基于积分滑模面的飞机姿态模糊滑模控制  

Fuzzy Sliding Mode Control for Airplane Attitude Based on Integral Sliding Mode Surface

作　　者：胡盛斌[1,2] 陆敏恂[1] 陆文华[2] 

机构地区：[1]同济大学机械工程学院,上海201804 [2]上海工程技术大学航空运输学院,上海201620

出　　处：《系统仿真学报》2013年第3期530-534,共5页Journal of System Simulation

基　　金：上海市教委重点学科(第五期)建设项目(J51403);上海市科委科研计划项目(09170502400)

摘　　要：飞机姿态控制是一个非线性、强耦合、多输入多输出的复杂系统。为了提高一般滑模控制的控制精度,通过反馈线性化方法对飞机姿态非线性动力学模型进行线性化处理,在此基础上设计了一种基于积分滑模面的滑模控制方法。为了减弱积分滑模控制的抖振,利用模糊推理根据滑模面的变化情况自适应调整滑模切换控制部分,从而达到减弱抖振的目的。采用Lyapunov原理证明了系统的稳定性。仿真实验表明了所提方法的有效性。The airplane attitude control is a nonlinear coupling multitude input multitude output system. To improve the control accuracy of sliding mode control, the nonlinear dynamic model for airplane attitude control was linearized by the feedback linearization technique, and a sliding mode control law for airplane attitude based on integral sliding mode surface was designed. To reduce the chattering of integral sliding mode control, a fuzzy control was designed to adaptively tune the switch part of integral sliding mode control. Moreover, the system stability was proved by Lyapunov principle. Simulation results show the validity of the control scheme.

关 键 词：积分滑模控制 模糊控制 抖振 姿态控制 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]