变结构自适应制导规律研究  

A Guidance Law of Variable Structure Adaptive for Missile Following Its Optimal Nominal Trajectory

作　　者：汤善同[1] 李忠应[2] 

机构地区：[1]北京电子系统工程研究所,北京100854 [2]北京航空航天大学,北京100083

出　　处：《系统工程与电子技术》2002年第7期68-73,76,共7页Systems Engineering and Electronics

基　　金："九五"国防预研基金资助课题 (A2 4 4)

摘　　要：由于变结构控制的滑动模态具有完全的自适应 ,不必全面研究系统的各种摄动及外干扰 ,而只需要根据高速度大机动目标的特点 :一个是机动 ,一个是高速 (包括速度变化 ) ,对两者实现自适应 ,把各种干扰及偏差的影响归入有关增益系数上加以考虑 ,在选择增益系数上进行了深入的研究。应用变结构自适应控制理论 ,推导出一种适用于导弹拦截高速度大机动运动目标的空间制导规律 ,该制导规律能将系统引向滑动面 ,并保持在滑动面上运动。因此将它应用于导弹跟踪标准优化弹道 ,经导弹拦截目标弹道数字仿真 ,取得了良好的结果。Due to self-adaptability of the slip model of the variable structure control there is needless to totally study the system various perturbation and external interference, but only to realize the self-adaptability for the following two factors according to the characteristics of the high-velocity, high-maneuverable target: maneuverability and high-velocity (including the change of the velocity). The effects of the various interference and deviation are considered in the design of the relative gain factor. So this paper are carried out deep study on the selection of the agin factors. Variable structure adaptive control theorem is used to obtain a three-dimensional guidance law which is suitable for the missile to intercept the target of high velocity and maneuver. This guidance law will be led the system onto slip plane and will be maintained it onto slip plane. Therefore, the guidance law is applied to the missile following its optimal nominal trajectory. The simulation results obtained are well through digital computer simulation of the missile intercepting target trajectory.

关 键 词：自适应制导 变结构自适应 制导规律 跟踪 标准优化弹道 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]