拦截导弹的制导律辨识与弹道预报

摘要

Guidance law estimation and trajectory prediction of interceptor missile are discussed.The en-gagement model is established in three dimensions,w hose state variables are ranges,range rates,interceptor accelerations and guidance coefficients.The observability condition of the system is deduced by using the nonlin-ear local weak observability theory.Then,an extended Kalman filter is designed based on the condition.Using the filter results as initial values,the interceptor future position is predicted by fourth-order Runge-Kutta method with a model of proportional navigation.Simulation results show that when the line-of-sight rate is large enough,the filter can estimate well and the prediction can meet the requirement of convergence and accuracy.%讨论了拦截导弹的制导律辨识和弹道预报问题.在三维状态下,以相对距离、相对速度、导弹加速度、两通道制导系数作为系统的状态变量,建立了相遇过程中的观测模型.用非线性系统局部弱可观理论分析了系统可观的条件,然后在此基础上设计了扩展卡尔曼滤波器.以滤波结果为初值,用四阶龙格库塔方法基于比例导引律的模型对导弹未来的位置进行了预报.仿真结果表明,在视线角速率较大的情况下滤波器可以取得较好的效果,弹道预报可以满足一定的精度和速度要求.