变结构制导规律及其实现  

Guidance Law of the Variable Structure and Its Realization

作　　者：尹肖云[1] 邹强[1] 张笑颜[1] 

机构地区：[1]海军航空工程学院飞行器工程系,山东烟台264001

出　　处：《海军航空工程学院学报》2013年第1期6-10,共5页Journal of Naval Aeronautical and Astronautical University

摘　　要：由于变结构控制的滑动模态具有完全的自适应性,不必全面研究系统的各种摄动及外干扰,只需根据高速度大机动目标的特点,对其实现自适应,将各种干扰及偏差的影响归入有关增益系数上加以考虑。应用变结构滑膜控制理论,推导了出一种适用于拦截高速大机动目标的空间制导规律,该制导规律能将系统引向滑动面并保持在其上运动。算例仿真证明,变结构项保证了对目标机动的鲁棒性,简单易行利于工程实现。Due to self-adaptability of the sliding model of the variable structure control, there is needless to total- ly study the system various perturbation and external interference, but only to realize the self-adaptability accord- ing to the characteristics of the high-velocity, high-maneuverable target. The effects of the various interference and deviation are considered in the design of the relative gain factor. Variable structure adaptive control theo- rem was used to obtain a three-dimensional guidance law which was suitable for the missile to intercept the target of high velocity and maneuver. This guidance law would be led the system onto sliding plane and would be maintained it onto sliding plane. Simulation experiments indicated that variable structure item guaranteed the robustness to target maneuverability.

关 键 词：变结构控制 滑动模态 制导律 大机动目标 

分 类 号：V448[航空宇航科学与技术—飞行器设计]