27178 # p 51 A87-18453 * # p 3 N87-10928 # P21 A87-27180 # p46 N87-10932 # P52 A87-18481 # p60 A87-27449 # p29 Listings in this index are arranged alpha-numeri- A87-18486 # p60 N87-10933 # P52 A87-27454 # p61 N87-10934 # P 52 cally by accession number. The page number listed A87-18487 '# p 18 A87-27455 # p5 A87-18489 # p 16 N87-10935 # P53 on the right indicates the page on which the citation A87-27603 # p 69 N87-10938 # P32 A87-18490 # p27 A87-27605 # p 5 is located. An asterisk (*) indicates that the item A87-18495 # p16 N87-10940 # P53 A87-27616 # p61 N87-10945 * # P 70 A87-18508 * # p 3 is a NASA report. A pound sign (X) indicates that A87-27617 # p 12 N87-10947 # P70 the item is available in microfiche. A87-18554 # p50 A87-27621 # p 69 A87-18852 # p67 N87-10949 # P53 A87-27936 * # p 52 N87-10950 # P53 A87-I8867 # p50 A87-27948 * # p 29 A87-18940 '# p 19 N87-10951 # P 53 A87-15450 # p 26 A87-28526 # p 69 N87-10952 # P53 A87-10026 # p 63 A87-19122 * # p 50 A87-15805 # p 65 A87-28537 # p 30 A87-10043 '# p 1 A87-19342 # p 50 N87-10954 # P54 A87-15806 # p 65 A87-28544 # p 30 A87-10092 # p 11 A87-19343 # p 50 N87-10956 # P70 A87-15808 # p65 A87-28552 # p 12 A87-19707 # p44 N87-10957 # P32 A87-I0901 # p23 A87-I5814 # p2 A87-28558 # p30 A87-19789 # p3 N87-10960 * # P 54 A87-I0997 # p63 A87-I5817 '# p 2 A87-28569 # p30 A87-19805 # p51 N87-10982 # P54 A87-11003 # p63 A87-15818 # p2 A87-28577 # p 19 N87-I1066 # P 70 A87-19872 # P44 A87-I1008 # p 64 A87-15819 # PI1 A87-28578 # p30 N87-I1352 # P47 A87-19874 * # P 45 A87-11013 # p64 A87-15871 # p65 A87-28882 * # p 16 N87-11640 # P6 A87-19878 # P45 A87-11159 # p23 A87-15893 # p 11 A87-28953 $ p 5 N87-I1641 # p6 A87-20055 * # p 67 A87-11355 * # p 48 A87-15898 # p42 A87-29368 # p 30 N87-I1717 '# p71 A87-20076 # p67 A87-I1359 # p 58 A87-I5904 # p2 A87-29401 # p 69 A87-20082 # P 19 N87-I 1750 * # P 71 A87-I1384 # p 48 A87-15913 # p63 A87-29441 # p69 N87-11761 '# p13 A87-20083 * # P 60 A87-11842 '# p 15 A87-15929 # p 15 A87-29466 # p70 N87-11762 '# p 13 A87-20144 # p67 A87-11847 # p 49 A87-15930 * # p 15 A87-29753 # p46 N87-11765 * # p 32 . A87-20148 # PI6 A87-12086 # p 1 A87-15931 * # P 26 A87-30294 * # p 30 N87-I1766 '# P 33 A87-20149 # P51 A87-12139 # p24 A87-15932 # p 26 A87-30296 # p 19 N87-11827 # p 6 A87-20247 # P 19 A87-12285 # p 58 A87-15933 # p15 A87-30545 # p 30 N87-I1829 # P33 A87-21257 # P 11 A87-13051 * # p 64 A87-15934 # p 15 A87-30891 # p 5 N87-11832 # P21 A87-21801 # P67 A87-13067 # p 49 A87-15935 # p 59 A87-30893 '# p 46 N87-11833 # p71 A87-21807 * # P 3 A87-13071 # p49 .A87-15936 # PI8 A87-31095 * # p 31 N87-I1834 # P33 A87-21975 # P67 A87-13097 # p49 A87-15939 # P 18 A87-31112 '# p70 N87-I 1838 * # P 71 A87-21992 * # P 51 A87-13098 # p49 A87-15957 # p26 A87-31121 # PI2 N87-11966 # P 21 A87-21993 # p51 . 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N87-14389 '# P 55 N87-17571 * # p 9 N87-14391 *# P 55 N87-17656 * # p 74 N87-14392 '# P 56 N87-17746 * # p 9 N87-14394 # P72 N87-17783 * # p 23 N87-14423 * # P 72 N87-17799 '# p 10 N87-15028 # P 73 N87-17810 # p74 ~87.15252 # P 56 N87-17820 * # p 75 N87-15259 * # P 73 N87-17821 * # p 75 N87-15260 * # P 61 N87-17822 * # p 39 N87-15262 * # P 34 N87-17823 * # p 40 N87-15263 # P34 N87-17824 * # p 40 N87-15264 # P22 N87-17825 * # p 40 N87-15377 # P47 N87-17826 * # p 23 N87-15472 # P61 N87-17827 * # p 40 N87-15898 # P7 N87-17828 '# p 14 N87-15908 # P7 N87-17829 * # p 40 N87-15990 # 1156 N87-17830 * # p 40 N87-16014 * # P 73 N87-17831 * # p 40 N87-16015 * # P 56 N87-17832 * # p 40 N87-16017 '# p 34 N87-17833 * # p 41 N87-16018 '# P 7 N87-17834 * # p 41 N87-16019 * # P 34 N87-17835 * # p 41 N87-16021 * # p 22 N87-17836 '# p 10 N87-16022 * # P 7 N87-17837 '# p 10 N87-16025 * # p 35 N87-17838 * # p 75 N87-16026 '# p 35 N87-17845 # p41 N87-16027 '# p 73 N87-17846 # p 10 N87-16028 '# P 35 N87-17863 # P 57 N87-16029 ' # p 8 N87-17906 * # p 57 N87-16030 * # p 8 N87-18015 # P57 N87-16031 '# p 17 N87-18101 # P4l N87-16032 * # p 35 N87-18583 * # p 75 N87-16033 '# p 8 N87-18595 * # p 62 N87-16034 * # p 8 N87-18596 * # p 62 N87-16035 '# p 35 N87-18598 * # p 48 N87-16036 '# p 36 N87-18600 * # p 41 N87-16037 '# p 36 N87-18613 '# p 57 N87-16040 * # p 36 N87-18669 * # p 57 N87-16041 '# p 36 N87-18879 '# p 41 N87-16042 '# p 14 N87-18880 ' # p 42 N87-16043 ' # p 36 N87-18984 ' # p 62 N87-16044 * # p 36 N87-19310 '# p 10 N87-16045 '# p 37 N87-19434 # p42 N87-16046 '# p 37 N87-19435 # p42 N87-16047 * # p 37 N87-19441 # p62 N87-16048 * # p 37 N87-19442 # p23 N87-16050 * # p 37 N87-19457 # p58 N87-16055 # p17 N87-19755 ' # p 42 N87-16056 # p38 N87-19814 # p75 N87-16058 # p 14 N87-20057 * # p 75 N87-16059 # p38 N87-20063 * # p 48 N87-16321 '# p 73 N87-20064 * # p 10 N87-16322 * # p 14 N87-20066 * # p 14 N87-16323 * # p 8 N87-20069 * # p 48 N87-16326 * # p 62 N87-20071 '# p 75 N87-16338 * # p 73 N87-20079 * # p 76 N87-16341 '# p38 N87-20080 * # p 48 N87-16366 # p73 N87-20351 '# p 62 N87-16662 # p 74 N87-16766 * # p 38 N87-16848 * # p 8 N87-16870 '# p 17 N87-16871 # p38 N87-16872 # p38 N87-16880 * # p 39 N87-16925 # p14 N87-16926 # p39 N87-16927 # p8 N87-16928 # p 8 N87-16929 # p56 N87-16930 # p56 N87-16931 # p 17 N87-16933 # p9 N87-16934 # p14 N87-16935 # p9 N87-16936 # p56 N87-16937 # p22 N87-16938 # p18 N87-16939 # p9 N87-16941 # p47 N87-16942 # p39 N87-16943 # p47 N87-16944 # p74 N87-16946 # p74 N87-16947 # p 39 N87-16948 # p 22 N87-16949 # p22 N87-16952 # p22 N87-16956 * # p 23 N87-16971 * # p 47 N87-17029 # p39 N87-17036 * # p 74 N87-17056 # p 56 N87-17152 * # p 9 N87-17277 # p 47 N87-17449 # p39

6-2 AVAILABILITY OF CITED PUBLICATIONS

IAA ENTRIES (A87-10000 Series) Publications announced in IAA are available from the AlAA Technical Information Service as follows: Paper copies of accessions are available at $10.00 per document (up to 50 pages), additional pages $0.25 each. Microfiche"' of documents announced in IAA are available at the rate of $4.00 per microfiche on demand. Standing order microfiche are available at the rate of $1.45 per microfiche for IAA source documents and $1.75 per microfiche for AlAA meeting papers. Minimum air-mail postage to foreign countries is $2.50. All foreign orders are shipped on payment of pro-forma invoices. All inquiries and requests should be addressed to: Technical Information Service, American Institute of Aeronautics and Astronautics, 555 West 57th Street, New York, NY 10019. Please refer to the accession number when requesting publications.

STAR ENTRIES (N87-10000 Series) One or more sources from which a document announced in STAR is available to the public is ordinarily given on the last line of the citation. The most commonly indicated sources and their acronyms or abbreviations are listed below. If the publication is available from a source other than those listed, the publisher and his address will be displayed on the availability line or in combination with the corporate source line.

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FEDERAL DEPOSITORY LIBRARY PROGRAM In order to provide the general public with greater access to U.S.Government publications, Congress established the Federal Depository Library Program under the Government Printing Office (GPO), with 50 regional depositories responsible for permanent retention of material. inter-library loan, and reference services. At least one copy of nearly every NASA and NASA-sponsored publication, either in printed or microfiche format, is :eceived and retained by the 50 regional depositories. A list of the regional GPO libraries, arranged alphabetically by state, appears on the inside back cover. These libraries are not sales outlets. A local library can contact a Regional Depository to help locate specific reports, or direct contact may be made by an individual. ADDRESSES OF ORGANIZATIONS

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Schedule A STANDARD PRICE DOCUMENTS AND MICROFICHE

NORTH PRICE PAGE AMERICAN FOREIGN CODE RANGE PRICE PRICE A01 Microfiche $6.50 $13.00 A02 001 -025 9.95 19.90 A03 026-050 11.95 23.90 AO4-AO5 051 -100 13.95 27.90 A06-AO9 101-200 18.95 37.90 A10-Al3 201 -300 24.95 49.90 A14-Al7 301 -400 30.95 61.90 A18-A21 401-500 36.95 73.90 A22425 501 -600 42.95 85.90 A99 601 -up NO1 45.00 80.00 NO2 48.00 80.00

Schedule E EXCEPTION PRICE DOCUMENTS AND MICROFICHE

NORTH PRICE AMERICAN FOREIGN CODE PRICE PRICE E01 $ 7.50 15.00 E02 10.00 20.00 E03 11.00 22.00 EO4 13.50 27.00 E05 15.50 31.00 E06 18.00 36.00 E07 20.50 41.00 E08 23.00 46.00 EO9 25.50 51.00 E10 28.00 56.00 Ell 30.50 61.00 E12 33.00 66.00 E13 35.50 71 .00 E14 38.50 77.00 E15 42.00 84.00 E16 46.00 92.00 E17 50.00 100.00 E18 54.00 108.00 E19 60.00 120.00 E20 70.00 140.00 E99

*Contact NTlS for price quote.

IMPORTANT NOTICE NTlS Shipping and Handling Charges U.S., Canada, Mexico - ADD $3.00 per TOTAL ORDER All Other Countries - ADD $4.00 per TOTAL ORDER Exceptions - Does NOT apply to: ORDERS REQUESTING NTlS RUSH HANDLING ORDERS FOR SUBSCRIPTION OR STANDING ORDER PRODUCTS ONLY NOTE: Each additional delivery address on an order requires a separate shipping and handling charge. 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA SP-7046 (17) 4. Title and Subtitle 5. Report Date Technology for Large Space Systems October, 1987 A Bibliography with Indexes 6. Performing Organization Code

7. Author@) 8. Performing Organization Report No.

10. Work Unit No. 9. Performing Organization Name and Address National Aeronautics and Space Administration Washington, DC 20546 11. Contract or Grant No.

t13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address

14. Sponsoring Agency Code

I 15. Supplementary Notes Compiled by Technical Library Branch and edited by Space Station Office, Langley Research Center, Hampton, Virginia.

16. Abstract

This bibliography lists 512 reports, articles and other documents introduced into the NASA scientific and technical information system between January 1, 1987 and June 30, 1987. 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 Authors@)) 18. Distribution Statement Large Space Antenna Unclassified - Unlimited Large Space Structures Large Space Systems

19. Security Classif. (of this report) 20. Security Classif. (of this page) 21. No. of Pages 22. Price Unclassified Unclassified 142 AO7lHC