考虑执行机构故障的导弹姿态控制系统的集成容错控制  

Integrated Fault-Tolerant Control for Missile Attitude Control System Subjected to Actuator Faults

作　　者：曹祥宇 胡昌华[1] 乔俊峰[2] 

机构地区：[1]第二炮兵工程大学302教研室,西安710025 [2]西安电子科技大学理学院,西安710071

出　　处：《宇航学报》2013年第7期938-945,共8页Journal of Astronautics

基　　金：国家杰出青年科学基金(61025014);国家自然科学基金(60736026)

摘　　要：研究了一类发动机十字型布局的导弹姿态控制系统的容错控制问题,提出了一种考虑执行机构故障的导弹姿态控制系统集成容错控制方法。该方法针对执行机构的恒增益变化故障和卡死故障,首先提出了集成容错控制的总体策略,然后分别基于线性矩阵不等式方法和故障补偿思想,给出了在圆盘极点指标和H∞指标两个相容指标约束下的状态反馈满意容错控制器和故障补偿器的设计方法。最后在Matlab/Simulink环境下将该方法应用于导弹姿态控制系统进行仿真实验,结果表明了该方法的有效性和可行性。Fault-tolerant control problem of a class of missile attitude control system with cross-type rocket engine＇ s actuators is researched, and a kind of integrated fault-tolerant control method for missile attitude control system with actuator faults is proposed. For constant gain variation fault and deadlock fault of actuators, a general strategy of integrated fault-tolerant control method is proposed firstly, then, based on the linear matrix inequality approach and the fault compensation idea, the design method for state feedback satisfactory fault-tolerant controller under the constraints of consistent circular disc pole index and H-infinity index and the design method for fault compensator are derived respectively. Finally, a simulation for a missile attitude control system is implemented by using the Matlab/Simuliuk programming, and the results demonstrate effectiveness and feasibility of the proposed method.

关 键 词：执行机构故障 导弹 姿态控制系统 容错控制 

分 类 号：TP273[自动化与计算机技术—检测技术与自动化装置]