Missile Guidance Law with Terminal Impact Angle Constraint

KIM M,GRIDER K V.Terminal guidance for impact attitude angle constrained flight trajectories[J].IEEE Trans.on Aerospace and Electronic Systems,1973,9(6):852-859.[2] KIM B S,LEE J G,HAN H S.Biased PNG law for impact with angular constraint[J].IEEE Trans.on Aerospace and Electronic Systems,1998,34(1),277-288.[3] KIM B S,LEE J.Homing guidance with terminal angular against non-maneuvering and maneuvering target[C] ∥AIAA Guidance,Navigation and Control Conference,New Orleans:[s.n.] ,1997:189-199.[4] 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.[5] RYOO C K,CHO H,TAHK M J.Time-to-go weighted optimal guidance with impact angle constraint[J].IEEE Trans.Control Systems Technology,2006,14(3):483-492.[6] TAHK M J,RYOO C K,CHO H.Recursive time-to-go estimation for homing guidance missiles[J].IEEE Trans.Aerospace and Electronic Systems,2002,38(1):13-24.[7] 钱杏芳,林瑞雄,赵亚男.导弹飞行力学[M].北京:北京理工大学出版社,2000.[8] JEON I S,LEE J I,TAHK M J.Guidance law to control impact time and angle[J].IEEE Trans.Aerospace and Electronic Systems,2007,43(1):301-310.[9] JEON I S,LEE J I,TAHK M J.Impact-time-control guidance law for anti-ship missiles[J].IEEE Trans on Control Systems Technology,2006,14(2):260-266,