基于虚拟拦截点的预测制导算法设计  

Design of predictive guidance algorithm based on virtual intercepting points

作　　者：陈文钰 邵雷[1] 谭诗利 王华吉[1] 李世杰 CHEN Wenyu;SHAO Lei;TAN Shili;WANG Huaji;LI Shijie(Air and Missile Defence College,AFEU,Xi'an 710051,China)

机构地区：[1]空军工程大学防空反导学院,陕西西安710051

出　　处：《飞行力学》2020年第3期70-76,共7页Flight Dynamics

基　　金：国家自然科学基金资助(61503408,61703421,61773398,61873278)。

摘　　要：针对临近空间拦截弹中制导段大部分所处空域空气稀薄的情景,提出一种基于虚拟拦截点的预测制导直接力修正算法。首先,为提高预报速度,利用弹道拟合法对再入段的滑翔弹道进行快速预报;其次,利用预报弹道的终点和预测拦截点的几何关系得到虚拟拦截点,针对虚拟拦截点解二体Lambert问题以确定变轨需用速度,并依据此速度预报弹道,解算零控脱靶量;最后,经多次预报后得到零控脱靶量最小的虚拟拦截点,以此确定最终变轨需用速度并利用速度增益进行修正。仿真结果表明,与无虚拟拦截点修正的策略相比,针对虚拟拦截点的拦截修正方法有效减少了发动机燃料消耗和零控脱靶量,更好地满足中制导能量约束和精度要求。Aiming at the situation of air thinning in most of the near space interceptor’s midcourse guidance phase,based on virtual intercepting point,a predictive guidance direct force correction algorithm was proposed.Firstly,the gliding trajectory of reentry phase was predicted by using the trajectory fitting method to improve the prediction speed.Secondly,the virtual intercepting point was obtained by using the geometric relationship,which was between the predicted trajectory end point and the predicted intercepting point,and the two-body Lambert problem was solved for the virtual intercepting point to determine the required speed for orbit change.Finally,with the smallest zero-control miss distance,the virtual intercepting point was obtained by choosing the virtual intercepting point several times,so as to determine the required velocity for final orbit change and correct it by using the velocity gain.Compared with the strategy without virtual intercepting point correction,the simulation results show that the intercepting correction method for virtual intercepting point can effectively reduce engine fuel consumption and zero-control miss distance,and better meet the energy constraints and range constraints of midcourse guidance.

关 键 词：临近空间拦截弹 预测制导 虚拟拦截点 速度增益 Lambert问题 

分 类 号：V448[航空宇航科学与技术—飞行器设计]