United-proportional-navigation law for interception of high-speed maneuvering targets
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摘要: 针对高速机动目标,提出了三维联合比例制导律.该制导律通过时变导航比将顺、逆轨拦截优势相结合,由2个平面制导律合成三维制导律后,可实现顺顺轨、逆逆轨和顺逆轨结合3种拦截模式,极大地扩展了经典比例制导律捕获区域.在二维条件下,根据目标加速度推导了视线角速率的解析式,设计了时变导航比.将二维联合比例制导律扩展到三维,修正了之前算法中俯仰平面的拦截弹路径倾角与速度计算误差,并给出了目标加速度背离拦截弹的机动模型.仿真结果表明:对于高速机动目标,联合比例制导律捕获区域更大,且较经典比例制导律和负比例制导律脱靶量更低、较增广比例制导律控制力更小.Abstract: Aimed to high-speed maneuvering targets, three dimensional united proportional navigation (UPN) law was proposed. The guidance law combines the advantages of head-on and head-pursuit engagement through time-varying navigation ratio. The three-dimensional UPN law consisted of two planar laws can execute head-on with head-on, head-pursuit with head-pursuit and head-on with head-pursuit mixed models, which enlarge the capture region of interceptor tremendously. At planar engagement geometry, the analytic expression of line of sight (LOS) angular rate was deduced according to the target acceleration, and the time-variant navigation ratio was designed. While the planar UPN guidance law was extended into a three dimensional condition, the mistake of interceptor path angle and velocity at pitch plane in prior algorithm was modified and the target evading model was given. The simulation results show that, for high speed maneuvering targets, UPN has less miss distance than proportional navigation (PN) and retro proportional navigation (RPN), less control effort than augmented proportional navigation (APN) and larger capture region than the others.
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[1] 陈峰,肖叶伦,陈万春.基于需用速度增益曲面的大气层外超远程拦截导引方法[J].航空学报,2010,31(2):342-349. Chen F,Xiao Y L,Chen W C.Guidance based on velocity-to-be-gained surface for super-range exoatomospheric intercept[J].Acta Aeronautica et Astronautica Sinica,2010,31(2):342-349(in Chinese). [2] 宋愿贇,陈万春. 高精度快速趋近滑膜变结构末端导引方法[J].北京航空航天大学学报,2012,38(3):319-323. Song Y Y,Chen W C.High-accuracy quick-reaching sliding mode variable structure terminal guidance law[J].Journal of Beijing University of Aeronautics and Astronautics,2012,38(3): 319-323(in Chinese). [3] Kuroda T,Imado F.Advanced missile guidance system against a very high speed maneuvering target[C]//AIAA Guidance,Navigation and Control Conference.Reston:AIAA,1989:176-180. [4] Kuroda T,Imado F.Advanced missile guidance system against very high speed target[C]//AIAA Guidance,Navigation and Control Conference.Reston:AIAA,1988:320-324. [5] Lin Y P,Lin C L,Li Y H.Development of 3-D modified proportional navigation guidance law against high-speed targets[J].IEEE Transactions on Aerospace and Electronic Systems,2013,49(1):677-687. [6] TyanF,Jeng F S.Capture region of three dimensional PPN guidance law against a high speed-nonmaneuvering target[C]//Proceedings of the American Control Conference.Piscataway,NJ:Institute of Electrical and Electronics Engineers Inc,2008:3488-3493. [7] Taur D R. Composite Guidance and Navigation Strategy for a SAM Against High-Speed Target[C]//AIAA Guidance,Navigation,and Control Conference and Exhibit.Reston:AIAA,2003:1-10. [8] Golan O M,Shima T.Headpursuit guidance for hypervelocity interception[C]//AIAA Guidance,Navigation and Control Conference.Reston:AIAA,2004:1437-1444. [9] Shima T,Golan O M.Head pursuit guidance[J].Journal of Guidance,Control,and Dynamics,2007,30(5):1437-1444. [10] Shima T. Intercept-angle guidance[J].Journal of Guidance,Control,and Dynamics,2011,34(2):484-492. [11] Prasanna H M,Ghose D.Retro-proportional-navigation:a new guidance law for interception of high-speed targets[J].Journal of Guidance,Control,and Dynamics,2012,35(2):377-386. [12] Siouris G M. Missile guidance and control systems[M].New York:Springer Group,2004:142-173. [13] Francis C,Lukenbill.A target/missile engagement scenario using classical proportional navigation[D].California:Naval Postgraduate School,1990. [14] Peppas D I. A computer analysis of proportional navigation and command to line of sight of a command guided missile for a point defence system[D].California:Naval Postgraduate School,1992. [15] Costello P. Simulink simulation of proportional navigation and command to line of sight missile guidance[D].California:Naval Postgraduate School,1995. [16] Kim B S,Lee J G,Han H S.Biased PNG law for impact with angular constraint[J].IEEE Transactions on Aerospace and Electronic Systems,1998,34(1):277-288.
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