Analysis Of Flutter Characteristics And Active Control For Flexible Wings

In this thesis,the main content is to establish the finite element model of the flexible wing.The aeroelastic analysis of the wing is carried out by the finite element software.According to the principle of equivalence between mass and stiffness,the force and load transfer characteristics of each part of the wing are simplified.Without changing the main bearing mode and dynamic characteristics,a finite element model is selected to establish the finite element model of the wing.A kinetic model of the flexible wing is established by Patran and Nastran software is used for modal analysis.The wing aerodynamic model is created in Flightloads software and P-K method is used to calculate the flutter of different height and Mach number.It can obtain the flutter speed and flutter frequency under different flying heights and different flying Mach number,which can provide reference for the design of flexible wing.The flutter analysis is carried out by establishing the dynamics model of the wing without the control surface.Compared with the flutter calculation results of the wing model with control surface,it can obtain the influence of control surface on the flutter analysis results of the flexible wing with large aspect ratio.Based on the LQG control law,the active control of the flexible wing is studied,and the simulation analysis is carried out through the matlab/Simulink platform.