挠性飞行器姿态控制系统——鲁棒稳定性分析的区间矩阵方法  

A INTERVAL MATRIX METHOD FOR THE ROBUSTNESS STABILITY ANALYSIS OF ATTITUDE CONTROL SYSTEM OF A FLEXIBLE SPACECRAFT

作　　者：徐世杰[1] 吴瑶华[1] 段广仁[1] 

机构地区：[1]哈尔滨工业大学航天学院

出　　处：《宇航学报》1990年第2期45-51,共7页Journal of Astronautics

摘　　要：本文应用区间矩阵的理论,研究三轴稳定的挠性空间飞行器姿态控制系统的鲁棒稳定性分析问题。太阳帆板的转动、燃料消耗及动量轮的转速变化引起的不确定性被描述为区间矩阵的形式,几个相应的鲁棒稳定性定理被导出,一个实际算例说明了所给方法的应用过程。In this paper, the robustness stability analysis of the attitude control system of a three-axis stabilized flexible spacecraft is investigated. The uncertainties which result from the rotation of solar arrays, the expenditure of fuel and the rate change of momentum wheels are described by interval matrices. Some robustness stability theorems are derived. A numerical example is given.

关 键 词：挠性飞行器 姿态控制 鲁棒稳定性 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]