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Three-dimensional structure measuring device and measuring method of incident shock wave

A technology of three-dimensional structure and measuring device, applied in the field of aerodynamics, can solve the problems such as obstacles to the development of three-dimensional reconstruction technology of supersonic flow field, inability to obtain quantitative information, and interference with measurement flow field, etc., and achieve simple structure, improved accuracy, and equipment requirements. low effect

Active Publication Date: 2018-10-02
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

These technologies mainly have the following disadvantages: first, some of them can only measure the flow field qualitatively, and cannot obtain quantitative information; secondly, most of the methods have strict requirements on the measurement optical path, the operation process is very cumbersome, and even interfere with the measurement of the flow field
The above factors have become the main obstacles to the development of supersonic flow field 3D reconstruction technology.

Method used

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  • Three-dimensional structure measuring device and measuring method of incident shock wave
  • Three-dimensional structure measuring device and measuring method of incident shock wave
  • Three-dimensional structure measuring device and measuring method of incident shock wave

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Embodiment Construction

[0035] In order to facilitate the understanding of those skilled in the art, the present invention will be further described below in conjunction with the embodiments and accompanying drawings, and the contents mentioned in the embodiments are not intended to limit the present invention.

[0036] refer to figure 1 As shown, a kind of incident shock wave three-dimensional structure measuring device of the present invention includes: wedge 1, Laval nozzle 2, background pattern plate 3, light source 4, bracket 5, guide rail 6, high-speed camera A7, high-speed camera B8, Equal straight pipeline 9, rotation angle plate 10, wherein,

[0037] The supersonic gas flow at the outlet of the Laval nozzle 2 generates an incident shock wave at the leading edge of the wedge 1 and extends to the lower wall of the straight pipe 9 . The material of the side walls of the straight pipes 9 is optical glass, which has high light transmission and is convenient for light transmission; the lower wall...

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Abstract

The invention relating to the field of aerodynamics discloses a three-dimensional structure measuring device and measuring method of an incident shock wave. The measuring device comprises Laval nozzle, an equal straight pipe, a tapered wedge, a rotary angle disk, a guide rail, a light source, a background pattern plate, a high speed camera, and the like. The measuring device having a simple structure is operated conveniently; and because the model employs the integrated flow / measurement design, three-dimensional reconstruction of the incident shock wave and measurement of the flow field density field and the wall friction field are realized.

Description

technical field [0001] The invention belongs to the technical field of aerodynamics, and specifically refers to a three-dimensional structure measurement device and method for incident shock waves based on background schlieren measurement technology and liquid crystal coating technology. Background technique [0002] In the study of the flow field of supersonic / hypersonic vehicles, the shock wave is a basic flow field structure, and the shock wave / shock wave and shock wave / boundary layer interference flow coupled with it have always been the field of high-speed aerodynamics. research hotspots and priorities. For a long time, many scholars have devoted themselves to the study of the three-dimensional flow field structure related to the shock wave, which is of great significance to the system design and engineering application of aircraft. [0003] At present, commonly used measurement methods for supersonic flow field containing shock waves in this field mainly include: high...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/06
CPCG01M9/06
Inventor 王成鹏徐培王英玉杨馨
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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