气动弹性机翼的反演滑模控制  

Backstepping Sliding Mode Control for Aerofoil System

作　　者：侯小燕[1] 薛文涛[1] 李泰[1] 

机构地区：[1]江苏科技大学电子信息学院,江苏镇江212003

出　　处：《控制工程》2016年第1期69-74,共6页Control Engineering of China

基　　金：国家自然科学基金项目(51307074);江苏省博士后基金(1301005B)

摘　　要：针对机翼系统的颤振问题,采用一种积分和反演相结合的准滑模控制方法对机翼的浮沉和俯仰自由度进行控制。首先对带前后副翼的机翼气动弹性系统进行建模,基于建立的模型设计了积分和反演相结合的准滑模控制器,并利用Lyapunov稳定性理论对机翼控制系统的稳定性进行分析。最后,基于Matlab对该机翼气动弹性反演准滑模控制系统进行仿真,并与传统滑模控制的系统进行了分析和比较。仿真结果表明,所设计的反演准滑模控制器能在保证系统稳定运行的同时实现期望状态的快速稳定跟踪,同时能削弱滑模控制的抖振,取得了良好的控制效果。For the flutter question of wing systems, a control method ofbackstepping sliding mode combined with integral is proposed to control the plunge displacement and pitch angle of aerofoil. Firstly, the wing aeroelastic system with leading edge and trailing edge is modeled, the quasi sliding mode controller is designed with the combination of integral and backstepping based on the established model, the stability of the aerofoil control system is analyzed by using the Lyapunov stability theory. Finally, the control system of aerofoil aeroelasticity with backstepping quasi sliding mode is simulinked in Matlab. The simulation results show that the design of the backstepping sliding mode controller can guarantee the stable running of the system and realize the rapid and steady tracking of the desired states, also the chattering characteristic of SMC is weakened and good control effect is achieved.

关 键 词：机翼 反演 准滑模变结构控制 颤振抑制 

分 类 号：V215.3[航空宇航科学与技术—航空宇航推进理论与工程]