基于正则摄动理论的无动力飞行器末段制导方法  

Final Guidance Law of Glide Vehicle Based on Regular Perturbation Method

作　　者：孟静伟 赵鹏雷 杨宇和 石宝兰 MENG Jingwei;ZHAO Penglei;YANG Yuhe;SHI Baolan(Beijing Institute of Astronautical Systems Engineering,Beijing 100076,China)

机构地区：[1]北京宇航系统工程研究所,北京100076

出　　处：《宇航总体技术》2024年第2期39-45,共7页Astronautical Systems Engineering Technology

摘　　要：以无动力飞行器末制导问题为研究对象,用正则摄动理论对其纵向弹道方程进行处理。在零阶方程中考虑重力和气动力的主导部分,在一阶方程中考虑重力和气动力的剩余部分,进而获得了弹道方程的解析解,仿真证明了该解析解具有较高的计算精度和计算效率。基于弹道解析解所获得的脱靶量,提出了正则摄动制导方法,仿真证明了该方法具有最优性。The regular perturbation method is applied to solving the trajectory equation of glide vehicle in the final guidance stage.Most of the gravity and aerodynamic forces are considered in the zero order equation,and the residual gravity and aerodynamic forces are considered in the first order equation.The analytical solution of the trajectory equation is obtained by analytical integration.The simulation results show that the analytical solution has high accuracy and computational efficiency.Based on miss distance generated by analytical solution,guidance based on regular perturbation method is proposed.The simulation results prove that this guidance law has optimality in control.

关 键 词：正则摄动 导引律 解析解 

分 类 号：V412[航空宇航科学与技术—航空宇航推进理论与工程]