飞航导弹横测通道协调变结构飞行控制系统设计  

Coordinated Yaw/Roll Channel Autopilot Design for Cruise Missle Based on Variable Structure Control Theory

作　　者：王琦[1] 崔立君[1] 

机构地区：[1]西北工业大学,陕西西安710072

出　　处：《计算机测量与控制》2007年第12期1756-1757,1765,共3页Computer Measurement &Control

摘　　要：某型面对称布局飞航导弹采取BTT控制方式,可以使战术导弹在各方面获得良好的性能。但由于其横侧向通道之间具有强烈的耦合,传统的STT导弹采用的控制系统及其综合方法已经不再适用于BTT导弹,一个具有运动学耦合,惯性耦合,以及控制作用耦合的多自由度的系统综合问题被提出;应用变结构控制理论,结合经典的双回路飞行控制系统方案分别设计了偏航和滚动通道自动驾驶仪;仿真结果表明用该方法设计的飞行控制系统能够有效克服横侧向通道间的耦合以及参数摄动影响。Some cruise missile with symmetrical design adopts the BTT control mode, may lead the tactical missile to obtain the good performance in various aspects. But yaw and roll channels of some cruise missile are severe coupled, the traditional control system and synthesis method for STT missile was already unsuitable for the BTT missile, the system synthesis problem about kinematics coupling, inertia coupling and control coupling of multi-freedom was asked. Classical two-loop structure autopilots based on variable structure control theory are designed for the missile to eliminate the effects of coupling between the two channels and parameters perturbation. The results of simulation indicate that autopilots work perfectly.

关 键 词：飞航导弹 变结构 飞行控制系统 

分 类 号：TP273[自动化与计算机技术—检测技术与自动化装置]