CN113597079A - Electronic accelerator device for lunar surface charging environment simulation - Google Patents
Electronic accelerator device for lunar surface charging environment simulation Download PDFInfo
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- CN113597079A CN113597079A CN202110765197.8A CN202110765197A CN113597079A CN 113597079 A CN113597079 A CN 113597079A CN 202110765197 A CN202110765197 A CN 202110765197A CN 113597079 A CN113597079 A CN 113597079A
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- vacuum
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- electron gun
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- vacuum chamber
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05H—PLASMA TECHNIQUE; PRODUCTION OF ACCELERATED ELECTRICALLY-CHARGED PARTICLES OR OF NEUTRONS; PRODUCTION OR ACCELERATION OF NEUTRAL MOLECULAR OR ATOMIC BEAMS
- H05H5/00—Direct voltage accelerators; Accelerators using single pulses
- H05H5/02—Details
- H05H5/03—Accelerating tubes
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05H—PLASMA TECHNIQUE; PRODUCTION OF ACCELERATED ELECTRICALLY-CHARGED PARTICLES OR OF NEUTRONS; PRODUCTION OR ACCELERATION OF NEUTRAL MOLECULAR OR ATOMIC BEAMS
- H05H5/00—Direct voltage accelerators; Accelerators using single pulses
- H05H5/02—Details
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05H—PLASMA TECHNIQUE; PRODUCTION OF ACCELERATED ELECTRICALLY-CHARGED PARTICLES OR OF NEUTRONS; PRODUCTION OR ACCELERATION OF NEUTRAL MOLECULAR OR ATOMIC BEAMS
- H05H7/00—Details of devices of the types covered by groups H05H9/00, H05H11/00, H05H13/00
- H05H7/14—Vacuum chambers
Abstract
The invention provides an electronic accelerator device for lunar surface charging environment simulation, and belongs to the technical field of space environment simulation. The problem of the simulation of the charging environment on the surface of the existing moon is solved. The electron gun is connected with the accelerating tube, the electron gun is connected with an electron gun power supply, the electron gun comprises an anode, a cathode assembly, a focusing electrode, a high-voltage corona ring and a filament power supply connector, one end of the focusing electrode is provided with the cathode assembly, the other end of the focusing electrode is connected with the filament power supply connector, the anode is arranged at the front end of the cathode assembly, the high-voltage corona ring is arranged on the outer side of the filament power supply connector, the accelerating tube comprises a ceramic tube, a grading ring and an electrode plate, and the grading ring is arranged on the outer side of the ceramic tube. The method is mainly used for lunar surface charging environment simulation.
Description
Technical Field
The invention belongs to the technical field of space environment simulation, and particularly relates to an electronic accelerator device for lunar surface charging environment simulation.
Background
The moon is the only natural satellite of the earth, and the moon exploration is always the hot topic of the Chinese spaceflight, however, the extremely severe environments of vacuum, high and low temperature, charged dust and the like on the surface of the moon are a great test for moon-based equipment (including landers, patrollers, robots, detectors and the like) and lunar astronauts, especially the charged moon dust, and the tiny moon dust is easy to charge under the actions of approximate vacuum, huge temperature difference, solar wind, ultraviolet irradiation and electronic radiation of the moon. The charged lunar dust has strong adsorption force and is adhered and accumulated on various devices which can be contacted under the action of electrostatic force. The lunar surface static electricity and the electrostatic lunar dust have serious influence on lunar equipment, and the lunar dust floating due to the electrostatic action can block the detection sight, cover the surface of the detection equipment by adsorption and even enter the instrument equipment carried by the lunar probe. The lunar dust entering the lunar probe acts on an optical system, a power supply system, a thermal control system and even a astronaut system of the lunar probe, so that the problems of visual blurring, reading error, sealing failure, material abrasion, reduction of the efficiency of the thermal control system and the power supply system, inhalation and allergy of astronauts and the like are caused. Therefore, the simulation of the charged lunar dust is significant when the lunar environment is simulated.
Disclosure of Invention
The invention provides an electron accelerator device for lunar surface charging environment simulation, aiming at solving the problems in the prior art.
In order to achieve the purpose, the invention adopts the following technical scheme: an electron accelerator device for simulating a moon surface charging environment comprises an electron gun, an accelerating tube, a vacuum system, a magnet system, a beam measuring system and a control system, wherein the electron gun is connected with the accelerating tube, the electron gun is connected with an electron gun power supply, the electron gun comprises an anode, a cathode component, a focusing electrode, a high-voltage corona ring and a filament power supply connector, one end of the focusing electrode is provided with the cathode component, the other end of the focusing electrode is connected with the filament power supply connector, the anode is arranged at the front end of the cathode component, the high-voltage corona ring is arranged on the outer side of the filament power supply connector, the accelerating tube comprises a ceramic tube, a grading ring and an electrode plate, the grading ring is arranged on the outer side of the ceramic tube, the electrode plate is arranged on the inner side of the ceramic tube, the grading ring is connected with the electrode plate, the vacuum system comprises a vacuum pipeline, a vacuum valve and a vacuum pump, the vacuum pipeline comprises three six-way joints, two adapter flanges, two sections of stainless steel vacuum chambers and a section of ceramic vacuum chamber, wherein the three six-way joints are respectively a first six-way joint, a second six-way joint and a third six-way joint, the two adapter flanges are respectively a first adapter flange and a second adapter flange, the two sections of stainless steel vacuum chambers are respectively a first stainless steel vacuum chamber and a second stainless steel vacuum chamber, one end of the first six-way joint is butted with the accelerating tube, the other end of the first six-way joint is connected with one end of the first stainless steel vacuum chamber through the first adapter flange, the other end of the first stainless steel vacuum chamber is connected with one end of the second six-way joint, the other end of the second six-way joint is connected with one end of the second stainless steel vacuum chamber, the other end of the second stainless steel vacuum chamber is connected with one end of the third six-way joint, and the other end of the third six-way joint is connected with the ceramic vacuum chamber through the second adapter flange, the utility model discloses a laser beam measuring device, including ceramic vacuum chamber, first six-way joint, magnet system, correction magnet, control system, scanning magnet power, electron gun power, vacuum pump and beam measurement system control, ceramic vacuum chamber links to each other with the vacuum valve, the lower extreme interface that first six-way joint and second six-way joint all link to each other with the vacuum pump, the last port of three six-way joint links to each other with beam measurement system, the magnet system includes magnetic lens, correction magnet and scanning magnet, magnetic lens links to each other with the magnetic lens power, correction magnet links to each other with the scanning magnet power, correction magnet sets up on first stainless steel vacuum chamber, scanning magnet quantity is two, and two scanning magnets all set up on ceramic vacuum chamber, control system links to each other with magnetic lens power, correction magnet power, scanning magnet power, electron gun power, vacuum pump and beam measurement system control respectively.
Still further, the beam measurement system includes a fluorescent target and a faraday cage.
Furthermore, the electron gun is a hot cathode high voltage direct current electron gun.
Furthermore, a magnetic lens is arranged on the first stainless steel vacuum chamber.
Further, the electron gun is connected to the acceleration tube via a stainless steel flange.
Furthermore, the grading ring is connected with the electrode plate through a grading ring support.
Furthermore, the vacuum valve is a pneumatic gate valve.
Furthermore, the vacuum pump comprises two molecular pumps, a dry pump and a controller thereof.
Furthermore, a vacuum measuring component is arranged in the vacuum system.
Further, the vacuum measuring unit includes a cold gauge and a controller thereof.
Compared with the prior art, the invention has the beneficial effects that: the invention solves the problem of simulation of the charging environment of the surface of the moon in the prior art. The wide-spectrum and wide-flow strong-irradiation electron accelerator is the first domestic electron accelerator applied to the lunar vacuum high-low temperature environment, and is used for irradiating dust and simulating charged lunar dust and lunar surface charging extreme environments. The maximum energy of the generated electron beam is 200keV, and the energy is adjustable between 10 keV and 200 keV; the maximum flow intensity is 15mA, and 1-15 mA can be adjusted; the scanning area of the beam current of 1000mm multiplied by 1000mm is realized on an irradiation plane about 3.5m away from the outlet of the accelerator, and the scanning frequency is more than or equal to 200 Hz.
A thermal emission direct current electron gun is selected as an electron source. The filament is heated to increase the kinetic energy of electrons in the cathode, so that part of the electrons have enough kinetic energy to overcome the potential barrier on the surface of the solid cathode and escape out of the body to form electron emission, the electrons are accelerated under the action of a plurality of serial electrodes of the accelerating tube, a vacuum system works to provide a vacuum environment for the electrons to realize the transition from high pressure to low pressure, and the beam position deviation caused by installation errors and interference magnetic fields is corrected when the magnet is corrected; and the beam spot detector is reached to measure the shape and the beam position of the beam spot, and the Faraday barrel current intensity detector is reached to measure the beam current intensity, so that real-time monitoring is realized to ensure that the electron beam is positioned in the center when reaching the vacuum valve, and the energy loss is low.
Drawings
FIG. 1 is a schematic diagram of an installation position of an electron accelerator device for simulating a charging environment of a lunar surface according to the present invention;
FIG. 2 is a schematic view of a three-dimensional connection structure of an electron gun and an accelerating tube according to the present invention;
FIG. 3 is a schematic view of an electron gun according to the present invention;
FIG. 4 is a schematic view of an acceleration tube structure according to the present invention;
FIG. 5 is a schematic view of a vacuum system according to the present invention;
FIG. 6 is a schematic diagram of an electron accelerator apparatus for simulating a lunar surface charging environment according to the present invention;
FIG. 7 is a functional schematic of a control system according to the present invention;
fig. 8 is a schematic view of an installation position of the beam measuring system according to the present invention.
1-electron gun, 2-accelerating tube, 3-stainless steel flange, 4-anode, 5-cathode component, 6-ceramic tube, 7-focusing electrode, 8-high voltage corona ring, 9-filament power connector, 10-equalizing ring, 11-electrode plate, 12-equalizing ring support, 13-ceramic vacuum chamber, 14-stainless steel vacuum chamber, 15-vacuum pump, 16-adapter flange, 17-six-way connector, 18-magnetic lens, 19-correcting magnet, 20-beam measuring system, 21-scanning magnet and 22-vacuum valve.
Detailed Description
The technical solution in the embodiments of the present invention will be clearly and completely explained below with reference to the drawings in the embodiments of the present invention.
Referring to fig. 1 to illustrate the present embodiment, an electron accelerator apparatus for lunar surface charging environment simulation includes an electron gun 1, an accelerating tube 2, a vacuum system, a magnet system, a beam measuring system 20 and a control system, where the electron gun 1 is connected to the accelerating tube 2, the electron gun 1 is connected to an electron gun power supply, the electron gun 1 includes an anode 4, a cathode assembly 5, a focusing electrode 7, a high-voltage corona ring 8 and a filament power supply connector 9, one end of the focusing electrode 7 is provided with the cathode assembly 5, the other end is connected to the filament power supply connector 9, the anode 4 is disposed at the front end of the cathode assembly 5, the high-voltage corona ring 8 is disposed outside the filament power supply connector 9, the accelerating tube 2 includes a ceramic tube 6, a grading ring 10 and an electrode plate 11, the grading ring 10 is disposed outside the ceramic tube 6, the electrode plate 11 is disposed inside the ceramic tube 6, the equalizing ring 10 is connected with an electrode plate 11, the vacuum system comprises a vacuum pipeline, a vacuum valve 22 and a vacuum pump 15, the vacuum pipeline comprises three six-way joints 17, two adapter flanges 16, two sections of stainless steel vacuum chambers 14 and one section of ceramic vacuum chamber 13, the three six-way joints 17 are respectively a first six-way joint, a second six-way joint and a third six-way joint, the two adapter flanges 16 are respectively a first adapter flange and a second adapter flange, the two sections of stainless steel vacuum chambers 14 are respectively a first stainless steel vacuum chamber and a second stainless steel vacuum chamber, one end of the first six-way joint is in butt joint with the accelerating tube 2, the other end of the first six-way joint is connected with one end of the first stainless steel vacuum chamber through the first adapter flange, the other end of the first stainless steel vacuum chamber is connected with one end of the second six-way joint, the other end of the second six-way joint is connected with one end of the second stainless steel vacuum chamber, the other end of the second stainless steel vacuum chamber is connected with one end of a third six-way joint, the other end of the third six-way joint is connected with the ceramic vacuum chamber 13 through a second adapter flange, the ceramic vacuum chamber 13 is connected with a vacuum valve 22, lower end interfaces of the first six-way joint and the second six-way joint are both connected with a vacuum pump 15, an upper end interface of the three six-way joint 17 is connected with a beam measuring system 20, the magnet system comprises a magnetic lens, a correcting magnet 19 and a scanning magnet 21, the magnetic lens is connected with a magnetic lens power supply, the correcting magnet 19 is connected with a correcting magnet power supply, the scanning magnet 21 is connected with a scanning magnet power supply, the correcting magnet 19 is arranged on the first stainless steel vacuum chamber, the number of the scanning magnets 21 is two, the two scanning magnets 21 are arranged on the ceramic vacuum chamber 13, and the control system is respectively connected with the magnetic lens power supply, The correcting magnet power supply, the scanning magnet power supply, the electron gun power supply, the vacuum pump 15 and the beam measuring system 20 are connected in a control way.
The embodiment is used for carrying out electron beam irradiation charging on dust, and the dust is to be installed on the wall of a tank body of a lunar dust cabin, and the installation position is shown in figure 1. The main working modes comprise deflection and direct injection, wherein the direct injection working mode irradiates a vibrating screen and a sprinkling process, and the deflection working mode irradiates the sprinkling process and the surface of a sample table.
The electron gun 1 and the accelerating tube 2 are important components of the electron accelerator in this embodiment, the electron gun 1 provides an electron beam source for the electron accelerator, and the high voltage electron accelerating tube 2 is used for accelerating the electron beam and increasing the energy of the electron beam. Mainly comprises 1 hot cathode high voltage direct current electron gun, a high voltage electron accelerating tube 2 and an electron gun high voltage power supply. The electron gun 1 and the accelerating tube 2 are designed in a separated structure, the two parts are connected through a CF150 vacuum stainless steel flange 3, and the hot cathode high-voltage direct current electron gun increases the kinetic energy of electrons in the cathode by using a filament heating method, so that the kinetic energy of partial electrons is large enough to overcome the surface potential barrier of the solid cathode and escape out of the body to form electron emission. The high-voltage electron accelerating tube 2 accelerates electrons by using the pressure difference between the electrode plates 11, and the grading ring 10 is connected with the electrode plates 11 through grading ring supporting columns 12.
In order to meet the working environment and beam transmission of an electron gun and solve the problems that the interface of a 'lunar dust cabin' is in a low vacuum (about 5 multiplied by 10 < -4 > Pa) environment, and the cathode of the electron gun is required to work in an ultrahigh vacuum (10 < -5 > to 10 < -7 > Pa) environment, a differential vacuum system is adopted to provide a high vacuum environment for the generation and transmission of electron beams, the service life of the cathode is prolonged, and the beam transmission efficiency is improved. The vacuum valve 22 is a pneumatic gate valve, the vacuum pump 15 comprises two molecular pumps, a dry pump and a controller thereof, a vacuum measuring part is arranged in the vacuum system, and the vacuum measuring part comprises a cold gauge and a controller thereof. The pneumatic gate valve is a CF200 standard mounting flange, is arranged between the ceramic vacuum chamber 13 and the lunar dust cabin corrugated pipe, and is used for vacuum isolation of the electron accelerator and the lunar dust cabin. The butt joint of the electron accelerator and the lunar dust cabin adopts a vacuum corrugated pipe which is used for absorbing relative deformation and displacement between the electron accelerator and the lunar dust cabin.
The magnet system is mainly used for focusing, deflecting, scanning and the like of the electron beams in the electron beam transmission process, the magnetic lens 18 is arranged on the first stainless steel vacuum chamber, and the magnetic lens 18 is used for controlling the transverse envelope of the electron beams, so that the long-distance transmission of the electron beams is ensured, and the loss in the beam transmission process is reduced. The correcting magnet 19 is used for correcting beam position deviation caused by installation errors and interference magnetic fields and ensuring the center of a beam track digit vacuum chamber. The scanning magnet 21 is used for scanning the beam in the range of 1m × 1 m.
The control system is an electronic control main body of the electronic accelerator, and according to the requirements of demand items, the bottom hardware control of the control system of the electronic accelerator of the lunar dust charging system is divided into power supply equipment control, vacuum equipment control and beam current measuring equipment control. As shown in fig. 7, the power supply device control module is mainly responsible for controlling and monitoring the states of the magnetic lens magnet power supply, the calibration magnet power supply, the scanning magnet power supply and the high-voltage power supply of the electron gun; the vacuum equipment control module is mainly responsible for controlling the molecular pump and acquiring vacuum gauge data in real time; the beam current measuring equipment control module is mainly responsible for the Faraday cylinder, the movement control of the fluorescent target detector, the real-time acquisition of Faraday cylinder signals, the acquisition of fluorescent target video signals and the real-time online monitoring of beam current intensity.
The beam measurement system 20 includes a fluorescent target and a faraday cage. The beam measurement system serves as a main tool for adjusting beam, checking and accepting of the device and diagnosing during operation. The beam measuring system is divided into two types of on-line equipment and debugging equipment, wherein the on-line equipment comprises a fluorescence target beam spot detector and a Faraday cylinder flow intensity detector, the beam spot detector is used for measuring the shape and the beam position of a beam spot, the Faraday cylinder flow intensity detector is used for measuring the beam flow intensity, and the on-line real-time data of the beam energy is given by high voltage applied by an electron gun and an accelerating tube. As shown in fig. 8, the beam current measuring device can be flexibly mounted at 3 different positions to measure beam current parameters; energy measurement, intensity measurement and scanning uniformity measurement of the irradiation region are taken as debugging tools to be added at the initial debugging stage of the accelerator and removed during normal operation.
The present invention provides an electron accelerator device for simulating a lunar surface charging environment, which is described in detail above, and the principle and the implementation of the present invention are explained herein by applying specific examples, and the description of the above examples is only used to help understanding the method of the present invention and the core idea thereof; meanwhile, for a person skilled in the art, according to the idea of the present invention, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present invention.
Claims (9)
1. An electron accelerator device for lunar surface charging environment simulation, comprising: the electron gun comprises an electron gun (1), an accelerating tube (2), a vacuum system, a magnet system, a beam measuring system (20) and a control system, wherein the electron gun (1) is connected with the accelerating tube (2), the electron gun (1) is connected with an electron gun power supply, the electron gun (1) comprises an anode (4), a cathode component (5), a focusing electrode (7), a high-voltage corona ring (8) and a filament power supply connector (9), one end of the focusing electrode (7) is provided with the cathode component (5), the other end of the focusing electrode is connected with the filament power supply connector (9), the anode (4) is arranged at the front end of the cathode component (5), the high-voltage corona ring (8) is arranged outside the filament power supply connector (9), the accelerating tube (2) comprises a ceramic tube (6), a grading ring (10) and an electrode plate (11), the grading ring (10) is arranged outside the ceramic tube (6), the electrode plate (11) is arranged on the inner side of the ceramic tube (6), the grading ring (10) is connected with the electrode plate (11), the vacuum system comprises a vacuum pipeline, a vacuum valve (22) and a vacuum pump (15), the vacuum pipeline comprises three six-way joints (17), two adapter flanges (16), two sections of stainless steel vacuum chambers (14) and one section of ceramic vacuum chamber (13), the three six-way joints (17) are respectively a first six-way joint, a second six-way joint and a third six-way joint, the two adapter flanges (16) are respectively a first adapter flange and a second adapter flange, the two sections of stainless steel vacuum chambers (14) are respectively a first stainless steel vacuum chamber and a second stainless steel vacuum chamber, one end of the first six-way joint is in butt joint with the accelerating tube (2), and the other end of the first six-way joint is connected with one end of the first stainless steel vacuum chamber through the first adapter flange, the other end of the first stainless steel vacuum chamber is connected with one end of a second six-way joint, the other end of the second six-way joint is connected with one end of a second stainless steel vacuum chamber, the other end of the second stainless steel vacuum chamber is connected with one end of a third six-way joint, the other end of the third six-way joint is connected with a ceramic vacuum chamber (13) through a second adapter flange, the ceramic vacuum chamber (13) is connected with a vacuum valve (22), the lower end interfaces of the first six-way joint and the second six-way joint are both connected with a vacuum pump (15), the upper end interfaces of the three six-way joints (17) are connected with a beam measuring system (20), the magnet system comprises a magnetic lens (18), a correcting magnet (19) and a scanning magnet (21), the magnetic lens (18) is connected with a magnetic lens power supply, the correcting magnet (19) is connected with a correcting magnet power supply, and the scanning magnet (21) is connected with a scanning magnet power supply, the device is characterized in that a magnetic lens (18) is arranged on the first stainless steel vacuum chamber, the correcting magnets (19) are arranged on the first stainless steel vacuum chamber, the number of the scanning magnets (21) is two, the two scanning magnets (21) are arranged on the ceramic vacuum chamber (13), and the control system is respectively connected with the solenoid coil power supply, the correcting magnet power supply, the scanning magnet power supply, the electron gun power supply, the vacuum pump (15) and the beam measuring system (20) in a control mode.
2. An electron accelerator device for lunar surface charging environment simulation according to claim 1, wherein: the beam measurement system (20) includes a fluorescent target and a Faraday cage.
3. An electron accelerator device for lunar surface charging environment simulation according to claim 1, wherein: the electron gun (1) is a hot cathode high-voltage direct current electron gun.
4. An electron accelerator device for lunar surface charging environment simulation according to claim 1, wherein: the electron gun (1) is connected with the accelerating tube (2) through a stainless steel flange (3).
5. An electron accelerator device for lunar surface charging environment simulation according to claim 1, wherein: the grading ring (10) is connected with the electrode plate (11) through grading ring supporting columns (12).
6. An electron accelerator device for lunar surface charging environment simulation according to claim 1, wherein: the vacuum valve (22) is a pneumatic gate valve.
7. An electron accelerator device for lunar surface charging environment simulation according to claim 1, wherein: the vacuum pump (15) comprises two molecular pumps, a dry pump and a controller thereof.
8. An electron accelerator device for lunar surface charging environment simulation according to claim 1, wherein: and a vacuum measuring component is arranged in the vacuum system.
9. An electron accelerator device for lunar surface charging environment simulation according to claim 9, wherein: the vacuum measurement assembly includes a cold gauge and a controller therefor.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110765197.8A CN113597079B (en) | 2021-07-06 | 2021-07-06 | Electron accelerator device for moon surface charging environment simulation |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110765197.8A CN113597079B (en) | 2021-07-06 | 2021-07-06 | Electron accelerator device for moon surface charging environment simulation |
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| CN113597079A true CN113597079A (en) | 2021-11-02 |
| CN113597079B CN113597079B (en) | 2023-08-22 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115220511A (en) * | 2022-07-14 | 2022-10-21 | 无锡卓海科技股份有限公司 | High-voltage power supply device of electron gun capable of detecting heating current and emission current of filament |
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| CN113597079B (en) | 2023-08-22 |
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