具有攻击角约束的非奇异终端滑模导引律设计  

Nonsingular terminal sliding mode guidance law with impact angle constraint

作　　者：周慧波[1,2] 宋申民[1] 刘海坤[2] 

机构地区：[1]哈尔滨工业大学控制理论与制导技术研究中心,哈尔滨150001 [2]哈尔滨师范大学数学科学学院,哈尔滨150009

出　　处：《中国惯性技术学报》2014年第5期606-611,618,共7页Journal of Chinese Inertial Technology

基　　金：国家自然科学基金创新群体项目(61021002);黑龙江省自然科学基金(A201111)

摘　　要：为了满足导弹拦截高速大机动目标时高精度制导的需求,首先对二维平面内的弹目相对运动方程进行状态扩张,对于影响制导性能的目标总扰动采用了扩张状态观测器的方法进行动态补偿。然后在非奇异终端滑模面的基础上选取了两种滑模趋近律,设计了两种具有攻击角约束的非奇异终端滑模导引律。最后数值仿真结果表明,在观测器对扩张系统状态进行实时有效估计的前提下,针对不同的期望视线角和目标机动方式,所设计的两种导引律在满足期望的性能要求的同时,可实现导弹对目标的高精度快速打击。In order to realize high-precision guidance when a missile intercepts high-speed maneuvering targets, the states in missile-target relative motion equations were extended in two-dimension plane, and an extended state observer was selected to implement motion compensation for the total disturbance that affects guidance performance. After that, two reaching laws were proposed based on a nonsingular terminal sliding mode surface, and two nonsingular terminal sliding-mode guidance laws with impact angle constraints were proposed. The numerical simulation demonstrate that, by using the observer to make real-time effective estimation for the extension of system state, the two designed guidance laws could meet the expected performance requirements, and the missiles could attack the targets quickly and precisely for different desired line-of sight angle and the manner of the target maneuver.

关 键 词：扩张状态观测器 非奇异终端滑模面 趋近律 有限时间 导引律 

分 类 号：V448.133[航空宇航科学与技术—飞行器设计]