基于变结构理论的巡航导弹复合控制  

Compound Control of Cruise Missile Based on Variable Structure Control

作　　者：史莹晶[1] 马广富[2] 马洪忠[3] 

机构地区：[1]电子科技大学自动化工程学院,成都610054 [2]哈尔滨工业大学航天学院,哈尔滨150001 [3]中国航天科工集团公司第三研究院,北京100074

出　　处：《弹道学报》2008年第4期61-64,共4页Journal of Ballistics

基　　金：教育部高校博士点基金项目(20050213010);国家自然科学基金项目(60774062)

摘　　要：针对大空域巡航导弹在飞行过程中的执行机构饱和问题,设计了变结构控制律.通过李亚普诺夫稳定性理论,证明了控制器的稳定性,利用矩阵理论为工具,证明了系统的鲁棒性.根据变结构控制律的自然分解特性,将控制器分解的常规项部分利用俯仰舵来实现,将控制器分解的符号项部分利用发动机尾喷管来实现,这使复杂的控制律在工程上变得简单.仿真表明,所设计的控制律能避免执行机构的饱和问题,使各项指标满足系统设计要求.Aiming at saturation problem of actuator during flight course of cruise missile, variable structure control law was designed. Stability of controller was proved using Lyapunov stability theory. Robustness of the system was proved by matrix theory. According to natural decomposability of variable structure controller, the routine part of natural decomposability was realized using pitching rudder; the sign part was realized by tail pipe of engine. As a result, complicated control law is easy to realize in engineering. Simulation results show that saturation problem of actuator can be avoided by designed controller, and all the indexes satisfy design requests of the system.

关 键 词：巡航导弹 变结构控制 复合控制 大空域机动 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程]