Large wind tunnel nozzle test section integrated device

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

Active Publication Date: 2018-09-11
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Although various methods of reducing shock wave interference have been adopted, the

Method used

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  • Large wind tunnel nozzle test section integrated device
  • Large wind tunnel nozzle test section integrated device
  • Large wind tunnel nozzle test section integrated device

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Embodiment Construction

[0020] Below in conjunction with accompanying drawing and specific embodiment the present invention is described in further detail:

[0021] The invention provides a large-scale wind tunnel nozzle test section integration device, which adopts the design of combining the traditional supersonic nozzle and the test section, and eliminates the seam at the joint between the original nozzle and the test section, thereby eliminating the seam The step wave at the place improves the quality of the flow field in the wind tunnel test area; the modular design is adopted, the manufacturing cost is low, compatible with the existing wind tunnel equipment, does not affect the wind tunnel test production, the transformation cost is low, and the economy of the whole device is high ;The integrated section of the nozzle test, the outlet flange section and the frame car are replaced and placed by driving the wheel set to walk on the track. The guide positioning is accurate, the operation is simple,...

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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 testing, in particular to an integrated device for the nozzle test section of a large wind tunnel. Background technique [0002] The Mach number range of the test section of the subtransonic wind tunnel is 0.4≤Ma≤4.5. Since the establishment of supersonic flow depends on the ratio of the roar to the outlet cross-sectional area, most conventional sub-transonic wind tunnels are equipped with multiple supersonic nozzles to obtain different Mach numbers in the test section, including several sub-transonic nozzles and sub-transonic 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 and the supersonic test section are connected and docked through flanges, and the joints are sealed by clamping rubber pads, which inevitably leads to dislocation steps and gaps...

Claims

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Application Information

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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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