The dynamic derivative test device for pitching and yaw forced vibration of high-speed flying wing model at large angle of attack

A test device and model technology, applied in aerodynamic tests, measuring devices, aircraft component tests, etc., can solve problems such as uncontrollable instability, insufficiency, lack of control efficiency, etc., to achieve increased coincidence, increased stiffness and strength, The effect of reducing the amount of overall deformation

Active Publication Date: 2021-08-10
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, there are obvious shortcomings in the dynamic stability and control of flying-wing layout aircraft. Flying in the edge area of ​​​​the stable boundary will cause uncontrollable instability during supermaneuvering
Insufficiency and lack of dynamic stability and control seriously restrict the wide application of flying wing layout aircraft in future aircraft

Method used

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  • The dynamic derivative test device for pitching and yaw forced vibration of high-speed flying wing model at large angle of attack
  • The dynamic derivative test device for pitching and yaw forced vibration of high-speed flying wing model at large angle of attack
  • The dynamic derivative test device for pitching and yaw forced vibration of high-speed flying wing model at large angle of attack

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Embodiment

[0063] When using the pitching and yaw forced vibration dynamic derivative test device of the present invention under the large angle of attack of the high-speed flying wing model to carry out the test, the 10 ° turning head of the device is installed on the scimitar of the wind tunnel, and the front end of the signal measuring device and the flying wing The models are connected together, the theoretical center of mass of the test model coincides with the rotation center of the signal measuring device, the motor drive device is controlled to rotate at a specified frequency through the motor control system, and the amplitude is adjusted through the eccentric shaft 15, so that the model can be simplified at the specified frequency and amplitude. Harmonic motion, the switching between pitch vibration and yaw vibration can be realized by rotating the strut 12 by 90°. During the test, the force, torque signal and angular displacement signal of the signal measuring device are measure...

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Abstract

A device for testing the dynamic derivative of forced vibration of pitching and yaw under the large angle of attack of a high-speed flying wing model, including: a motor drive device, a rigid support device, a simple harmonic motion conversion device, a motion transmission device, and a signal measurement device; the motor drive device is The torque output part of the entire dynamic derivative test device; the rigid support device installs the entire test device in the wind tunnel, and supports the motor drive device, the simple harmonic motion conversion device and the signal measurement device; the simple harmonic motion conversion device outputs the motor drive device The continuous rotary motion is converted into the simple harmonic motion required by the test, and the simple harmonic motion is transmitted to the motion transmission device; the motion transmission device is directly connected to the middle of the signal measurement device, and the signal measurement device is driven to perform a specified form of simple harmonic motion; the signal measurement device Measure force, moment and angular displacement signals throughout the motion.

Description

technical field [0001] The invention relates to a wind tunnel test device for measuring the dynamic derivative in the pitch / yaw direction of a high-speed flying wing model under a large attack angle through a small-amplitude forced vibration method. Background technique [0002] The aerodynamic design and control system design of the aircraft require the dynamic stability derivative data of the aircraft under its flight conditions. When the aircraft changes its attitude or is disturbed by the air flow, it will produce pitch, yaw or roll vibrations that deviate from the equilibrium attitude. The purpose of dynamic stability research is to predict the attenuation trend and law of these vibrations. For aircraft with passive damping control, the dynamic flight quality and reliability requirements of the aircraft put forward extremely high requirements for the prediction of the dynamic stability of the aircraft. Too low dynamic stability will easily lead to the divergence of th...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/00G01M9/04G01M9/06B64F5/60
CPCB64F5/60G01M9/00G01M9/04G01M9/06
Inventor 刘金宋玉辉胡静陈兰秦汉王方剑
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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