中文摘要：

针对导弹主动防御应用中拦截导弹制导行为辨识问题,提出一种比例导引（PN）制导律多模型辨识滤波方法,对拦截导弹加速度和制导律导航常数进行辨识。采用非线性可观性理论对制导模型的可观性进行了分析。得出在拦截导弹使用PN制导律时,制导模型可观的充要条件。与以往工作相比,该方法考虑了拦截导弹末制导初期由于瞄准误差校正而引起的控制器饱和现象,在拦截导弹执行器处于饱和或退出饱和阶段都能精确对制导律进行辨识。另外,以往工作假定PN制导律常数已知,该方法将PN制导律常数当做制导模型的一个状态进行估计。仿真结果校验了所提方法的性能。

英文摘要：

The intercepting missile guidance behavior identification problem in missile active defense application is investigated,and a Proportional Navigation（ PN） guidance law multi-model identification method is proposed,which can estimate the intercepting missile＇s accelerations and guidance constants. The observability of the systems is analyzed using the nonlinear system observability theory. Under the assumption of the intercepting missile with PN guidance law,the necessary and sufficient condition of the guidance system observability is derived. Compared with the previous research,the actuator saturation of the intercepting missile due to eliminating the initial aiming errors is considered in the proposed method. Thus,under both the intercepting missile＇s actuator saturation and unsaturation situations,the guidance law can be estimated accurately. Additionally,different from the previous research in which guidance constants of PN guidance law were assumed to be known,the proposed method treats the guidance constants as a state of the guidance system needed to be estimated. The simulations demonstrate that the proposed method outperforms the pure PN guidance law identification Kalman filtering.