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Aircraft wind tunnel model flutter blowing test system

A test system and model technology, applied in the field of aircraft wind tunnel flutter test, to achieve the effect of preventing infinite divergence

Inactive Publication Date: 2018-06-22
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] The purpose of the present invention is to provide a kind of aircraft wind tunnel model flutter blowing test system, to solve at least one problem existing in the existing aircraft wind tunnel model flutter blowing test

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Embodiment Construction

[0024] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. 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. Embodiments of the present invention will be described in detail below ...

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Abstract

The invention relates to the field of aircraft wind tunnel flutter test field and especially relates to an aircraft wind tunnel model flutter blowing test system. The system comprises a wind tunnel; amodel to be tested, which is fixedly arranged on a wind tunnel floor in a wind tunnel through a test clamp; a limit device, which is arranged on the bottom portion of the model to be tested and is used for limiting the amplitude of the model to be tested; a sensor, which is arranged at the position of large relative amplitude of the model to be tested and is used for monitoring real-time amplitude of the model to be tested in real time; a data acquisition and control system, which is used for receiving real-time amplitude information transmitted by the sensor in real time and is used for controlling the limit device to limit the amplitude of the model to be tested when the real-time amplitude is larger than preset amplitude; and a blowing test control system, which is used for controllingthe model to be tested in the wind tunnel to carry out flutter blowing test. The aircraft wind tunnel model flutter blowing test system can enable model flutter to be controlled within a fixed range,thereby preventing the model from diverging indefinitely, and protecting the model from having flutter damage.

Description

technical field [0001] The invention relates to the field of aircraft wind tunnel flutter tests, in particular to an aircraft wind tunnel model flutter blowing test system. Background technique [0002] The design of aircraft flutter characteristics is an important part of aircraft design. In the process of aircraft forward design, in order to find out the aircraft flutter characteristics, a series of wind tunnel model flutter blowing tests are carried out. By adjusting the wind tunnel airflow parameters Make the aircraft wind tunnel model reach the flutter state, obtain relevant data, and provide a basis for real aircraft design. Once the model enters the flutter state, if corresponding measures are not taken in time to prevent the further divergence of the model flutter state, the model will be disintegrated and damaged, which cannot be achieved. Follow-up tests are carried out, and the production cost of the wind tunnel model is very high, and once it is damaged, it will ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/02G01M9/04
CPCG01M9/02G01M9/04
Inventor 张雪飞柏楠王鑫何乾强
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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