电子设计工程
電子設計工程
전자설계공정
Electronic Design Engineering
2015年
21期
82-85
,共4页
二元机翼%滑模控制%反演控制%颤振抑制
二元機翼%滑模控製%反縯控製%顫振抑製
이원궤익%활모공제%반연공제%전진억제
two-dimensional aerofoil%sliding mode control%backsteppingmethod%flutter suppression
针对带后缘面的二元机翼的颤振问题，设计一种反演滑模控制方法对机翼的浮沉和俯仰运动进行控制。首先，基于准定常气动理论建立二元机翼的气动弹性系统模型，然后设计一种反演滑模控制器对机翼颤振进行抑制，并利用Lyapunov理论证明了机翼控制系统的稳定性。仿真结果表明，所提出反演滑模控制方法能提高非线性气动弹性机翼系统的稳定性，并能有效消除颤振。
針對帶後緣麵的二元機翼的顫振問題，設計一種反縯滑模控製方法對機翼的浮沉和俯仰運動進行控製。首先，基于準定常氣動理論建立二元機翼的氣動彈性繫統模型，然後設計一種反縯滑模控製器對機翼顫振進行抑製，併利用Lyapunov理論證明瞭機翼控製繫統的穩定性。倣真結果錶明，所提齣反縯滑模控製方法能提高非線性氣動彈性機翼繫統的穩定性，併能有效消除顫振。
침대대후연면적이원궤익적전진문제，설계일충반연활모공제방법대궤익적부침화부앙운동진행공제。수선，기우준정상기동이론건립이원궤익적기동탄성계통모형，연후설계일충반연활모공제기대궤익전진진행억제，병이용Lyapunov이론증명료궤익공제계통적은정성。방진결과표명，소제출반연활모공제방법능제고비선성기동탄성궤익계통적은정성，병능유효소제전진。
In view of the flutter problems of two-dimensional aerofoil with a trailing-edge control surface, abackstepping sliding model control approach is proposed to control both the plunge displacement and pitch angle of aerofoil. Firstly, the basicmotion equations are established by using quasi-teady aerodynamic theory.Moreover, the controller iscombinedsliding model control with backstepping is designed to suppress the flutter. The stability of aerofoil control system has been proved by using Lyapunov theory. The simulation results show that the backstepping sliding mode controlmethod can improve the stability of thenonlinear quasi-steady aerodynamicsystem and eliminate the flutter effectively.
