基于模型参考滑模控制的飞行器姿态控制  

Spacecraft Attitude Control Laws Based on Mode Reference Sliding Mode Control

作　　者：王洪强[1,2] 方洋旺[1] 伍友利[1] 

机构地区：[1]空军工程大学工程学院,西安710038 [2]95998部队,北京100076

出　　处：《系统仿真学报》2009年第12期3718-3721,共4页Journal of System Simulation

基　　金：国家自然科学基金(60674031);空军工程大学工程学院优秀博士学位论文创新基金(BC07004)

摘　　要：研究了空间飞行器大角度机动飞行的变结构姿态控制。采用参考模型的方法设计滑模控制律,首先应用误差四元数来描述参考模型姿态运动,设计符合姿态控制要求的参考模型控制量。在此基础上,应用滑模变结构控制理论设计系统控制量,能使得系统状态跟踪参考模型又能快速趋近滑动面,有效缩短了变结构控制系统中趋近过程,从而提高了变结构控制律的品质。数字仿真结果表明了该控制算法的有效性。A Variable structure attitude control of spacecraft large angle maneuver flight was studied. The sliding mode controller was designed based on mode reference. Firstly the attitude dynamics was described by error quatemion, the reference mode controller was designed satisfying the attitude control. The sliding mode variable structure controller was designed based on the reference mode, so that the system trajectory could track the states of reference mode and quickly approximate the sliding plan, and short tend process in the sliding mode control system. Thus the performance of the variable structure control system was improved. The numerical results show the effectiveness of the proposed control algorithm.

关 键 词：飞行器姿态控制 变结构控制 四元数 LYAPUNOV稳定性 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]