Category 01 Systems Includes mission and program concepts and requirements, focus missions, conceptual studies, technology planning, systems analysis and integration, and Category 02 Analysis and Design Techniques Includes interactive techniques, computerized technology design and development programs, dynamic analysis techniques, environmental modeling, Includes erectable structures (joints, struts, and columns), deployable platforms and booms, solar sail, deployable reflectors, space fabrication techniques and Includes modeling, systems identification, attitude and control techniques, surface accuracy measurement and control techniques and systems, sensors and Includes techniques for power and data distribution, antenna RF performance analysis, communications systems, and spacecraft charging effects. Includes matrix composites, polyimide films and thermal control coatings, bonding 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. LARGE SPACE SYSTEMS A Bibliography (Suppl. 13) MARCH 1986 01 SYSTEMS Includes mission and program concepts and requirements, focus missions, conceptual studies, technology planning, systems analysis and integration, and flight experiments. A85-12502# SPACE EXPLOITATION - SPACELAB AN EASY APPROACH FOR DEVELOPING COUNTRIES: PROSPECTIVES AND SUGGESTIONS BY AERITALIA E. VALLERANI (Aeritalia S.p.A., Turin, Italy) IN: International Scientific Conference on Space, 23rd, Rome, Italy, March 24, 25, 1983, Proceedings. Rome, Rassegna Internazionale Elettronica Nucleare ed Aerospaziale, 1984, p. 45-49. The problem of access by developing countries to space information and resources is discussed from the Italian point of view. The international cooperation involved in the development of IRIS, Spacelab, and Eureca is considered; the ongoing commercialization of space in the STS, Ariane, and Space Station programs is examined; and the need for careful planning and preparation in the developing countries to take advantage of future space-exploitation opportunities is stressed. It is proposed that Italian universities and industry provide assistance in training personnel and designing payloads to meet the needs of developing countries. T.K. A85-13016# UTILIZATION AND ECONOMICS OF A EUROPEAN LOW EARTH R. C. PARKINSON and I. V. FRANKLIN (British Aerospace, PLC, In addition to the manned, core station, the facilities of the Space Station are to include also a Teleoperated Service Vehicle, a cryogenic Orbit Transfer Vehicle, and unmanned Space Platforms. Following President Reagan's invitation for international participation in the Space Station program, the Space Platform is of particular interest to Europe. A Space Platform is defined as an unmanned orbiting facility in which essential services are supplied by a common Resources Module while payloads can be attached or recovered on a temporary basis. The present investigation is concerned with the extent of potential interest in Europe in using such a Platform, the associated costs of development and operation, and the economic attractions to Europe of undertaking such a development. It is concluded that the Space Platform (or Platforms) appears to represent a cost-effective area of participation in the U.S. Space Station program, at a cost Europe could afford, and with a function useful both to Europe and the U.S. G.R. A85-13009# UTILIZATION OF A TELEOPERATED SERVICE VEHICLE FOR SPACECRAFT SERVICING C. COUGNET (Matra, S.A., Toulouse, France) and C. BERGER (Matra, S.A., Velizy-Villacoublay, Yvelines, France) International Astronautical Federation, International Astronautical Congress, 35th, Lausanne, Switzerland, Oct. 7-13, 1984. 15 p. Research supported by the European Space Agency. (IAF PAPER 84-48) Potential, commercially oriented European space missions are discussed in terms of the required capabilities, equipment, and applications. A trend toward heavier lift launch vehicles is foreseen, together with an interface with a long-life orbital base of operations and teleoperated service vehicles (TSV). On-orbit servicing of satellites is inevitable for improving the reliability, mission duration, and cost effectiveness of space utilization hardware. The TSV would operate out of a space station and be capable of orbital transfer, rendezvous, and servicing functions. It would place, retrieve, and repair satellites and provide space station logistic support. The TSV could also be either ground-based or expendable, and in any case would be controlled via relay satellite, unless interfacing with the Shuttle or functioning in proximity to the Space Station. Particularly frequent use would be made of the TSV in servicing space-based materials processing facilities. M.S.K. A85-13045# SOME RESULTS OF THE MSAT PHASE B STUDIES AND THEIR IMPACT ON SYSTEM DESIGN J. L. MCNALLY, H. R. RAINE, and J. D. B. KENT (Canadian Department of Communications, Communications Research Centre, Nepean, Ontario, Canada) International Astronautical Federation, International Astronautical Congress, 35th, Lausanne, Switzerland, Oct. 7-13, 1984. 10 p. refs (IAF PAPER 84-89) In 1980, the Department of Communications (DOC) decided to commence Phase A feasibility studies for a mobile satellite system in the 800 MHz band. The considered system would use a geostationary satellite to provide direct communication with vehicles in nonurban areas throughout Canada including offshore coverage of territorial waters. Promising results were obtained with respect to potential market, system feasibility, and commercial viability. It was, therefore, decided to proceed with the second phase (Phase B Project Definition) in April 1982. Phase B involved an examination of system architecture, spacecraft, mobile radios, ground stations, Demand Assignment Multiple Access (DAMA) systems, and business requirements. The present investigation attempts to provide an outline of some of the results and to project some plans for the future. It is concluded that during the studies there has been an evolution toward a commercially-realizable first generation system. G.R. A85-13144# ECONOMICS OF PERMANENT POLAR PLATFORMS (PPP) FOR GLOBAL MONITORING D. E. KOELLE (ERNO Raumfahrttechnik GmbH, Ottobrunn, West Germany) International Astronautical Federation, International Astronautical Congress, 35th, Lausanne, Switzerland, Oct. 7-13, 1984. 8 p. (IAF PAPER 84-226) Economic considerations in the development of a design for a Permanent Polar Platform (PPP) for global monitoring are discussed. Attention is given to the need for interchaneability in the design of various payload modules including: propulsion system, an auxiliary tank system, an equipment and avionics system and an orbital crew cabin. The costs of several different design configurations are compared with total LANDSAT system costs are found to be competitive. It is shown that the overall costs of the system can be cut in half once the permanent platforms are in place. A85-13233# I.H. CONSTRUCTION OF LARGE PRECISION REFLECTORS USING J. M. HEDGEPETH (Astro Research Corp., Carpinteria, CA), T. B. The Aft Cargo Carrier (ACC) will provide a large-sized volume for launching into orbit. This paper reports a conceptual study aimed at examining approaches for using this capability in aiding the establishment of large precision reflectors in space. Attention is paid, in particular, to infrared telescopes with decameter apertures. The ACC is described, and various stowage schemes are discussed. A novel technique of compacting the backup structure during launch is explained. Author A85-16109*# National Aeronautics and Space Administration, Washington, D.C. THE FUTURE OF SPACE FLIGHT J. W. MOORE (NASA, Washington, DC) International Air Transport Association, Dr. Albert Plesman Memorial Lecture, 9th, Technische Hogeschool Delft, Delft, Netherlands, Oct. 26, 1984, Paper. 61 p. The history of the NASA space program is traced, and future plans are outlined. Projects discussed include Mercury, Gemini, Apollo, Skylab, Apollo-Soyuz, science-applications spacecraft (Ranger, Surveyor, Mariner, Pioneer, and Voyager), the Space Shuttle, the planned Space Station, orbital maneuvering vehicles, lunar bases, and planetary exploration. Numerous photographs and drawings are provided. T.K. A85-20507 INTERNATIONAL SPACE PROGRAMMES AND POLICIES The Second United Nations Conference on the Exploration and Peaceful Uses of Outer Space (UNISPACE) took place in Vienna, Austria, from 9 to 20 August 1982 with 94 states participating. Part I of this publication provides a report which was adopted at the Conference, taking into account the state of space science and technology, applications of space science and technology, and international cooperation and the role of the United Nations. The subjects discussed include experiments in the space environment, telecommunications, meteorology, remote sensing, navigation, global positioning, geodesy, space transportation and space platform technologies, mobile communications, maritime and aeronautical communication, satellite broadcasting, choices and difficulties in the use of space technology, mechanisms for enabling all states to benefit from space technology, and the compatibility of satellite systems. Part II of the publication is concerned with the papers presented by 61 countries, while Part III provides a summary of the proceedings of the Conference along with the text of selected statements made at the Conference. G.R. A85-20866*# National Aeronautics and Space Administration. G. P. MENEES, C. PARK (NASA, Ames Research Center, Moffett (AIAA PAPER 85-0327) A method is proposed that provides advance information about unpredictable atmospheric density dispersions that must be accommodated during random operations of aeroassisted-orbital-transfer vehicles (AOTVs). The principal feature is that a test or 'scout' projectile precedes the AOTV through the same region of the atmosphere as that of the predicted transatmospheric flight trajectory. The atmospheric density structure is determined from the vehicle's aerodynamic deceleration characteristics by on-board or ground-based tracking equipment. The time lag between passage of the projectile and the AOTV can be adjusted to only that time necessary to implement required guidance, navigation, and control (GN&C) corrections. The various strategies available to control the projectile's flight characteristics are analyzed in detail. The results are correlated with aerothermodynamic heating and materials requirements to ensure the survival of the projectile and, consequently, the capability of the AOTV to navigate a variable upper atmosphere within specified limits. Author A85-22577* Arizona Univ., Tucson. DEPLOYABLE REFLECTOR CONFIGURATIONS A. B. MEINEL, M. P. MEINEL (Arizona, University, Tucson, AZ), and N. J. WOOLF (Steward Observatory, Tucson, AZ) IN: Deployable optical systems; Proceedings of the Meeting, Los Angeles, CA, January 18, 19, 1983. Bellingham, WA, SPIE - The International Society for Optical Engineering, 1983, p. 2-10. (Contract JPL-955687; NAGW-121) Both the theoretical reasons for considering a non-circular format for the Large Deployable Reflector, and a potentially realizable concept for such a device, are discussed. The optimum systems for diffraction limited telescopes with incoherent detection have either a single filled aperture, or two such apertures as an interferometer to synthesize a larger aperture. For a single aperture of limited area, a reflector in the form of a slot can be used to give increased angular resolution. It is shown how a 20 x 8 meter telescope can be configured to fit the Space Shuttle bay, and deployed with relatively simple operations. The relationship between the sunshield design and the inclination of the orbit is discussed. |