考虑导弹自动驾驶仪动态特性的带攻击角度约束制导律  

Impact angle guidance law considering missile's dynamics of autopilot

作　　者：熊少锋[1,2] 王卫红[1,2] 刘晓东[3,4] 王森[1,2] 武亮[1,2] 

机构地区：[1]北京航空航天大学自动化科学与电气工程学院,北京100191 [2]北京航空航天大学飞行器控制一体化技术重点实验室,北京100191 [3]北京航天自动控制研究所,北京100854 [4]宇航智能控制国防科技重点实验室,北京100854

出　　处：《控制与决策》2015年第4期585-592,共8页Control and Decision

基　　金：科研基金项目(B212013XXXX)

摘　　要：针对打击机动目标时带攻击角度约束的制导问题,采用扩张状态观测器和动态面控制方法设计一种考虑自动驾驶仪动态特性的制导律.考虑期望视线角的变化率正比于未知的目标加速度,采用扩张状态观测器对未知目标加速度进行估计.为了避免奇异问题,并克服非匹配不确定项对系统性能的影响,采用非奇异终端滑模和动态面控制方法进行制导律设计.与传统的将目标加速度设为零的制导律相比较,仿真结果表明所提出的制导律具有良好的制导性能.Aiming at the problem of guidance law design for intercepting maneuvering targets with the impact angle constraint, a guidance law is designed considering missile＇s dynamics of the autopilot based on the extended state observer and dynamic surface control methods. Considering that the change rate of the desired line of sight angle is proportional to the unknown target acceleration, the extended state observer is employed to estimate the unknown target acceleration. In order to avoid the singularity problem and eliminate the influence of mismatched uncertainties on the system performance, the nonsingular terminal sliding mode control and dynamic surface control schemes are proposed for the guidance law design. Compared with the traditional guidance law which simply treats the unknown target acceleration as zero, the simulation results show that the proposed guidance law provides better interception performance.

关 键 词：非线性制导律 攻击角度约束 动态面控制 扩张状态观测器 机动目标 

分 类 号：V448.13[航空宇航科学与技术—飞行器设计]