临近空间目标拦截弹弹道设计与验证  

Design and Verification of Near Space Target Interceptor Trajectory

作　　者：陈文钰 邵雷[1] 谭诗利 徐晨洋 李世杰 Chen Wenyu;Shao Lei;Tan Shili;Xu Chenyang;Li Shijie(Air and Missile Defense College,Air Force Engineering University,Xi’an 710051,China)

机构地区：[1]空军工程大学防空反导学院,西安710051

出　　处：《航空兵器》2021年第2期27-33,共7页Aero Weaponry

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

摘　　要：针对临近空间高超声速目标拦截弹弹道方案进行了设计和验证。首先,论述了临近空间高超声速目标拦截弹弹道设计的必要性,以临近空间飞行器高抛-再入-滑翔方案为参考设计弹道,将全弹道分为主动段和滑翔段分段建模;然后,根据主动段、滑翔段分别以射程最远、末端速度最大为性能指标,通过飞行过程分析约束条件,建立弹道优化的最优控制模型;最后,基于Gauss伪谱法对主动段和滑翔段弹道优化问题进行求解。仿真结果表明,所得的弹道轨迹特征与高抛-再入-滑翔弹道方案一致,飞行参数满足约束条件。The trajectory of the near space hypersonic target interceptor is designed and verified.Firstly,this paper discusses the necessity of the trajectory design of the near space hypersonic target interceptor.Taking the high throw-reentry-glide trajectory scheme of the near space hypersonic as the reference trajectory,the whole trajectory is divided into active phase and glide phase.Secondly,the active phase takes the longest range as the performance index,and the glide phase takes the maximum terminal velocity as the performance index.According to the constraints of flight process analysis,it establishes the optimal control model of trajectory optimization.Lastly,the Gauss pseudo-spectral method is used to plan the trajectory of the active and gliding phases.The simulation results show that the obtained trajectory characteristics are consistent with the high-throw-reentry-glide trajectory scheme,and the flight parameters satisfy the constraints.This study can provide some reference for the trajectory planning of the near-space interceptor.

关 键 词：临近空间目标 拦截弹弹道 GAUSS伪谱法 弹道规划 拦截 

分 类 号：TJ761.7[兵器科学与技术—武器系统与运用工程] V412.4[航空宇航科学与技术—航空宇航推进理论与工程]