垂直发射导弹Terminal滑模姿态控制系统设计  

The Design of Terminal Sliding Control System for Vertical Launching Missile

作　　者：李大鹏[1] 胡云安[1] 何金新[1] 

机构地区：[1]海军航空工程学院,山东烟台264001

出　　处：《弹箭与制导学报》2009年第6期9-11,16,共4页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：国家自然科学基金(60674090)资助

摘　　要：为了降低垂直发射导弹转弯段姿态方程的复杂程度,运用精确反馈线性化方法,将姿态通道线性化解耦成三个单输入单输出系统。而且垂直发射导弹的转弯需要快速完成,因而对每个通道分别设计全局快速Terminal变结构控制器,该控制器能够保证系统在要求的时间内收敛至平衡点,即能够实现快速转弯。通过数字仿真验证了方法的有效性。In order to decrease design complexity of attitude control system of vertical launching missile, the attitude channel was decoupled into three SISO linear systems by accurate feedback linearization. Then, the fast terminal sliding mode controller was designed for each attitude channel to ensure the turning speed. This controller can make the missile complete turning in anticipant time, and numerical simulations prove that it is effective.

关 键 词：垂直发射导弹 快速转弯姿态控制 反馈线性化 滑模变结构控制 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]