Time-to-go weighted optimal trajectory shaping guidance law  

作　　者：王辉 林德福 程振轩 

机构地区：[1]School of Aerospace Engineering,Beijing Institute of Technology [2]China North Industries Group Corporation

出　　处：《Journal of Beijing Institute of Technology》2011年第3期317-323,共7页北京理工大学学报（英文版）

摘　　要：For maneuvering target, the optimal trajectory shaping guidance law which can simultaneously achieve the designed specifications on miss distance and final impact angle was deduced using optimal control theory based on the time-to-go weighted function. Based on the same cost function, the closed-form solutions of the guidance law were derived when the initial displacement of missile, final impact angle, heading error and target maneuver was introduced into the lag-free guidance system. To validate the closed-form solutions, the simulation of the lag-free system was done and the simulation results exactly matched the closed-form solutions and only when the exponent is greater than zero, the final acceleration approaches to zero.For maneuvering target, the optimal trajectory shaping guidance law which can simultaneously achieve the designed specifications on miss distance and final impact angle was deduced using optimal control theory based on the time-to-go weighted function. Based on the same cost function, the closed-form solutions of the guidance law were derived when the initial displacement of missile, final impact angle, heading error and target maneuver was introduced into the lag-free guidance system. To validate the closed-form solutions, the simulation of the lag-free system was done and the simulation results exactly matched the closed-form solutions and only when the exponent is greater than zero, the final acceleration approaches to zero.

关 键 词：trajectory shaping guidance optimal control TIME-TO-GO close-form solution 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程] TP13[自动化与计算机技术—控制理论与控制工程]