Emergency method for flutter suppression in low-speed flutter wind tunnel test

A wind tunnel test and flutter technology, applied in aerodynamic test, aircraft component test, machine/structural component test, etc., to achieve the effect of cost protection, clear principle and easy implementation

Inactive Publication Date: 2021-09-24
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

[0005] The purpose of this application is to provide an emergency method for flutter suppres...

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  • Emergency method for flutter suppression in low-speed flutter wind tunnel test
  • Emergency method for flutter suppression in low-speed flutter wind tunnel test
  • Emergency method for flutter suppression in low-speed flutter wind tunnel test

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Embodiment Construction

[0026] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application. 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 application. The embodiments described below by referring to the figures are exemplary, and are intended to explain the present application, and should not be construed as limiting the present application. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of this application. Embodiments of the present application will be described in detail below in conjunction with th...

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Abstract

The invention belongs to the field of aeroelastic mechanics, and particularly relates to an emergency method for flutter suppression in a low-speed flutter wind tunnel test. The emergency method comprises the steps that 1 an emergency system for flutter suppression is constructed, the emergency system comprises a low-speed flutter model and a skin damage mechanism, the low-speed flutter model comprises a frame section and a dimensional skin, and the skin damage mechanism is installed at a flutter sensitive part in the low-speed flutter model; and 2 when flutter occurs, the dimensional skin of the low-speed flutter model is damaged through the skin damage mechanism. According to the emergency method for flutter suppression in the low-speed flutter wind tunnel test, an emergency flutter suppression measure is provided, when flutter occurs, the skin damage mechanism is adopted to damage the dimensional skin of the low-speed flutter model, and the purpose of protecting the safety of the overall structure of the model at a low cost is achieved. The method is clear in principle and easy to implement, and can protect the model safety when other reversible flutter suppression measures are invalid.

Description

technical field [0001] The application belongs to the field of aeroelasticity, and in particular relates to an emergency method for flutter suppression in a low-speed flutter wind tunnel test. Background technique [0002] The flutter wind tunnel test is an important means to study the flutter characteristics of aircraft. In the wind tunnel test, increase the wind speed of the wind tunnel to make the model reach the critical speed of flutter, and obtain the flutter characteristics of the model. However, the flutter speed is the critical speed for the model to be between convergent vibration and divergence. In the test, the model continuously absorbs energy from the airflow, and the continuous increase of the amplitude is likely to cause damage to the model. [0003] At present, in order to prevent the fluttering damage of the airfoil flutter model, the method of protection line is commonly used. When flutter occurs, the protection line is tensioned to provide an additional ...

Claims

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Application Information

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IPC IPC(8): G01M9/00G01M9/08B64F5/60
CPCG01M9/00G01M9/08B64F5/60
Inventor 脱朝智赵飞宇胡鑫
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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