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A Follow-up Compensation Mechanism for Continuously Variable Sideslip Angle Wind Tunnel Test

A wind tunnel test and follow-up compensation technology, which is applied in aerodynamic tests, machine/structural component testing, instruments, etc., can solve the vacancy of the wall plate structure, affect the uniformity of the flow field in the model area, the followability of the flow field adjustment, Problems affecting the accuracy of test data, etc., to achieve the effect of improving accuracy and good adaptability

Active Publication Date: 2021-06-22
INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

In this way, the sideslip angle of the model is changed by rotating the model and the support system around the fixed point of the wind tunnel. During operation, the support mechanism will be biased to one side of the central axis, and there will be structural vacancies in the wall plate of the test section, which will affect the flow field in the model area. Uniformity and followability of flow field adjustment, and ultimately affect the accuracy of test data

Method used

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  • A Follow-up Compensation Mechanism for Continuously Variable Sideslip Angle Wind Tunnel Test
  • A Follow-up Compensation Mechanism for Continuously Variable Sideslip Angle Wind Tunnel Test
  • A Follow-up Compensation Mechanism for Continuously Variable Sideslip Angle Wind Tunnel Test

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Embodiment 1

[0049] exist figure 1 , figure 2 Among them, the high-speed wind tunnel follow-up compensation mechanism of this embodiment is installed in the high-speed wind tunnel test section, surrounded by wind tunnel wall panels. The dynamic compensation mechanism is composed of a left movable assembly, a right movable assembly and a model supporting mechanism 2. Wherein, the left movable assembly and the right movable assembly are symmetrical structures, which are respectively installed on both sides of the model support mechanism 2, and are used to compensate for structural vacancies that occur when the model support mechanism 2 changes position. Two chutes are arranged symmetrically on the model support mechanism 2, which are respectively recorded as the left chute 21 and the right chute 22; sides.

[0050] In this embodiment, the left movable assembly is a set of combined parts, which includes a first linear guide rail 11, a first slider 12, a second linear guide rail 13, a seco...

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Abstract

The invention discloses a follow-up compensation mechanism for continuously variable sideslip angle wind tunnel tests, which belongs to the technical field of aerodynamic wind tunnel tests. The follow-up compensation mechanism includes a left movable assembly and a right movable assembly; the left movable The assembly includes a first linear guide rail for fixed connection with the wind tunnel, a first slider matched with the first linear guide rail, a second linear guide rail for fixed connection with the wind tunnel, and a second linear guide rail matched with the second linear guide rail The second slider, the left movable plate, the left sliding slider, and the left shift fork shaft, the first linear guide rail and the second linear guide rail are arranged parallel to each other, and the first slider is arranged on the first linear guide rail And the first slider can slide relatively along the first linear guide rail, and the second slider is arranged on the second linear guide rail. The invention can follow and compensate in real time the structural vacancy in the part of the wind tunnel when the model support mechanism moves in a horizontal line or rotates around the fixed central point of the wind tunnel.

Description

technical field [0001] The invention relates to the technical field of aerodynamic wind tunnel tests, in particular to a follow-up compensation mechanism for wind tunnel tests with continuously variable sideslip angles. Background technique [0002] The change law of the aircraft lateral force (moment) with the sideslip angle is the key to evaluate the aerodynamic characteristics of the basic lateral direction. The test is carried out by changing the sideslip angle at a constant angle of attack. At present, the main methods that can realize this operating condition include There are three types of attitude angle coupling method, double axis method and double degree of freedom method. [0003] Among them, the attitude angle coupling method uses the angle of attack mechanism and the roll angle mechanism around the axis of the strut to realize the sideslip angle of the model. When the angle of attack of the model is different, the position of the lift surface of the model in th...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/06G01M9/08G01M9/04
CPCG01M9/04G01M9/06G01M9/08
Inventor 吴军强刘光远师建元陈德华刘大伟李强彭鑫邓吉龙熊贵天
Owner INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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