This paper investigates the attitude stability of a flexible spacecraft made of a rigid platform and multiple flexible appendages during retargeting rest to rest slew maneuver. In addition to the attenuation of external disturbances and model uncertainties, the designed fuzzy controller goal is to suppress the vibration caused by the minimum time manoeuver of the appendages, and to stabilize the attitude of the spacecraft subject to independent time delay and actuators saturation. The fuzzy controller-observer is formulated as a set of linear matrix inequalities and utilizes the parallel distributed compensator to obtain the feedback control and the observer gains. Numerical simulations are provided to measure the performance of the proposed controller.
Attitude Stabilization during Retargeting Maneuver of Flexible Spacecraft Subject to Time Delay and Actuators Saturation
01.03.2020
2238372 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
Spacecraft Attitude Tracking and Maneuver Using Combined Magnetic Actuators
British Library Conference Proceedings | 2010
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