Aeroelasticity And Flutter Suppression Of A Two-dimensional Wing With Dual Control Surfaces

Aeroelastic phenomenon of aircraft system is an important problem in aerospace field.Because the future development of aircraft tends to be flexible structure,how to solve aeroelastic flutter in aircraft design has attracted great attention of aeroelastic researchers at home and abroad.This paper presents pneumatic elastic chatter analysis of a two-dimensional wing with dual control face and internal fuel shaking based on the theory of structural dynamics of aerocrafts and modern control theory.A combination of theoretical calculation and numerical simulation are applied to carry out the research on Modeling of a two-dimensional wing pneumatic elastic system,chatter suppression controller design and chatter active suppression of pneumatic elastic system.The main work of the paper is as follows:(1)The aerodynamic elastic dynamics model of a two-dimensional wing with dual control plane and internal fuel shaking was established based on Lagrangian equations and Grossman quasi constant aerodynamic theory,and the chatter critical conditions of wing system in different degrees of freedom coupling case were calculated according to the Liyaponov linear system theory.The stability of the wing system is lowest for the case considering simultaneously the fuel shaking and dual control plane vibration.(2)The Runge Kutta method is used to simulate the open-loop wing system without controller.The time histories of attenuation,self excitation and divergence of each degree of freedom are studied and analyzed.The time for the system to enter the steady state is the longest when the fuel oil shaking and dual control plane vibration are simultaneously present in the wing system.(3)The aerodynamic elastic dynamic model of a two-dimensional wing is used as the control object,and a controller to suppress wing system chatter is designed by active disturbance rejection control technology,then the wing closed loop system with ADRC controller is numerically simulated by the Runge Kutta method,and then the designed self-interference controller effectively suppresses wing system chatter.(4)When the incoming flow velocity increases,the Runge Kutta method is used to simulate the closure failure of the wing system with different degrees of freedom coupling.The controller of the pneumatic elastic coupled system fails when the coming velocity reaches the maximum velocity that the closed-loop system can withstand.The active disturbance rejection controller improves the flight packet wire of the pneumatic elasticity model built in this paper by about 56.01%.