一种高超声速滑翔式导弹轨迹优化方法  

A Trajectory Optimization Method for Hypersonic Gliding Missile

作　　者：刘仲信 苗昊春 皇甫逸伦 李雅君 高登巍 付博 LIU Zhongxin;MIAO Haochun;HUANGFU Yilun;LI Yajun;GAO Dengwei;FU Bo(Xi an Modern Control Technology Research Institute,Xi an 710065,Shaanxi,China)

机构地区：[1]西安现代控制技术研究所,陕西西安710065

出　　处：《弹箭与制导学报》2024年第3期35-42,共8页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：以高斯伪谱法为基础,考虑多段多复杂约束,提出了一种面向突防任务需求,通过罚函数法处理非全程飞行高度与飞行攻角约束的高超声速滑翔式导弹轨迹优化方法。通过仿真结果可以看出,初始状态约束、控制约束、过程约束与终端状态约束均得到了有效控制,且罚函数法处理突防任务段约束相较于常规分段约束法在约束量收束方面更具备优势,能够为后续设计工作保留更多的余量。此外,仿真结果还验证了该方法在不同射程、不同发射点高度和目标点高度条件下的有效覆盖能力。In this paper,a trajectory optimization method of hypersonic glide missile is put forward by using penalty function method to hand non full course flying height and angle of attack constraints,which is based on Gauss Pseudo-spectral Method and takes into account multi phases,multi complex constraints and penetration mission-oriented requirements and so on.Its simulation results show that all constraint indexes are effectively controlled,and the penalty function method has more advantages in handling mission segmented constraints compared to conventional segmented constraint methods,which verified the effective coverage ability of the method under different ranges,launch heights and target heights.

关 键 词：高斯伪谱法 性能指标 罚函数 轨迹优化 

分 类 号：TJ013[兵器科学与技术—兵器发射理论与技术] V412[航空宇航科学与技术—航空宇航推进理论与工程] V448.1