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Wind tunnel test device and test method based on device

A technology of wind tunnel test and test method, which can be used in measurement devices, aerodynamic tests, testing of machine/structural components, etc. The problem is to ensure the safety of the test and eliminate the impact load.

Active Publication Date: 2020-04-10
INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] However, these measures have certain shortcomings or difficulty in implementation: increasing the strength and rigidity increases the difficulty of mechanical design; Wingspan model; increasing the design margin of the balance will reduce the quality of the force measurement data of the balance; reducing the total pressure when the shock wave passes has high requirements on the control system, which cannot be achieved for a wind tunnel without independent air intake and ejection

Method used

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  • Wind tunnel test device and test method based on device
  • Wind tunnel test device and test method based on device
  • Wind tunnel test device and test method based on device

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Embodiment 1

[0032] refer to figure 1 and figure 2 As shown in the figure, a wind tunnel test device is disclosed. The wind tunnel test device at least includes a model 1, a wind tunnel test section 2 and a model position adjustment unit. Wherein, the wind tunnel test section 2 is located directly above the position adjustment part of the model 1, and the position adjustment part of the model 1 is connected to the model 1, and can send the model 1 into or out of the wind tunnel test section 2.

[0033] Preferably, the model 1 is provided with a balance mechanism. The model 1 is the object of the wind tunnel test, and is a scaled-down model of a real aircraft. Wherein, the balance mechanism is a sensor for measuring the force of the model 1 .

[0034] Preferably, the wind tunnel test section 2 is a square pipe structure, and the bottom of the wind tunnel test section 2 is provided with a test section hatch 9 . The wind tunnel test section 2 is the pipeline through which the high-spee...

Embodiment 2

[0046] On the basis of the disclosed wind tunnel test device in embodiment 1, the present invention also discloses a kind of test method based on wind tunnel test device, such as image 3 shown.

[0047] Described test method comprises the following steps at least:

[0048] Step S1: Start the wind tunnel, adjust the pressure in the wind tunnel, and establish a flow field in the test section 2 of the wind tunnel.

[0049] Step S2: Open the test section hatch 9 at the bottom of the wind tunnel test section 2, and the model 1 position adjustment unit raises the model 1 to a preset position in the wind tunnel test section 2 through the test section hatch 9.

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Abstract

The invention discloses a wind tunnel test device which at least comprises a model, a wind tunnel test section and a model position adjusting part, the wind tunnel test section is located over the model position adjusting part, and the model position adjusting part is connected with the model and can send the model into or take the model out of the wind tunnel test section. The function of bringing the model into or out of the wind field after the flow field is established in the wind tunnel test section is realized, so that the impact load caused by the opening and closing of the supersonic wind tunnel is eliminated, and the test safety of the large-wingspan aircraft model is ensured.

Description

technical field [0001] The invention belongs to the field of high-speed wind tunnel tests, in particular to a wind tunnel test device and a test method based on the device. Background technique [0002] Start-up and shutdown impact loads are a common problem faced by supersonic wind tunnels. The loads on the model and balance at the moment of start-up and shutdown of the wind tunnel are much greater than the aerodynamic loads after the airflow stabilizes. When starting and shutting down a supersonic wind tunnel, especially when starting and shutting down at a high Mach number, the pressure ratio between the upstream and downstream inside the wind tunnel is very high, the normal shock wave passing through the test section is strong and asymmetrical, and the model and balance are strongly stressed. Symmetrical airflow will cause violent vibration, which will easily cause damage to the model and balance, and seriously threaten the safety of the test. [0003] With the developm...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/06G01M9/08
CPCG01M9/00G01M9/062G01M9/08
Inventor 刘奇刘常青郑杰匀张利波肖楚璠荣祥森
Owner INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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