基于线性重力差模型的拦截弹中制导技术

Interceptor Midcourse Guidance Technology Based on Linear Gravity Difference Model

针对机载动能拦截弹的中制导段气动力作用可忽略且存在无法实时精确计算重力偏差等特点,提出了一种基于线性重力差模型的预测制导方法。通过线性模型逼近中制导过程中拦截弹与目标之间的重力偏差,以此为依据调整拦截弹的推力矢量并将重力偏差值消除。在此基础上采用延迟点火的策略使得拦截弹的拦截器助推级更好地修正预测模型与实际情况的偏差,经过仿真验证可以将整个中制导段的脱靶量限制在一个较小数值,从而为末制导段提供良好的初始条件。

A predictive guidance method based on linear gravity difference model is proposed for the midcourse guidance of an airborne kinetic energy interceptor,which has the characteristics of negligible aerodynamic force and the inability to accurately calculate gravity deviation in real time.The gravity deviation between the interceptor and the target is approximated by a linear model.The thrust vector of the interceptor is adjusted and the gravity deviation is eliminated.On this basis,the delay ignition strategy is adopted to make the interceptor boost stage of interceptor better correct the deviation between the prediction model and the actual situation.The simulation results show that the miss distance of the whole midcourse guidance can be limited to a smaller value,thus providing a good initial condition for the terminal guidance.