Optimal parameters of a satellite/stabilizer gravitational system
Abstract
The gravitational attitude control system consists of a satellite and a stabilizer coupled to each other by means of a spherical joint, the position of the stabilizer with respect to the satellite being fixed by centering springs. The dynamics of a satellite employing such a stabilization system is analyzed, along with two equilibrium positions of the satellite/stabilizer system moving along a circular orbit. The values of the timeoptimal parameters of the system are determined analytically, assuming that damping is achieved by friction in the spherical joint. A scheme where friction in the joint is absent, but where the stabilizer is equipped to generate a damping moment that is proportional to the angular velocity of the stabilizer with respect to the orbital system of coordinates is analyzed and is shown to provide more precise and rapid damping of the natural vibrations than the system based on friction.
 Publication:

Kosmicheskie Issledovaniia
 Pub Date:
 March 1976
 Bibcode:
 1976KosIs..14..209S
 Keywords:

 Circular Orbits;
 Gravitational Effects;
 Satellite Attitude Control;
 Spacecraft Stability;
 Vibration Damping;
 Angular Velocity;
 Eccentricity;
 Elliptical Orbits;
 Equations Of Motion;
 Free Vibration;
 Linear Equations;
 Mathematical Models;
 Optimization;
 Time Optimal Control;
 Astrodynamics