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Arc discharge driving-based high-Mach shock tube experimental device

A technology of arc discharge and experimental equipment, applied in the aerospace field, can solve problems such as difficult to reach Mach number, upper limit of shock wave velocity, difficult to meet research needs, etc.

Active Publication Date: 2021-06-25
INST OF FLUID PHYSICS CHINA ACAD OF ENG PHYSICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Existing shock tube experimental devices mainly generate high-speed shock waves through mechanical drive or detonation drive. Due to the limitations of physical mechanisms such as gas molecular heat conduction, these two types of drive methods have an upper limit on the shock wave speed, which is difficult to achieve. Meet higher Mach number requirements
At present, the shock tubes or large-scale wind tunnel shock wave simulation facilities built in my country can achieve a Mach number less than 20 Mach, and the corresponding shock wave speed is about 6~7km / s, which is difficult to meet the research needs of higher shock wave speed.

Method used

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  • Arc discharge driving-based high-Mach shock tube experimental device
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  • Arc discharge driving-based high-Mach shock tube experimental device

Examples

Experimental program
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Effect test

Embodiment 1

[0055] Based on the high Mach shock tube experimental device driven by arc discharge developed by the present invention, the specific implementation parameters given in this embodiment: the shape of the explosion chamber is cylindrical, its diameter is 10 cm, its length is 25 cm, and its volume is about 2 L. Helium is selected as the working gas with a pressure of 0.5Mpa. A single tungsten wire is selected as the electric explosion wire, with a diameter of about 0.1mm. The diaphragm material is aluminum, with a thickness of 1.5mm, engraved with cross grooves, and a length of 8cm; the power supply energy storage system is composed of eight 50μF capacitors connected in parallel, the working voltage is 32kV, and the discharge current is about 0.8MA; the pressure sensor is driven at an interval of 25cm layout on the segment.

[0056] Experiments were carried out with the experimental device configured above, and the experimental results were as follows: Figure 3a and Figure 3...

Embodiment 2

[0058] Based on the high Mach shock tube experimental device driven by arc discharge developed by the present invention, the specific implementation parameters given in this embodiment are: the shape of the explosion chamber is cylindrical, its diameter is 10 cm, its length is 25 cm, and its volume is about 2 L , also choose helium as the working gas, the pressure is 0.1Mpa. A single tungsten wire with a diameter of about 0.2mm is selected for the electric explosion metal wire; stainless steel is selected for the diaphragm material, the thickness is 1.0mm, and the cross groove is engraved, and the length is 6cm; 32kV, the discharge current is about 1.0MA; the pressure sensors are arranged on the driven section at intervals of 25cm.

[0059] Through the test method in Example 1, it can be calculated that the shock wave velocity that can be generated by the experimental device in this implementation is Mach 38.1.

Embodiment 3

[0061] Based on the high Mach shock tube experimental device driven by arc discharge developed by the present invention, the specific implementation parameters given in this embodiment are: the shape of the explosion chamber is cylindrical, its diameter is 10 cm, its length is 25 cm, and its volume is about 2 L , choose helium as the working gas, the pressure is 1Mpa, the electric explosion metal wire chooses a single copper wire, the diameter is about 0.5mm; the diaphragm material chooses aluminum, the thickness is 4.0mm, engraved with a cross groove, and the length is 6cm; the power supply energy storage system It is composed of eight 50μF capacitors connected in parallel, the working voltage is 36kV, and the discharge current is about 0.6MA. The pressure sensors are arranged on the driven section at intervals of 25cm.

[0062] Through the test method in Example 1, it can be calculated that the shock wave velocity that can be generated by the experimental device in this imple...

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Abstract

The invention discloses an arc discharge driving-based high-Mach shock tube experimental device, which comprises a power supply energy library system, a driving section, a driven section, a control system, a vacuum system and a test and data acquisition system; the power supply energy library system provides current for the driving section, the driving section generates electric explosion under the action of large current, therefore, high-temperature and high-pressure gas is generated in the explosion cavity of the driving section, the diaphragm between the driven section and the driving section is broken through, and high-speed shock waves are formed in the driven section. The invention discloses a high-Mach shock tube experimental device based on arc discharge driving, which is a shock tube experimental device designed based on a new principle and a new method, and can generate at least 40-Mach (about 14 km / s) hypersonic shock waves. A novel experimental device is provided for researching the scientific problems of loading real gas aerodynamic heat into the atmosphere under the hypersonic speed condition, the physical process of gas dynamics, thermal protection materials of aircrafts, structural design and the like.

Description

technical field [0001] The invention belongs to the field of aerospace, in particular to a high Mach shock tube experimental device driven by arc discharge. Background technique [0002] As a technology with important military applications, hypersonic aircraft has attracted worldwide attention. Shock wave is a very important flow field structure in the flow field of hypersonic vehicle. Ground simulation facilities such as shock tunnels and shock tubes are an important way to carry out research and exploration of hypersonic vehicle atmosphere or planetary reentry processes. However, as the speed and altitude of the aircraft continue to increase, the shock wave velocity of ground simulation devices such as shock tubes also requires a higher Mach number. [0003] Existing shock tube experimental devices mainly generate high-speed shock waves through mechanical drive or detonation drive. Due to the limitations of physical mechanisms such as gas molecular heat conduction, these...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/00G09B23/12G09B23/18
CPCG01M9/00G09B23/12G09B23/18
Inventor 肖金水马勋顾云军杨光李洪涛陈其峰邓维军栾崇彪康传会李松杰丁明军檀妹静高扬周禹于明星李潞宁
Owner INST OF FLUID PHYSICS CHINA ACAD OF ENG PHYSICS