考虑路径点约束的攻击时间与攻击角度控制制导方法  

Impact time and angle control guidance method with way-point constraint

作　　者：雷刚 王和 李少朋 罗炜 LEI Gang;WANG He;LI Shaopeng;LUO Wei(College of Missile Engineering,Rocket Force University of Engineering,Xi’an 710025,China)

机构地区：[1]火箭军工程大学导弹工程学院,西安710025

出　　处：《中国惯性技术学报》2025年第2期172-178,共7页Journal of Chinese Inertial Technology

基　　金：国家自然科学基金(62103432)。

摘　　要：为提升导弹武器在进行协同打击时的效能,对仅满足攻击时间与攻击角度控制的制导方法进行扩展,设计了一种带有路径点约束的多项式飞行轨迹,推导建立了指令加速度与飞行时间的关系。通过在飞行轨迹上设置路径点约束,改变了战术导弹的飞行轨迹,提高了导弹的机动突防能力。通过仿真对设计的制导方法进行验证,实验条件下所提方法的导弹攻击时间与攻击角度误差为0,脱靶量小于0.18 m,路径点偏差小于0.12 m。仿真结果表明所提出的制导方法能够有效实现攻击时间和攻击角度的控制且满足路径点约束。In order to improve the effectiveness of missile weapons in conducting coordinated strikes,an extended guidance method is proposed that not only satisfies control over impact time and angle but also incorporates a polynomial flight trajectory with way-point constraint.The relationship between command acceleration and flight time is derived,enabling improved maneuvering penetration capabilities by altering the missile's flight path through way-point constraint.The proposed guidance method is verified by simulation.Under experimental conditions,the missile impact time and angle without error,the miss distance is less than 0.18 m,and the way-point deviation is less than 0.12 m.The simulation results show that the proposed guidance method can effectively realize impact time and angle control and satisfy the way-point constraint.

关 键 词：路径点约束 攻击时间与攻击角度控制 多项式 

分 类 号：V448[航空宇航科学与技术—飞行器设计]