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带落点和落角约束的最优末制导律研究
引用本文:常超,林德福,祁载康,王辉.带落点和落角约束的最优末制导律研究[J].北京理工大学学报,2009,29(3):233-237.
作者姓名:常超  林德福  祁载康  王辉
作者单位:北京理工大学,宇航科学技术学院,北京,100081
摘    要:为了研究带有落角约束的最优末制导律,利用拉格朗日法,构造带有落点和落角约束的导弹运动方程,研究了制导系统中的动力学滞后对脱靶量和落角误差的影响. 指出高阶动力学滞后的时间常数是影响误差的主要因素,而系统阶数对误差收敛时间的影响较小. 研究结果表明,增加末导时间可以减小导弹的脱靶量和落角误差,并给出满足脱靶量和落角误差要求所需要的最少末导时间与时间常数的关系.

关 键 词:最优末制导律  脱靶量  落角误差  末导时间
收稿时间:2008/3/16 0:00:00

Study on the Optimal Terminal Guidance Law with Interception and Impact Angle
CHANG Chao,LIN De-fu,QI Zai-kang and WANG hui.Study on the Optimal Terminal Guidance Law with Interception and Impact Angle[J].Journal of Beijing Institute of Technology(Natural Science Edition),2009,29(3):233-237.
Authors:CHANG Chao  LIN De-fu  QI Zai-kang and WANG hui
Institution:School of Aerospace Science and Engineering;Beijing Institute of Technology;Beijing 100081;China
Abstract:An optimal terminal guidance law with both interception and impact angle constraint is derived according to simplified missile movement equation and Lagrange method.The effect of guidance system's dynamics on the miss distance and impact angle error is studied.Simulations demonstrate that it is the time constant of the system but not the system order which is the main factor inducing the miss.Increasing engagement time will decrease the miss distance and impact angle error,and the appropriate multiple is co...
Keywords:optimal terminal guidance law  miss distance  impact angle error  engagement time  
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