带旋转挠性太阳帆板卫星自适应控制

Adaptive Control of the Spacecraft with a Rotating Flexible Solar Array

为了应对航天器质量分布变化对姿态控制系统性能产生的影响,本文研究了带旋转挠性太阳帆板卫星的自适应姿态控制问题,其中对卫星本体转动惯量阵设计了参数自适应律,而惯量参数的不确定性是通过线性参数化方法表达的。基于类Lyapunov分析方法,这一时变系统的闭环稳定性和估计误差的有界性得到了证明。与PD控制的仿真对比表明,自适应控制对于卫星姿态和帆板驱动具有更好的性能。

In order to attenuate the influence caused by the variation of the mass distribution of satellites to the attitude control system,this paper is concerned with the adaptive attitude control problem of a satellite with a rotating flexible solar array.An adaptive control scheme is designed to adjust the variations of the mass distributions of the spacecraft central body.The uncertain inertia parameters are isolated by linear parameterization method.Based on the Lyapunov-like analysis,closed-loop stability and boundedness of identification errors of this time-varying system are ensured.Numerical simulations compared with PD control are performed to show that the adaptive control for the spacecraft and the solar array has better performances.