Adaptive torque equilibrium control of the Space Station SHAIN, E. B.; SPECTOR, V. A. (TRW Inc., TRW Electronics and Defense Sector, Redondo Beach, CA) American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting, 23rd, Reno, NV, Jan. 14-17, 1985. 8 p. Report No.: AIAA PAPER 85-0028 Language: English Country of Origin: United States. Country of Publication: United States Document Type: PREPRINT Most documents available from AIAA Technical Library Journal Announcement: IAA8507 The large size, low altitude, and long life requirement of the Space Station make momentum management an important consideration in its design. This paper presents a new approach to momentum management for a nominally earth-pointing Space Station. The adaptive torque equilibrium attitude (ATEA) unloading method controls momentum through the use of gravity-gradient torques by automatically commanding appropriate attitude biases. The attitude-control and unloading algorithms were verified using simulation and linear analysis. The ATEA unloading law was shown to be able to limit pitch-control momentum to 12,000 N-m-s and roll and yaw momenta to 400 N-m-s. (Author) Source of Abstract (Subfile): AIAA/TIS Descriptors: *ATTITUDE CONTROL; *CONTROL MOMENT GYROSCOPES; *SPACE STATIONS; *SPACECRAFT CONTROL; *TORQUE; ALGORITHMS; MOMENTUM; SYSTEMS SIMULATION; UNLOADING Subject Classification: 7518 Spacecraft Design, Testing & Performance (1975- ) Dumbbell-shaped gravity-gradient stabilized satellite LIN, L.; XU, N.; JIANG, W. Chinese Society of Astronautics, Journal, no. 3, 1983, p. 65-78. In Chinese, with abstract in English. Language: Chinese Country of Origin: China, People's Republic of. Country of Publication: China, People's Republic of. Document Type: JOURNAL ARTICLE Most documents available from AIAA Technical Library Journal Announcement: IAA8507 This paper discusses some problems on dynamics, system scheme and system design of the dumbbell-shaped gravity-gradient satellite. The system composition, function and the main parameter selection are also considered. Finally, the result of mathematical simulation is given. (Author) Source of Abstract (Subfile): AIAA/TIS Descriptors: * ATTITUDE STABILITY; *COMPUTERIZED SIMULATION; ♦GRAVITY GRADIENT SATELLITES; *SATELLITE ATTITUDE CONTROL; ♦SATELLITE DESIGN; EQUATIONS OF MOTION; ERROR ANALYSIS; MAGNETIC EFFECTS; ORBIT PERTURBATION; SATELLITE PERTURBATION; SYSTEMS SIMULATION Subject Classification: 7518 Spacecraft Design, Testing & Performance (1975- )
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