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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 ,并对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。
A missile missile model and its movement characteristics in flight are studied. The attitude control system model of the missile is simplified. The dynamic characteristics of the missile attitude control system under perturbation of parameters are analyzed, and the influence of the system performance The mutual compensation of parameter deviation is studied. The results show that, in the event that some test parameters deviate from the allowable conditions, if the system has sufficient stability margins, it can be fired as long as it is not a functional issue.