control techniques. A combination of passive (spring-mass-damper suspension systems) and active (sensor/disturbance-cancelling device) systems are expected to be used. (L.T.) Source of Abstract (Subfile): AIAA/TIS Descriptors: ‘ATTITUDE CONTROL; *CONTROL SYSTEMS DESIGN; ‘SPACE STATIONS; ‘SPACECRAFT CONTROL; AUTONOMY; SERVICE LIFE; STABILIZATION; TEST EQUIPMENT; TORQUE Subject Classification: 7518 Spacecraft Design, Testing & Performance (1975- ) Optimal configurations for dual-spin satellites subject to gravitational torques LI, T. (Beijing, Institute of Control Engineering, Beijing, People's Republic of China; Columbia University, New York, NY); LONGMAN, R. W. (Columbia University, New York, NY) Celestial Mechanics (ISSN 0008-8714), vol. 33, Aug. 1984, p. 319-336. 11 Refs. Language: English. Country of Origin: China, People's Republic of. Country of Publication: Netherlands Document Type: JOURNAL ARTICLE Most documents available from AI A A Technical Library Journal Announcement: IAA8508 That equilibrium which is most stable in that the energy required to perturb orientation is maximized is used as the criterion for determining the best of equilibria for dual-spin satellites subject to gravitational torques. The criterion, which is the smallest eigenvalue of the Hessian matrix of dynamic potential energy, is used to show that the conventional configuration for dual spin satellites is not always the best orientation; the optimum orientation is instead one in which the moment of inertia is always aligned with the local vertical, and also in which the principal axis of maximum moment of inertia shifts from the perpendicular to the orbital plane and then to a position in-plane, as rotor angular momentum is increased from zero to some sufficiently large value which is determined as a function of several parameters. (O.C.) Source of Abstract (Subfile): AIAA/TIS Descriptors: ‘DUAL SPIN SPACECRAFT; ‘GRAVITY GRADIENT SATELLITES; ‘SATELLITE ATTITUDE CONTROL; ‘SATELLITE ORIENTATION; ‘SATELLITE ROTATION; ‘SPACECRAFT STABILITY; ANGULAR MOMENTUM; ATTITUDE STABILITY; GRAVITATIONAL EFFECTS; GYROSCOPES; MOMENTS OF INERTIA; OPTIMAL CONTROL Subject Classification: 7518 Spacecraft Design, Testing & Performance (1975- ) Space Station truss structures and construction considerations MIKULAS, M. M., JR.; CROOMES, S. D.; SCHNEIDER, W.; BUSH, H. G.; NAGY, K.; PELISCHEK, T.; LAKE, M. S.; WESSELSKI, C. National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. Corp. Source Code: ND210491, Jan. 1985. 119 p. Publication Note: Prepared in cooperation with NASA. Johnson Space Center. Report No.: NASA-TM-86338; NAS 1.15:86338 Language: English Country of Origin: United States. Country of Publication: United States
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