A near Earth satellite orbiting in the altitude range of 15 km to 450 km encounters small but non-negligible aerodynamic forces. It is possible to generate sufficient aerodynamic torques by providing 'all-moving' control surfaces of suitable size to achieve active attitude control. This report is a preliminary study of such an active attitude control system. The satellite configuration considered has four all-moving control surfaces and the dominant gravity gradient torques and aerodynamic torques are considered in the analysis. The resulting equations of motion are linearized and modern optimal control theory concepts are applied to synthesize a feedback control surfaces to obtain the necessary control torques. The numerical studies carried out indicate that it is possible to control a near Earth satellite by using control surfaces of reasonable size. Damping times of the order of from a few orbits to a fraction of an orbit seem reasonable. (Author)
Optimal Aerodynamic Attitude Stabilization of Near Earth Satellites
1971
130 pages
Report
Keine Angabe
Englisch
Spacecraft Trajectories & Flight Mechanics , Unmanned Spacecraft , Attitude control systems , Stabilization systems , Satellites(Artificial) , Low-orbit trajectories , Configuration , Remote control systems , Feedback , Equations of motion , Optimization , Computer programs , Control theory , Gravity gradient satellites
The aerodynamic drag of near earth satellites
TIBKAT | 1960
|ATTITUDE CONTROL OF EARTH SATELLITES
NTRS | 1958
|Attitude Stabilization of Satellites in Orbit
NTIS | 1971