A rolling forced vibration dynamic derivative test device suitable for Mach 8.0
A test device and drive device technology, applied in the direction of aerodynamic test, measuring device, machine/structural component test, etc., can solve problems affecting aircraft flight attitude, aircraft angular motion divergence, low dynamic stability, etc., to improve Effects of measurement accuracy, improved reliability, and reduced wear
Active Publication Date: 2020-07-14
CHINA ACAD OF AEROSPACE AERODYNAMICS
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Problems solved by technology
Too low dynamic stability will easily cause the angular motion of the aircraft to diverge, which will seriously affect the flight attitude of the aircraft
Method used
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Embodiment
[0063] When using the rolling forced vibration dynamic derivative test device for Mach number 8.0 of the present invention to carry out the test, the scimitar connector 17 of the device is installed on the wind tunnel scimitar, and the front end of the five-component dynamic balance 1 is connected to the model Together, the theoretical center of mass of the test model coincides with the rotation center of the rolling hinge 15, the motor AM8023 22 is controlled to rotate at a specified frequency through the motor control system, and the amplitude is adjusted through the eccentric shaft 27, so that the model can perform simple harmonic motion at a specified frequency and amplitude . During the test, the force and moment signals of the five-component dynamic balance 1 and the angular displacement signals of the rolling hinge 15 are measured simultaneously, and the corresponding dynamic stability derivatives can be obtained through corresponding processing of the two signals.
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Disclosed is a rolling forced vibration dynamic derivative testing device suitable for mach number of 8.0 or below. The rolling forced vibration dynamic derivative testing device comprises a driving device, a water cooling device, a supporting device, a movement conversion device, a torque transmission device, a rolling hinge and a five-component dynamic balance; the driving device serves as a power source of the whole testing device; the water cooling device provides a normal working environment for the driving device, and the whole testing device is installed in an air tunnel through the supporting device; meanwhile, the supporting device provides installation support for the driving device, the water cooling device and the movement conversion device; the movement conversion device is used for converting the output of the driving device into a simple harmonic motion and transmitting the simple harmonic motion to the torque transmission device; one end of the rolling hinge is connected with the torque transmission device, and one end of the rolling hinge is connected with the supporting device, and the angular displacement of the torque transmission device is measured through therolling hinge; and the five-component dynamic balance is installed at the front end of the torque transmission device, the torque transmission device drives the five-component dynamic balance to do asimple harmonic motion, and the five-component dynamic balance is used for measuring a torque signal of a test model mounted at the front end of the five-component dynamic balance.
Description
technical field [0001] The invention relates to a wind tunnel test device for measuring the dynamic derivative of an aircraft test model in the roll direction through a small-amplitude forced vibration method under a hypersonic wind tunnel with a Mach number of 8.0. 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...
Claims
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IPC IPC(8): G01M9/06G01M9/04
CPCG01M9/04G01M9/06
Inventor 刘金宋玉辉胡静
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS