临近空间拦截弹中制导弹道设计

Design of midcourse guidance trajectory for near space interceptor

为提高临近空间拦截弹的飞行性能,基于弹道优化理论设计了中制导段的拦截弹道,分析了临近空间典型目标的弹道特性,选择滑翔/巡航段进行拦截。采用弹道与导引律分离设计的方案,从增大射程和末速度的角度,设计了高抛再入弹道,分析了拦截过程中的路径约束与性能指标,并基于纯比例导引律(PPN)给出了末制导的捕获条件,从而为建立中制导终端约束模型提供了参考。通过数字仿真对交接班捕获区进行了定量描述,验证了分离设计的高抛再入弹道能以更大的动能和有利的阵位进入末制导,且控制上更易实现。

To improve the performance of near space interceptor,an interception trajectory was designed based on the theory of trajectory optimization. The trajectory characteristics of representative targets in near space were analyzed,and the gliding/cruise phase was chosen for intercept.In terms of increasing flight range and terminal velocity,a parabola-reentry trajectory scheme was designed by separation design of trajectory and guidance law. The path constraints and performance index of interception process are analyzed.The capture conditions are derived based on pure proportional navigation（ PPN）,which facilitates to model the terminal constraints of interceptor.By means of digital simulation,the capture region of handover is described quantitatively,and it is validated that the parabola-reentry trajectory has more kinetic energy and better attack station to enter terminal guidance.Moreover,it is easy to implement in terms of control.