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Continuous wind tunnel wing type dynamic characteristic testing mechanism

A dynamic characteristic and airfoil technology, applied in aerodynamic testing, machine/structural component testing, measurement devices, etc., can solve the problems of complex test equipment and inaccurate airfoil dynamic motion control, so as to improve experimental efficiency, Save valuable time and achieve precise selection results

Inactive Publication Date: 2014-06-11
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] However, at present, domestic airfoil dynamic characteristic experimental devices generally have problems such as inaccurate airfoil dynamic motion control and complicated test equipment.

Method used

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  • Continuous wind tunnel wing type dynamic characteristic testing mechanism
  • Continuous wind tunnel wing type dynamic characteristic testing mechanism
  • Continuous wind tunnel wing type dynamic characteristic testing mechanism

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Experimental program
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Embodiment Construction

[0028] Describe the present invention below in conjunction with specific embodiment:

[0029] like figure 1 As shown, the continuous wind tunnel airfoil dynamic characteristic test mechanism in this embodiment includes a wind tunnel, a window turning mechanism, a driving device, a crank device, a connecting rod, and a model support oscillation device.

[0030] The driving device provides the original power for the movement mechanism, including the motor and its support, the reducer, the rotating shaft and its support, etc., such as figure 2 shown. The large gear is installed on the rotating shaft; the small gear is installed on the motor shaft. The power of the motor is 2.5Kw and the speed is 3000 rpm. The motor drives the small gear to rotate. After gear transmission and deceleration, the torque of the large gear increases. Ensuring sufficient power output. After gear reduction, the oscillation frequency of the mechanism can still reach about 33Hz, which can meet the curr...

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Abstract

The invention provides a continuous wind tunnel wing type dynamic characteristic testing mechanism which comprises a wind tunnel, a pivot window mechanism, a driving device, a crank device, a connecting rod and a model supporting oscillation device. The continuous wind tunnel wing type dynamic characteristic test is realized through the driving device, the crank device, the connecting rod and the model supporting oscillation device; wing-type dynamic motion range adjustment is realized by adjusting the position of a slide block along an axis of a sliding rod in the crank device and adjusting the length of two sections of rod in the connecting rod; an oscillating shaft flange plate and an average incidence angle flange plate are matched through different pin holes, an initial angle of the wing type is accurately selected; according to the special pivot window mechanism, pivot window parts needing to be detached due to model change in the traditional pivot window structure are optimized, for example, the window does not need to be detached after one-step installation, so that the condition that the model needs to be recalibrated due to one-step detachment is effectively avoided, lots of precious time is saved for preparatory work of the wing-type test, and the experimental efficiency is effectively improved.

Description

technical field [0001] The invention belongs to the field of aerospace wind tunnel test equipment, in particular to a continuous wind tunnel airfoil dynamic characteristic test mechanism. Background technique [0002] Helicopters are widely used in civil and military fields. The dynamic characteristics of the helicopter rotor are closely related to the dynamic characteristics of the airfoil used. The dynamic characteristics of the airfoil have an important effect on the aerodynamic load of the rotor, the handling characteristics, the life of the rotor moving parts, and even the performance of the helicopter. influences. When the helicopter is flying forward, the rotation speed is superimposed on the forward flight speed, and the forward blade may experience transonic shock wave stall, and the backward blade may experience high angle of attack dynamic stall and airflow separation. Therefore, to provide a reliable design basis for rotor design, it is necessary to carry out in...

Claims

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Application Information

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IPC IPC(8): G01M9/02G01M9/04
Inventor 李方吉王莹郗忠祥吕哲李峰盛强李征
Owner NORTHWESTERN POLYTECHNICAL UNIV
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