A Model Supporting Device Applied in Wind Tunnel Test

A technology of support device and wind tunnel test, which is applied in measurement device, aerodynamic test, testing of machine/structural components, etc. It can solve the problems of large aerodynamic interference of the model, improve the test accuracy and make the strength design reasonable. , easy to use effect

Active Publication Date: 2021-08-24
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 separately and installed separately. The size and shape of the support greatly interfere with the aerodynamic force of the model.

Method used

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  • A Model Supporting Device Applied in Wind Tunnel Test
  • A Model Supporting Device Applied in Wind Tunnel Test
  • A Model Supporting Device Applied in 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 + fake tail support + repair nozzle" test device, and conduct hypersonic wind tunnel tests;

[0051] b. to dismantle figure 1 The false tail rod support 5 and the fake tail rod 6 in the model, at the same time, replace the tail of model 1 with the real nozzle, and get figure 2 The "back support + real nozzle" test device shown, and the hypersonic wind tunnel test;

[0052] c. to dismantle 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 influence of "back support interference" and "nozzle modification + tail support interference" to obtain the aerodynamic force of model 1 of the real-surface nozzle .

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Abstract

The invention discloses a model support device applied to wind tunnel tests. The device includes a model back support, a false tail rod and a middle bracket to form a triangular connection structure. The model back support and the middle bracket are integrally processed; a balance is installed inside the model, the model back support is supported on the back of the model, and the fake tail rod extends into the model. The tail of the model is isolated from the model and does not touch each other. The dummy tail rod is fixed on the dummy tail rod support. Both the model back support and the dummy tail rod support are fixedly connected to the upper part of the middle bracket, and the lower end of the middle bracket extends downward and is fixed. On the bottom support platform, the bottom support platform is fixed on the lower wall plate of the wind tunnel. The device has compact structure, miniaturization, reasonable layout and convenient use, which effectively reduces the interference of the size and shape of the support on the aerodynamic force of the model, and meets the requirements of the 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] Conventional wind tunnel tests are 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 on the aerodynamic force of the model. [0003] For some models with nozzles at the tail, the tail support test will destroy the profile of the nozzle at the tail, and when the back support (or belly support) is used, the influence of the back support (or belly support) on the aerodynamic force of the model is relatively large. Therefore, in order to obtain the aerodynamic fo...

Claims

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Application Information

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Patent Type & Authority Patents(China)
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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