Testing device for static aeroelasticity test of wind tunnel

A test device and aero-elastic technology, applied in aerodynamic test, measurement device, elasticity test, etc., can solve the problems of rudder surface reaction, lift surface lift divergence, and rudder surface efficiency decline.

Active Publication Date: 2017-01-04
CHINA ACAD OF AEROSPACE AERODYNAMICS
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Problems solved by technology

There is also a divergence of the lift force on the lift surface. When the pressure center of the lift surface is located in front of the elastic deformation axis of the lift surface, when the flight speed pressure exceeds a certain value, the nose-up moment caused by the deformation of th

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  • Testing device for static aeroelasticity test of wind tunnel
  • Testing device for static aeroelasticity test of wind tunnel
  • Testing device for static aeroelasticity test of wind tunnel

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Embodiment Construction

[0033] The present invention will be further described in detail below in conjunction with the accompanying drawings, so that those skilled in the art can implement it with reference to the description.

[0034] Such as figure 1 , figure 2 , image 3 and Figure 4 As shown, the present invention provides a test device for the static aeroelastic test in a wind tunnel, comprising: a base 2, which has an accommodating cavity with an upper opening, and the base 2 has a longitudinal symmetry plane H; pads 13, which It is accommodated in the accommodation cavity 17, and the first side wall 24 of the cushion block 13 is attached to and detachably connected to a side wall 18 of the accommodation cavity 13 parallel to the longitudinal symmetry plane H; Balance 5, which is accommodated in the accommodating cavity 17, and is detachably connected to the second side wall 25 of the cushion block 13 that forms a certain angle with the first side wall 24; the wing model 10, It includes a...

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Abstract

The invention discloses a testing device for a static aeroelasticity test of a wind tunnel, and the device comprises a pedestal which is provided with an accommodation cavity with an upper opening and is also provided with a longitudinal symmetric surface; a cushion block which is disposed in the accommodation cavity, wherein a first side wall of the cushion block is closely attached to and detachably connected with one side wall, parallel to the longitudinal symmetric surface, of the accommodation cavity; a balance which is disposed in the accommodation cavity, and is detachably connected to a second side wall, forming an inclined angle with the first side wall, of the cushion block; a missile wining model which comprises a main body part and a root part located below the main body part, wherein the main body part vertically extends above the pedestal, and the root part stretches into the accommodation cavity, and is connected to the balance. Through the selection of the cushion block from a plurality of cushion blocks with different inclined angles, the installation angle of the missile wining model relative to the longitudinal symmetric surface. The method can precisely measure the aerodynamic force and torque characteristics of the missile wining model at different attack angles under the action of an aerodynamic load after elastic changes.

Description

technical field [0001] The invention relates to a wind tunnel test device, in particular to a test device for a wind tunnel static aeroelastic test. Background technique [0002] The problem of aeroelastic statics (static aeroelasticity) is to study the influence of elastic deformation on the distribution of steady aerodynamic force and to study the stability characteristics of static deformation produced by aerodynamic force. This detailed knowledge is of particular importance for the structural design of lifting and control surfaces in aircraft. In addition, elastic deformation also has a rather adverse effect on flight static stability. [0003] The aircraft is an elastic body, and the structure of the airframe is elastically deformed under the action of aerodynamic load during flight, while the wind tunnel test model is generally processed into a rigid body. The model of the static elastic test is made to have elastic deformation. The purpose of the test is to obtain t...

Claims

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Application Information

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IPC IPC(8): G01M5/00G01M9/00
CPCG01M5/0016G01M5/005G01M9/00
Inventor 刘金吕计男
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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