基于滑模变结构的导弹高度控制系统设计  

The Design of Sliding Mode Controller for Missile Altitude Loop Based on Lyapunov Function

作　　者：顾文锦[1] 盖玉华[1] 李聪颖[1] 

机构地区：[1]海军航空工程学院,烟台264001

出　　处：《航天控制》2009年第1期57-60,共4页Aerospace Control

摘　　要：对一类采用过载控制的飞行器的高度控制系统,采用Lyapunov函数方法,进行了基于滑模理论的变结构控制器设计。该方案使得不同初始状态与控制目的的高度控制系统,均能在输入受限的条件下,收敛到系统原点领域。高度控制系统是一类非线性系统,本文通过构造Lyapunov函数方法,确保了系统的稳定性。最后仿真结果表明了该方案的有效性。By adopting Lyapunov function theory, a sliding-mode variable structure controller is designed for the altitude loop of a kind of aircraft with overload control. The method can converge the state of the altitude control system to equilibrium point with different initial states and aims of control under the condition that the input is limited. The altitude control system is a kind of nonlinear system , the stability of which is ensured by constructing Lyapunov function. Finally, the simulation results are presented to show the excellent control effect of the proposed method.

关 键 词：高度回路 滑模 稳定 李雅普洛夫函数 非线性 

分 类 号：TP273[自动化与计算机技术—检测技术与自动化装置]