Attitude Control of a Flexible Spacecraft

descriptionPublicationkeyboard_double_arrow_right Article 01 Jan 1980 English Publisher:American Institute of Aeronautics and Astronautics (AIAA)Journal:Journal of Guidance and Control, volume 3, pages 37-41 (issn: 0162-3192,

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Authors: Martin, Gary D.; Bryson, Arthur E. jun.;

doi: 10.2514/3.55944

Attitude Control of a Flexible Spacecraft

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Abstract

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.

Keywords

Controllability, flexible spacecraft, designing optimal low-order controllers, Linear systems in control theory, Model systems in control theory, Control/observation systems governed by ordinary differential equations

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