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

A technology for aero-elastic correction and wind tunnel testing, applied in the field of aviation wind tunnel testing, can solve the problems of lack of multiple iterative couplings, deviation of model deformation results, etc.

Active Publication Date: 2021-02-26
BEIJING AERONAUTIC SCI & TECH RES INST OF COMAC +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

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

Method used

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

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Embodiment 1

[0031] figure 1 It is a flow chart of the wind tunnel test data static air bomb correction method provided by Embodiment 1 of the present invention. This embodiment can be applied to the wind tunnel test of civil passenger aircraft. The swept wing of the test model generates static air under the action of aerodynamic force. In the case of elastic deformation, the method specifically includes the following steps:

[0032] Step 110 , based on the three-dimensional structured fluid grid of the wing test model, perform fluid dynamics numerical simulation to obtain aerodynamic load data on the surface of the wing test model.

[0033] The output file of the fluid dynamics numerical simulation software contains aerodynamic load data and three-dimensional structured fluid grid information, and the three-dimensional structured fluid grid includes information such as x, y, z coordinates and i, j, k coordinates of each node of the grid. Therefore, the aerodynamic load data on the surfac...

Embodiment 2

[0047] figure 2 It is a flow chart of the static aeroelastic correction method for wind tunnel test data provided by Embodiment 2 of the present invention. This embodiment is embodied on the basis of the above-mentioned embodiments. Such as figure 2 As shown, Embodiment 2 of the present invention provides a static aeroelastic correction method for wind tunnel test data, including the following steps:

[0048] Step 210, based on the digital model of the wing test model, generate a three-dimensional structured fluid grid and a geometrically nonlinear structural finite element model of the wing test model.

[0049] The digital model of the wing test model is the digital model used in the processing of the wing, which fully reflects the internal structural characteristics of the wing test model. According to the digital model of the wing test model, it can be used to construct the three-dimensional structure of the wing test model A geometrically nonlinear structural finite el...

Embodiment 3

[0097] Figure 4 A structural schematic diagram of a static aeroelastic correction device for wind tunnel test data provided by Embodiment 3 of the present invention, which can be used for static aeroelastic deformation of the swept wing of the test model in the wind tunnel test under the action of aerodynamic force, Furthermore, it is necessary to test the static aeroelastic correction of the wind tunnel test data, so as to reduce the deviation of the static aeroelastic correction of the wind tunnel test data. The device can be realized by software and / or hardware.

[0098] Such as Figure 4 As shown, the device includes: a first execution module 410, a numerical analysis module 420 and a second execution module 430, wherein,

[0099] The first execution module 410 is used to perform fluid dynamics numerical simulation based on the three-dimensional structured fluid grid of the wing test model, and obtain the aerodynamic load data on the surface of the wing test model;

[...

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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...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/06
CPCG01M9/06Y02T90/00
Inventor 王介龙赖国俊杨薇薛帮猛任启龙林大楷
Owner BEIJING AERONAUTIC SCI & TECH RES INST OF COMAC
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