一种新的非线性末制导律设计  

A New Nonlinear Terminal Guidance Law Design

作　　者：李志平[1] 周军[1] 郭建国[1] 

机构地区：[1]西北工业大学精确制导与控制研究所,西安710072

出　　处：《火力与指挥控制》2014年第3期148-150,158,共4页Fire Control & Command Control

基　　金：航天支撑基金资助项目(N11XW0001)

摘　　要：基于拦截机动目标的末制导问题,提出了一种新的具有鲁棒性的非线性末制导律。基于二维平面内弹目相对运动学关系,将目标机动作为有界干扰量,建立了描述弹目相对运动的数学模型。引入一阶弹体动态特性,借助于零化弹目视线角速率的思想,采用Nussbaum-type增益技术,设计一种非线性鲁棒末制导律,同时利用Lyapunov稳定性理论证明了在该制导律作用下末制导系统的稳定性。最后通过与比例导引律进行对比,数字仿真验证了所设计的非线性制导律的有效性,具有很强的鲁棒性和适应性。For the case of the maneuvering targets interception, a new nonlinear terminal guidance law with robustness is proposed. The mathematic model is built according to two-dimensional relationship between missile and target whose acceleration as disturbance is introduced. The autopilot dynamic is considered, and by employing the Nussbaum-type gain technique, a global nonlinear control strategy is contrived to obtain the nonlinear guidance law based on the method of zeroing the rate of line-of-sight angle, and the stability of guidance system is strictly proven under the nonlinear guidance law based on Lypunov theory. Finally an illustrative example is given to show that new guidance law is suitable to the missile for intercepting the target with maneuver than proportional navigation law, and the better precision of guidance law is obtained.

关 键 词：末制导律 非线性 稳定性 视线角速率 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]