摘要
针对大落角攻击要求,分析了终端落角约束制导律的解析解和脱靶量特性,提出了满足命中位置、落角、需用过载及目标跟踪要求的落角约束值装定设计方法;给出了终端落角约束制导律的推导过程,基于解析解分析了制导律的指令特性及飞行器速度、位置变化规律,并进行了仿真验证;利用伴随法分析了无量纲位置、角度脱靶量特性,确定了制导律收敛时间为至少15倍制导动力学时间;分析了制导律角度权系数变化对终端落角的影响,给出了装定落角约束值与精确落角约束之间的转换设计方法,并通过仿真验证了装定设计方法的正确性。
The guidance characteristics for terminal large impact angle attack have been researched. And a method is presented for impact angle design to satisfy terminal constraints. The derivation process of terminal impact angle constraint guidance law is given. Based on the close-form solution of terminal guidance law, the characteristics of guidance command, velocity and location are analyzed and verified. The non-dimensional miss distance and the impact angle error are analyzed by using the adjoint mathematical method, and the covergence time of the guidance law is determined to be at least 15 times of the guidance dynamic time. The effect of guidance weighted coefficients on impact angle is analyzed, and the conversion design method between constraint and actual impact angle value is proposed. The simulation results show that the conversion design method is valid.
作者
李强
王永海
刘涛
赵振平
田源
Li Qiang;Wang Yonghai;Liu Tao;Zhao Zhenping;Tian Yuan(Beijing Institute of Space Long March Vehicle, Beijing 100076, China;Beijing Aerospace Wanyuan Science & Technology Co.Ltd., Beijing 100076, China)
出处
《航空兵器》
CSCD
北大核心
2019年第3期19-26,共8页
Aero Weaponry
关键词
飞行器控制
导航技术
终端落角约束
解析解
无量纲脱靶量
control of aerocraft
navigation technology
terminal constraint of impact angle
closed-form solution
non-dimensional miss
