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Transonic wind tunnel test supporting device, installation method and application thereof

A technology of wind tunnel test and support device, applied in the field of wind tunnel test, can solve the problems affecting the accuracy of test data, potential safety hazards, and distortion of test results, and achieve the effect of ensuring data reliability, improving accuracy, and reducing support interference.

Active Publication Date: 2016-04-27
AERODYNAMICS NAT KEY LAB
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  • Abstract
  • Description
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AI Technical Summary

Problems solved by technology

[0006] The purpose of the present invention is to provide a transonic wind tunnel test method for the problems of partially distorted test results, certain potential safety hazards, and affecting the accuracy of test data when a large aircraft uses the existing concave bending support mechanism for wind tunnel tests. Hole test support device, its installation method and application

Method used

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  • Transonic wind tunnel test supporting device, installation method and application thereof
  • Transonic wind tunnel test supporting device, installation method and application thereof

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Embodiment 1

[0034] The schematic diagram of the concave bending support adopted by the existing large aircraft is as follows: figure 1shown. In this structure, the balance element is used to measure the force and moment received by the aircraft model; the concave support front section, the concave support middle section, and the concave support rear section form a concave support mechanism to support the aircraft model and the balance element; among them, the lower wall plate of the test section Corresponding slots are not provided. The principle is as follows: the front part of the concave support enters from the abdomen of the aircraft model and is connected with the balance element to support the aircraft model; the rear part of the concave support is connected to the middle of the scimitar in the wind tunnel, so that the aircraft model and the balance components are fixed in the wind tunnel test section . This support method has technical deficiencies such as large support interfere...

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Abstract

The invention discloses a transonic wind tunnel test supporting device, an installation method and application thereof, and aims to solve the problems that the test result is partially distorted, certain potential risk is present and the accuracy of test data is influenced when an aircraft carries out wind tunnel test by adopting an existing concave bent supporting mechanism. In the device, the existing concave bent supporting structure is improved, so that the test result is more accurate; meanwhile, the bearing mode is changed into tension-compression bearing, so that the longitudinal bearing area, rigidity and strength are improved, and model vibration in test is reduced. Under the coordination of a linear supporting rod and a wind tunnel curved knife, the device can realize continuous variable attack angle test, the attack angle variation range is enlarged, and the test efficiency is greatly improved. The device is reasonable in design and simple in structure, can effectively improve the accuracy of data and the efficiency of test and reduce vibration in test, and has a good application prospect.

Description

technical field [0001] The invention relates to the field of wind tunnel tests, in particular to a support device for transonic wind tunnel tests, its installation method and application. Background technique [0002] Wind tunnel test refers to an aerodynamic test method that places an aircraft or other object model in a wind tunnel to study the gas flow and its interaction with the model to understand the aerodynamic characteristics of the actual aircraft or other objects. At present, wind tunnel test is the main means to obtain the aerodynamic characteristics of large aircraft. During the wind tunnel test, the aircraft model is fixed in the test section through the support device, and the model shape at the connection of the support device will be damaged to varying degrees. Since the rear fuselage of a large aircraft is upturned and contracted in the shape of a stern, serious damage to its shape will affect the measurement of its cruise resistance. Therefore, it is nece...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/04G01M9/08
CPCG01M9/04G01M9/08
Inventor 陈德华唐良锐许新刘大伟姜明杰刘光远彭鑫李强史晓军
Owner AERODYNAMICS NAT KEY LAB
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