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Correction of wind tunnel force test data for high aspect ratio aircraft

A technology of force measurement test and large aspect ratio, which is used in electrical digital data processing, special data processing applications, instruments, etc., can solve the problem of not performing aerodynamic data correction, etc., to ensure the accuracy of calculation, and the calculation method is efficient and fast. , the effect of reducing costs

Active Publication Date: 2019-02-01
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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AI Technical Summary

Problems solved by technology

[0003] At present, the influence of elastic deformation of the wind tunnel test model is ignored in the domestic force measurement wind tunnel test, and the aerodynamic data correction is generally not performed
Using deformed aerodynamic data for aircraft design, there are errors from the source of the data

Method used

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  • Correction of wind tunnel force test data for high aspect ratio aircraft
  • Correction of wind tunnel force test data for high aspect ratio aircraft
  • Correction of wind tunnel force test data for high aspect ratio aircraft

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Embodiment Construction

[0016] The application will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the related application, not to limit the application. In addition, it should be noted that, for ease of description, only parts relevant to the present application are shown in the drawings.

[0017] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and embodiments.

[0018] figure 1 It is a schematic flowchart of a method for correcting wind tunnel dynamometric test data of a large-aspect-ratio aircraft provided in an embodiment of the present application. Such as figure 1 As shown, the method includes the following steps:

[0019] Step 10...

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Abstract

A method for correct wind tunnel force test data of a high aspect ratio aircraft include establishing a CFD model, a dipole model, and a structural finite element model based on a wind tunnel force test model; According to the CFD model, the whole aircraft pressure distribution under the wind tunnel test condition is obtained. Establishing an aerodynamic / structural coupling calculation model according to the dipole model and the structural finite element model; Loading the whole-machine pressure distribution onto the aerodynamic / structural coupling calculation model to obtain the whole-machineelastic deformation and aerodynamic force correction; A test data of wind tunnel force measurement is corrected accord to that aerodynamic correction quantity.

Description

technical field [0001] This application relates to the technical fields of full-aircraft load design and full-aircraft static aeroelasticity prediction, and specifically provides a method for correcting wind tunnel dynamometric test data of a large-aspect-ratio aircraft. Background technique [0002] With the development of civil aircraft with large aspect ratio, the development of advanced civil aircraft requires a large number of aerodynamic tests in high Reynolds number pressurized wind tunnels. During the wind tunnel test of this type of aircraft, due to the model material, processing technology and other reasons, the structure inevitably undergoes elastic deformation, which further affects the aerodynamic characteristics of the model. Especially for aircraft with large aspect ratio, the deformation of the model is very obvious. Therefore, in the aerodynamic test of the large-aspect-ratio aircraft pressurized wind tunnel model, it is very necessary to remove the influen...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/23G06F30/15Y02T90/00
Inventor 张家齐陈同银徐港唐超瓮哲秦叶
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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