技术领域technical field
本发明属于空间环境模拟技术领域，特别是涉及一种用于月球表面充电环境模拟的电子加速器装置。The invention belongs to the technical field of space environment simulation, in particular to an electron accelerator device used for simulation of the charging environment on the surface of the moon.
背景技术Background technique
月球是地球唯一的天然卫星，探月一直是中国航天的热门话题，然而月球表面的真空、高低温、带电尘埃等极端恶劣的环境对月基装备(包括着陆器、巡视器、机器人、探测器等)和与登月航天员都是一项重大考验,尤其是带电月尘,细小的月尘在月球的近似真空、巨大温差、太阳风、紫外辐照、电子辐射的作用下，很容易带上电荷.由于月球的高真空环境，月尘颗粒在这种环境下可以长的时间保持带电状态。带电月尘有很强的吸附力，在静电力作用下，粘着和堆积到各种能够接触到的装置上。月球表面静电以及带静电月尘对登月设备的影响十分严重，由于静电作用而漂浮的月尘能够阻挡探测视线、吸附覆盖探测装备表面甚至进入月球探测器所载仪器设备中。进入月球探测器的月尘作用于登月探测器的光学系统、电源系统、热控系统甚至航天员系统，造成视觉模糊、读数错误、密封失效、材料磨损、热控系统、电源系统效率减低、航天员吸入和过敏等问题。因此，模拟月球环境时模拟带电月尘有重要意义。The moon is the only natural satellite of the earth. Exploring the moon has always been a hot topic in China's aerospace industry. However, the extremely harsh environment of the moon's surface, such as vacuum, high and low temperature, and charged dust, has a great impact on lunar-based equipment (including landers, rovers, robots, and detectors). etc.) and astronauts on the moon are a major test, especially the charged moon dust. Under the action of the approximate vacuum of the moon, huge temperature difference, solar wind, ultraviolet radiation, and electron radiation, the fine moon dust is easy to carry Electric charge. Due to the high vacuum environment of the Moon, particles of lunar dust can remain charged for long periods of time in this environment. Charged moon dust has a strong adsorption force, and under the action of electrostatic force, it sticks and accumulates on various accessible devices. Static electricity on the surface of the moon and electrostatically charged moon dust have a serious impact on lunar landing equipment. The floating moon dust due to static electricity can block the detection line of sight, absorb and cover the surface of the detection equipment, and even enter the instruments and equipment carried by the lunar probe. The moon dust entering the lunar probe acts on the optical system, power system, thermal control system and even the astronaut system of the lunar probe, causing blurred vision, reading errors, seal failure, material wear, thermal control system, power system efficiency reduction, Issues such as inhalation and allergies for astronauts. Therefore, it is of great significance to simulate charged moon dust when simulating the lunar environment.
发明内容Contents of the invention
本发明为了解决现有技术中的问题，提出一种用于月球表面充电环境模拟的电子加速器装置。In order to solve the problems in the prior art, the present invention proposes an electron accelerator device for simulating the charging environment on the surface of the moon.
为实现上述目的，本发明采用以下技术方案：一种用于月球表面充电环境模拟的电子加速器装置，它包括电子枪、加速管、真空系统、磁铁系统、束测系统和控制系统，所述电子枪与加速管相连，所述电子枪与电子枪电源相连，所述电子枪包括阳极、阴极组件、聚焦电极、高压电晕环和灯丝电源连接器，所述聚焦电极一端设置有阴极组件，另一端与灯丝电源连接器相连，所述阳极设置在阴极组件的前端，所述高压电晕环设置在灯丝电源连接器的外侧，所述加速管包括陶瓷管、均压环和电极片，所述均压环设置在陶瓷管的外侧，所述电极片设置在陶瓷管的内侧，所述均压环与电极片相连，所述真空系统包括真空管道、真空阀和真空泵，真空管道包括三个六通接头、两个转接法兰、两段不锈钢真空室和一段陶瓷真空室，所述三个六通接头分别为第一六通接头、第二六通接头和第三六通接头，所述两个转接法兰分别为第一转接法兰和第二转接法兰，所述两段不锈钢真空室分别为第一不锈钢真空室和第二不锈钢真空室，所述第一六通接头一端与加速管对接，另一端通过第一转接法兰与第一不锈钢真空室一端相连，第一不锈钢真空室的另一端与第二六通接头一端相连，第二六通接头另一端与第二不锈钢真空室一端相连，第二不锈钢真空室的另一端与第三六通接头一端相连，第三六通接头的另一端通过第二转接法兰与陶瓷真空室相连，所述陶瓷真空室与真空阀相连，所述第一六通接头和第二六通接头的下端接口均与真空泵相连，所述三个六通接头的上端接口与束测系统相连，所述磁铁系统包括磁透镜、校正磁铁和扫描磁铁，所述磁透镜与磁透镜电源相连，所述校正磁铁与校正磁铁电源相连，所述扫描磁铁与扫描磁铁电源相连，所述校正磁铁设置在第一不锈钢真空室上，所述扫描磁铁数量为两个，两个扫描磁铁均设置在陶瓷真空室上，所述控制系统分别与磁透镜电源、校正磁铁电源、扫描磁铁电源、电子枪电源、真空泵和束测系统控制相连。To achieve the above object, the present invention adopts the following technical solutions: a kind of electron accelerator device for the simulation of the charging environment on the surface of the moon, which includes an electron gun, an accelerating tube, a vacuum system, a magnet system, a beam measurement system and a control system, and the electron gun and The accelerating tube is connected, and the electron gun is connected to the electron gun power supply. The electron gun includes an anode, a cathode assembly, a focusing electrode, a high-voltage corona ring and a filament power connector. One end of the focusing electrode is provided with a cathode assembly, and the other end is connected to the filament power supply. The anode is set at the front end of the cathode assembly, the high-voltage corona ring is set outside the filament power connector, the accelerating tube includes a ceramic tube, a voltage equalizing ring and an electrode sheet, and the voltage equalizing ring It is arranged on the outside of the ceramic tube, the electrode sheet is arranged on the inside of the ceramic tube, the pressure equalizing ring is connected to the electrode sheet, the vacuum system includes a vacuum pipeline, a vacuum valve and a vacuum pump, and the vacuum pipeline includes three six-way joints, Two adapter flanges, two sections of stainless steel vacuum chambers and one section of ceramic vacuum chambers, the three six-way joints are the first six-way joint, the second six-way joint and the third six-way joint, the two turning The connecting flanges are respectively the first transfer flange and the second transfer flange, the two sections of stainless steel vacuum chambers are respectively the first stainless steel vacuum chamber and the second stainless steel vacuum chamber, one end of the first six-way joint is connected to the acceleration The other end is connected to 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 to one end of the second six-way joint, and the other end of the second six-way joint is connected to the second stainless steel vacuum chamber. One end of the chamber is connected, 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, and 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, and the upper interfaces of the three six-way joints are connected with the beam measurement system. The magnet system includes a magnetic lens, a correction magnet and The scanning magnet, the magnetic lens is connected to the magnetic lens power supply, the correction magnet is connected to the correction magnet power supply, the scanning magnet is connected to the scanning magnet power supply, the correction magnet is arranged on the first stainless steel vacuum chamber, and the scanning magnet The quantity is two, and the two scanning magnets are arranged on the ceramic vacuum chamber. 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 control.
更进一步的，所述束测系统包括荧光靶和法拉第筒。Furthermore, the beam measurement system includes a fluorescent target and a Faraday cage.
更进一步的，所述电子枪为热阴极高压直流电子枪。Furthermore, the electron gun is a hot cathode high voltage direct current electron gun.
更进一步的，所述第一不锈钢真空室上设置有磁透镜。Further, the first stainless steel vacuum chamber is provided with a magnetic lens.
更进一步的，所述电子枪通过不锈钢法兰与加速管相连。Furthermore, the electron gun is connected with the acceleration tube through a stainless steel flange.
更进一步的，所述均压环通过均压环支柱与电极片相连。Furthermore, the pressure equalizing ring is connected to the electrode sheet through a pressure equalizing ring support.
更进一步的，所述真空阀为气动闸板阀。Furthermore, the vacuum valve is a pneumatic gate valve.
更进一步的，所述真空泵包括两台分子泵、干泵及其控制器。Furthermore, the vacuum pump includes two molecular pumps, a dry pump and its controller.
更进一步的，所述真空系统内设置有真空测量部件。Furthermore, a vacuum measuring component is arranged in the vacuum system.
更进一步的，所述真空测量部件包括一个冷规及其控制器。Furthermore, the vacuum measurement component includes a cold gauge and its controller.
与现有技术相比，本发明的有益效果是：本发明解决了现有月球表面充电环境模拟的问题。是国内首个应用于月球真空高低温环境下的宽能谱、宽流强辐照的电子加速器，用于辐照粉尘，模拟带电月尘和月表充电极端环境。所产生电子束能量最大为200keV，并10～200keV可调；最大流强15mA，并1～15mA可调；在距离加速器出口处约3.5m的辐照平面实现束流1000mm×1000mm的扫描面积，扫描频率≥200Hz。Compared with the prior art, the beneficial effect of the present invention is that: the present invention solves the problem of the existing lunar surface charging environment simulation. It is the first electron accelerator in China with wide energy spectrum and wide current and strong irradiation applied in the lunar vacuum high and low temperature environment. It is used to irradiate dust and simulate the extreme environment of charged lunar dust and lunar surface charging. The maximum energy of the generated electron beam is 200keV, which is adjustable from 10 to 200keV; the maximum current intensity is 15mA, and is adjustable from 1 to 15mA; the scanning area of the beam current is 1000mm×1000mm at the irradiation plane about 3.5m away from the exit of the accelerator. Scanning frequency ≥ 200Hz.
选用热发射直流电子枪作为电子源。灯丝加热使阴极内部电子的动能增加，以致有部分电子的动能大到足以克服固体阴极表面势垒而逸出体外，形成电子发射，在加速管的多个串联电极的作用下进行加速，真空系统工作，为电子提供真空环境实现从高压到低压的过渡，通过校正磁铁时，矫正由于安装误差和干扰磁场导致的束流位置偏差；到达束斑检测器，测量束斑形状和束流位置，到达法拉第桶流强检测器用于测量束流流强，实现实时监测以保证电子束到达真空阀时位于中心，且能量损耗低。A thermal emission DC electron gun was selected as the electron source. The heating of the filament increases the kinetic energy of the electrons inside the cathode, so that the kinetic energy of some electrons is large enough to overcome the surface barrier of the solid cathode and escape from the body, forming electron emission, which is accelerated under the action of multiple series electrodes of the acceleration tube. The vacuum system Work, provide a vacuum environment for electrons to achieve the transition from high voltage to low voltage, correct the beam position deviation caused by installation errors and disturbing magnetic fields when correcting the magnet; reach the beam spot detector, measure the beam spot shape and beam position, and reach Faraday The barrel current detector is used to measure the beam current intensity to realize real-time monitoring to ensure that the electron beam is in the center when it reaches the vacuum valve, and the energy loss is low.
附图说明Description of drawings
图1为本发明所述的一种用于月球表面充电环境模拟的电子加速器装置安装位置示意图；Fig. 1 is a schematic diagram of the installation position of an electron accelerator device used for the simulation of the charging environment on the surface of the moon according to the present invention;
图2为本发明所述的电子枪和加速管三维连接结构示意图；Fig. 2 is the schematic diagram of the three-dimensional connection structure of the electron gun and the accelerating tube of the present invention;
图3为本发明所述的电子枪结构示意图；Fig. 3 is the structural schematic diagram of the electron gun of the present invention;
图4为本发明所述的加速管结构示意图；Fig. 4 is the structural schematic diagram of accelerating tube of the present invention;
图5为本发明所述的真空系统结构示意图；Fig. 5 is a schematic structural diagram of the vacuum system of the present invention;
图6为本发明所述的一种用于月球表面充电环境模拟的电子加速器装置组成结构示意图；Fig. 6 is a schematic diagram of the composition and structure of an electron accelerator device for simulating the charging environment on the surface of the moon according to the present invention;
图7为本发明所述的控制系统功能示意图；Fig. 7 is a functional schematic diagram of the control system of the present invention;
图8为本发明所述的束测系统安装位置示意图。Fig. 8 is a schematic diagram of the installation position of the beam measuring system according to the present invention.
1-电子枪，2-加速管，3-不锈钢法兰，4-阳极，5-阴极组件，6-陶瓷管，7-聚焦电极，8-高压电晕环，9-灯丝电源连接器，10-均压环，11-电极片，12-均压环支柱，13-陶瓷真空室，14-不锈钢真空室，15-真空泵，16-转接法兰，17-六通接头，18-磁透镜，19-校正磁铁，20-束测系统，21-扫描磁铁，22-真空阀。1-electron gun, 2-accelerator tube, 3-stainless steel flange, 4-anode, 5-cathode assembly, 6-ceramic tube, 7-focusing electrode, 8-high voltage corona ring, 9-filament power connector, 10 -Equalizing ring, 11-Electrode piece, 12-Equalizing ring pillar, 13-Ceramic vacuum chamber, 14-Stainless steel vacuum chamber, 15-Vacuum pump, 16-Transfer flange, 17-Six-way joint, 18-Magnetic lens , 19-calibration magnet, 20-beam measuring system, 21-scanning magnet, 22-vacuum valve.
具体实施方式Detailed ways
下面将结合本发明实施例中的附图，对本发明实施例中的技术方案进行清楚、完整地阐述。The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention.
参见图1说明本实施方式，一种用于月球表面充电环境模拟的电子加速器装置，它包括电子枪1、加速管2、真空系统、磁铁系统、束测系统20和控制系统，所述电子枪1与加速管2相连，所述电子枪1与电子枪电源相连，所述电子枪1包括阳极4、阴极组件5、聚焦电极7、高压电晕环8和灯丝电源连接器9，所述聚焦电极7一端设置有阴极组件5，另一端与灯丝电源连接器9相连，所述阳极4设置在阴极组件5的前端，所述高压电晕环8设置在灯丝电源连接器9的外侧，所述加速管2包括陶瓷管6、均压环10和电极片11，所述均压环10设置在陶瓷管6的外侧，所述电极片11设置在陶瓷管6的内侧，所述均压环10与电极片11相连，所述真空系统包括真空管道、真空阀22和真空泵15，真空管道包括三个六通接头17、两个转接法兰16、两段不锈钢真空室14和一段陶瓷真空室13，所述三个六通接头17分别为第一六通接头、第二六通接头和第三六通接头，所述两个转接法兰16分别为第一转接法兰和第二转接法兰，所述两段不锈钢真空室14分别为第一不锈钢真空室和第二不锈钢真空室，所述第一六通接头一端与加速管2对接，另一端通过第一转接法兰与第一不锈钢真空室一端相连，第一不锈钢真空室的另一端与第二六通接头一端相连，第二六通接头另一端与第二不锈钢真空室一端相连，第二不锈钢真空室的另一端与第三六通接头一端相连，第三六通接头的另一端通过第二转接法兰与陶瓷真空室13相连，所述陶瓷真空室13与真空阀22相连，所述第一六通接头和第二六通接头的下端接口均与真空泵15相连，所述三个六通接头17的上端接口与束测系统20相连，所述磁铁系统包括磁透镜、校正磁铁19和扫描磁铁21，所述磁透镜与磁透镜电源相连，所述校正磁铁19与校正磁铁电源相连，所述扫描磁铁21与扫描磁铁电源相连，所述校正磁铁19设置在第一不锈钢真空室上，所述扫描磁铁21数量为两个，两个扫描磁铁21均设置在陶瓷真空室13上，所述控制系统分别与磁透镜电源、校正磁铁电源、扫描磁铁电源、电子枪电源、真空泵15和束测系统20控制相连。Refer to Fig. 1 and illustrate present embodiment, a kind of electron accelerator device that is used for lunar surface charge environment simulation, it comprises electron gun 1, accelerating tube 2, vacuum system, magnet system, beam measuring system 20 and control system, described electron gun 1 and The accelerating tube 2 is connected, and the electron gun 1 is connected to the 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 connector 9, and one end of the focusing electrode 7 is arranged There is a cathode assembly 5, the other end of which is connected to the filament power connector 9, the anode 4 is arranged on the front end of the cathode assembly 5, the high-voltage corona ring 8 is arranged on the outside of the filament power connector 9, and the accelerating tube 2 Comprising ceramic tube 6, pressure equalizing ring 10 and electrode piece 11, described pressure equalizing ring 10 is arranged on the outside of ceramic tube 6, and described electrode piece 11 is arranged on the inner side of ceramic tube 6, and described pressure equalizing ring 10 and electrode piece 11, the vacuum system includes a vacuum pipeline, a vacuum valve 22 and a vacuum pump 15, and the vacuum pipeline includes three six-way joints 17, two adapter flanges 16, two sections of stainless steel vacuum chambers 14 and one section of ceramic vacuum chambers 13. The three six-way joints 17 are respectively the first six-way joint, the second six-way joint and the third six-way joint, and the two transfer flanges 16 are respectively the first transfer flange and the second transfer method Lan, the two sections of stainless steel vacuum chambers 14 are respectively the first stainless steel vacuum chamber and the second stainless steel vacuum chamber, one end of the first six-way joint is connected to the acceleration tube 2, and the other end is connected to the first through the first adapter flange. One end of the stainless steel vacuum chamber is connected, 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 the third One end of the six-way joint is connected, the other end of the third six-way joint is connected with the ceramic vacuum chamber 13 through the second adapter flange, and the ceramic vacuum chamber 13 is connected with the vacuum valve 22, and the first six-way joint and the second The lower end interfaces of the six-way joints are all connected to the vacuum pump 15, and the upper end interfaces of the three six-way joints 17 are connected to the beam measuring system 20. The magnet system includes a magnetic lens, a correction magnet 19 and a scanning magnet 21. The magnetic lens Connect to the magnetic lens power supply, the correction magnet 19 is connected to the correction magnet power supply, the scanning magnet 21 is connected to the scanning magnet power supply, the correction magnet 19 is arranged on the first stainless steel vacuum chamber, and the number of the scanning magnets 21 is two One, 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 measurement system 20 control.
本实施例用于对粉尘进行电子束辐照充电，将安装于月尘舱罐体筒壁，安装位置如图1所示。主要工作模式有偏转和直射两种，其中直射工作模式照射振动筛和洒落过程，偏转工作模式照射洒落过程和样品台表面。This embodiment is used to charge the dust by electron beam irradiation, and will be installed on the tank wall of the lunar dust cabin, and the installation position is shown in Figure 1. There are two main working modes: deflection and direct radiation. The direct radiation mode illuminates the vibrating screen and the spilling process, and the deflection mode illuminates the spilling process and the surface of the sample table.
本实施例电子枪1和加速管2是电子加速器的重要组成部分，电子枪1为电子加速器提供电子束源，高压电子加速管2用于加速电子束，提升电子束能量。主要包括1台热阴极高压直流电子枪，一只高压电子加速管2，一台电子枪高压电源。电子枪1和加速管2采用分离式结构设计，两部分通过CF150真空不锈钢法兰3连接，热阴极高压直流电子枪利用灯丝加热的方法使阴极内部电子的动能增加，以致有部分电子的动能大到足以克服固体阴极表面势垒而逸出体外，形成电子发射。高压电子加速管2用电极片11之间的压差对电子进行加速，所述均压环10通过均压环支柱12与电极片11相连。In this embodiment, the electron gun 1 and the accelerating tube 2 are important components of the electron accelerator. The electron gun 1 provides the electron beam source for the electron accelerator, and the high-voltage electron accelerating tube 2 is used to accelerate the electron beam and increase the energy of the electron beam. It mainly includes a hot cathode high-voltage DC electron gun, a high-voltage electron accelerating tube 2, and a high-voltage power supply for the electron gun. The electron gun 1 and the accelerating tube 2 adopt a separate structure design, and the two parts are connected by a CF150 vacuum stainless steel flange 3. The hot cathode high-voltage DC electron gun uses filament heating to increase the kinetic energy of the electrons inside the cathode, so that the kinetic energy of some electrons is large enough to It overcomes the surface barrier of the solid cathode and escapes from the body, forming electron emission. The high-voltage electron accelerating tube 2 accelerates electrons by using the pressure difference between the electrode sheets 11 , and the pressure equalizing ring 10 is connected to the electrode sheet 11 through a pressure equalizing ring support 12 .
为了满足电子枪的工作环境和束流传输，解决“月尘舱”接口处为低真空(约5×10-4Pa)环境，而电子枪阴极要求在超高真空(10-5～10-7Pa)环境下工作的问题，采用差分真空系统为电子束的产生和传输提供高真空环境，增加阴极使用寿命并提高束流传输效率。所述真空阀22为气动闸板阀，所述真空泵15包括两台分子泵、干泵及其控制器，所述真空系统内设置有真空测量部件，所述真空测量部件包括一个冷规及其控制器。气动闸板阀为CF200标准安装法兰，安装于陶瓷真空室13和月尘舱波纹管之间，用于电子加速器与月尘舱的真空隔离。电子加速器和月尘舱对接采用真空波纹管，用于吸收两者之间的相对形变和位移。In order to meet the working environment and beam transmission of the electron gun, the interface of the "lunar dust cabin" is solved in a low vacuum (about 5×10-4Pa) environment, while the cathode of the electron gun is required to be in an ultra-high vacuum (10-5～10-7Pa) environment For the problem of work, the differential vacuum system is used to provide a high vacuum environment for the generation and transmission of electron beams, to increase the service life of the cathode and to improve the beam transmission efficiency. The vacuum valve 22 is a pneumatic gate valve. The vacuum pump 15 includes two molecular pumps, a dry pump and a controller thereof. The vacuum system is provided with a vacuum measuring component, and the vacuum measuring component includes a cold gauge and its controller. The pneumatic gate valve is a CF200 standard installation flange, which is installed between the ceramic vacuum chamber 13 and the bellows of the lunar dust cabin, and is used for vacuum isolation between the electron accelerator and the lunar dust cabin. The vacuum bellows are used for the docking of the electron accelerator and the lunar dust capsule to absorb the relative deformation and displacement between the two.
磁铁系统主要用于在电子束传输过程，对电子束进行聚焦、偏转、扫描等，所述第一不锈钢真空室上设置有磁透镜18，磁透镜18用于对电子束的横向包络进行控制，保证电子束的远距离传输，减少束流传输过程中的损失。校正磁铁19用于矫正由于安装误差和干扰磁场导致的束流位置偏差，确保束流轨迹位数真空室中心。扫描磁铁21用于实现束流在1m×1m范围的扫描。The magnet system is mainly used to focus, deflect, scan, etc. the electron beam during the transmission process of the electron beam. The first stainless steel vacuum chamber is provided with a magnetic lens 18, which is used to control the transverse envelope of the electron beam , to ensure the long-distance transmission of the electron beam and reduce the loss during beam transmission. The correction magnet 19 is used to correct the deviation of the beam current position caused by the installation error and the disturbing magnetic field, so as to ensure that the beam current trajectory is at the center of the vacuum chamber. The scanning magnet 21 is used to realize the scanning of the beam current in the range of 1m×1m.
控制系统是电子加速器的电控主体，按照需求项目的要求，月尘充电系统电子加速器的控制系统底层硬件控制分为电源设备控制、真空设备控制以及束流测量设备控制。如图7所示，其中电源设备控制模块主要负责磁透镜磁铁电源、校正磁铁电源、扫描磁铁电源以及电子枪高压电源的控制和状态监测；真空设备控制模块主要负责分子泵的控制以及真空计数据的实时采集；束流测量设备控制模块主要负责法拉第筒、荧光靶探测器运动控制、法拉第筒信号的实时采集、荧光靶视频信号的获取以及束流流强的实时在线监测。The control system is the electronic control body of the electron accelerator. According to the requirements of the demand project, the underlying hardware control of the electron accelerator control system of the lunar dust charging system is divided into power equipment control, vacuum equipment control, and beam current measurement equipment control. As shown in Figure 7, the power supply equipment control module is mainly responsible for the control and status monitoring 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 the control of the molecular pump and the data collection of the vacuum gauge Real-time acquisition; the control module of the beam measurement equipment is mainly responsible for the motion control of the Faraday cup and the fluorescent target detector, the real-time collection of the Faraday cup signal, the acquisition of the video signal of the fluorescent target, and the real-time online monitoring of the beam current intensity.
束测系统20包括荧光靶和法拉第筒。束测系统作为装置调束、验收和运行时诊断的主要工具。束测系统分为在线设备和调试设备两类，在线设备包括荧光靶束斑检测器和法拉第筒流强检测器，其中束斑检测器用于束斑形状和束流位置测量，法拉第桶流强检测器用于束流流强测量，束流能量的在线实时数据由电子枪及加速管所施加的高压给出。如图8所示，可以灵活安装于3个不同位置测量束流参数；辐照区的能量测量、强度测量和扫描均匀度测量作为调试工具在加速器调试初期加入，正式运行时移除。Beaming system 20 includes a fluorescent target and a Faraday cage. The beam test system is used as the main tool for device beam adjustment, acceptance and runtime diagnosis. The beam measurement system is divided into two types: online equipment and debugging equipment. The online equipment includes a fluorescent target beam spot detector and a Faraday cup flow intensity detector. The beam spot detector is used for beam spot shape and beam position measurement, and the Faraday bucket flow intensity detector For beam current intensity measurement, the online real-time data of beam energy is given by the high voltage applied by the electron gun and accelerating tube. As shown in Figure 8, it can be flexibly installed in three different positions to measure beam parameters; the energy measurement, intensity measurement and scanning uniformity measurement of the irradiation area are added as debugging tools at the initial stage of accelerator debugging, and removed during official operation.
以上对本发明所提供的一种用于月球表面充电环境模拟的电子加速器装置，进行了详细介绍，本文中应用了具体个例对本发明的原理及实施方式进行了阐述，以上实施例的说明只是用于帮助理解本发明的方法及其核心思想；同时，对于本领域的一般技术人员，依据本发明的思想，在具体实施方式及应用范围上均会有改变之处，综上所述，本说明书内容不应理解为对本发明的限制。Above, a kind of electron accelerator device used for the simulation of the lunar surface charging environment provided by the present invention has been introduced in detail. In this paper, specific examples have been used to illustrate the principle and implementation of the present invention. The description of the above embodiments is only used To help understand the method of the present invention and its core idea; at the same time, for those of ordinary skill in the art, according to the idea of the present invention, there will be changes in the specific implementation and scope of application. In summary, this specification The content should not be construed as a limitation of the invention.
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| CN202110765197.8ACN113597079B (en) | 2021-07-06 | 2021-07-06 | An electron accelerator device for simulating charging environment on the lunar surface |
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| CN202110765197.8ACN113597079B (en) | 2021-07-06 | 2021-07-06 | An electron accelerator device for simulating charging environment on the lunar surface |
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