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A Pitching Motion Protection Device for a Supersonic Wind Tunnel Model

A technology of pitching motion and protection device, which is applied in the direction of measuring device, aerodynamic test, machine/structural component test, etc., and can solve the problem of inability to simulate high-pressure transverse jet flow at subsonic and transonic speeds

Active Publication Date: 2022-04-26
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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  • A Pitching Motion Protection Device for a Supersonic Wind Tunnel Model
  • A Pitching Motion Protection Device for a Supersonic Wind Tunnel Model
  • A Pitching Motion Protection Device for a Supersonic Wind Tunnel Model

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 withdraw from the locking cone 16, then unlock the locking clutch 20, drive the clutch 23, and make the aircraft model 10 enter the 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 at...

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Abstract

The invention discloses a pitching motion protection device for a supersonic wind tunnel model. The pitching protection device includes a lateral support, the main body of which is a tubular support rod, which passes through the center of mass of the aircraft model, and supports the aircraft model on the central axis of the wind tunnel test section; outside the wind tunnel test section, the lateral The tubular support rod protruding from the left side of the support is sequentially installed with a motion bearing, a mechanical limit mechanism and an impact-resistant cone locking mechanism, and the tubular support rod protruding from the right side of the lateral support is sequentially installed with a motion bearing and a mechanical limit mechanism And emergency forced return to zero mechanism. The pitching motion protection device can provide three-level protection from weak to strong for the aircraft model in the supersonic wind tunnel simulation test. It has the advantages of reliable structure and convenient control. It is extended to be used in the support model system on both sides of subsonic and transonic wind tunnels.

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 Patents(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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