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Supersonic wind tunnel model pitching motion protection device

A technology of pitching motion and protection device, applied in measurement devices, aerodynamic tests, instruments, etc., can solve the problems of subsonic and transonic speeds that cannot simulate high-pressure lateral jets

Active Publication Date: 2021-01-26
INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] At present, among domestic and foreign wind tunnel virtual flight test devices, only subsonic and transonic test devices that cannot simulate high-pressure transverse jet flow have been constructed.

Method used

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  • Supersonic wind tunnel model pitching motion protection device
  • Supersonic wind tunnel model pitching motion protection device
  • Supersonic wind tunnel model pitching motion protection device

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0052] The specific control steps of the present embodiment are as follows:

[0053] 1. Before the start of the wind tunnel, the angle of attack of the aircraft model 10 is 0°, the locking clutch 20 and the driving clutch 23 are both in the meshing state, the locking cone rod 16 enters the cone hole of the lateral support 13, and the entire pitching motion protection device is at Fully locked state; when the wind tunnel is started, the locking cone rod 16, locking clutch 20, driving clutch 23, etc. together resist the shock wave impact;

[0054] 2. After the flow field in the supersonic wind tunnel is stable, first exit the locking cone 16, then unlock the locking clutch 20 and drive the clutch 23, so that the aircraft model 10 enters a free movement state;

[0055] 3. In the supersonic wind tunnel test process, once the aircraft model 10 enters an out-of-control state, first the locking clutch 20 and the driving clutch 23 are engaged simultaneously to stabilize the attitude o...

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PUM

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Abstract

The invention discloses a supersonic wind tunnel model pitching motion protection device. The pitching motion protection device comprises a transverse support, the main body of the transverse supportis a tubular support rod, and the tubular support rod penetrates through the mass center of an aircraft model to support the aircraft model on the central axis of a wind tunnel test section; a motionbearing, a mechanical limiting mechanism and an anti-impact conical surface locking mechanism are sequentially installed on the tubular supporting rod extending out of the left side of the transversesupport outside the wind tunnel test section, and a motion bearing, a mechanical limiting mechanism and an emergency forced zero returning mechanism are sequentially installed on the tubular supporting rod extending out of the right side of the transverse support. The pitching motion protection device can provide three-level protection from weak to strong for an aircraft model of a supersonic windtunnel simulation test, has the advantages of being reliable in structure and convenient to control, has the functions of high resistance to high-energy impact, forced zero returning and the like, and can be expanded to be used in supporting model systems on the two sides of a subsonic wind tunnel and a transonic wind tunnel.

Description

technical field [0001] The invention belongs to the technical field of supersonic wind tunnel tests, and in particular relates to a pitching motion protection device for a supersonic wind tunnel model. Background technique [0002] In order to accurately measure the aerodynamic characteristics of the aircraft in the state of supersonic flight, it is necessary to build a virtual flight hardware-in-the-loop simulation test platform capable of simulating the compound control of the pitch direction and the roll direction. Test needs. [0003] At present, among domestic and foreign wind tunnel virtual flight test devices, only subsonic and transonic test devices that cannot simulate high-pressure transverse jet flow have been constructed. [0004] Because in the supersonic test, the model system and support system must bear the influence of very large shock wave shock and aerodynamic load, in order to develop a supersonic wind tunnel virtual flight test system, it is necessary t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/04G01M9/08
CPCG01M9/04G01M9/08
Inventor 赵忠良徐扬帆李浩苗磊杨海泳陈建中李玉平廖晓林邹涵李乾丁家宝王晓冰叶林车伟
Owner INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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