拦截临近空间目标制导律的工程化设计研究

Engineering Design of Guidance Law for Intercepting Near Space Targets

针对防空导弹拦截临近空间目标时制导控制回路发散较早的问题,从工程应用的角度对天线罩误差斜率影响进行分析,提出对有效导航比的修正,并在制导律设计中引入已知的控制回路时间常数信息,采用非线性反演方法求得该制导规律。仿真结果表明,该制导律既能有效抑制天线罩误差斜率的影响,确保系统的有效导航比,同时又能减小系统动力学的等效时间常数,推迟导弹视线角速度的发散时刻,从而提高导弹的制导精度。

For the problem of early divergence of the guidance control loop when the missile intercepts near space targets,the impact of radome error slope is analyzed in this paper from perspective of engineering application.To reduce this impact,the compensation of effective navigation ratio is proposed,and the known time constant information of control loop is introduced into the design of guidance law.The guidance law is obtained by nonlinear inversion method.The simulation results show that the new guidance law can not only ensure the effective navigation ratio by suppressing the influence of radome error slope,but also delay the divergence of missile line of sight(LOS)angular speed by reducing the equivalent time constant of system dynamics,so as to improve the guidance accuracy of missile.