考虑导弹速度时变的带落角约束制导律
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摘要
针对小型战术导弹可能具有一定程度变速能力的问题,将导弹的速度曲线拟合为速度关于相对距离的指数函数,通过直接求解黎卡提方程得到了一种速度时变条件下的满足落角约束的最优制导律。仿真表明,该制导律可以满足设计要求,且在速度时变条件下,相比传统的最优制导律具有更平直的弹道和更小的需用过载。
Aiming at the problem that small size tactical missiles may have a capability of varying speed,a new impact angle control guidance law considering time-varing speed is proposecl,which can be fitted as a function of relative distance. By solving the Riccati equation directly,the optimal guidance law is obtained. Compared with the traditional optimal guidance law,the law proposed in this paper has a more straight trajectory and a smaller overload.
Aiming at the problem that small size tactical missiles may have a capability of varying speed,a new impact angle control guidance law considering time-varing speed is proposecl,which can be fitted as a function of relative distance. By solving the Riccati equation directly,the optimal guidance law is obtained. Compared with the traditional optimal guidance law,the law proposed in this paper has a more straight trajectory and a smaller overload.
引文
[1] RATNOO A,GHOSE D. Impact Angle Constrained Interception of Stationary Targets[J]. Journal of Guidance,Control,and Dynamics,2008,31(6):1817-1822.
[2] AKHIL D,GHOSE D. Biased PN Based Impact Angle Constrained Guidance Using a Nonlinear Engagement Model[C]∥American Control Conference. Fairmont Queen Elizabeth:IEEE Press,2012:950-955.
[3] PRASANNA H M,GHOSE D. Retro-Proportional-Navigation:A New Guidance Glaw for Interception of HighSpeed Targets[J]. Journal of Guidance,Control,and Dynamics,2012,35(2):377-386.
[4]李惠峰,葛亚杰,李昭莹.高超声速飞行器自适应BTT末制导律[J].北京航空航天大学学报,2013,39(5):569-573.LI Hui-feng,GE Ya-jie,LI Zhao-ying. Adaptive BTT Terminal Guidance Law for Hypervelocity Vehicle[J].Journal of Beijing University of Aeronautics and Astronautics,2013,39(5):569-573.
[5]陈克俊,赵汉元.一种适用于攻击地面固定目标的最优再入机动制导律[J].宇航学报,1994,15(1):1-7.CHEN Ke-jun,ZHAO Han-yuan. An Optimal Reentry Guidance Law for Fixed Targets[J]. Journal of Astronautics,1994,15(1):1-7.
[6] LEE C H,TAHK M J,LEE J I. Generalized Formulation of Weighted Optimal Guidance Laws with Impact Angle Constraint[J]. IEEE Transactions on Aerospace and Electronic Systems,2012,49(2):1317-1322.
[7] CHO H,RYOO C K. Optimal Impact Angle Control Guidance Law Based on Linearization about Collision Triangle[J]. Journal of Guidance,Control,and Dynamics,2014,37(3):958-964.
[8] KIM H S,PARK S S,RYOO C K. Relative Impact Angle Control Guidance Law to Intercept Maneuvering Target[C]∥SICE Annual Conference 2015,Hangzhou:IEEE Press,2015:836-841.
[9]宋建梅,张天桥.带末端落角约束的变结构导引律[J].弹道学报,2008,13(1):16-20.SONG Jian-mei,ZHANG Tian-qiao. The Passive Homing Missile’s Variable Structure Proportional Navigation with Terminal Impact Angular Constraint[J]. Journal of Ballistics,2001,13(1):16-20.
[10] CHO D,KIM H J,TAHK M J. Impact Angle Constrained Sliding Mode Guidance Against Maneuvering Target With Unknown Acceleration[J]. IEEE Transactions on Aerospace and Electronic Systems,2015,51(2):1310-1323.
[11] HUANG Rui-song,LI Wei. Optimal Sliding Mode Guidance Law with Height Deviation and Terminal Impact Angle Constraints[J]. IEEE,2015:1-7
[12] ZHOU Hui-bo,LIU Hong-liang,SONG Shen-min. FiniteTime Sliding Mode Guidance Law Design with Impact Angle Constraints[C]∥Proceedings of the 33rd Chinese Control Conference,Nanjing:IEEE Press,2014:675-680.
[13]马国欣,张友安.导弹速度时变的攻击时间与攻击角度控制导引律[J].飞行力学,2013,31(3):255-259.MA Guo-xin,ZHANG You-an. Impact Time and Impact Angle Control Guidance Law for Missiles with Timevarying Velocity[J]. Flight Dynamics,2013,31(3):255-259.]
[14] TAUB I. Intercept Angle Guidance under Time Varying Speed[C]∥AIAA Guidance,Navigation,and Control Conference,Kissimmee,2015:1-16.
[15]巨永锋.最优控制[M].重庆:重庆大学出版社,2005:122-148.JU Yong-feng. Optimal Control[M]. Chongqing:Chongqing University Press,2005:122-148.
[2] AKHIL D,GHOSE D. Biased PN Based Impact Angle Constrained Guidance Using a Nonlinear Engagement Model[C]∥American Control Conference. Fairmont Queen Elizabeth:IEEE Press,2012:950-955.
[3] PRASANNA H M,GHOSE D. Retro-Proportional-Navigation:A New Guidance Glaw for Interception of HighSpeed Targets[J]. Journal of Guidance,Control,and Dynamics,2012,35(2):377-386.
[4]李惠峰,葛亚杰,李昭莹.高超声速飞行器自适应BTT末制导律[J].北京航空航天大学学报,2013,39(5):569-573.LI Hui-feng,GE Ya-jie,LI Zhao-ying. Adaptive BTT Terminal Guidance Law for Hypervelocity Vehicle[J].Journal of Beijing University of Aeronautics and Astronautics,2013,39(5):569-573.
[5]陈克俊,赵汉元.一种适用于攻击地面固定目标的最优再入机动制导律[J].宇航学报,1994,15(1):1-7.CHEN Ke-jun,ZHAO Han-yuan. An Optimal Reentry Guidance Law for Fixed Targets[J]. Journal of Astronautics,1994,15(1):1-7.
[6] LEE C H,TAHK M J,LEE J I. Generalized Formulation of Weighted Optimal Guidance Laws with Impact Angle Constraint[J]. IEEE Transactions on Aerospace and Electronic Systems,2012,49(2):1317-1322.
[7] CHO H,RYOO C K. Optimal Impact Angle Control Guidance Law Based on Linearization about Collision Triangle[J]. Journal of Guidance,Control,and Dynamics,2014,37(3):958-964.
[8] KIM H S,PARK S S,RYOO C K. Relative Impact Angle Control Guidance Law to Intercept Maneuvering Target[C]∥SICE Annual Conference 2015,Hangzhou:IEEE Press,2015:836-841.
[9]宋建梅,张天桥.带末端落角约束的变结构导引律[J].弹道学报,2008,13(1):16-20.SONG Jian-mei,ZHANG Tian-qiao. The Passive Homing Missile’s Variable Structure Proportional Navigation with Terminal Impact Angular Constraint[J]. Journal of Ballistics,2001,13(1):16-20.
[10] CHO D,KIM H J,TAHK M J. Impact Angle Constrained Sliding Mode Guidance Against Maneuvering Target With Unknown Acceleration[J]. IEEE Transactions on Aerospace and Electronic Systems,2015,51(2):1310-1323.
[11] HUANG Rui-song,LI Wei. Optimal Sliding Mode Guidance Law with Height Deviation and Terminal Impact Angle Constraints[J]. IEEE,2015:1-7
[12] ZHOU Hui-bo,LIU Hong-liang,SONG Shen-min. FiniteTime Sliding Mode Guidance Law Design with Impact Angle Constraints[C]∥Proceedings of the 33rd Chinese Control Conference,Nanjing:IEEE Press,2014:675-680.
[13]马国欣,张友安.导弹速度时变的攻击时间与攻击角度控制导引律[J].飞行力学,2013,31(3):255-259.MA Guo-xin,ZHANG You-an. Impact Time and Impact Angle Control Guidance Law for Missiles with Timevarying Velocity[J]. Flight Dynamics,2013,31(3):255-259.]
[14] TAUB I. Intercept Angle Guidance under Time Varying Speed[C]∥AIAA Guidance,Navigation,and Control Conference,Kissimmee,2015:1-16.
[15]巨永锋.最优控制[M].重庆:重庆大学出版社,2005:122-148.JU Yong-feng. Optimal Control[M]. Chongqing:Chongqing University Press,2005:122-148.