导弹姿态控制系统鲁棒稳定性分析

研究了某型导弹弹体模型及其在飞行中的运动特性，对其姿态控制系统模型进行了简化，分析了导弹姿态控制系统在参数摄动条件下的动态特性，并时影响系统性能的不同参数偏差间的相互补偿进行了研究。结果表明，在某些测试参数偏差超出允许的条件下，如果系统有足够稳定裕度，只要不是功能性问题，仍可以进行发射。

ROBUST STABILITY ANALYSIS ON MISSILE ATTITUDE CONTROL SYSTEM

In this paper, the missile body model and the motion character of missile in flight were studied; also, the model of attitude control system was simplified. The dynamic performance of the missile attitude control system under the condition of parameter perturbation was analysed, and the mutual deviation compensation between different testing parameters, which effect the system performance, was discussed too. The result showed that the missile can be launched even if some testing parameters exceed allowable deviation, if only the system has enough stability margin and no functional problem.