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针对挠性航天器姿态稳定控制,基于退步控制方法与直接自适应控制方法提出了一种自适应控制策略。首先将挠性航天器模型分解为运动学子系统和动力学子系统,并设计具有理想控制性能的参考模型;然后在姿态小角度的假设下,对满足近似严格正实性的姿态运动学子系统设计了直接自适应中间控制律;最后运用退步控制方法对航天器动力学子系统设计了姿态控制器,并证明了闭环系统的稳定性。理论分析和数值仿真结果表明该控制器对挠性航天器的姿态稳定控制是有效的。
Aiming at the attitude stability control of flexible spacecraft, an adaptive control strategy is proposed based on backstepping control method and direct adaptive control method. First, the flexible spacecraft model is decomposed into kinematic subsystem and dynamic subsystem, and a reference model with ideal control performance is designed. Then, under the assumption of small angle of attitude, the attitude kinematic subsystem that satisfies the approximation of exact positive realness is designed Directly adapt to the intermediate control law. Finally, the backstop control method is used to design the attitude controller for the spacecraft dynamics subsystem and to prove the stability of the closed-loop system. The theoretical analysis and numerical simulation results show that the controller is effective in attitude stability control of flexible spacecraft.