Method of time-to-go estimation based on predicted crack point
-
摘要: 分别针对顺轨与逆轨拦截飞行轨迹的特点,设计了相应的剩余飞行时间(TGO)估计方法。该方法通过对弹目碰撞点的预测,降低了发射条件差异对TGO估计精度的影响。首先对线性比例导引运动方程进行变形,得到拦截弹飞行轨迹关于弹目距离的一阶微分方程,基于预测碰撞点,对不同初始发射角造成的积分结果误差进行修正,得出了2种拦截模式下的TGO解析表达式。通过与3种现有估计方法对比分析,验证了提出方法的实时性和估计精度,且能够优化制导性能。Abstract: Aimed at the different characters of the head-pursuit and head-on interception flight trajectory, the time-to-go (TGO) estimation methods are designed. According to the prediction of the crack point for the interceptor and target, the influence of different launch conditions on the precision of TGO estimation is decreased. At first, the linear proportional navigation motion equation is transformed, and the first order differential equation about the distance between interceptor and target is obtained. Based on the predicted crack point, the error for the integration result caused by the different initial launch angles is corrected. Then the TGO analytical expressions of two interception models are obtained. Compared with the existing three methods, the simulation result verifies the real time performance and the estimation precision of the proposed method which is able to optimize the guidance performance effectively.
-
[1] RYOO C,CHO H,TAHK M.Time-to-go weighted optimal guidance with impact angle constraints[J].IEEE Transactions on Control Systems Technology,2006,14(3):483-492. [2] KIM K B,KIM M,CHOI J W.Modified receding horizon guidance law with information on small accurate time-to-go[J].IEEE Transactions on Aerospace and Electronic Systems,2000,36(2):725-729. [3] TANAKA A,MAEDA H.Studies on the time-to-go indexing control scheme for an automatic aircraft landing system[J].Transactions of the Japan Society for Aeronautical and Space Sciences,1973,16(31):1-18. [4] WHANG I,RA W.Time-to-go estimation filter for anti-ship missile application[C]//Society of Instrument and Control Engineers (SICE).Piscataway,NJ:IEEE Press,2008:247-250. [5] YORK R,PASTRICK H.Optimal terminal guidance with constraints at final time[J].Journal of Spacecraft and Rockets,1977,14(6):381-382. [6] JEON I,LEE J,TAHK M.Impact-time-control guidance law for anti-ship missiles[J].IEEE Transactions on Control Systems Technology,2006,14(2):260-266. [7] LIU P,SUN R,LI W.Homing guidance law with falling angle and flying time control[J].Journal of Harbin Institute of Technology,2014,21(1):55-61. [8] KIM T H,LEE C H,TAHK M J.Time-to-go polynomial guidance with trajectory modulation for observability enhancement[J].IEEE Transactions on Aerospace and Electronic Systems,2013,49(1):55-73. [9] 马国欣,张友安,李君.带导引头视场限制的多约束导引律及剩余时间估计[J].系统工程与电子技术,2014,36(8):1609-1613.MA G X,ZHANG Y A,LI J.Guidance law with multiple constraints and seeker field-of-view limit and the time-to-go estimation[J].Systerms Engineering and Electronics,2014,36(8):1609-1613(in Chinese). [10] 李辕,闫梁,赵继广,等.顺轨拦截模式剩余飞行时间估计方法研究[J].航空学报,2015,36(9):3032-3041.LI Y,YAN L,ZHAO J G,et al.Method of time-to-go estimation for head-pursuit interception mode[J].Acta Aeronautica et Astronautica Sinica,2015,36(9):3032-3041(in Chinese). [11] 刘剑锋,庄志洪.利用导引头测角信息进行遭遇段剩余飞行时间估计的算法[J].兵工学报,2006,27(1):27-31.LIU J F,ZHUANG Z H.The algorithm of time-to-go using angle information provided by seeker during missile-target encounter[J].Acta Armamentarii,2006,27(1):27-31(in Chinese). [12] RIGGS J T L.Linear optimal guidance for short range air-to-air missile[C]//Proceedings of National Aerospace and Electronics Conference NAECON'79.Piscataway,NJ:IEEE Press,1979:757-764. [13] HULL D G,RADKE J J,MACK R E.Time-to-go prediction for homing missiles based on minimum-time intercepts[J].Journal of Guidance,Control,and Dynamics,1991,14(5):865-871. [14] DHANANJAY N,GHOSE D.Accurate time-to-go estimation for proportional navigation guidance[J].Journal of Guidance,Control,and Dynamics,2014,37(4):1378-1383. [15] TAHK M,RYOO C,CHO H.Recursive time-to-go estimation for homing guidance missiles[J].IEEE Transactions on Aerospace and Electronic Systems,2002,38(1):13-24. [16] 常青,邢超,李言俊.利用导弹轴向加速度估算剩余飞行时间的新方法[J].弹箭与制导学报,2002,22(4):112-114.CHANG Q,XING C,LI Y J.A new method for time-to-go using the acceleration along the axis of missile[J].Journal of Projectiles Rockets Missiles and Guidance,2002,22(4):112-114(in Chinese). [17] 张友安,马国欣.大前置角下比例导引律的剩余时间估计算法[J].哈尔滨工程大学学报,2013,34(11):1409-1414.ZHANG Y A,MA G X.Time-to-go estimation algorithm for the proportional navigation guidance law with a large lead angle[J].Journal of Harbin Engineering University,2013,34(11):1409-1414(in Chinese). [18] 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. [19] SHIMA T.Intercept-angle guidance[J].Journal of Guidance,Control,and Dynamics,2011,34(2):484-492. [20] TAL S,GOLAN O M.Head pursuit guidance[J].Journal of Guidance,Control,and Dynamics,2007,30(5):1437-1444. [21] ZARCHAN P.Tactical and strategic missile guidance[M].3rd ed.Reston:AIAA,2002:15. [22] YUAN P,CHERN J.Ideal proportional navigation[J].Journal of Guidance,Control,and Dynamics,1992,15(5):1161-1165.
点击查看大图
计量
- 文章访问数: 982
- HTML全文浏览量: 80
- PDF下载量: 504
- 被引次数: 0