适用于大距离拦截问题的零控脱靶量计算方法

Zero Effort Miss Formulation for Longer Range Targeting

对于中制导后具有较长滑行距离的大气层外拦截问题,为了精确确定零控脱靶量,两飞行器间的重力差必须被合理考虑。利用牛顿二项式定理及现代控制理论推导了两飞行器间相对运动状态解析表达式,并利用牛顿迭代法计算零控脱靶量发生时刻,最后得出一种快速而又具有较高精度的预测零控脱靶量改进方法。为验证预测方法的精度,介绍了几种常见的零控脱靶量计算方法并进行了数学仿真,仿真结果表明改进的ZEM预测方法具有明显的应用优势。

For long range targeting applications with significant ballistic coasting after burnout, determination of the zero effort miss must account for the different gravitational accelerations experienced by each vehicle. A new expression of relative motion is derived using the Newton＇s Binomial Theorem and Modem Control Theory, then the final time at miss is calculated by Newton iter- ation, and a modified predicted method of zero effort miss is obtained. In order to validate the fidelity of proposed zero effort miss, several methods of determination of the zero effort miss are compared with proposed method by simulation. Simulation results show that zero effort miss formulation better than other methods and has obvious advantages of the application.