CN113597079B - Electron accelerator device for moon surface charging environment simulation - Google Patents
Electron accelerator device for moon surface charging environment simulation Download PDFInfo
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- CN113597079B CN113597079B CN202110765197.8A CN202110765197A CN113597079B CN 113597079 B CN113597079 B CN 113597079B CN 202110765197 A CN202110765197 A CN 202110765197A CN 113597079 B CN113597079 B CN 113597079B
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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
-
- 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 electron accelerator device for simulating a lunar surface charging environment, and belongs to the technical field of space environment simulation. The problem of current moon surface charging environment simulation is solved. The electronic gun is connected with the accelerating tube, the electronic gun is connected with an electronic gun power supply, the electronic 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, an equalizing ring and an electrode sheet, and the equalizing ring is arranged on the outer side of the ceramic tube. The method is mainly used for simulating the moon surface charging environment.
Description
Technical Field
The invention belongs to the technical field of space environment simulation, and particularly relates to an electron accelerator device for simulating a lunar surface charging environment.
Background
Moon is the only natural satellite of earth, and the lunar exploration is always a hot topic of China spaceflight, however, extremely severe environments such as vacuum, high and low temperature, charged dust and the like on the surface of the moon are a great test on lunar base equipment (including landers, inspection devices, robots, detectors and the like) and on a lunar astronaut, especially on charged lunar dust, fine lunar 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 moon dust has strong adsorption force and is adhered and accumulated on various devices which can be contacted under the action of electrostatic force. The electrostatic on the moon surface and the electrostatic moon dust have serious influence on the lunar climbing equipment, and the moon dust floating under the action of the electrostatic can block the detection sight, adsorb and cover the surface of the detection equipment and even enter the instrument and equipment carried by the moon detector. The moon dust entering the moon detector acts on an optical system, a power supply system, a thermal control system and even a astronaut system of the moon detector, so that the problems of vision ambiguity, wrong reading, sealing failure, material abrasion, efficiency reduction of the thermal control system and the power supply system, inhalation and allergy of astronauts and the like are caused. Therefore, it is important to simulate the charged moon dust when simulating the moon environment.
Disclosure of Invention
The invention provides an electron accelerator device for simulating a lunar surface charging environment, which aims to solve the problems in the prior art.
In order to achieve the above purpose, the present invention adopts the following technical scheme: an electron accelerator device for moon surface charging environment simulation 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 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 at the outer side of the filament power supply connector, the accelerating tube comprises a ceramic tube, a grading ring and an electrode sheet, the grading ring is arranged at the outer side of the ceramic tube, the electrode sheet is arranged at the inner side of the ceramic tube, the grading ring is connected with the electrode sheet, 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 in butt joint 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, the other end of the third six-way joint is connected with the ceramic vacuum chamber through the second adapter flange, the ceramic vacuum chamber is connected with the vacuum valve, the lower end interfaces of the first six-way joint and the second six-way joint are connected with the vacuum pump, the upper end interfaces of the three six-way joints are connected with the beam measuring system, the magnet system comprises a magnetic lens, a correction magnet and a scanning magnet, the magnetic lens is connected with a magnetic lens power supply, the correction magnet is connected with a correction magnet power supply, the scanning magnet is connected with a scanning magnet power supply, the correction magnet is arranged on the first stainless steel vacuum chamber, the number of the scanning magnets is two, the two scanning magnets are arranged on the ceramic vacuum chamber, and the control system is respectively connected with the magnetic lens power supply, the correction magnet power supply, the scanning magnet power supply, the electron gun power supply, the vacuum pump and the beam measuring system.
Still further, the beam measurement system includes a fluorescent target and a Faraday cage.
Further, the electron gun is a hot cathode high voltage direct current electron gun.
Further, a magnetic lens is arranged on the first stainless steel vacuum chamber.
Further, the electron gun is connected with the accelerating tube through a stainless steel flange.
Further, the grading ring is connected with the electrode plate through the grading ring support post.
Further, the vacuum valve is a pneumatic gate valve.
Further, the vacuum pump comprises two molecular pumps, a dry pump and a controller thereof.
Further, a vacuum measuring part is arranged in the vacuum system.
Further, the vacuum measuring part comprises 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 the existing moon surface charging environment simulation. The electronic accelerator is a first electronic accelerator applied to wide energy spectrum and wide-current strong radiation in lunar vacuum high-low temperature environments in China, is used for radiating dust, and simulates charged lunar dust and lunar surface charging extreme environments. The energy of the generated electron beam is maximally 200keV and is adjustable by 10-200 keV; maximum current intensity is 15mA, and 1-15 mA is adjustable; the scanning area of 1000mm multiplied by 1000mm of beam current is realized on an irradiation plane which is about 3.5m away from the outlet of the accelerator, and the scanning frequency is more than or equal to 200Hz.
A heat 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 the kinetic energy of partial electrons is large enough to overcome the potential barrier on the surface of the solid cathode and escape outside the body, electron emission is formed, acceleration is carried out under the action of a plurality of electrodes connected in series of an accelerating tube, a vacuum system works to provide a vacuum environment for electrons to realize transition from high voltage to low voltage, and the position deviation of beam current caused by installation errors and interference magnetic fields is corrected when the magnet is corrected; the beam spot detector is reached, the beam spot shape and the beam current position are measured, the Faraday barrel current intensity detector is used for measuring the beam current intensity, real-time monitoring is realized, the electron beam is ensured to be 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 lunar surface charging environment 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 accelerating tube 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 device 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 the installation position of the beam measuring system according to the present invention.
The device comprises a 1-electron gun, a 2-accelerating tube, a 3-stainless steel flange, a 4-anode, a 5-cathode assembly, a 6-ceramic tube, a 7-focusing electrode, an 8-high-voltage corona ring, a 9-filament power connector, a 10-equalizing ring, an 11-electrode plate, a 12-equalizing ring strut, a 13-ceramic vacuum chamber, a 14-stainless steel vacuum chamber, a 15-vacuum pump, a 16-adapting flange, a 17-six-way joint, a 18-magnetic lens, a 19-correction magnet, a 20-beam measuring system, a 21-scanning magnet and a 22-vacuum valve.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.
Referring to fig. 1 for describing the present embodiment, an electron accelerator apparatus for moon surface charging environment simulation includes an electron gun 1, an acceleration 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 acceleration tube 2, the electron gun 1 is connected with 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 with the filament power supply connector 9, the anode 4 is provided at the front end of the cathode assembly 5, the high voltage corona ring 8 is provided outside the filament power supply connector 9, the acceleration tube 2 includes a ceramic tube 6, a grading ring 10 and electrode pieces 11, the grading ring 10 is provided outside the ceramic tube 6, the electrode pieces 11 are provided inside the ceramic tube 6, the equalizing 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, 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, the lower end interfaces of the first six-way joint and the second six-way joint are 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, a correction magnet 19 and a scanning magnet 21, the magnetic lens is connected with a magnetic lens power supply, the correction magnet 19 is connected with a correction magnet power supply, the scanning magnet 21 is connected with a scanning magnet power supply, the correction 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 all arranged on the ceramic vacuum chamber 13, and the control system is respectively connected with the magnetic lens power supply, the correction magnet power supply, the scanning magnet power supply, the electron gun power supply, the vacuum pump 15 and the beam measuring system 20.
The embodiment is used for carrying out electron beam irradiation charging on dust, and is arranged 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 include deflection and direct irradiation, wherein the direct irradiation working mode irradiates the vibrating screen and the sprinkling process, and the deflection working mode irradiates the sprinkling process and the surface of the sample table.
The electron gun 1 and the accelerating tube 2 are important components of an electron accelerator, 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 electron beams and improving energy of the electron beams. Mainly comprises 1 hot cathode high-voltage direct current electron gun, one high-voltage electron accelerating tube 2 and one electron gun high-voltage power supply. The electron gun 1 and the accelerating tube 2 adopt a separated structural design, 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 potential barrier on the surface of the solid cathode and escape from the body, thereby forming electron emission. The high-voltage electron acceleration tube 2 accelerates electrons by a pressure difference between the electrode plates 11, and the grading ring 10 is connected to the electrode plates 11 through the grading ring support 12.
In order to meet the working environment and beam current transmission of an electron gun, the problem that the interface of a 'moon dust cabin' is in a low vacuum (about 5 multiplied by 10 < -4 > Pa) environment, and a cathode of the electron gun is required to work in an ultrahigh vacuum (10 < -5 > -10 < -7 > Pa) environment is solved, a differential vacuum system is adopted to provide a high vacuum environment for generating and transmitting electron beams, the service life of the cathode is prolonged, and the beam current 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, and a vacuum measuring part is arranged in the vacuum system and comprises a cold gauge and a controller thereof. The pneumatic gate valve is a CF200 standard mounting flange and is arranged between the ceramic vacuum chamber 13 and the corrugated pipe of the moon-dust cabin and used for vacuum isolation of the electron accelerator and the moon-dust cabin. The electron accelerator and the lunar dust cabin are in butt joint by adopting a vacuum corrugated pipe 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 beam in the electron beam transmission process, the magnetic lens 18 is arranged on the first stainless steel vacuum chamber, the magnetic lens 18 is used for controlling the transverse envelope of the electron beam, the long-distance transmission of the electron beam is ensured, and the loss in the beam current transmission process is reduced. The correction magnet 19 is used for correcting the deviation of the beam position caused by installation errors and disturbing magnetic fields and ensuring the center of the vacuum chamber with the number of beam track positions. The scanning magnet 21 is used to realize scanning of the beam current in the range of 1m×1 m.
The control system is an electronic control main body of the electronic accelerator, and according to requirements of a requirement project, bottom hardware control of the control system of the electronic accelerator of the moon dust charging system is divided into power supply equipment control, vacuum equipment control and beam measuring equipment control. As shown in fig. 7, the power supply device control module is mainly responsible for controlling and monitoring the state of the magnetic lens magnet power supply, the correction 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 collecting data of the vacuum gauge in real time; the beam measuring equipment control module is mainly responsible for faraday cage, fluorescent target detector motion control, real-time acquisition of faraday cage signals, acquisition of fluorescent target video signals and real-time on-line monitoring of beam intensity.
The beam measurement system 20 includes a fluorescent target and a faraday cage. The beam measurement system is used as a main tool for beam adjustment, acceptance and run-time diagnosis of the device. The beam measuring system is divided into two types of online equipment and debugging equipment, wherein the online equipment comprises a fluorescent target beam spot detector and a Faraday barrel flow intensity detector, the beam spot detector is used for measuring the beam spot shape and the beam current position, the Faraday barrel flow intensity detector is used for measuring the beam current intensity, and online real-time data of beam current energy is given by high voltage applied by an electron gun and an accelerating tube. As shown in fig. 8, the device can be flexibly arranged at 3 different positions to measure beam parameters; the energy measurement, the intensity measurement and the scanning uniformity measurement of the irradiation area are added as debugging tools in the initial stage of accelerator debugging, and removed in the formal operation.
The above description of the present invention provides an electron accelerator device for simulating the charging environment of the lunar surface, and specific examples are applied to illustrate the principles and embodiments of the present invention, and the above examples are only used to help understand the method and core idea of the present invention; meanwhile, as those skilled in the art will have variations in the specific embodiments and application scope in accordance with the ideas of the present invention, the present description should not be construed as limiting the present invention in view of the above.
Claims (8)
1. An electron accelerator device for moon surface charging environment simulation, characterized in that: the vacuum tube 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 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 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 assembly (5), the high-voltage corona ring (8) is arranged at the outer side of the filament power supply connector (9), the accelerating tube (2) comprises a ceramic tube (6), a pressure equalizing ring (10) and an electrode sheet (11), the ceramic equalizing ring (10) is arranged at the outer side of the ceramic tube (6), the inner side of the ceramic tube (6), the pressure equalizing ring (10) is connected with the electrode sheet (11), the vacuum tube (4) comprises a pipeline (22), two vacuum segments (16), a vacuum pump (16), a vacuum transfer ring (16) and a vacuum segment (13), a vacuum flange (13) and a vacuum segment (13), the three six-way connectors (17) are respectively a first six-way connector, a second six-way connector and a third six-way connector, 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 connector is in butt joint with the accelerating tube (2), the other end of the first six-way connector 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 connector, the other end of the second six-way connector 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 connector, the other end of the third six-way connector is connected with the ceramic vacuum chamber (13) through the second adapter flange, the ceramic vacuum chamber (13) is connected with the vacuum valve (22), the lower end interfaces of the first six-way connector and the second six-way connector are all connected with the accelerating tube (2), the other end interfaces of the first six-way connector is connected with the vacuum pump (15), the magnet (19) is connected with the magnet (19), the magnet (18) is connected with the magnet (19) and the magnet (18) is provided with the magnet (18) and the magnet (18) on the magnet (18) and the magnet (18), the number of the scanning magnets (21) is two, the two scanning magnets (21) are arranged on the ceramic vacuum chamber (13), the control system is respectively connected with a solenoid coil power supply, a correction magnet power supply, a scanning magnet power supply, an electron gun power supply, a vacuum pump (15) and a beam measuring system (20) in a control mode, and the electron gun (1) is a hot cathode high-voltage direct current electron gun.
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 connected with the accelerating tube (2) through a stainless steel flange (3).
4. 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 the grading ring support (12).
5. An electron accelerator device for lunar surface charging environment simulation according to claim 1, wherein: the vacuum valve (22) is a pneumatic gate valve.
6. 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.
7. An electron accelerator device for lunar surface charging environment simulation according to claim 1, wherein: a vacuum measuring component is arranged in the vacuum system.
8. An electron accelerator apparatus for lunar surface charging environment simulation according to claim 7, wherein: the vacuum measuring component comprises a cold gauge and a controller thereof.
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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 CN113597079A (en) | 2021-11-02 |
| CN113597079B true CN113597079B (en) | 2023-08-22 |
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| CN115220511B (en) * | 2022-07-14 | 2023-10-31 | 无锡卓海科技股份有限公司 | High-voltage power supply device of electron gun for detecting filament heating current and emission current |
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| US8461526B2 (en) * | 2010-12-01 | 2013-06-11 | Kla-Tencor Corporation | Electron beam column and methods of using same |
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| CN1109226A (en) * | 1993-10-14 | 1995-09-27 | 周符明 | Electric power generator and method therefor |
| CN1943284A (en) * | 2002-10-25 | 2007-04-04 | 独立行政法人科学技术振兴机构 | Electron accelerator and radiotherapy apparatus using same |
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