The Design Of Typical Wing Flutter Test Model And Wind Tunnel Test

Aeroelastic experiment is a method to verify the theoretical model,study the phenomenon beyond the theoretical scope,and verify the safety and integrity of the new aeroelastic system.For aircraft,aeroelastic wind tunnel test,with its advantages of high reliability and low cost,has become the main method and means of aircraft flutter design and research.As a typical airfoil model,two-dimensional airfoil is widely used to verify the aeroelastic theory and study the flutter mechanism.In this paper,a flutter test model with 2-DOF elastic support is designed for the two-dimensional wing model.The GVT and wind tunnel test are carried out for the flutter test model,and its applicability in aeroelastic research is verified through the test.The main contents are as follows:Based on the typical theoretical model of the wing segment of the buoyancy pitching degree of freedom elastic system,the motion equation is derived.The aerodynamic force of the model is the unsteady aerodynamic force of Theodore Dawson.Then,the V-G method is used to solve the flutter velocity of the model,and the results are used as the reference for the subsequent design.According to the mathematical model of the two-dimensional wing,a 2-DOF elastic support flutter test device is designed,and the simulation methods of the buoyancy support stiffness and the pitch support stiffness of the elastic device are introduced respectively.The device can adjust the stiffness of the floating support and the pitch support separately,which can meet the requirement of flutter test under different support stiffness.By using the finite element simulation software,the finite element model of the designed flutter test model is established.Through the structural dynamics calculation and flutter calculation,the flutter characteristics of the model are analyzed,and the feasibility of the model design is verified.The results of finite element method and V-G method are compared,and the accuracy of the results is further illustrated by the good consistency between them.According to the results of simulation calculation,the ground vibration test of the model is carried out.Referring to the results of vibration test,the wind tunnel test of the binary model is carried out.The installation of wind tunnel test model,data acquisition and subsequent data processing methods are introduced.Finally,a 3-DOF model is tested to verify the feasibility of the test device.In this paper,a flutter test model of a two degree of freedom elastic support is successfully designed.A series of test results show that the device can achieve the independent control of the pitch stiffness,and verify the applicability and feasibility of the test model in aeroelasticity.The device has important research significance for the exploration of aircraft flutter characteristics.The typical flutter test model designed in this paper successfully reveals the mechanism of coupled bending and torsion flutter,and the complex mechanical problem of coupled bending and torsion flutter can be reproduced by specific tests.