CN117750604A - Device for generating hypersonic particle flow by electric arc driving - Google Patents
Device for generating hypersonic particle flow by electric arc driving Download PDFInfo
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- CN117750604A CN117750604A CN202311680236.XA CN202311680236A CN117750604A CN 117750604 A CN117750604 A CN 117750604A CN 202311680236 A CN202311680236 A CN 202311680236A CN 117750604 A CN117750604 A CN 117750604A
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Abstract
The invention discloses a device for generating hypersonic particle flow by arc driving, which comprises a driving end, a buffer section, a driven section, an unloading section, a recovery tank, a vacuum and inflation system, a control system and a parameter testing and data acquisition system. The invention can drive and generate 20-60 Mach plasma flow, breaks through the upper limit of particle flow in the prior art, can be used for providing a ground superhigh heat, high enthalpy and hypersonic test environment and a diagnosis platform, and researching the radiation heating problem of an impact layer under the condition that earth and spark enter (reentry) and the interaction of hypersonic plasma flow and a target; the experimental and diagnostic device is provided for aerodynamic thermal analysis of hypersonic aircrafts, engineering design of thermal protection materials and improvement of radiation heating prediction models.
Description
Technical Field
The invention belongs to the technical field of shock wave physics and aerospace, and particularly relates to a device for generating hypersonic particle flow by arc driving.
Background
In order to generate radiation heating in the laboratory for studying earth and spark craft entry (reentry) conditions, providing the need for ground hyperthermia, high enthalpy and hypersonic environments, it is important to study radiation heating, aerodynamic thermal analysis, thermal protective materials, and high temperature unbalanced radiation transport prediction models in earth and spark entry (reentry) conditions, and to develop hypersonic mach (20-60) arc driven shock tubes and radiation photovoltaic diagnostic platforms.
The existing shock tube experimental device mainly generates high-speed shock waves in a gas, free piston and oxyhydrogen detonation arc driving mode, the driving modes are difficult to generate super-heat and high-enthalpy environments, and the requirements of super-heat and hypersonic particle flow cannot be met due to the limitation of the molecular mass of driving gas. The patent which is visible in China at present only has an arc discharge driving-based high Mach shock tube experimental device (patent number: ZL 202110598890.0), the patent mainly gives an explanation of the driving end of the arc discharge driving-based high Mach shock tube, the device can generate hypersonic shock waves of 40 Mach (14 km/s), but the driving end of the device is provided with an electric explosion inflation load cavity which is cylindrical, an explosion triggering metal wire high-current switch adopts a pneumatic pull-piston switch, and a diagnosis system for the light radiation characteristic of a shock compression layer is lacked, and hypersonic ions and targets are not interacted for testing, so that under the same energy loading condition, the further improvement of the energy density of the electric explosion gas load cavity and the flow speed of hypersonic particles generated by arc driving is limited, and the requirements of ultrahigh heat, high enthalpy and higher Mach number are difficult to meet, and the diagnosis of the light radiation characteristic of the shock compression layer and the physical parameters of the interaction of hypersonic ions and the targets is lacked. In view of the above, there is an urgent need to explore new mechanisms in the aspect of generating high energy density by arc driving, break through the technical bottleneck of the existing arc driving end, develop a shock tube device for generating hypersonic mach (20-60) particle flow by arc driving and an experimental device for heating optical diagnosis of an impact radiation layer and interaction between hypersonic particle flow and materials, provide high-heat, high-enthalpy and hypersonic environments, and provide technical support for researching radiation heating, aerodynamic thermal analysis, thermal protection materials and high-temperature unbalanced radiation transport theoretical modeling under the earth and spark entry (reentry) conditions.
Disclosure of Invention
In view of the above-mentioned problems with the background art, the present invention has as its object: it is intended to provide an arc-driven device for generating hypersonic particle flow.
In order to achieve the technical purpose, the invention adopts the following technical scheme:
an apparatus for generating hypersonic particle flow by arc driving, comprising
The driving end consists of a high-voltage power supply system, a power supply energy warehouse system, a collecting ring, an insulating sleeve load cavity (a cylindrical-conical-cylindrical gas driving load cavity of an electric explosion metal wire), a conducting switch, a charge-discharge current and voltage testing unit and a control and monitoring system;
the buffer section consists of a stainless steel tube, a vacuumizing/buffering air filling interface, a polyester plate reflecting diaphragm, a shock wave arrival time and a pressure testing unit;
the driven section is provided with a stainless steel metal pipe body, a pressure and shock wave speed testing unit, a shock wave arrival time and light radiation intensity testing unit, a spectrum and light radiation intensity testing unit and a driven section parameter testing window of the optical diagnosis platform are connected, and a vacuumizing/gas filling tested gas system is arranged on the metal pipe body;
an unloading section starting from the third diaphragm/blind plate to a kefir hypersonic nozzle at the outlet of the unloading tube;
the recovery tank consists of a stainless steel cylindrical metal shell, an exhaust waste gas valve, a vacuumizing system, a target object/target, a five-dimensional adjusting bracket, a particle flow speed, a spectrum, a high-speed camera shooting/imaging test system and the like;
the control system comprises a power supply energy store charge and discharge control system, a high-voltage power supply system, a charge and discharge start and stop control module and a parameter test and data acquisition control system, and is used for ensuring safety and realizing remote optical fiber isolation communication;
the vacuum and inflation system comprises a driving end driving cavity for vacuumizing/inflating driving gas, a buffer section for vacuumizing/inflating buffer gas, a driven section for vacuumizing/inflating tested gas at the front end and the rear end of the driven section, a large mechanical pump vacuumizing system at the tail part of the recovery tank and an exhaust valve;
the parameter testing and data acquisition system comprises a charging and discharging current and voltage testing unit at the driving end; the shock wave arrival time and pressure testing unit of the buffer section; the device comprises a pressure and shock wave speed testing unit, a shock wave arrival time and light radiation intensity testing unit, a spectrum and light radiation intensity testing unit and an optical diagnosis platform; the particle flow speed, spectrum and high-speed shooting/imaging test system for interaction of shock wave and material in the recovery tank comprises a data acquisition channel, a digitizer and computer hardware/software.
Preferably, the driving end comprises a cylindrical-conical-cylindrical metal wire explosion cavity with a variable driving gas load cavity structure, and the volume of the explosion cavity is about 1.3-2.6 liters, wherein the first cylindrical section is phi 6cm multiplied by 9cm, the diameter of the upper end of the conical section is phi 6cm, the diameter of the lower end of the conical section is phi 10cm, the length of the conical section is 12-38 cm, the diameter of the second cylindrical section is phi 10cm multiplied by 5cm, a high-current electromagnetic switch is adopted for triggering and conducting the explosion metal wire in the driving cavity, and the speed regulation range is 40-60 m/s.
Preferably, the buffer section comprises a stainless steel pipe body with the inner diameter of 10cm, the outer diameter of 13cm and the length of 3m, and is in butt joint with the tail end of the driven end, a second diaphragm isolates the buffer section from the driven section, the second diaphragm is a polyester plate with the optional thickness of 2.6-4.0 mu m, a thin aluminum coating is coated on the second diaphragm, the thin aluminum coating is used for reflecting the radiation of the driving gas so as to prevent the radiation heating of the tested gas, and the thickness of the second diaphragm is important for realizing high speed and is determined according to experimental optimization; the first diaphragm is positioned between the buffer section and the tail end of the cylindrical-conical-cylindrical metal wire explosion load cavity, the buffer section metal pipe body is respectively provided with a pressure sensor A, a pressure sensor B and a pressure sensor C at the positions 2m, 2.4m and 2.8m away from the first diaphragm, the pressure sensor measures the arrival time and the arrival pressure of shock waves, and the buffer section metal pipe body is connected with a vacuumizing/buffering gas filling system.
Preferably, the driven section is from the second diaphragm to the third diaphragm/blind plate at the tail end of the unloading section, and the metal pipe body of the driven section is 10cm in inner diameter, 13cm in outer diameter and 9 m in length; the third diaphragm can also be replaced by a blind plate, the blind plate is adopted to generate reflected shock waves, the tested gas is secondarily compressed, a pressure sensor D, a pressure sensor E, a pressure sensor F, a pressure sensor G, a photomultiplier PMT1, a photomultiplier PMT2 and a photomultiplier PMT3 are respectively arranged on a pipe body at a position 3m away from the second diaphragm, each 50cm distance is used for detecting pressure and shock wave speed, the photomultiplier is used for detecting shock wave arrival time and shock wave compression layer light radiation intensity, test windows are arranged at the positions of a metal pipe body at a driven section 6.6m and 6.8m away from the second diaphragm, the test windows are in butt joint with a spectrum and light radiation intensity test unit, the test windows consist of a monochromator + photomultiplier PMT 4/pressure sensor H, a monochromator + photomultiplier PMT 5/pressure sensor J, the monochromator + photomultiplier/pressure sensor is used for measuring the radiation intensity evolution characteristic of a reflected wave compression layer along with time, each 20cm interval is arranged on a metal pipe body of a driven section at a position 7m away from a second diaphragm, shock wave arrival time and light radiation intensity tests are carried out on the upper side and the lower side of the metal pipe body, the monochromator + photomultiplier/pressure sensor is composed of 12 sets of quick response pressure sensors/monochromators combined with photomultiplier PMTs, rectangular windows with the size of 12cm multiplied by 0.8mm are arranged on the left side and the right side at a position 7.8m away from the second diaphragm, the rectangular windows are made of magnesium fluoride (MgF 2) or lithium fluoride (LiF), the rectangular windows are butted with an optical diagnosis platform, the optical diagnosis platforms on the left side and the right side are respectively arranged on a left moving guide rail and a right moving guide rail which play a role of carrying, and the first vacuumizing/filling tested gas system and the second vacuumizing/filling tested gas system are respectively arranged at the position 1.5m and the position 8.6m away from the second diaphragm at the lower side of the pipe body.
Preferably, the interface from the third diaphragm/blind plate to the supersonic Rafier nozzle is an unloading section, the unloading section pipe body is composed of a 2m stainless steel pipe body, the unloading section extends into the recovery tank at a position 1.5m away from the third diaphragm/blind plate, and the supersonic Rafier nozzle is arranged at the tail end of the unloading section.
Preferably, the recovery tank is composed of two sections of cylindrical metal pipes, each section is 1m long and 1.5m in diameter, the two sections are in butt joint sealing, the front section is fixed, the other section can move on a guide rail, an independent vacuumizing system is arranged at the tail part of the recovery tank, an exhaust valve is arranged at the top part of the recovery tank, multiple flanges are arranged at two sides of the recovery tank and used for installing cables, an outlet of a supersonic Lafil nozzle is opposite to a target object/target, and the target object/target is installed on a five-dimensional adjusting support.
Preferably, the parameter testing and data acquisition system comprises a charging and discharging current and voltage testing unit at the driving end; the shock wave arrival time and pressure testing unit of the buffer section; the system comprises a pressure and shock wave speed testing unit, a shock wave arrival time and light radiation intensity testing unit, a spectrum and light radiation intensity testing unit and an optical diagnosis platform in a driven section; particle flow velocity, spectrum, high-speed camera/imaging test system of shock wave and material interaction in the recovery tank; in the optical diagnosis platform of the driven section, a sampling light beam enters a filtering unit through a sampling unit and an optical beam shrinking imaging assembly, and is incident to a spectrum measuring unit, and a detection device of the spectrum measuring unit comprises a monochromator, a photomultiplier, an ultraviolet resolution transient spectrometer, a visible space resolution transient spectrometer and a near infrared space resolution transient spectrometer; when testing Vacuum Ultraviolet (VUV) spectrum, a sampling unit, an optical beam-shrinking imaging component, a filtering unit, a monochromator, a photomultiplier and a vacuum ultraviolet spectrometer are required to be placed in a high vacuum box, and the vacuum degree of the vacuum box is below 10-5 Pa; the charge/discharge current measurement adopts a non-contact Rogowski coil, and the charge/discharge voltage measurement is performed in a voltage division manner; the shock wave arrival time and the pressure are measured by a pressure sensor; the time evolution of the radiation intensity and the arrival time measurement of the shock wave are combined with a photomultiplier by a monochromator; the ion flow velocity measurement adopts a Doppler laser interferometer; time and space resolution spectrum measurement adopts a stripe optical scanning camera; a camera for recording the particle stream interaction process with the target object/target; the transmission and processing system of the parameter test and data acquisition system consists of a data acquisition channel, a digitizer and computer hardware/software.
The invention has the beneficial effects that: the invention discloses a device for generating hypersonic particle flow by arc driving, which is a novel principle and a novel method for improving the energy density of driving gas, and the hypersonic particle flow generating device is designed by utilizing the novel technology, can be used for driving and generating 20-60 Mach plasma flow, breaks through the upper limit of the particle flow in the prior art, can be used for providing a ground superhigh heat, high enthalpy and hypersonic test environment and a diagnosis platform, and is used for researching the radiation heating problem of an impact layer under the condition of entering (reentry) of the earth and the spark and the interaction between hypersonic plasma flow and a target; the experimental and diagnostic device is provided for aerodynamic thermal analysis of hypersonic aircrafts, engineering design of thermal protection materials and improvement of radiation heating prediction models.
Drawings
The invention can be further illustrated by means of non-limiting examples given in the accompanying drawings;
FIG. 1 is a schematic view showing the composition of an embodiment of an apparatus for generating hypersonic particle flow by arc driving in accordance with the present invention;
FIG. 2 is a schematic view of an embodiment of an arc-driven hypersonic particle stream generating apparatus according to the present invention;
FIG. 3 is a schematic view showing the composition of an optical diagnostic platform in an embodiment of an apparatus for generating hypersonic particle flow by arc driving in accordance with the present invention;
the main reference numerals are as follows:
1. a driving end; 2. a buffer section; 3. a driven section; 4. an unloading section; 5. a recovery tank; 6. a vacuum and inflation system; 7. a control system; 8. the parameter testing and data acquisition system; 9. a first membrane; 10. a second membrane; 11. a third membrane; 12. a charge-discharge current-voltage test unit; 13. the shock wave arrival time and pressure testing unit; 14. a pressure and shock velocity test unit; 15. the shock wave arrival time and light radiation intensity testing unit; 16. a spectrum and light radiation intensity test unit; 17. an optical diagnostic platform; 18. particle flow speed, spectrum, high-speed camera/imaging test system;
1-1, a collecting ring; 1-2, an insulating layer; 1-3, cylindrical-conical-cylindrical wire explosion load chamber; 1-4, a driving end metal shell;
2-1, a buffer section metal pipe body;
3-1, a driven section metal pipe body; 3-2, rectangular window;
4-1, unloading the section metal pipe body; 4-2, supersonic Rafier nozzle; 4-3, a vacuum sealing section connected between the unloading section and the recovery tank;
5-1, target; 5-2, recovering the metal shell of the tank; 5-3, five-dimensional adjusting brackets;
6-1, driving the end to vacuumize/charge the driving gas system; 6-2, a buffer section vacuumizing/filling buffer gas system; 6-3, vacuumizing/filling the tested gas system in the first driven section; 6-4, vacuumizing/filling a tested gas system in the second driven section; 6-5, vacuumizing system; 6-6, exhaust valve;
9. a first membrane;
10. a second membrane;
11. a third membrane;
13-1, a pressure sensor A;13-2, a pressure sensor B;13-3, a pressure sensor C;
14-1, a pressure sensor D;14-2, a pressure sensor E;14-3, a pressure sensor F;14-4, a pressure sensor G;
15-1, photomultiplier PMT1;15-2, photomultiplier PMT2;15-3, photomultiplier PMT3;15-4, combining a pressure sensor/monochromator with a photomultiplier PMT;
16-1, monochromator+photomultiplier PMT 4/pressure sensor H;16-2, monochromator+photomultiplier PMT 5/pressure sensor J;
17-1, a sampling unit; 17-2, an optical attenuation imaging assembly; 17-3, a filtering unit; 17-4, a spectrum measuring unit; 17-5, left side optical diagnostic platform; 17-6, a right optical diagnostic platform; 17-7, a left moving guide rail; 17-8, right movable guide rail;
18-1, a flange plate; 18-2, an ion flow velocity measurement system; 18-3, high speed camera/imaging system; 18-4, radiation and spectral measurement system.
Detailed Description
In order that those skilled in the art will better understand the present invention, the following technical scheme of the present invention will be further described with reference to the accompanying drawings and examples.
An arc-driven hypersonic particle stream generating device shown in fig. 1 comprises a driving end 1, a buffer section 2, a driven section 3, an unloading section 4, a recovery tank 5, a control system 7, a vacuum and inflation system 6 and a parameter testing and data acquisition system 8.
The driving end 1 is shown in fig. 2, and the driving end 1 is composed of a power source energy storage system, a constant-current high-voltage power supply, a collecting ring 1-1, an insulating layer 1-2, a variable-speed heavy-current explosion metal wire triggering and conducting electromagnetic switch, an insulating variable cavity, a driving end vacuumizing/charging driving gas system 6-1, a charging and discharging current and voltage testing unit 12 and an arc driving control and monitoring system. The insulation variable cavity is a cylindrical-conical-cylindrical metal wire explosion cavity 1-3, and the volume can be variable from 1.3 to 2.6 liters; the first cylindrical section of the insulation variable cavity structure is phi 6cm multiplied by 9cm, the diameter of the upper end of the conical section is phi 6cm, the diameter of the lower end of the conical section is phi 10cm, the length of the conical section is 12-38 cm, and the second cylindrical section is phi 10cm multiplied by 5cm. The speed adjustable range of the explosion metal wire triggering and conducting high-current electromagnetic switch in the driving cavity is 40-60 m/s; the power supply energy warehouse system comprises a capacitor group formed by connecting a plurality of capacitors in parallel according to the requirement, wherein each capacitor group gathers electric energy to the collecting ring 1-1 through two low-inductance coaxial cables to provide energy for driving gas in the explosive wire load cavity, and the energy can be regulated through the number of the capacitors and the voltage. Under the condition of feeding loading energy, the energy density of the driving gas can be optimally increased according to the speed of the particle flow to be generated, namely, the driving gas is realized by optimizing the configuration and the volume of the cylindrical-conical-cylindrical metal wire explosion cavity 1-3, the pressure of the driving gas, the molecular mass and the type of the driving gas, the selection of the material of the electric explosion metal wire, the material and the thickness of the first diaphragm 9 and the like.
The buffer section 2 is formed by butting the stainless steel buffer section metal tube body 2-1 with the inner diameter of 10cm, the outer diameter of 13cm and the length of 3m with the tail end of the cylindrical-conical-cylindrical metal wire explosion cavity 1-3, the buffer section 2 is isolated from the driven section 3 by the second diaphragm 10, the second diaphragm 10 is a polyester plate with the optional thickness of 2.6-4.0 mu m, the second diaphragm 10 is provided with a thin aluminum coating, the coating is used for reflecting the radiation of the driving gas, so that the radiation heating of the tested gas is prevented, the thickness of the second diaphragm 10 is an important parameter affecting the shock wave speed, and the thickness needs to be determined according to experimental optimization. And a shock wave arrival time and pressure testing unit 13 is arranged on the buffer section metal pipe body 2-1. A pressure sensor A (13-1), a pressure sensor B (13-2) and a pressure sensor C (13-3) are respectively arranged at the positions with the distances of 2m, 2.4m and 2.8m from the first diaphragm 9, and the pressure sensors measure the arrival time and the pressure of shock waves. The buffer section metal pipe body 2-1 is connected with a buffer section vacuumizing/filling buffer gas system 6-2, and the buffer gas filling pressure is determined by optimizing parameters of the length of the buffer section and the second diaphragm 10, and is generally selected to be 10 to 1000 times of the measured gas pressure. The type of buffer gas can be optimally selected by the desired particle flow velocity or shock velocity to be generated.
The driven section 3 is driven section 3 from the second diaphragm 10 to the third diaphragm 11/blind plate at the tail end of the unloading section 4; the metal tube body 3-1 of the driven section has an inner diameter of 10cm, an outer diameter of 13cm and a length of 9 m; the third diaphragm 11/blind plate can also be replaced by a blind plate, when selected, the radiation properties of the reflected shock wave and the compression layer can be studied. On the tube body at a position 3m away from the second diaphragm (10), a pressure sensor D (14-1), a pressure sensor E (14-2), a pressure sensor F (14-3), a pressure sensor G (14-4), a photomultiplier PMT1 (15-1), a photomultiplier PMT2 (15-2) and a photomultiplier PMT3 (15-3) are respectively arranged at 50cm intervals, the pressure sensor is used for detecting the pressure and the shock velocity, and the photomultiplier is used for detecting the arrival time of the shock and the light radiation intensity of a shock compression layer. And a test window is arranged at the position, 6.6m and 6.8m away from the second diaphragm (10), of the driven section metal pipe body 3-1, the test window is in butt joint with a spectrum and light radiation intensity test unit 16, and the spectrum and light radiation intensity test unit 16 consists of a monochromator, a photomultiplier tube PMT 4/pressure sensor H (16-1) and a monochromator, a photomultiplier tube PMT 5/pressure sensor J (16-2), wherein the monochromator, the photomultiplier tube/pressure sensor is used for measuring the radiation intensity evolution characteristic of a reflected wave compression layer along with time. The shock wave arrival time and the light radiation intensity are tested on the driven section metal tube body 3-1 at intervals of 20cm at the position 7m away from the second diaphragm (10), and the shock wave arrival time and the light radiation intensity are detected on the upper side and the lower side by 12 sets of fast-response pressure sensors/monochromators combined with photomultiplier PMT (15-4) to detect the shock wave arrival time and the light radiation intensity evolution history.
Rectangular windows 3-2 are arranged on the left side and the right side of the position 7.8m away from the second diaphragm (10), the size of the rectangular window 3-2 is 12cm multiplied by 0.8mm, the material is magnesium fluoride (MgF 2) or lithium fluoride (LiF), and the optical diagnosis platform 17 is abutted through the rectangular window 3-2. The left optical diagnostic platform 17-5 and the right optical diagnostic platform 17-6 are mounted on the left and right moving rails 17-7 and 17-8, respectively, which serve as carriers. A first vacuumizing/inflating tested gas system (6-3) is arranged on the lower side of a driven section metal tube body 3-1 which is 1.5m away from a second diaphragm (10), and a second vacuumizing/inflating tested gas system (6-4) is arranged at 8.6m away from the second diaphragm (10). If the process of re-entering the earth atmosphere is to be studied, the driven section 3 is inflated with air, and the pressure can correspond to the altitude pressure of the nearby space; if the study is carried into the earth atmosphere, a H2-He mixture with a gas ratio of 89% to 11% by volume is charged into the driven section 3.
The unloading section 4 comprises an unloading section metal pipe body 4-1, a vacuum sealing section 4-3 connected between the unloading section and a recovery tank, and an interface from the unloading section to a supersonic Rafier nozzle 4-2, wherein the unloading section 4 is an unloading section 4, and the unloading section metal pipe body 4-1 consists of a stainless steel pipe body with the length of 2 m; at a distance of 1.5m from the third membrane 11/blind plate, the unloading section 4 protrudes into the recovery tank 5, and the unloading section 4 can discharge exhaust gases, broken membranes etc. into the recovery tank 5. A supersonic kefir nozzle 4-2 is mounted at the end of the unloading section 4 and can be used to study the interaction of supersonic high temperature gas particle (ion) streams with the target object/target 5-1.
The recovery tank 5 is a metal shell 5-2 of the recovery tank, which is formed by two sections of cylindrical metal pipes, each section is 1m long and 1.5m in diameter, the two sections are in butt joint sealing, wherein the front section is fixed, and the other section can move on a guide rail. The tail of the recovery tank 5 is provided with an independent vacuumizing system 6-5, the top of the recovery tank is provided with a waste gas exhaust valve 6-6, both sides of the recovery tank 5 are provided with various flanges 18-1 for installing cables of a control system 7 and a parameter testing and data acquisition system 8, a supersonic Lafil nozzle 4-2 in the recovery tank 5 is opposite to a target object/target 5-1, and the target object/target 5-1 is arranged on a five-dimensional adjusting bracket 5-3.
The control system 7 comprises a power supply energy store charge and discharge control system, a test and data acquisition control module, a device start-stop control module and the like, and mainly achieves the functions of charge and discharge control, data acquisition trigger control, emergency stop operation control and the like of a power supply driving system.
The vacuum and inflation system 6 comprises a driving end vacuumizing/inflating driving gas system 6-1 of a driving end 1 cylindrical-conical-cylindrical driving gas load cavity 1-3 of an electric explosion metal wire, a vacuumizing/inflating buffer gas system 6-2 of a buffer section 2, a driven section first vacuumizing/inflating tested gas system (6-3) at the front end of a driven section, a driven section second vacuumizing/inflating tested gas system (6-3) at the rear end of the driven section, a large-scale mechanical pumping vacuum system 6-5 at the tail part of a recovery tank 5 and a waste gas discharge valve 6-6. The vacuum and inflation system is provided with a vacuum gauge and a barometer.
The parameter testing and data acquisition system 8 is composed of a data testing, transmitting and processing system. The parameter test and data acquisition 8 comprises a charge-discharge current voltage test unit 12 at the driving end 1; a shock wave arrival time and pressure test unit 13 at the buffer section 2; a pressure and shock wave speed test unit 14, a shock wave arrival time and light radiation intensity test unit 15, a spectrum and light radiation intensity test unit 16 and an optical diagnosis platform 17 of the driven section 3; a particle flow velocity, spectral, high speed camera/imaging test system 18 for interaction of shock waves with material is installed in recovery tank 5.
The above described optical diagnostics in the recovery tank 5 as shown in fig. 2, the particle flow velocity, spectrum, high speed camera/imaging test system 18 is comprised of an ion flow velocity measurement system 18-2, a high speed camera/imaging system 18-3, and a radiation and spectrum measurement system 18-4.
As shown in FIG. 3, the optical diagnostic platform 17 of the driven section 3 makes the sampling beam coming out of the rectangular window 3-2 enter the filtering unit 17-3 through the butt joint sampling unit 17-1 and the optical beam shrinking imaging assembly 17-2, and then enter the spectrum measuring unit 17-4, and the spectrum measuring unit 17-4 is provided with a monochromator, a photomultiplier, an ultraviolet resolution transient spectrometer, a visible spatial resolution transient spectrometer and a near infrared spatial resolution transient spectrometer. The optical beam-shrinking imaging assembly 17-2 is composed of a plane reflecting mirror and a concave mirror, the beam caliber of the sampling beam of the rectangular window 3-2 after being shrunk is matched with the slit of the spectrum measuring unit 17-4, and the rectangular window is imaged to the incident slit of the spectrum measuring unit 17-4. According to the test requirements, the filter unit 17-3 added before the entrance of the spectrum measuring unit 17-4 carries out filter processing on the light beam entering the spectrum measuring unit 17-4, selects the spectrum range and eliminates the secondary spectrum influence. When testing Vacuum Ultraviolet (VUV) spectrum, the sampling unit 17-1, the optical beam-shrinking imaging component 17-2, the filter unit 17-3, the monochromator, the photomultiplier and the vacuum ultraviolet spectrometer are placed in a high vacuum box, the vacuum degree of the vacuum box is below 10-5Pa, and a molecular pump is adopted for vacuumizing.
The charge/discharge current measurement adopts a non-contact rogowski coil, the charge/discharge voltage measurement adopts a partial pressure mode, the shock wave arrival time and the pressure measurement adopt pressure sensors, the time evolution of radiation intensity and the shock wave arrival time measurement adopt a monochromator combined with a photomultiplier, the ion flow velocity measurement adopts a Doppler laser interference velocity tester, the light radiation and spectrum measurement and the time and space resolution spectrum measurement adopt a stripe optical scanning camera, and a camera/imaging system is used for recording the interaction process of particle flow and a target object/target 5-1. The transmission and processing system of the parameter testing and data acquisition system 8 consists of a data acquisition channel, a digitizer, computer hardware/software.
The intensity and wavelength of the optical radiation in the parametric test and data acquisition system 8 need to be calibrated before the experiment. A standard light source, such as a mercury argon lamp, is used for calibrating the wavelength by utilizing an optical radiation calibration system; standard light sources for calibrating the intensity of the light radiation are special lamps such as deuterium lamps, bromine tungsten lamps, for which absolute irradiance and irradiance calibration are known.
In the experiment, firstly, the cylindrical-conical-cylindrical metal wire explosion load cavity 1-3 of the driving end 1, the buffer section 2, the driven section 3 and the recovery tank 5 are vacuumized, and the vacuum degree of each part is checked to enable the parts to reach a high vacuum state; then, the cylindrical-conical-cylindrical metal wire explosion load cavity 1-3 is filled with driving gas, and the driving gas selects small molecular weight gas such as helium, hydrogen and the like in order to obtain hypersonic shock waves; the buffer section 2 is filled with buffer gas, the type of the buffer gas can be optimally selected by the particle flow speed or shock wave speed required to be generated, and the pressure is generally 10 to 1000 times of the pressure of the detected gas; the driven section 3 is filled with the tested gas, and the tested gas is determined according to the research object, for example, air and H2-He mixed gas (89% to 11%) are respectively adopted in the process of researching the earth atmosphere and loading the earth atmosphere. Setting a charging voltage and a capacitor voltage, starting charging, ending charging after the charging reaches a set value, starting an electromagnetic trigger switch, triggering an explosion metal wire in a driving cavity to discharge, and recording a discharging current and a voltage by a driving end charging and discharging current voltage testing unit 12; the explosion metal wire in the driving cavity discharges to enable the driving gas to generate high-temperature plasma, so that the driving gas reaches tens of thousands degrees and the transient pressure reaches the rupture pressure, the first diaphragm 9 breaks the membrane, and meanwhile, the parameter testing and data acquisition system 8 is in a data acquisition waiting state; the shock wave enters the buffer section 2, and the light radiation of the driving gas is reflected by the second diaphragm 10, so that the radiation heating of the tested gas is effectively prevented; when the shock wave reaches the second diaphragm 10, the second diaphragm 10 breaks the diaphragm, and the shock wave enters the driven section 3; during the shock wave propagation process, the test equipment of the buffer section 2 and the driven section 3 respectively record the arrival time, pressure, time evolution of the light radiation intensity, time and space resolution spectrum of the shock wave; when the shock wave reaches the third diaphragm 11/blind plate, the third diaphragm 11/blind plate breaks the diaphragm, the shock wave and the particle flow enter the unloading section 4, the particle flow passes through the supersonic Lafil nozzle 4-2, hypersonic particle flow is generated to interact with the target object/target 5-1, and the test system in the recovery tank 5 records data such as particle flow speed, spectrum, high-speed shooting/imaging and the like respectively. Finally, the residual electric energy of the power supply energy reservoir of the driving end 1 is discharged, the exhaust valve 6-6 is opened, the recovery tank 5 is opened after exhaust gas is discharged, the recovered sample in the target object/target 5-1 is taken out, and the chemical reaction, the change of physical properties of the material and the like generated by the interaction of particle flow and the material are analyzed according to the surface ablation and the surface composition change of the target object/target 5-1.
The above embodiments are merely illustrative of the principles of the present invention and its effectiveness, and are not intended to limit the invention. Modifications and variations may be made to the above-described embodiments by those skilled in the art without departing from the spirit and scope of the invention. Accordingly, it is intended that all equivalent modifications and variations of the invention be covered by the claims of this invention, which are within the skill of those skilled in the art, can be made without departing from the spirit and scope of the invention disclosed herein.
Claims (7)
1. An apparatus for generating hypersonic particle flow by arc driving, characterized in that: the device comprises a driving end (1), a buffer section (2), a driven section (3), an unloading section (4), a recovery tank (5), a vacuum and inflation system (6), a control system (7) and a parameter testing and data acquisition system (8).
2. An arc driven hypersonic particle stream generating apparatus as claimed in claim 1 wherein: the drive end (1) comprises:
the variable cavity structure is a cylindrical-conical-cylindrical metal wire explosion load cavity (1-3) with the volume of 1.3-2.6 liters, wherein the first cylindrical section isThe diameter of the upper end of the conical section is +.>The diameter of the lower end is +.>The length is 12-38 cm, the second cylindrical section is +.>The explosion metal wire in the explosion load cavity (1-3) of the column-cone-column metal wire is triggered and conducted by a high-current electromagnetic switch, and the adjustable speed range is 40-60 m/s.
3. An arc driven hypersonic particle stream generating apparatus as claimed in claim 2 wherein: the buffer section (2) is formed by butt joint of a buffer section metal pipe body (2-1) with the inner diameter of 10cm, the outer diameter of 13cm and the length of 3m and the tail end of a cylindrical-conical-cylindrical metal wire explosion load cavity (1-3), in addition, a second diaphragm (10) isolates the buffer section (2) from a driven section (3), the second diaphragm (10) is a polyester plate with the optional thickness of 2.6-4.0 mu m, a thin aluminum coating is coated on the second diaphragm (10), and a buffer section vacuumizing/buffering gas filling system (6-2) is arranged outside the buffer section metal pipe body (2-1); on the buffer section metal tube body (2-1), a first diaphragm (9) is positioned between the buffer section (2) and the tail end of the cylindrical-conical-cylindrical metal wire explosion load cavity (1-3), the buffer section metal tube body (2-1) is respectively provided with a pressure sensor A (13-1), a pressure sensor B (13-2) and a pressure sensor C (13-3) at positions which are 2m, 2.4m and 2.8m away from the first diaphragm (9), and the arrival time and the arrival pressure of shock waves are measured.
4. A device for generating hypersonic particle flow driven by an electric arc as claimed in claim 3, characterized in that: the driven section (3) comprises:
a driven section metal pipe body (3-1) with the size of 10cm in inner diameter, 13cm in outer diameter and 9 m in length is provided with a third diaphragm (11) or a blind plate between the driven section (3) and the unloading section (4);
the metal tube body (3-1) of the driven section starts at a position 3 meters away from the second diaphragm (10), and a pressure sensor D (14-1), a pressure sensor E (14-2), a pressure sensor F (14-3), a pressure sensor G (14-4), a photomultiplier PMT1 (15-1), a photomultiplier PMT2 (15-2) and a photomultiplier PMT3 (15-3) are respectively arranged at intervals of 50cm, so that the pressure, the arrival time of shock waves and the light radiation intensity of a shock compression layer are respectively detected;
the method comprises the steps that a test window is arranged at a driven section metal pipe body (3-1) 6.6m and 6.8m away from a second diaphragm (10), the test window is connected with a spectrum and light radiation intensity test unit, the spectrum and light radiation intensity test unit consists of a monochromator, a photomultiplier PMT 4/a pressure sensor H (16-1) and a monochromator, a photomultiplier PMT 5/a pressure sensor J (16-2), the radiation intensity evolution characteristic of a reflected wave compression layer is measured, shock wave arrival time and light radiation intensity tests are carried out on the driven section metal pipe body (3-1) 7m away from the second diaphragm (10) at intervals of 20cm, and a structure for carrying out the test consists of 12 sets of fast-response pressure sensors/monochromators combined with a photomultiplier PMT (15-4) and is used for detecting the shock wave arrival time and light radiation intensity evolution history;
rectangular windows (3-2) are arranged on the left side and the right side of the position 7.8m away from the second diaphragm (10), the size of the rectangular windows (3-2) is 12cm multiplied by 0.8mm, the rectangular windows (3-2) are made of magnesium fluoride or lithium fluoride, the rectangular windows (3-2) are in butt joint with an optical diagnosis platform (17), and a first optical diagnosis platform (17-5) on the left side and a second optical diagnosis platform (17-6) on the right side are respectively arranged on a left movable guide rail (17-7) and a right movable guide rail (17-8) which serve as carrying functions;
the first driven section vacuumizing/inflating tested gas system (6-3) and the second driven section vacuumizing/inflating tested gas system (6-4) are respectively arranged at the position 1.5m away from the second diaphragm (10) and at the lower side of the driven section metal pipe body (3-1) at the position 8.6m away from the second diaphragm.
5. An arc driven hypersonic particle stream generating apparatus as claimed in claim 4 wherein:
from a third diaphragm (11) or a blind plate, the ultrasonic Lafeil nozzle is arranged at the joint of the unloading section metal pipe body (4-1), the unloading section (4) and the recovery tank (5) through a vacuum sealing section (4-3) connected with the unloading section metal pipe body (4-1), the unloading section metal pipe body (4-1) consists of a stainless steel pipe body with the length of 2m, the unloading section (4) extends into the recovery tank (5) at the position 1.5m away from the third diaphragm (11) or the blind plate, and the ultrasonic Lafeil nozzle (4-2) is arranged at the tail end of the unloading section (4).
6. An arc driven hypersonic particle stream generating apparatus as in claim 5 wherein: the metal shell (5-2) of the recovery tank is composed of two sections of cylindrical metal tubes, each section is 1m long and 1.5m in diameter, the two sections are in butt joint sealing, the front section is fixed, the other section can move on a guide rail, an independent vacuumizing system (6-5) is arranged at the tail part of the recovery tank (5), an exhaust valve (6-6) is arranged at the top part of the recovery tank, flanges (18-1) for installing a control system (7) and a parameter testing and data collecting system (8) are arranged on two sides of the recovery tank (5), the outlet of a Lafel nozzle (4-2) is opposite to a target object/target (5-1), and the target object/target (5-1) is arranged on a five-dimensional adjusting bracket (5-3).
7. The arc driven hypersonic particle stream generating apparatus as set forth in claim 6, wherein: the parametric test and data acquisition (8) comprises:
a charge-discharge current-voltage test unit (12) for driving the end (1); the shock wave arrival time and pressure testing unit (13) is arranged at the buffer section (2); the device comprises a pressure and shock wave speed testing unit (14) arranged on a driven section (3), a shock wave arrival time and light radiation intensity testing unit (15), a spectrum and light radiation intensity testing unit (16) and an optical diagnosis platform (17); a particle flow velocity, spectral, high-speed camera/imaging test system (18) disposed within the recovery tank (5) for interaction of the shock wave with the material;
in an optical diagnosis platform (17) of the driven section (3), a sampling light beam enters a sampling unit (17-1), an optical beam-shrinking imaging component (17-2) and a filtering unit (17-3) through a rectangular window (3-2) and is incident to a spectrum measuring unit (17-4);
the particle flow speed, spectrum and high-speed shooting/imaging test system (18) consists of an ion flow speed measuring system (18-2), a high-speed shooting/imaging system (18-3) and a radiation and spectrum measuring system (18-4);
the charge and discharge current measurement adopts a non-contact Rogowski coil, and the charge and discharge voltage measurement is performed in a voltage division mode;
the shock wave arrival time and the pressure are measured by a pressure sensor;
the time evolution of the radiation intensity and the arrival time measurement of the shock wave are combined with a photomultiplier by a monochromator;
the ion flow velocity measurement adopts a Doppler laser interferometer;
time and space resolution spectrum measurement adopts a stripe optical scanning camera;
a camera for recording the interaction of the particle stream with the target object/target (5-1);
the data transmission and processing of the parameter testing and data acquisition system (8) consists of a data acquisition channel, a digitizer and computer hardware/software.
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| CN202311680236.XA CN117750604A (en) | 2023-12-07 | 2023-12-07 | Device for generating hypersonic particle flow by electric arc driving |
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| CN202311680236.XA CN117750604A (en) | 2023-12-07 | 2023-12-07 | Device for generating hypersonic particle flow by electric arc driving |
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