Wind tunnel test data static aeroelastic correction method, device and equipment, and medium

Abstract

The invention discloses a wind tunnel test data static aeroelastic correction method, device and equipment, and a medium. The wind tunnel test data static aeroelastic correction method comprises the following steps of: based on a three-dimensional structured fluid grid of a wing test model, carrying out hydromechanics numerical simulation to obtain aerodynamic load data of the surface of the wingtest model; performing structural finite element numerical analysis on the geometric nonlinear structure finite element model loaded with the aerodynamic load data to obtain a difference value betweenthe current wing tip displacement and the previous wing tip displacement; and if a difference value between the current wing tip displacement and the previous wing tip displacement is smaller than apreset difference value, acquiring a corrected aerodynamic force of the wing test model based on the obtained aerodynamic force difference of the wing test model. According to the three-dimensional structured fluid grid of the wing test model and the geometric nonlinear finite element model, the obtained aerodynamic force difference of the wing test model is solved through multiple iterations, andthen the corrected aerodynamic force of the wing test model is obtained.

Description

technical field [0001] Embodiments of the present invention relate to aviation wind tunnel test technology, in particular to a method, device, equipment and medium for static aeroelastic correction of wind tunnel test data. Background technique [0002] In order to fly at high subsonic speeds, modern civil airliners use swept wings. The characteristic of the swept wing is that under the action of aerodynamic force, it will produce combined deformation of bending and torsion. This deformation causes an aerodynamic change in the wing, which in turn further changes the amount of wing deformation until the wing structure reaches a state of static equilibrium. This phenomenon of coupled structure and aerodynamic force is called the static aeroelastic effect. In the wind tunnel test of civil passenger aircraft, the swept wing of the test model will also produce static aeroelastic deformation under the action of aerodynamic force. The aerodynamic variation of the model wing caus...

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Problems solved by technology

[0004] In the prior art, in the process of correcting the test deviation, the hydrodynamic analysis and the finite element analysis only carried out aerodynamic load data transmission once, lacking multiple iterative couplings, resulting in large deviations in the obtained model deformation results

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