Supersonic-speed wind tunnel test section regulating device with angle adjustment function

A technology of wind tunnel test and angle adjustment, which is applied in the direction of measuring device, aerodynamic test, machine/structural component test, etc. It can solve problems such as unrealizable, limited model volume, and failure to reach Mach number step accuracy, etc. To achieve the effect of improving efficiency

Active Publication Date: 2017-06-13
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Application Information

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Problems solved by technology

This method has shortcomings. The first is that the Mach number interval of the supersonic flow is at least 0.25, which has not yet reached the Mach number step accuracy required for the study of the shock reflectio

Method used

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  • Supersonic-speed wind tunnel test section regulating device with angle adjustment function
  • Supersonic-speed wind tunnel test section regulating device with angle adjustment function
  • Supersonic-speed wind tunnel test section regulating device with angle adjustment function

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Embodiment Construction

[0047] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0048] The regulating piece of the supersonic wind tunnel test section is generally fixed as the inner wall of the wind tunnel during the test. The present invention improves on the basis of the existing regulating piece, so that one of the original fixed regulating pieces is divided into two layers to become a transitional regulating piece. tab and turn the adjustment tab. The transition adjustment piece is located on the lower layer, and the connection method with the remaining fixed adjustment piece on the frame is compression; the rotating adjustment piece is located on the upper layer, and an arc-shaped guide rail is installed between the transition adjustment piece, wherein the guide rail seat is fixed on the transition adjustment piece, and the guide rail is fixed On the rotation adjustment piece, the arc-shaped guide rail restricts th...

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Abstract

The invention discloses a supersonic-speed wind tunnel test section regulating device with the angle adjustment function and belongs to the field of wind tunnel test device design. The device includes a frame, an elastic beam, a hinge shaft, a fixed adjusting piece, a transition adjusting piece, a rotating adjusting piece, an ejector rod, an arc-shaped guide rail, a roll ball screw rod module, a servo motor, a reducer, a pull wire sensor and the like. A rail body of the arc guide rail is installed on the transition adjusting piece fixedly connected with the frame, a slider of the arc-shaped guide rail is connected with the rotating adjusting piece, the ejector rod is driven by means of a linear motion mechanism composed of the servo motor, the speed reducer and the roll ball screw rod module to walk, the rotation of the adjusting pieces is achieved, and oblique shock waves with the continuously variable shock wave angle is generated. The device has the function of accurately adjusting a wind tunnel flow field, can be applied in shock wave reflection and continuously variable Maher number research projects, can also be applied in pressure measuring, air inlet channel measuring and other supersonic-speed wind tunnel special tests, and effectively expands the capacity of the wind tunnel test.

Description

technical field [0001] The invention relates to a supersonic wind tunnel test section adjustment device with an angle adjustment function, which can be used for supersonic wind tunnel special test items such as shock wave reflection, continuously variable Mach number, pressure measurement, and air intake, and belongs to the design field of wind tunnel test devices . Background technique [0002] As a basic physical phenomenon of aerodynamics, shock wave has important physical significance and academic research value. As an important research field of aerodynamics, shock wave reflection phenomenon has been widely concerned in physics research. [0003] Figure 1(a) ~ Figure 1(f) is the change of the incoming flow Ma1 and the shock wave at the head of the wedge in the two-dimensional flow field. Figure 1(a) shows that when the incoming flow Ma1 just exceeds the speed of sound, an isolated shock wave appears in front of the wedge ; Figure 1(b) shows that the speed of Ma1 conti...

Claims

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Application Information

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IPC IPC(8): G01M9/04
CPCG01M9/04
Inventor 袁雄杨辉李世强
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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