面向摆动喷管的导弹非线性姿态控制  

Nonlinear attitude control for missile with swing nozzle

作　　者：周成宝[1] 周荻[1] 

机构地区：[1]哈尔滨工业大学航天学院,黑龙江哈尔滨150001

出　　处：《系统工程与电子技术》2016年第5期1107-1113,共7页Systems Engineering and Electronics

基　　金：国家自然科学基金(61174203);国家自然科学基金委创新研究群体科学基金(61021002)资助课题

摘　　要：针对采用摆动喷管作为执行机构的导弹姿态控制系统,研究了导弹初始垂直发射过程中三通道姿态耦合控制问题。详细推导了采用摆动喷管的导弹的姿态动力学模型,并与欧拉角描述的导弹姿态运动学模型结合,基于动态面控制技术,在考虑系统中气动参数不确定性情况下设计了一个新的动态面自适应滑模控制器,并应用Lyapunov方法给出了严格的稳定性证明。为避免控制设计中的抖振问题,控制器中的符号函数用饱和函数来代替。数值仿真分析验证了所提出的控制方法的有效性。With the swing nozzle as the actuator of the missile attitude control system, the three-channel at- titude coupling control problem of the initial vertical launch of missile is investigated A detailed attitude dynamics model of the missile with swing nozzle is established and then is combined with the attitude kinematics model de- noted by Euler angles. Based on the dynamic surface control technology, a new adaptive sliding mode controller is designed under the condition of aerodynamic parameter uncertainty, and a rigorous stability proof is given u- sing the method of Lyapunov. In order to avoid the chattering, the sign functions in the control law are replaced with saturation functions. Numerical simulation results verify the effectiveness of the proposed controller.

关 键 词：姿态控制 动态面控制 滑模控制 自适应控制 摆动喷管 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]