Model supporting device applied to wind tunnel test

A technology of wind tunnel test and support device, which is used in measurement device, aerodynamic test, machine/structural component test, etc. The effect of reasonable strength of support structure

Active Publication Date: 2021-01-29
中国空气动力研究与发展中心超高速空气动力研究所
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In the traditional back support test device, the model back support and the dummy tail rod support are designed separ

Method used

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  • Model supporting device applied to wind tunnel test
  • Model supporting device applied to wind tunnel test
  • Model supporting device applied to wind tunnel test

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0049] The implementation process of this embodiment is as follows:

[0050] a. According to figure 1 Install the "back support + false tail strut + modified nozzle" test device, and conduct a hypersonic wind tunnel test;

[0051] b. Demolition figure 1 The false tail strut support 5 and the false tail strut 6 in the model 1 are replaced with the real nozzle at the same time, and the obtained figure 2 The "back support + real nozzle" test device shown, and the hypersonic wind tunnel test was carried out;

[0052] c. Demolition figure 2 Replace the "tail support + repair nozzle" test device, and conduct a hypersonic wind tunnel test;

[0053] d. Perform data processing on the test results obtained in steps a, b, and c, and deduct the influences of "back support interference" and "nozzle modification + tail support interference" to obtain the aerodynamic force of model 1 of the real profile nozzle .

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PUM

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Abstract

The invention discloses a model supporting device applied to a wind tunnel test. The device comprises a model back support, a false tail supporting rod and a middle support which form a triangular connecting structure, wherein the model back support and the middle support are integrally machined; a balance is installed in the model, the model back support is supported on the back of the model, thefalse tail support rod stretches into the tail of the model and is isolated from the model without making contact with the model, the false tail support rod is fixed to the false tail support rod support, and the model back support and the false tail support rod support are fixedly connected to the upper portion of the middle support; the lower end of the middle support extends downwards and is fixed to a bottom supporting platform, and the bottom supporting platform is fixed to a wind tunnel lower wall plate. The device is compact in structure, miniaturized, reasonable in layout and convenient to use, effectively reduces the interference of the size and shape of the support on the aerodynamic force of the model, and meets the requirements of a wind tunnel model support system.

Description

technical field [0001] The invention belongs to the technical field of hypersonic wind tunnels, and in particular relates to a model support device applied to wind tunnel tests. Background technique [0002] The conventional wind tunnel test is divided into tail support, back support and abdominal support according to the position of the support of the model. The size and shape of the support will interfere with the aerodynamic force of the model to a certain extent. Therefore, before carrying out the wind tunnel test, the support of the model must be optimized to minimize the interference of the support to the aerodynamic force of the model. [0003] For some models with a nozzle at the tail, the tail support test will destroy the profile of the tail nozzle, and when back support (or ventral support) is used, the influence of back support (or ventral support) on the model's aerodynamic force is relatively small. Therefore, in order to obtain the aerodynamic force of the mo...

Claims

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Application Information

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IPC IPC(8): G01M9/04G01M9/02G01M9/08
CPCG01M9/02G01M9/04G01M9/08
Inventor 何超许晓斌舒海峰向立光吴友生唐友霖
Owner 中国空气动力研究与发展中心超高速空气动力研究所
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