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Wind tunnel test deflector

A deflector device and wind tunnel test technology, which is applied in the cabin-level wind tunnel test field, can solve the problems that the cabin cannot be assessed separately, and achieve the effect of meeting the requirements of wind tunnel tests, small structural size, and easy implementation

Active Publication Date: 2020-05-19
BEIJING AEROSPACE TECH INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The invention provides a wind tunnel test diversion device, which can solve the technical problem in the prior art that a certain section of the cabin cannot be individually assessed

Method used

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Embodiment Construction

[0021] 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 following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. The following description of at least one exemplary embodiment is merely illustrative in nature and in no way taken as limiting the invention, its application or uses. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0022] It should be noted that the terminology used here is only for describing specific implementations, and is not intended to limit t...

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Abstract

The invention provides a wind tunnel test flow-guiding device. The device comprises a base, a flow guiding assembly, an angle adjusting piece and a calibration assembly, a test piece to be examined isarranged on the flow guiding assembly, the flow guiding assembly is used for smoothly transitioning air flow at a wind tunnel air outlet to a surface of the test piece to be examined, the angle adjusting piece is used for adjusting the angle of attack of the test piece to be examined to match a thermal environment state of the set test piece to be examined, the calibration assembly is used for measuring the thermal environment state of the test piece to be examined to calibrate the thermal environment state of the test piece to be examined, and when the thermal environment state measured by the calibration assembly is different from the set thermal environment state, the wind tunnel test flow-guiding device adjusts the angle of attack of the test piece to be examined through the angle adjusting piece to reach the set thermal environment state of the test piece to be examined. The technical scheme of the invention is applied to solve the technical problem in the prior art that a certain section of cabin cannot be examined separately.

Description

technical field [0001] The invention relates to the technical field of cabin-level wind tunnel tests, in particular to a flow guide device for wind tunnel tests. Background technique [0002] High-speed and high-speed are the development direction of future aircraft. The aerodynamic and thermal problems of high-speed aircraft are key issues that cannot be avoided. With the continuous increase of the flight Mach number, the aerodynamic and thermal problems are becoming more and more serious. A lot of work has been done in the field to deal with the aerodynamic and thermal problems brought about by high-speed flight. At present, the thermal prediction problem is limited by the existing technology and theoretical development level, and there is still a certain gap between the accuracy and the expectation. In particular, the numerical prediction accuracy is restricted by many interference factors. The wind tunnel test can provide a relatively real application environment. One o...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/04
CPCG01M9/04
Inventor 陈凯王庆伟王磊宋月娥
Owner BEIJING AEROSPACE TECH INST
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