空间飞行器姿态控制设计和鲁棒性分析

基于奇异摄动思想,将飞行器姿态控制系统分为慢变化的姿态角回路和快变化的角速度回路分别设计。每个回路的设计均采用精确线性化方法。对于内回路即角速度回路,考虑到飞行器转动惯量的参数摄动,应用小增益原理分析了系统的鲁棒稳定性。

Design and Robust Analysis for Spacecraft Attitude Controller

The spacecraft's attitude control system was divided into the outer loop that was angle loop and the inner loop that was angle velocity loop based on their time scales.Then the control law of each loop was designed independently using exact linearization method.In the inner loop,robust stability was analysed using small-gain theorem considering the existence of perturbation of spacecraft moment inertia.