滑模干扰观测器的反机动目标末制导律设计  

A Design Method Based on Sliding Mode Guidance Law Anti-Maneuvering Targets

作　　者：时建明[1] 王洁[1] 冯刚[1] 刘少伟[1] 

机构地区：[1]空军工程大学防空反导学院,西安710051

出　　处：《空军工程大学学报（自然科学版）》2016年第6期23-27,共5页Journal of Air Force Engineering University(Natural Science Edition)

基　　金：航空科学基金(20120196006);学院科研创新基金(15DYCX011)

摘　　要：针对大气层外拦截器拦截机动目标的末段制导问题,提出基于滑模干扰观测器的滑模制导律设计方法。建立基于视线的拦截器-目标相对运动方程,采用滑模控制理论,设计使纵向平面和侧向平面内的视线角速率趋于零的制导律。通过超扭曲滑模干扰观测器,估计目标机动,从而补偿制导系统中的不确定项,并避免滑模切换控制的抖动问题。反机动目标末制导仿真结果表明,所研究的滑模制导方法具有满意的制导精度和鲁棒性。Aimed at the pro are uncertain at endgame endgame guidance law. Th blem that maneuvering targets guidance, this paper presents e paper establishes a relative mo tween target and interceptor by adopting a robust guidanc intercepted by int a design method tion equation with e law with sliding erceptor at out of atmosphere based on three-dimensional respect to the line of sight be- mode control theory, and de- signs a guidance law to make the line of sight angular rates in elevation and azimuth engagement planes tend towards zero respectively. The paper integrates the super-twisting sliding mode disturbance observers （SMDO） into the guidance law to compensate uncertainties such as target maneuvers, thus reducing the required switching gains in the guidance law significantly. The simulation results indicate that the proposed sliding mode guidance law is high in guidance accuracy and is good in robustness to maneuvering target.

关 键 词：大气层外拦截器 末制导 超扭曲滑模算法 干扰观测器 

分 类 号：V448.12[航空宇航科学与技术—飞行器设计]