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A large-scale wind tunnel nozzle test section integrated device

A test section and nozzle technology, applied in the aerospace test field, can solve the problems of limited effect and low efficiency of wind tunnel test, and achieve the effects of convenient disassembly, reduced labor cost and high technical reliability

Active Publication Date: 2020-03-24
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Although various methods of reducing shock wave interference have been adopted, the effects are very limited, which also caused the inefficiency of the wind tunnel test

Method used

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  • A large-scale wind tunnel nozzle test section integrated device
  • A large-scale wind tunnel nozzle test section integrated device
  • A large-scale wind tunnel nozzle test section integrated device

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Experimental program
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Effect test

Embodiment Construction

[0020] The present invention will be further described in detail below in conjunction with the drawings and specific embodiments:

[0021] The invention provides a large-scale wind tunnel nozzle test section integrated device, which adopts a design that combines a traditional supersonic nozzle and a test section into one, eliminating the joints between the original nozzle and the test section, thereby eliminating the joints The step wave at the location improves the flow field quality in the wind tunnel test area; modular design, low processing and manufacturing costs, compatible with existing wind tunnel equipment, does not affect wind tunnel test production, low transformation costs, and high economy of the entire device ; By changing and placing the nozzle test integrated section, outlet flange section and the carriage using wheel drive to walk on the track, the guide positioning is accurate, the operation is simple, and the safety is high; the nozzle is adjusted by the wheel s...

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Abstract

The invention discloses a large wind tunnel nozzle test section integrated device, and relates to the technical field of aerospace testing. The large wind tunnel nozzle test section integrated devicecomprises an nozzle test integrated section, an outlet flange section, a support frame car, a thread pin and wind tunnel devices; the support frame car is horizontally placed on the ground; the nozzletest integrated section is placed horizontally on the upper surface of the support frame car, and the axial direction of the nozzle test integrated section is identical to the longitudinal directionof the support frame car; the outlet flange section is coaxially fixed and installed in an axial outlet end of the nozzle test integrated section; the outlet flange section and the nozzle test integrated section are fixedly connected through the threaded pin; the wind tunnel devices are coaxially and fixedly mounted on the axial inlet end of the nozzle test integrated section and the axial outer end of the outlet flange section. The large wind tunnel nozzle test section integrated device adopts the modular design, is low in processing and manufacturing cost, is high in economy; driving is achieved by a wheel set, guiding and positioning is achieved by a guide rail; the operation is simple, and the safety is high; and the precise positioning design reduces the labor cost, and the disassembly and assembly is convenient. .

Description

Technical field [0001] The invention relates to the technical field of aerospace tests, in particular to a large-scale wind tunnel nozzle test section integrated device. Background technique [0002] The range of the airflow Mach number in the test section of the subspan supersonic wind tunnel is 0.4≤Ma≤4.5. Since the establishment of supersonic airflow depends on the ratio of the cross-sectional area of ​​the roar to the exit, conventional subsonic wind tunnels are mostly equipped with multiple supersonic nozzles to obtain different test section Mach numbers, including several subsonic nozzles and subsonic nozzles. Transonic test section, multiple supersonic nozzles and several supersonic test sections, the typical configuration of the wind tunnel is as attached image 3 Shown. The supersonic nozzle is connected to the supersonic test section through flanges, and the joints are sealed by clamping rubber pads, which will inevitably produce dislocation steps and gaps. Although th...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/04
CPCG01M9/04
Inventor 李广良金佳林宋法振董金刚魏忠武袁雄刘森谌君谋张江赵顺友吴晋鹏
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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