Shock tube for dynamic pressure calibrating device

A verification device and dynamic pressure technology, applied in the field of shock tubes, can solve the problems of cumbersome preparation process and difficult clamping of the diaphragm, so as to meet the test requirements, facilitate loading and unloading, and facilitate the test operation

Active Publication Date: 2020-04-28
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The clamping section in the prior art mainly includes a clamping flange bolt connection structure, a tubular thread tightening structure, a cut serrated thread tightening st

Method used

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  • Shock tube for dynamic pressure calibrating device
  • Shock tube for dynamic pressure calibrating device
  • Shock tube for dynamic pressure calibrating device

Examples

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Example Embodiment

[0025] Example: A shock tube used in a dynamic pressure verification device, such as figure 1 , figure 2 with image 3 As shown, it includes a base support frame 1 and a shock tube body 2 fixedly connected to the top of the base support frame 1. The shock tube body 2 includes a high-pressure section 3 and a low-pressure section 4; the high-pressure section 3 and the low-pressure section 4 are installed between There is a clamping mechanism 5; the end of the low-pressure section 4 away from the clamping mechanism 5 is equipped with a sensor 6 to be tested; the clamping mechanism 5 includes a first fixing seat 7 fixedly connected to the outer wall of the end of the high-pressure section 3, and the end of the low-pressure section 4 The second fixing seat 8 fixedly connected to the outer wall, the ear seat 9 connected to the second fixing seat 8 and the two cylinders 10 respectively located on both sides of the high pressure section 3 fixedly connected to the ear seat 9 and the tele...

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Abstract

The invention discloses a shock tube for a dynamic pressure calibrating device, and relates to the technical field of aerospace experiments. Key points of the technical scheme are that the shock tubeincludes a base support frame and a shock tube body, and the shock tube body includes a high-pressure section, a low-pressure section and a film clamping mechanism; a to-be-detected sensor is arrangedat an end part of the low-pressure section; the film clamping mechanism includes a first fixed seat fixedly connected with an outer wall of the high-pressure section, a second fixed seat connected with the outer wall of the low-pressure section, a lug, two air cylinders fixedly connected with the lug and located on the two sides of the high-pressure section respectively, two trunnions connected with telescopic ends of the two air cylinders respectively, a first flange connected with an end portion of the high-pressure section, and a second flange connected with the end portion of the low-pressure section; a film rupture ring and a film clamping ring are arranged between the first flange and the second flange; and a diaphragm is fixed on the film rupture ring and is attached to the film clamping ring. According to the shock tube, a film clamping structure can be used for fully clamping the diaphragm, the diaphragm is convenient to assemble, disassemble, replace and maintain, a film breaking mode of the diaphragm is simple, test operation is facilitated, and test requirements are met.

Description

technical field [0001] The invention relates to the technical field of aerospace experiments, more specifically, it relates to a shock tube used for a dynamic pressure verification device. Background technique [0002] In wind tunnel and aircraft experiments, quantitative measurement of surface pressure is an important method to understand the aerodynamic characteristics of aircraft. For the design of aircraft, surface pressure measurement is an indispensable content. It is very important to understand the characteristics of the flow field and analyze the aerodynamic characteristics of the aircraft and its components. It is an important basis for aircraft design. Pressure distribution measurements provide key information on many important flow phenomena, such as shock wave shape, location, and flow separation. In addition, accurate pressure data play a key role in validating and validating the reliability of turbulence models, CFD programs and calculation results. [0003]...

Claims

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Application Information

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IPC IPC(8): G01M9/06
CPCG01M9/06Y02T90/00
Inventor 梁磊姜裕标段丕轩赵维明左承林杨强
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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