挠性航天器分散变结构控制稳定性研究  

Decentralized Variable Structure Control for Stability of Flexible Satellite Attitude Suitable for Engineering Application

作　　者：刘莹莹[1] 周军[1] 

机构地区：[1]西北工业大学精确制导与控制研究所,陕西西安710072

出　　处：《西北工业大学学报》2010年第3期338-342,共5页Journal of Northwestern Polytechnical University

基　　金：民用航天计划支持(C5120062702);空间智能控制技术国家级重点实验室(2008DC020008)资助

摘　　要：文章针对具有大面积太阳帆板的挠性航天器姿态控制问题,研究了分散变结构控制方案,设计了分散子系统滑动模态与控制律,并在分析和考虑航天器实际控制输出限制的基础上进行了合理简化,便于工程实现。由于实际航天器执行机构控制输出受限,以及系统不确定因素,不能始终满足滑动模态能达条件,证明了在控制受限情况下变结构控制系统的大范围渐进稳定性。开展了挠性航天器变结构姿态控制物理仿真实验,验证了控制系统的稳定性与有效性。Aim. The introduction of the full paper points out that, in our opinion, the stability research results in Refs. 1 through 3 are not suitable for engineering application because the control output is limited. Sections 1, 2 and 3 explain the decentralized variable structure control we designed. Their core is： ＂We first establish the attitude dynamics model of the satellite with a rigid body and a large flexible solar panel. The attitude dynamics model can be expressed in displacement and modal coordinate forms. We then study the decentralized variable structure control system of the attitude of the flexible satellite. The control system is divided into the subsystem whose states can be measured directly and the subsystem whose states can not be measured directly. We design the sliding mode control law for the control system. The control law is simplified by considering the control output limits in engineering practice. After that, the stability of the decentralized variable structure control system with limited control output is proved. The performance of the control system in the sliding mode is discussed. The control system is stable when control output satisfies the sliding mode reaching conditions. The stability of the system whose control output can not satisfy the sliding mode reaching conditions is also proved. ＂ Section 4 presents in Fig. 2 the results of flexible satellite control simulation experiments; of course, the control torque of the system is limited. The simulation experimental results and their analysis show preliminarily that the variable structure control system can reach the sliding mode and that the precision of the satellite attitude is within 0.05°, indicating that our control system is effective.

关 键 词：挠性航天器 分散变结构控制 稳定性 物理仿真实验 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]