Study On Reduced Order Model Of Aeroelasticity

The aeroelastic problem is an important one that must be solved in the process of aircraft designing.With the development of computing technology,numerical simulation methods have become and can be mutually verified with wind tunnel tests.In the aeroelastic calculation method,various unsteady aerodynamic models based on the linearization theory have been developed in the early days and been widely used.With the dramatic increasing of computer performance,finite element and computational fluid dynamics(CFD)methods have been used in many projects.Nowadays,the application has become the main method of aeroelastic calculation.Although the aeroelastic simulation calculation based on unsteady CFD technology has a great advantage in simulating non-linear problems,its disadvantages such as large amount of calculating and long time consumpting make the technology limited in aeroelastic analyzing,controlling and optimization design.The purpose of this project is to investigate the reduced-order model calculation methods to improve the unsteady CFD aerodynamics and nonlinear finite elements,aim to improve the calculation efficiency of aerodynamic and structural responses under the condition of ensuring the calculation accuracy.The main work of this article is as follows:1.Aiming at the accuracy and high efficiency of CFD/CSD coupling calculation for aeroelastic characteristics,based on the reduced-order model of SVM,the unconstrained aerodynamics SVM decision tree reduction model based on CFD technology was proposed and built.The CFD solver is used for aeroelastic analyzing at standard airfoil transonic speeds.2.Studied the principle of random forest algorithm,first introduced the random forest algorithm to the research field of unsteady aerodynamics modeling,constructed an unsteady aerodynamic reduction model based on the random forest algorithm,and applied the obtained model to the transonic speed.The standard aerodynamic elasticity of the airfoil is predicted.3.The reduced-order model of the finite element method of geometric nonlinear shell elements is studied.Based on the principle of the Proper Orthogonal Decomposition(POD)principle,an aeroelastic reduced-order model based on POD is established and applied to the simple-supported wall plate under hypersonic conditions.The study of aeroelastic calculations.