A method, device, equipment and medium for static aeroelastic correction of wind tunnel test data

An aeroelastic correction and wind tunnel test technology, which is applied in the field of aviation wind tunnel tests, can solve problems such as lack of multiple iterative couplings and deviations in model deformation results.

Active Publication Date: 2022-08-09
BEIJING AERONAUTIC SCI & TECH RES INST OF COMAC +1
View PDF0 Cites 0 Cited by
  • 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

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • A method, device, equipment and medium for static aeroelastic correction of wind tunnel test data
  • A method, device, equipment and medium for static aeroelastic correction of wind tunnel test data
  • A method, device, equipment and medium for static aeroelastic correction of wind tunnel test data

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0031] figure 1 This is a flow chart of a method for static aeroelastic correction of wind tunnel test data provided in Embodiment 1 of the present invention. This embodiment is applicable to the wind tunnel test of a 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 , perform numerical simulation of fluid mechanics based on the three-dimensional structured fluid grid of the wing test model to obtain aerodynamic load data on the surface of the wing test model.

[0033] The output file of the fluid mechanics numerical simulation software contains the aerodynamic load data and the information of the 3D structured fluid grid. The 3D structured fluid grid includes the x, y, z coordinates and i, j, k coordinates of each node of the grid and other information. Therefore, the aerodynamic load data on the surf...

Embodiment 2

[0047] figure 2 This is a flowchart of a method for static aeroelastic correction of wind tunnel test data provided in Embodiment 2 of the present invention, and this embodiment is embodied on the basis of the above-mentioned embodiment. like figure 2 As shown, the second embodiment 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 geometric nonlinear structure finite element model of the wing test model.

[0049] The digital model of the wing test model is the digital model used when processing 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. Geometrically nonlinear structural finite e...

Embodiment 3

[0097] Figure 4 This is a schematic structural diagram of a static aeroelastic correction device for wind tunnel test data provided in the third embodiment of the present invention. The device can be used for the 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 situation of 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 apparatus may be implemented by software and / or hardware.

[0098] like Figure 4 As shown, the apparatus 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 configured to perform numerical simulation of fluid mechanics based on the three-dimensional structured fluid grid of the wing test model to obtain aerodynamic l...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to view more

PUM

No PUM Login to view more

Abstract

The invention discloses a method, device, equipment and medium for static aero-elastic correction of wind tunnel test data. The method includes: performing numerical simulation of fluid mechanics based on a three-dimensional structured fluid grid of a wing test model to obtain aerodynamic load data on the surface of the wing test model; Structural finite element numerical analysis, to obtain the difference between the current wing displacement and the previous wing displacement; if the difference between the current wing displacement and the previous wing displacement is less than the preset difference, then based on the obtained The aerodynamic force difference of the wing test model is obtained, and the modified aerodynamic force of the wing test model is obtained. The above method uses the three-dimensional structured fluid grid of the wing test model and the geometric nonlinear finite element model to iteratively solve the aerodynamic difference of the wing test model obtained by multiple iterations, and then obtains the modified aerodynamic force of the wing test model.

Description

technical field [0001] Embodiments of the present invention relate to aeronautical wind tunnel test technology, and 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 a combination of bending and torsion deformation. This deformation causes changes in the aerodynamics of the wing, which in turn further changes the amount of deformation of the wing until the wing structure reaches a state of static equilibrium. This phenomenon of coupling between structure and aerodynamic force is called the static aeroelastic effect. In the wind tunnel test of the civil airliner, the swept wing of the test model will also produce static aeroelastic deformation under the action of aerodynamic force. The aerodynamic va...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to view more

Application Information

Patent Timeline
no application Login to view more
Patent Type & Authority Patents(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
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Try Eureka
PatSnap group products

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic.

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap