攻击时间控制的四阶多项式前置角制导律  

Four-order polynomial lead angle guidance law for impact time constraints

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

机构地区：[1]火箭军工程大学,陕西西安710025

出　　处：《飞行力学》2025年第1期78-82,共5页Flight Dynamics

摘　　要：针对导弹末端碰撞时间约束问题,基于水平面内弹目相对运动模型,提出了一种四阶多项式前置角制导律。首先,分析导弹在飞行过程初始时刻和末端时刻的约束,包括初始前置角约束、终端前置角约束、终端前置角速率约束和碰撞时间约束;然后,提出了一种结合约束项的四阶多项式前置角制导律,并证明该多项式满足约束要求。仿真结果表明,所设计的制导律能够在要求的打击时间准确命中固定目标。与传统滑模制导方法相比,所设计方法的法向过载变化连续,需用控制能量和最大法向过载较小,弹道后段较为平直。A four-order polynomial lead angle guidance law is proposed to solve the impact time con-straints problem,based on the relative motion model between missiles and targets in horizontal plane.Firstly,the constraints of the initial and terminal moments of the missile during flight are an-alyzed,including the constraints of the initial lead angle,the terminal lead angle,the terminal lead-angle rate and the impact time.Then,a four-order polynomial lead angle guidance law combined with constraint terms is proposed,which is proved satisfying the constraint requirements.The simu-lation results show that the designed guidance law can accurately hit the fixed target at the required attack time.Compared with the traditional sliding mode guidance method,the normal overload of the proposed method is continuous,the control energy and the maximum normal overload are smaller,and the rear trajectory is relatively straight.

关 键 词：制导律 碰撞时间约束 协同制导 多项式 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]