舵机卡死对X型舵飞航导弹控制性能的影响

摘要

A relationship model of input and output of X-rudder missile servo system under locking fault conditions was established. The influences of three aspects caused by a stagnation fault of servo system on control performance of missile were researched,including the descent of rudder effect,the introduction of constant error and the coupling of control system. In order to investigate the difference when missile servo system was locked at different time, a six-degree-of-freedom model of missile was established. The simulation result shows that one rudder locking can result in control performance degradation and impact point dispersion increase of missile. Under some extreme initial conditions, the pitch channel and yaw channel coupling can cause missile dropping. A case in flight test was analyzed, which verified the correctness of the simulation analysis conclusion.%建立了X型舵飞航导弹舵机卡死故障条件下执行机构输入与输出的关系模型，分析了舵机卡死引起舵效降低、常值误差和控制耦合三方面效应对导弹控制性能的影响。为考察不同时刻舵机卡死影响的差异，建立了导弹六自由度数学模型。仿真结果表明，单个舵机卡死会造成导弹控制性能下降，命中点散布变大；在一些极端初始条件下，俯仰和偏航通道产生严重的控制耦合，会使弹道畸变，导致导弹坠落。对飞行试验中出现的案例进行分析，验证了仿真分析结论的正确性。