SE(3)上航天器姿轨耦合固定时间容错控制

doi:10.7527/S1000-6893.2020.25089

Abstract

Abstract: To solve the difficulty of integrated control of the relative motion spacecraft's attitude and orbit, and considering the effect of actuator fault and control input saturation, a fuzzy adaptive fixed-time fault-tolerant control method based on sliding mode is proposed. Firstly, a dynamic model of the integrated attitude and position error of the relative motion spacecraft is established and derived under the framework of Lie group SE(3). Next, considering the actuator fault and control input saturation, a fault tolerant controller with fixed time stability is designed by adopting double-power fast terminal sliding mode surface and combining with fuzzy adaptive method, which can realize high precision and fast tracking control of relative motion spacecraft under actuator fault. Then, the Lyapunov method is used to prove the stability of the system. The controller can not only realize the fixed-time stability of sliding mode approach and arrival stage independent of the initial state of the system, but also because the fuzzy approximation method combined with the adaptive update strategy can estimate the total disturbance information of the system with high accuracy in real time, so It can achieve the goal of fast and high-precision fault-tolerant control. Finally, the proposed control method is analyzed by numerical simulation, and the results verify the effectiveness and feasibility of the method.

Key words: attitude and position coupled control, Lie group SE (3), fuzzy adaption, fixed time, fault-tolerant control

CLC Number:

MEI Yafei, LIAO Ying, GONG Kejie, LUO Da. Fixed-time fault-tolerant control for coupled spacecraft on SE(3)[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(11): 525089-525089.

References

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Fixed-time fault-tolerant control for coupled spacecraft on SE(3)

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