非线性三维H_∞鲁棒制导律设计  

Study on Nonlinear Three-Dimensional H_∞ Robust Guidance Law

作　　者：李新国[1] 陈红英[1] 

机构地区：[1]西北工业大学航天工程学院,陕西西安710072

出　　处：《飞行力学》2002年第4期61-64,共4页Flight Dynamics

基　　金：国防科技预研基金资助项目 (2 0 0 0 J1 .1 .3 .HK0 3 0 1 );航天科技创新基金资助项目 (2 0 0 1 CH0 80 4)

摘　　要：应用飞行力学和理论力学原理 ,基于导弹目标三维相对运动方程 ,提出了一种适用于大机动目标的非线性 H∞ 三维制导律。通过求解哈密尔顿 -雅可比偏微分不等式 ,给出了解析形式的 H∞ 制导律。对最坏情况下目标加速度的分析结果表明 ,H∞ 制导律具有很好的跟踪性能和鲁棒性。Because of linearization and hypotheses of low-angle-of-attack cannot be satisfied in intercepting the high maneuverable target, based on flight dynamics and theory mechanics, according to missile-target three-dimensional relative kinematics equation, a kind of three-dimensional nonlinear H ∞ guidance law is presented. The guidance law does not require the information of target acceleration, performance robustness can be achieved by the guidance law.The H ∞ guidance law is expressed by solving the associated Hamilton-Jacobi partial differential inequation analytically. The result from analysis of the worst-case target acceleration shows that the guidance exhibits good qualities and strong robustness.

关 键 词：鲁棒制导律 设计 三维制导 导弹 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]