The flexure-satellite attitude interaction due to two uniform beam arrays on a three-axis stabilized spacecraft is examined. The arrays are equivalent in mass and inertia distribution to 18 m x 2 m RAE-type arrays, being symmetrically disposed about the satellite roll/yaw plane and offset from the pitch axis. Three control actuators are used: thrusters, DGMW, and reaction wheels. On the assumption of a rigid structure, and after introduction of flexure dynamics, it is demonstrated that the performance degradation due to flexure in the pitch loops is negligibly small so that the three pitch controllers designed on the basis of a rigid satellite are adequate. This is also the situation for the roll/yaw loop of the DGMW system. In the case of the thruster roll and yaw loops, an increase in the number of thruster firings occurs; however, flexure interaction with the reaction wheel roll and yaw axes causes instability.
The Attitude Control of Three-Axis Stabilised Spacecraft with Flexible Appendages, Volume 2, Book 1
1976
196 pages
Report
No indication
English
Unmanned Spacecraft , Appendages , Flexible bodies , Satellite attit ude control , Stabilization , Actuators , Apogee boost motors , Control theory , Flexibility , Flexing , Pitch (Inclination) , Reaction wheels , Rigid structures , Roll , Satellite configurations , Solar arrays , Structural analysis , Yaw , Great Britain