tatsionnoi orientatsii SAZONOV, V. V.; SIDORIUK, M. E. Akademiia Nauk SSSR, Izvestiia, Mekhanika Tverdogo Tela (ISSN 0572-3299), Jan.-Feb. 1985, p. 3-13. In Russian. 10 Refs. Language: Russian Country of Origin: USSR Country of Publication: USSR Document Type: JOURNAL ARTICLE Most documents available from AI A A Technical Library Journal Announcement: IAA8512 The motion of a satellite relative to its center of mass due to a gravity moment in circular orbit is analyzed using an autonomous system of ordinary differential equations of the sixth order to describe the motion. The symmetric periodic solutions to this system, which are close to the periodic solutions to the corresponding generating system, are investigated analytically and numerically. Some of the solutions describe periodic oscillations or rotations of the satellite relative to the axis of the minimum moment of inertia aligned approximately along the radius-vector of the satellite center of mass relative to the center of attraction. It is suggested that these motions be used for the single-axis gravity gradient stabilization of the satellite. (V.L.) Source of Abstract (Subfile): AIAA/TIS Descriptors: *CENTER OF MASS; *GRAVITY GRADIENT SATELLITES; ♦SPACECRAFT MOTION; CIRCULAR ORBITS; DIFFERENTIAL EQUATIONS; EQUATIONS OF MOTION; MOMENTS OF INERTIA; SATELLITE ROTATION Subject Classification: 7513 Astrodynamics (1975- ) Application Number 3: Using tethers for attitude control MULLER, R. M. National Aeronautics and Space Administration. Goddard Space Flight Center, Greenbelt, Md. Corp. Source Code: NC999967 In NASA. Marshall Space Flight Center Appl. of Tethers in Space, Vol. 2 10 p (SEE N85-20361 11-37). Mar. 1985. Language: English Country of Origin: United States. Country of Publication: United States Document Type: CONFERENCE PAPER Most documents available from AI A A Technical Library Other Availability: NTIS HC A14/MF AOI Journal Announcement: STAR8511 Past application of the gravity gradient concept to satellite attitude control produced attitude stabilities of from 1 to 10 degrees. The satellite members were rigidly interconnected and any motion in one part of the satellite would cause motion in all members. This experience has restricted gravity gradient stabilization to applications that need attitude stability no better than 1 degree. A gravity gradient technique that combines the flexible tether with an active control that will allow control stability much better than 1 degree is proposed. This could give gravity gradient stabilization much broader application. In fact, for a large structure like a space station, it may become the preferred method. Two possible ways of demonstrating the techniques using the Tethered Satellite System (TSS) tether to control the attitude of the shuttle
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