真比例导引反高速目标拦截能力分析
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摘要
针对反高速目标拦截作战过程中拦截弹中末制导交接班时刻状态约束设置的问题,分析了真比例导引制导律的拦截能力。首先,通过分析末制导阶段拦截弹和目标的相对运动关系,推导得到了成功拦截目标的充分必要条件以及目标速度前置角需要满足的约束范围;其次,在中末制导交接班不满足拦截条件的情况下,针对拦截高速非机动目标作战情形,通过分析拦截弹速度前置角和目标速度前置角的变化关系,给出了真比例导引静态捕获区(static capture region,SCR)的定义以及构成;然后,针对拦截高速机动目标作战情形,结合目标速度前置角约束范围得到了真比例导引动态捕获区(dynamic capture region,DCR)的定义以及构成;最后开展了3种情形下的数字仿真,验证了真比例导引拦截能力分析的合理性和有效性。
To solve the problem of the state parameters constraints at the handover moment between the midcourse and terminal guidance in the hypersonic target interceptions,the interception capability of the true proportional navigation guidance law is analyzed.Firstly,the sufficient and necessary condition for a successful interception and the constraints for the target velocity heading angles are derived by analyzing the relative motion of the interceptor and the target in the terminal guidance phase.Secondly,in the cases where the interceptor fail to satisfy the interception condition against un-maneuvering hypersonic targets,the definition and constitution of the static capture region(SCR)of the true proportional navigation guidance law are given by analyzing the evolving relationships between the interceptor velocity heading angles and target velocity heading angles.Thirdly,aiming at the maneuvering hypersonic targets interceptions,the definition and constitution of the dynamic capture region(DCR)of the true proportional navigation guidance law are derived based on the target velocity heading angles constraints.Finally,three digital simulations are carried out,which validate the rationality and effectiveness of the true proportional navigation interception capability analysis.
To solve the problem of the state parameters constraints at the handover moment between the midcourse and terminal guidance in the hypersonic target interceptions,the interception capability of the true proportional navigation guidance law is analyzed.Firstly,the sufficient and necessary condition for a successful interception and the constraints for the target velocity heading angles are derived by analyzing the relative motion of the interceptor and the target in the terminal guidance phase.Secondly,in the cases where the interceptor fail to satisfy the interception condition against un-maneuvering hypersonic targets,the definition and constitution of the static capture region(SCR)of the true proportional navigation guidance law are given by analyzing the evolving relationships between the interceptor velocity heading angles and target velocity heading angles.Thirdly,aiming at the maneuvering hypersonic targets interceptions,the definition and constitution of the dynamic capture region(DCR)of the true proportional navigation guidance law are derived based on the target velocity heading angles constraints.Finally,three digital simulations are carried out,which validate the rationality and effectiveness of the true proportional navigation interception capability analysis.
引文
[1]ZHOU J,LEI H M,ZHANG D Y.Online optimal midcourse trajectory modification algorithm for hypersonic vehicle interceptions[J].Aerospace Science and Technology,2017,63:1-12.
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[17]刘少波,赵良玉.超视距防空导弹中末制导交接班时的目标捕获概率研究[J].固体火箭技术,2016,39(5):723-728.LIU S B,ZHAO L Y.Target acquisition probability at handoff from midcourse to terminal guidance of a BVR air defense missile[J].Journal of Solid Rocket Technology,2016,39(5):723-728.
[18]赵斌,周军,卢晓东,等.考虑终端角度约束的自适应积分滑模制导律[J].控制与决策,2017,32(11):1966-1972.ZHAO B.ZHOU J,LU X D,et al.Adaptive integral sliding mode guidance law considering impact angle constraint[J].Control and Decision,2017,32(11):1966-1972.
[19]王还乡,李为民,上官强,等.高超声速飞行器巡航段拦截作战需求分析[J].战术导弹技术,2012(2):36-40.WANG H X,LI W M,SHANG G Q,et al.Analysis of the battle demand to interception on the cruise phase of hypersonic vehicle[J].Tactical Missile Technology,2012(2):36-40.
[20]周梦琦,薛林,闫晓勇.近程防空导弹发动机推力方案优化研究[J].现代防御技术,2017,45(5):42-47.ZHOU M Q,XUE L,YAN X Y.Optimizing motor propulsion scheme in short range antiaircraft missiles[J].Modern Defence Technology,2017,45(5):42-47.
[21]张弫,郑时镜,于本水.远程防空导弹弹道设计技术研究[J].系统工程与电子技术,2003,25(3):304-369.ZHANG Z,ZHENG S J,YU B S.Study of the trajectory design technology for the long-range air-defense missile[J].Systems Engineering and Electronics,2003,25(3):304-369.
[22]LEONARDO A.Iterative learning control for homing guidance design of missiles[J].Defence Technology,2017,12:360-366.
[23]HE S M,LIN D F,WANG J.Compound control methodology for a robust missile autopilot design[J].Journal of Aerospace Engineering,2015,28(6):1-12.
[24]SUN S,LIU X D,WEI X L,et al.The switching condition of guidance laws for compound control missile[C]∥Proc.of the34th Chinese Control Conference,2015:5148-5152.
[25]朱隆魁,汤国建,余梦伦.防空导弹直接力/气动力复合控制系统设计[J].宇航学报,2008,29(6):1895-1900.ZHU L K,TANG G J,YU M L.Compound control system design with direct thrust and aerodynamic force for air defense missile[J].Journal of Astronautics,2008,29(6):1895-1900.
[26]TAL S,JOSEF S.Time-varying linear pursuit-evasion game models with bounded controls[J].Journal of Guidance,Control and Dynamics,2002,25(3):425-432.
[27]SIMONE B,TAL S.Differential games missile guidance with bearings-only measurements[J].IEEE Trans.on Aerospace and Electronic Systems,2014,50(4):2906-2915.
[28]RAJARSHI B,DEBASISH G.Nonlinear differential games based impact angle constrained guidance law[J].Journal of Guidance,Control,and Dynamics,2015,38(3):384-402.
[2]LEI H M,ZHOU J,ZHAI D L,et al.Optimal midcourse trajectory cluster generation and trajectory modification for hypersonic interceptions[J].Journal of Systems Engineering and Electronics,2017,28(6):1162-1173.
[3]RATNOO A,GHOSE D.Impact angle constrained guidance against nonstationary nonmaneuvering targets[J].Journal of Guidance,Control and Dynamics,2010,33(1):269-275.
[4]YAN L,ZHAO J G,SHEN H R,et al.Biased retro-proportional navigation law for interception of high-speed targets with angular constraint[J].Defense Technology,2014,10:60-65.
[5]LI Y,YAN L,ZHAO J G,et al.Combined proportional navigation law for interception of high-speed targets[J].Defense Technology,2014,10:298-303.
[6]LI Y,YAN L,ZHAO J G,et al.Combined proportional navigation law for interception of high-speed targets[J].Defense Technology,2014,10:298-303.
[7]闫梁,赵继广,李辕.带约束碰撞角的顺/逆轨制导律设计[J].北京航空航天大学学报,2015,41(5):857-863.YAN L,ZHAO J G,LI Y.Guidance law with angular constraints for head-pursuit or head-on engagement[J].Journal of Beijing University of Aeronautics and Astronautics,2015,41(5):857-863.
[8]FENG T.Unified approach to missile guidance laws:a 3Dextension[J].IEEE Trans.on Aerospace and Electronic Systems,2005,41(4):1178-1199.
[9]FENG T.Capture region of a GIPN guidance law for missile and target with bounded maneuverability[J].IEEE Trans.on Aerospace and Electronic Systems,2011,47(1):201-213.
[10]FENG T.Capture region of a 3DPPN guidance law for intercepting high-speed targets[J].Asian Journal of Control,2012,14(5):1215-1226.
[11]LIN Y P,LIN C L,LI Y H.Development of 3-D modified proportional navigation guidance law against high-speed targets[J].IEEE Trans.on Aerospace and Electronic Systems,2013,49(1):677-687.
[12]LI K B,CHEN L,BAI X.Differential geometric modeling of guidance problem for interceptors[J].Science China Technological Sciences,2011,54(9):2283-2295.
[13]LI K B,ZHANG T,CHEN L.Ideal proportional navigation for exoatmospheric interception[J].Chinese Journal of Aeronautics,2013,26(4):976–985.
[14]LI K B,CHEN L,TANG G.Improved differential geo-metric guidance commands for endoatmospheric interception of highspeed targets[J].Science China Technological Sciences,2013,56(2):518-528.
[15]于大腾,王华,李林森,等.能量约束下的动能拦截弹逆轨拦截攻击区建模[J].宇航学报,2017,38(7):704-713.YU D T,WANG H,LI L S,et al.Attack area modeling of kinetic kill vehicle head-on interception with energy constraint[J].Journal of Astronautics,2017,38(7):704-713.
[16]唐明南,郑学合,王天舒,等.多平台信息下机动目标拦截中末制导交班研究[J].系统工程与电子技术,2017,39(12):2757-2764.TANG M N,ZHENG X H,WANG T S,et al.Handover of guidance from midcourse to terminal in the maneuvering target interception based on multi-platform information[J].Systems Engineering and Electronics,2017,39(12):2757-2764.
[17]刘少波,赵良玉.超视距防空导弹中末制导交接班时的目标捕获概率研究[J].固体火箭技术,2016,39(5):723-728.LIU S B,ZHAO L Y.Target acquisition probability at handoff from midcourse to terminal guidance of a BVR air defense missile[J].Journal of Solid Rocket Technology,2016,39(5):723-728.
[18]赵斌,周军,卢晓东,等.考虑终端角度约束的自适应积分滑模制导律[J].控制与决策,2017,32(11):1966-1972.ZHAO B.ZHOU J,LU X D,et al.Adaptive integral sliding mode guidance law considering impact angle constraint[J].Control and Decision,2017,32(11):1966-1972.
[19]王还乡,李为民,上官强,等.高超声速飞行器巡航段拦截作战需求分析[J].战术导弹技术,2012(2):36-40.WANG H X,LI W M,SHANG G Q,et al.Analysis of the battle demand to interception on the cruise phase of hypersonic vehicle[J].Tactical Missile Technology,2012(2):36-40.
[20]周梦琦,薛林,闫晓勇.近程防空导弹发动机推力方案优化研究[J].现代防御技术,2017,45(5):42-47.ZHOU M Q,XUE L,YAN X Y.Optimizing motor propulsion scheme in short range antiaircraft missiles[J].Modern Defence Technology,2017,45(5):42-47.
[21]张弫,郑时镜,于本水.远程防空导弹弹道设计技术研究[J].系统工程与电子技术,2003,25(3):304-369.ZHANG Z,ZHENG S J,YU B S.Study of the trajectory design technology for the long-range air-defense missile[J].Systems Engineering and Electronics,2003,25(3):304-369.
[22]LEONARDO A.Iterative learning control for homing guidance design of missiles[J].Defence Technology,2017,12:360-366.
[23]HE S M,LIN D F,WANG J.Compound control methodology for a robust missile autopilot design[J].Journal of Aerospace Engineering,2015,28(6):1-12.
[24]SUN S,LIU X D,WEI X L,et al.The switching condition of guidance laws for compound control missile[C]∥Proc.of the34th Chinese Control Conference,2015:5148-5152.
[25]朱隆魁,汤国建,余梦伦.防空导弹直接力/气动力复合控制系统设计[J].宇航学报,2008,29(6):1895-1900.ZHU L K,TANG G J,YU M L.Compound control system design with direct thrust and aerodynamic force for air defense missile[J].Journal of Astronautics,2008,29(6):1895-1900.
[26]TAL S,JOSEF S.Time-varying linear pursuit-evasion game models with bounded controls[J].Journal of Guidance,Control and Dynamics,2002,25(3):425-432.
[27]SIMONE B,TAL S.Differential games missile guidance with bearings-only measurements[J].IEEE Trans.on Aerospace and Electronic Systems,2014,50(4):2906-2915.
[28]RAJARSHI B,DEBASISH G.Nonlinear differential games based impact angle constrained guidance law[J].Journal of Guidance,Control,and Dynamics,2015,38(3):384-402.