Design of guidance law of missile in attack with high angle

[1] Kim M, Grider K V.Terminal guidance for impact attitude angle constrained flight trajectories [J]. IEEE Transactions on Aerospace and Electronic Systems, 1973, 9(6):852-859 [2] Kim B S, Lee J G.Homing guidance with terminal angular constraint against non-maneuvering and maneuvering targets . AIAA-97-3474,1997: 189-199 [3] 曹邦武,姜长生,关世义,等.电视指令制导空地导弹垂直命中目标的末制导系统研究[J].宇航学报,2004, 25(4):393-397 Cao Bangwu, Jiang Changsheng, Guan Shiyi,et al. Research on the vertical intercept terminal guidance system of TV-command-guidance air-to-ground missile [J]. Journal of Astronautics,2004, 25(4):393-397(in Chinese) [4] 刘丹,祁载康.限制导弹落角和落点的最优制导律[J].北京理工大学学报,2001, 21(3): 278-281 Liu Dan, Qi Zaikang. Impact angel and final position constrained optimal guidance law [J]. Journal of Beijing Institute of Technology, 2001, 21(3): 278-281(in Chinese) [5] 刘强,范英飚.基于最优控制的落角约束设计[J].海军航空工程学院学报,2007, 22(2):215-218 Liu Qiang, Fan Yingbiao. Design of guidance law and controller of missile with terminal angular constraint based on optimal control [J]. Journal of Naval Aeronautical Engineering Institute, 2007, 22(2):215-218(in Chinese)