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中文摘要：
针对导弹飞行过程中执行机构的故障问题，提出了基于解析余度的导弹执行机构故障诊断方法．该方法借鉴解析余度的思想，在分析导弹姿态控制系统数学模型以及其执行机构的结构与功能的基础上，分别得到4个执行机构喷管摆角的理论计算值和反映喷管摆角的位移反馈电位计输出值，通过分析执行机构的结构与功能得到反映喷管摆角的位移反馈电位计输出值，从而根据二者在功能上的解析冗余关系得到了用于导弹执行机构在线故障诊断的残差，利用该残差的变化即可判断执行机构的故障情况．将该方法用于某型导弹伺服机构的在线故障诊断仿真实验，结果验证了该方法的有效性．
英文摘要：
A fault diagnosis method is proposed for missile actuator during flight, which is based on analytical redundancy. The concept of analytical redundancy is employed in this approach. By analyzing the mathematical model of missile attitude control system, theoretical values of cant angles for four missile nozzles could be obtained, and by understanding the structure and function of missile actuators, the corresponding output values of displacement feedback potentiometers which reflect the cant angles would be gotten. Further, the residuals for missile actuators online fault diagnosis could be obtained by functional analytical redundancy between theoretical and output values. Finally, the fault of missile actuator could be determined based on the change of residuals. Simulation shows the validity of the proposed method for missile actuator online fault diagnosis.
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