挠性航天器退步自适应姿态机动及主动振动控制

doi:10.3969/j.issn.1674-1579.2015.01.002

Abstract

Abstract: A backstepping direct adaptive attitude and vibration control method is proposed for flexible spacecraft with piezoelectric vibration suppression sensor and actuator pairs. Firstly, the attitude maneuver and vibration control model of a flexible spacecraft is derived, and the almost strict positive real property of the dynamics subsystem is discussed. Then, an attitude maneuver and vibration controller is designed based on backstepping directive control method, and the closedloop stability is proved. Finally, the controller is applied to a flexible spacecraft in different initial conditions. Theoretical analysis and simulation results validate that the controller has strong robustness against the spacecraft inertial and flexible model uncertainties. Both the attitude maneuver and vibration suppression can be accomplished effectively.

Key words: flexible spacecraft, attitude maneuver, active vibration control, directive adaptive control

CLC Number:

LIU Min, YANG Jun, LI Xue-Lin, XU Shi-Jie. Backstepping Adaptive Attitude Maneuver and Active Vibration Control of Flexible Spacecraft[J]., 2015, 41(1): 9-14.

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URL: http://journal01.magtech.org.cn/Jwk3_kjkzjs/EN/10.3969/j.issn.1674-1579.2015.01.002

http://journal01.magtech.org.cn/Jwk3_kjkzjs/EN/Y2015/V41/I1/9

References

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Backstepping Adaptive Attitude Maneuver and Active Vibration Control of Flexible Spacecraft

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