Gantry crane device for boundary layer measurement in pulse wind tunnel

A boundary layer and gantry crane technology, which is used in measuring devices, testing of machine/structural components, instruments, etc., can solve problems such as obvious pipeline effects, and achieve the effect of preventing airflow flow field blockage, reducing pipeline effects, and ensuring reliability.

Active Publication Date: 2021-03-23
CHINA AERODYNAMICS RES & DEV CENT
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The present invention aims to provide a gantry crane device for boundary layer measurement in a pulsed wind tunnel to solve the problem of pressure when the boundary layer pressure measurement points are densely arranged in the prior art. The problem of obvious pipe effect when sensors interfere with each other in geometric position and when connecting with long pitot tube

Method used

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  • Gantry crane device for boundary layer measurement in pulse wind tunnel
  • Gantry crane device for boundary layer measurement in pulse wind tunnel

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Embodiment Construction

[0037] Below in conjunction with accompanying drawing and embodiment the present invention is described in further detail:

[0038] like figure 1 and figure 2 As shown, the gantry crane device used for boundary layer measurement in the pulse wind tunnel includes the inlet model 1, four pressure bent frames 5, the gantry frame 6, the first screw 2, the positioning pin 3, the second screw 8, the third Screw 10 and the fourth screw 11, the gantry 6 is in the shape of a door frame, the contact surface profile between the inner sides of the two columns of the gantry 6 and the inlet model 1 is consistent with the local contours of the two side walls of the inlet model 1, and the gantry 6 The first screw 2 and the positioning pin 3 are connected above the inlet model 1, the inlet model 1 is arranged on the inner side of the two columns of the gantry frame 6, the front end of the gantry frame 6 is in the shape of a sharp wedge at 30°, and the gantry frame The crossbeam of 6 is prov...

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Abstract

The invention belongs to the technical field of experimental fluid mechanics, and discloses a gantry crane device for boundary layer measurement in a pulse wind tunnel, wherein the gantry crane devicecomprises an air inlet model, a pressure bent frame and a door-frame-shaped gantry frame, the gantry frame is connected above the air inlet model, mortises are formed in a cross beam of the gantry frame, and tenons are arranged on the upper side of the pressure bent frame; the tenons of the pressure bent frame penetrate through the mortises of the gantry frame to be connected with an upper coverplate, probe holes are formed in the windward side of the pressure bent frame, sensor mounting holes are formed in the leeward side of the pressure bent frame, pressure sensors are connected into thesensor mounting holes, and a sensor protection cover is connected to the lower portion of the leeward side of the cross beam of the gantry frame; and the leeward sides of a door frame of the gantry frame and the cross beam of the gantry frame are connected with a cable protection cover. The problems that in the prior art, when boundary layer pressure measuring points are densely arranged, the pressure sensors interfere with one another in the geometric position, and the pipeline effect is obvious when long pitot tubes are adopted for connection are solved, and the method is suitable for pulsewind tunnel boundary layer parameter measurement test research.

Description

technical field [0001] The invention relates to the technical field of experimental fluid mechanics, in particular to a gantry crane device used for boundary layer measurement in an impulse wind tunnel. Background technique [0002] When a hypersonic vehicle is flying, the viscosity of the fluid will cause the boundary layer on the surface of the solid wall to form a boundary layer whose velocity gradually changes from zero to the local mainstream velocity when the airflow passes through the solid wall. The existence of the boundary layer will cause the total pressure of the airflow in the inlet to be distorted , The total pressure recovery coefficient decreases, the turbulence of the airflow increases, and even the strong boundary layer interference directly affects the starting performance and compression performance of the inlet, thereby affecting the flight safety of the aircraft. Therefore, how to accurately measure the boundary layer flow field of the inlet, so as to d...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/06
CPCG01M9/062Y02T90/00
Inventor 余安远贺元元吴颖川杨辉杨大伟李一鸣张胜
Owner CHINA AERODYNAMICS RES & DEV CENT
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