An algorithm is presented for designing optimal low order compensators for high order systems and it is applied to the title problem where many vibration modes are excited by the control torque. These low order compensators are compared with the full order optimal compensator and found to be less sensitive to modeling errors and to provide near optimal attitude regulation.
Attitude control of a flexible spacecraft
Guidance and Control Conference ; 1978 ; Palo Alto, CA
1978-01-01
Miscellaneous
No indication
English
Attitude Control of Flexible Spacecraft
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