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.
出处
《飞行力学》
CSCD
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)
关键词
鲁棒制导律
设计
三维制导
导弹
three-dimensional guidance
nonlinear H_∞ control
robust guidance law
Hamilton-Jacobi partial differential inequation
