CN105460238A - Spacecraft surface potential active control system - Google Patents
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Abstract
本发明提供了一种航天器表面电位主动控制系统，通过采用液态金属离子发射器向空间发射正离子流来修正航天器表面的电流平衡，控制航天器表面电位，避免不等量带电现象，也可减少光电子扰乱等离子体离子和电子测量的能量带，接近仪器测量限制的范围，提高测量的稳定性和准确性；本发明的电位主动控制方法可以同时控制正电位和负电位，因此具有更广泛的应用范围；本发明的控制系统通过采用液态金属离子发射器对航天器表面电位进行控制，从卫星电源获得加热和高压供电，因此本系统具有结构简单，易于实现的特点。
The invention provides an active control system for the surface potential of a spacecraft, which corrects the current balance on the surface of the spacecraft by using a liquid metal ion emitter to launch a positive ion flow into space, controls the surface potential of the spacecraft, and avoids the phenomenon of unequal charging. It can reduce the photoelectron disturbance to the energy band of plasma ion and electronic measurement, close to the range of instrument measurement limit, improve the stability and accuracy of measurement; the active potential control method of the present invention can control positive potential and negative potential at the same time, so it has a wider range The scope of application; the control system of the present invention controls the surface potential of the spacecraft by using a liquid metal ion transmitter, and obtains heating and high-voltage power supply from the satellite power supply. Therefore, the system has the characteristics of simple structure and easy implementation.
Description
技术领域 technical field
本发明涉及航天器空间环境效应防护领域，尤其涉及一种航天器电位主动控制系统。 The invention relates to the field of spacecraft space environment effect protection, in particular to a spacecraft potential active control system.
背景技术 Background technique
航天器在轨运行期间，受空间等离子体、光照等空间环境影响，将产生表面电荷积累造成的带电现象。在地球阴影区，航天器表面电位有可能达到负的数千伏甚至上万伏；而在太阳光照条件下，受光电子发射影响，航天器光照表面的电位有可能达到正的数十伏。航天器表面带电现象会对其在轨安全稳定运行和探测数据的准确性造成严重影响： During the orbital operation of the spacecraft, affected by the space environment such as space plasma and light, the charging phenomenon caused by the accumulation of surface charges will occur. In the shadow area of the earth, the surface potential of the spacecraft may reach negative thousands of volts or even tens of thousands of volts; while under the condition of sunlight, affected by the emission of photoelectrons, the potential of the illuminated surface of the spacecraft may reach tens of volts of positive. The phenomenon of electrification on the surface of a spacecraft will seriously affect its safe and stable operation in orbit and the accuracy of detection data:
(1)航天器表面不可避免的要采用多种不同特性的材料，这些材料的介电常数、二次电子发射系数、光电子发射系数等参数都存在差异，因此在同种环境下也会产生电位差；航天器表面经常使用介质材料，在航天器表面光照区和非光照区的同种介质材料也会存在电位差。当上述电位差达到一定程度时，可能会发生放电，击穿表面材料或者干扰航天器运行； (1) It is inevitable to use a variety of materials with different characteristics on the surface of the spacecraft. The parameters such as the dielectric constant, secondary electron emission coefficient, and photoelectron emission coefficient of these materials are different, so potentials will also be generated in the same environment. Dielectric materials are often used on the surface of spacecraft, and there will be potential differences between the same dielectric material in the illuminated and non-illuminated areas of the spacecraft surface. When the above potential difference reaches a certain level, discharge may occur, breakdown the surface material or interfere with the operation of the spacecraft;
(2)航天器对空间环境尤其是等离子体环境进行精确测量时，要求航天器具有较低的电位，而航天器表面带电现象造成的表面电位会影响航天器周围等离子体的轨迹和能量，使等离子体分布函数变得扭曲，难以准确测量离子分布函数和低能电子谱。 (2) When the spacecraft accurately measures the space environment, especially the plasma environment, the spacecraft is required to have a low potential, and the surface potential caused by the charging phenomenon on the surface of the spacecraft will affect the trajectory and energy of the plasma around the spacecraft, so that The plasma distribution function becomes distorted, making it difficult to accurately measure ion distribution functions and low-energy electron spectra.
我国航天器设计过程中采用了严格接地等措施来防止不等量带电现象的发生。但是随着我国各轨道航天器的尺寸增大、寿命延长、工作电压提高等影响，单纯接地措施已经越来越难以满足要求。尤其是各类空间环境探测卫星对航天器电位控制提出了近乎苛刻的要求，因此，有必要开发一种航天器表面电位控制系统。 In the design process of my country's spacecraft, measures such as strict grounding are adopted to prevent the occurrence of unequal charging. However, with the increase in size, life extension, and increase in operating voltage of my country's orbiting spacecraft, it has become increasingly difficult for simple grounding measures to meet the requirements. In particular, all kinds of space environment exploration satellites put forward almost strict requirements on the potential control of spacecraft. Therefore, it is necessary to develop a surface potential control system of spacecraft.
发明内容 Contents of the invention
有鉴于此，本发明提供了一种航天器表面电位主动控制系统，通过采用液态金属离子发射器向空间发射正离子流来控制航天器表面电位，避免不等量带电现象，提高测量的稳定性和准确性，并可同时控制表面正电位和负电位，具有广泛的应用前景。 In view of this, the present invention provides an active control system for the surface potential of a spacecraft, which controls the surface potential of the spacecraft by using a liquid metal ion emitter to launch a positive ion flow into space, avoids the phenomenon of unequal charging, and improves the stability of the measurement and accuracy, and can simultaneously control the positive potential and negative potential of the surface, which has broad application prospects.
为了解决上述技术问题，本发明是这样实现的： In order to solve the problems of the technologies described above, the present invention is achieved in that:
一种航天器电位主动控制系统，包括控制单元、电源单元、表面电位监测探头以及液态金属离子发射器；所述控制单元分别与电源单元、表面电位监测探头以及液态金属离子发射器相连；所述电源单元分别与液态金属离子发射器和航天器中的卫星电源相连； An active potential control system for a spacecraft, comprising a control unit, a power supply unit, a surface potential monitoring probe, and a liquid metal ion emitter; the control unit is respectively connected to the power supply unit, the surface potential monitoring probe, and the liquid metal ion emitter; the The power supply unit is respectively connected with the liquid metal ion launcher and the satellite power supply in the spacecraft;
所述表面电位监测探头固定在航天器表面，用于实时采集航天器表面的电位，并将电位信号发送给所述控制单元； The surface potential monitoring probe is fixed on the surface of the spacecraft, and is used to collect the potential on the surface of the spacecraft in real time, and send the potential signal to the control unit;
所述液态金属离子发射器固定在航天器表面，液态金属离子发射器和航天器外表面均接地，两者互相绝缘；液态金属离子发射器用于向航天器所在的空间发射正离子流，同时，将其内部金属池的温度信号至所述控制单元； The liquid metal ion emitter is fixed on the surface of the spacecraft, the liquid metal ion emitter and the outer surface of the spacecraft are grounded, and the two are insulated from each other; the liquid metal ion emitter is used to launch a positive ion flow to the space where the spacecraft is located, and at the same time, signal the temperature of its internal metal pool to said control unit;
所述电源单元根据所述液态金属离子发射器的供电需求，将来自卫星电源的供电进行转换，并根据从控制单元接收的控制信号对液态金属离子发射器的固态金属提供加热供电或对液态金属离子发射器的引出极提供高压供电； The power supply unit converts the power supply from the satellite power supply according to the power supply requirements of the liquid metal ion emitter, and provides heating power to the solid metal of the liquid metal ion emitter or provides heating power to the liquid metal ion emitter according to the control signal received from the control unit. The extraction pole of the ion emitter provides high voltage power supply;
所述控制单元根据从液态金属离子发射器接收的温度信号，向所述电源单元发送控制信号，控制电源单元开始或结束对固态金属的加热供电，使金属池中的金属维持熔融状态； The control unit sends a control signal to the power supply unit according to the temperature signal received from the liquid metal ion emitter, and controls the power supply unit to start or stop heating and supplying power to the solid metal, so as to maintain the metal in the metal pool in a molten state;
所述控制单元根据从所述表面电位监测探头接收的电位信号，向所述电源单元发送控制信号：当电位信号高于预设电位范围时，向电源单元发送开始高压供电控制信号；当电位信号等于或低于预设电位范围时，向电源单元发送结束高压供电控制信号，由此实现对航天器表面电位的主动控制。 The control unit sends a control signal to the power supply unit according to the potential signal received from the surface potential monitoring probe: when the potential signal is higher than the preset potential range, sends a control signal to the power supply unit to start high-voltage power supply; when the potential signal When it is equal to or lower than the preset potential range, a control signal to end the high-voltage power supply is sent to the power supply unit, thereby realizing active control of the surface potential of the spacecraft.
所述控制单元对航天器表面电位的主动控制包括对正电位的控制和对负电位的控制： The active control of the surface potential of the spacecraft by the control unit includes the control of the positive potential and the control of the negative potential:
对正电位进行主动控制时：当判定航天器表面电位Vs大于预设正电位Vl时，向所述电源单元发送开始高压供电控制信号；当航天器表面电位Vs达到或小于预设正电位Vl时，向所述电源单元发送停止高压供电控制信号； When actively controlling the positive potential: when it is determined that the surface potential V s of the spacecraft is greater than the preset positive potential V l , a control signal to start high-voltage power supply is sent to the power supply unit; when the surface potential V s of the spacecraft reaches or is lower than the preset positive potential When the potential V1 , send a control signal to stop the high-voltage power supply to the power supply unit;
对负电位进行主动控制时：当判定航天器表面电位Vs小于预设的负电位下限值V2时，控制单元将液态金属离子发射器的接地断开，并同时向所述电源单元发送开始高压供电控制信号；当判定航天器表面电位Vs达到或大于预设负电位V3时，向所述电源单元发送停止高压供电控制信号； When actively controlling the negative potential: when it is determined that the surface potential V s of the spacecraft is less than the preset negative potential lower limit V 2 , the control unit disconnects the grounding of the liquid metal ion emitter and sends a signal to the power supply unit at the same time Start the high-voltage power supply control signal; when it is determined that the surface potential V s of the spacecraft reaches or exceeds the preset negative potential V 3 , send a control signal to stop the high-voltage power supply to the power supply unit;
其中，所述预设的负电位下限值V2取为航天器表面不发生放电的最低安全电位；所述预设负电位V3大于预设的负电位下限值V2。 Wherein, the preset negative potential lower limit V 2 is taken as the lowest safe potential for no discharge on the surface of the spacecraft; the preset negative potential V 3 is greater than the preset negative potential lower limit V 2 .
所述液态金属离子发射器中的金属选用金属铟。 The metal in the liquid metal ion emitter is selected from metal indium.
所述液态金属离子发射器向控制单元实时反馈加载在液态金属离子发射器的引出极上的电压；所述控制单元将反馈的引出极加载电压与向电源单元输出的所述电压值进行比较，一次判断电源单元是否处于正常工作状态。 The liquid metal ion emitter feeds back the voltage loaded on the extraction pole of the liquid metal ion emitter in real time to the control unit; the control unit compares the fed-back extraction pole loading voltage with the voltage value output to the power supply unit, It is judged once whether the power supply unit is in a normal working state.
所述控制单元还与航天器的卫星电源相连，用于对自身和表面电位监测探头进行供电。 The control unit is also connected with the satellite power supply of the spacecraft to supply power to itself and the surface potential monitoring probe.
所述控制单元还与航天器的开关机控制设备相连，用于接收航天器的开关机信号，在接收到航天器的开机信号后，才开始对电源单元进行控制。 The control unit is also connected with the power-on/off control device of the spacecraft for receiving the power-on/off signal of the spacecraft, and starts to control the power supply unit only after receiving the power-on signal of the spacecraft.
所述控制单元还分别与航天器的通信总线相连，将航天器表面的电位信号上传至航天器。 The control units are also respectively connected to the communication bus of the spacecraft, and upload the potential signal on the surface of the spacecraft to the spacecraft.
本发明具有如下有益效果： The present invention has following beneficial effects:
(1)本发明通过发射正离子束修正航天器表面的电流平衡，降低航天器表面电位，避免不等量带电现象，也可减少光电子扰乱等离子体离子和电子测量的能量带，接近仪器测量限制的范围，提高测量的稳定性和准确性； (1) The present invention corrects the current balance on the surface of the spacecraft by emitting positive ion beams, reduces the surface potential of the spacecraft, avoids the phenomenon of unequal charging, and can also reduce the photoelectron disturbance of the energy band of the plasma ion and electronic measurement, approaching the measurement limit of the instrument range, improve the stability and accuracy of measurement;
(2)本发明的电位主动控制方法可以同时控制正电位和负电位，因此具有更广泛的应用范围； (2) Potential active control method of the present invention can control positive potential and negative potential simultaneously, therefore has wider application scope;
(3)本发明的控制系统通过采用液态金属离子发射器对航天器表面电位进行控制，从卫星电源获得加热和高压供电，因此本系统具有结构简单，易于实现的特点。 (3) The control system of the present invention controls the surface potential of the spacecraft by using a liquid metal ion transmitter, and obtains heating and high-voltage power supply from the satellite power supply, so the system has the characteristics of simple structure and easy implementation.
附图说明 Description of drawings
图1为本发明的控制系统的结构示意图。 Fig. 1 is a structural schematic diagram of the control system of the present invention.
图2为本发明的控制系统的原理图。 Fig. 2 is a schematic diagram of the control system of the present invention.
其中，1-表面电位监测探头，2-液态金属离子发射器，3-控制单元，4-电源单元。 Among them, 1-surface potential monitoring probe, 2-liquid metal ion emitter, 3-control unit, 4-power supply unit.
具体实施方式 detailed description
下面结合附图并举实施例，对本发明进行详细描述。 The present invention will be described in detail below with reference to the accompanying drawings and examples.
本发明的一种航天器电位主动控制系统，如图1和2所示，包括控制单元、电源单元、表面电位监测探头以及液态金属离子发射器；控制单元分别与电源单元、表面电位监测探头以及液态金属离子发射器相连；电源单元分别与液态金属离子发射器和航天器中的卫星电源相连； A kind of spacecraft potential active control system of the present invention, as shown in Figure 1 and 2, comprises control unit, power supply unit, surface potential monitoring probe and liquid metal ion emitter; Control unit is connected with power supply unit, surface potential monitoring probe and The liquid metal ion launcher is connected; the power supply unit is respectively connected with the liquid metal ion launcher and the satellite power supply in the spacecraft;
表面电位监测探头固定在航天器表面，用于实时采集航天器表面的电位，并将电位信号发送给控制单元； The surface potential monitoring probe is fixed on the surface of the spacecraft, which is used to collect the potential on the surface of the spacecraft in real time, and send the potential signal to the control unit;
液态金属离子发射器固定在航天器表面，液态金属离子发射器和航天器外表面均接地，两者互相绝缘；液态金属离子发射器用于向航天器所在的空间发射正离子流，同时，将其内部金属池的温度信号至控制单元； The liquid metal ion emitter is fixed on the surface of the spacecraft, the liquid metal ion emitter and the outer surface of the spacecraft are both grounded, and the two are insulated from each other; the liquid metal ion emitter is used to launch positive ion flow to the space where the spacecraft is located, and at the same time, it The temperature signal of the internal metal pool to the control unit;
电源单元根据液态金属离子发射器的供电需求，将来自卫星电源的供电进行转换，并根据从控制单元接收的控制信号对液态金属离子发射器的固态金属提供加热供电或对引出极提供高压供电； The power supply unit converts the power supply from the satellite power supply according to the power supply requirements of the liquid metal ion emitter, and provides heating power to the solid metal of the liquid metal ion emitter or high-voltage power supply to the extraction pole according to the control signal received from the control unit;
控制单元根据从液态金属离子发射器接收的温度信号，向电源单元发送控制信号，控制电源单元开始或结束对固态金属的加热供电，使金属池中的金属维持熔融状态； The control unit sends a control signal to the power supply unit according to the temperature signal received from the liquid metal ion emitter, and controls the power supply unit to start or stop heating and supplying the solid metal, so that the metal in the metal pool remains in a molten state;
控制单元根据从表面电位监测探头接收的电位信号，向电源单元发送控制信号：当电位信号高于预设电位时，向电源单元发送开始高压供电控制信号；当电位信号等于或低于预设电位时，向电源单元发送结束高压供电控制信号，由此实现对航天器表面电位的主动控制。 The control unit sends a control signal to the power supply unit according to the potential signal received from the surface potential monitoring probe: when the potential signal is higher than the preset potential, it sends a control signal to the power supply unit to start high-voltage power supply; when the potential signal is equal to or lower than the preset potential When , send a control signal to the power supply unit to end the high-voltage power supply, thereby realizing the active control of the surface potential of the spacecraft.
其中，控制单元对航天器表面电位的主动控制包括对正电位的控制和对负电位的控制： Among them, the active control of the surface potential of the spacecraft by the control unit includes the control of the positive potential and the control of the negative potential:
对正电位进行主动控制时：当判定航天器表面电位Vs大于预设正电位Vl时，向电源单元发送开始高压供电控制信号，电源单元对液态金属离子发射器进行高压供电，液态金属离子发射器开始发射正离子流，降低航天器表面的正电位；当航天器表面电位Vs达到或小于预设正电位Vl时，向电源单元发送停止高压供电控制信号，液态金属离子发射器停止发射正离子流。 When actively controlling the positive potential: when it is determined that the surface potential V s of the spacecraft is greater than the preset positive potential V l , a control signal to start high-voltage power supply is sent to the power supply unit, and the power supply unit supplies high-voltage power to the liquid metal ion emitter, and the liquid metal ion The transmitter starts to emit positive ion flow to reduce the positive potential on the surface of the spacecraft; when the surface potential V s of the spacecraft reaches or is lower than the preset positive potential V l , a control signal to stop the high-voltage power supply is sent to the power supply unit, and the liquid metal ion transmitter stops Emits a stream of positive ions.
对负电位进行主动控制时：当判定航天器表面电位Vs小于预设的负电位下限值V2时，控制单元将液态金属离子发射器的接地断开，并同时向电源单元发送开始高压供电控制信号电源单元对液态金属离子发射器进行高压供电，液态金属离子发射器开始发射正离子流，由于航天器表面为负电位，发射的正离子流在引力作用下会回到航天器表面，由于液态金属离子发射器接地断开，并和航天器表面绝缘，发射正离子流并不会聚集电子，因此，回落的正离子中和了航天器表面的负电荷，由此提高了航天器表面电位；当判定航天器表面电位Vs达到或大于预设负电位V3时，向电源单元发送停止高压供电控制信号，液态金属离子发射器停止发射正离子流。 When actively controlling the negative potential: when it is determined that the surface potential V s of the spacecraft is less than the preset negative potential lower limit V 2 , the control unit disconnects the grounding of the liquid metal ion emitter and simultaneously sends a high voltage start to the power supply unit The power supply control signal power supply unit provides high-voltage power supply to the liquid metal ion emitter, and the liquid metal ion emitter starts to emit positive ion flow. Since the surface of the spacecraft is at a negative potential, the emitted positive ion flow will return to the surface of the spacecraft under the action of gravity. Since the liquid metal ion emitter is disconnected from the ground and is insulated from the surface of the spacecraft, the positive ion flow emitted does not gather electrons. Therefore, the positive ions that fall back neutralize the negative charges on the surface of the spacecraft, thereby improving the surface of the spacecraft. Potential; when it is determined that the surface potential V s of the spacecraft reaches or exceeds the preset negative potential V 3 , a control signal to stop the high-voltage power supply is sent to the power supply unit, and the liquid metal ion emitter stops emitting positive ions.
其中，预设的负电位下限值V2取为航天器表面不发生放电的最低安全电位；为避免液态金属离子源频繁开机，预设负电位V3大于预设的负电位下限值V2；为了延长液态金属离子源的使用寿命，要尽量减少液态金属离子源的开关机次数，因此预设负电位V3的大小要尽量保证航天器在轨道阴影区运行过程中，其表面电位不会再次下降到预设的负电位下限值V2。 Among them, the preset negative potential lower limit V 2 is taken as the lowest safe potential for no discharge on the surface of the spacecraft; in order to avoid frequent startup of the liquid metal ion source, the preset negative potential V 3 is greater than the preset negative potential lower limit V 2 ; in order to prolong the service life of the liquid metal ion source, the switching times of the liquid metal ion source should be reduced as much as possible, so the size of the preset negative potential V3 will ensure that the surface potential of the spacecraft does not change as far as possible during the operation of the orbital shadow area. It will drop to the preset negative potential lower limit value V 2 again.
液态金属离子发射器向控制单元实时反馈加载在引出极上的电压；控制单元将反馈的引出极加载电压与向电源单元输出的电压值进行比较，一次判断电源单元是否处于正常工作状态。 The liquid metal ion emitter feeds back the voltage loaded on the extraction pole to the control unit in real time; the control unit compares the fed-back voltage loaded on the extraction pole with the voltage value output to the power supply unit, and judges whether the power supply unit is in a normal working state.
控制单元还与航天器的卫星电源相连，用于对自身和表面电位监测探头进行供电。 The control unit is also connected to the satellite power supply of the spacecraft for powering itself and the surface potential monitoring probe.
控制单元还与航天器的开关机控制设备相连，用于接收航天器的开关机信号，在接收到航天器的开机信号后，才向电源单元发送控制信号。 The control unit is also connected with the power-on/off control equipment of the spacecraft for receiving the power-on/off signal of the spacecraft, and sends a control signal to the power supply unit only after receiving the power-on signal of the spacecraft.
控制单元还分别与航天器的通信总线相连，将航天器表面的电位信号上传至航天器。 The control units are also respectively connected to the communication bus of the spacecraft, and upload the potential signal on the surface of the spacecraft to the spacecraft.
液态金属离子发射器电位主动控制验证试验举例： Example of active control verification test of liquid metal ion emitter potential:
以液态金属离子发射器控制电航天器表面正电位为例，设计了一种基于铟液态金属离子发射器的控制系统。铟液态金属离子发射器电位主动控制工作时，控制系统先开启电压为30V的加热电源将液态金属加热在到180～200℃之间，通过表面电位监测探头监测表面电位，当表面电位大于预置电位时，控制系统开启点火电源，实际点火电压<8kV，点火成功后，实际运行电压<7kV；通过质谱计监测到离子能量为5～10keV，单个发射器离子束流为10～100μA，典型工作电流20μA时工作电压为6kV。通过实时检测表面电位，经控制系统分析处理，当表面电位降到预置电位时控制点火高压电源断电，使液态金属离子发射器关闭，从而实现对表面正电位的主动控制。 Taking liquid metal ion emitters as an example to control the positive potential on the surface of an electric spacecraft, a control system based on indium liquid metal ion emitters is designed. When the potential of the indium liquid metal ion emitter is actively controlled, the control system first turns on the heating power supply with a voltage of 30V to heat the liquid metal between 180 and 200°C, and monitors the surface potential through the surface potential monitoring probe. When the surface potential is greater than the preset At potential, the control system turns on the ignition power supply, the actual ignition voltage is <8kV, and after the ignition is successful, the actual operating voltage is <7kV; the ion energy monitored by the mass spectrometer is 5-10keV, and the ion beam current of a single emitter is 10-100μA, typical work The working voltage is 6kV when the current is 20μA. Through real-time detection of the surface potential, analyzed and processed by the control system, when the surface potential drops to a preset potential, the ignition high-voltage power supply is controlled to be powered off, so that the liquid metal ion emitter is turned off, thereby realizing active control of the positive surface potential.
为在地面验证此控制系统控制航天器表面正电位的可靠性，在装有太阳模拟器的真空系统中，安装铟液态金属离子发射器电位主动控制装置，作为简单模拟空间环境航天器充电电位主动控制试验。简要控制过程如下： In order to verify the reliability of the control system on the ground to control the positive potential of the spacecraft surface, in a vacuum system equipped with a solar simulator, an indium liquid metal ion emitter potential active control device is installed as a simple simulation space environment spacecraft charging potential active control device. control test. The brief control process is as follows:
1)通过控制单元打开液态金属离子发射器加热电源，使液态金属温度达到设计的温度范围，此时检测到液态金属离子发射器温度为185℃； 1) Turn on the heating power of the liquid metal ion emitter through the control unit, so that the temperature of the liquid metal reaches the designed temperature range. At this time, it is detected that the temperature of the liquid metal ion emitter is 185°C;
2)打开太阳模拟器模拟空间环境充电，实时检测表面电位，预置电压为0V，为模拟最恶劣环境充电到最高电位，未与预置电位进行比较。 2) Turn on the solar simulator to simulate charging in the space environment, detect the surface potential in real time, the preset voltage is 0V, and charge to the highest potential to simulate the worst environment, and do not compare with the preset potential.
3)当表面电位检测达+40V时，控制单元开启液态金属离子发射器工作。电压5kV时，液态金属离子发射器点火，引出极电压6kV时，检测发射电流为20μA； 3) When the surface potential detection reaches +40V, the control unit starts the liquid metal ion emitter to work. When the voltage is 5kV, the liquid metal ion emitter is ignited, and when the lead-out voltage is 6kV, the detected emission current is 20μA;
4)经过5～6分钟左右，检测到表面电位为0.4V； 4) After about 5 to 6 minutes, the surface potential is detected to be 0.4V;
5)当检测到表面电位为0V时，控制单元控制电源单元的高压供电单元关闭，液态金属离子发射器关闭，实现表面电位的主动控制。 5) When it is detected that the surface potential is 0V, the control unit controls the high-voltage power supply unit of the power supply unit to be turned off, and the liquid metal ion emitter is turned off, so as to realize the active control of the surface potential.
通过以上举例和试验验证为例，说明此系统能够有效实现航天器表面电位的主动控制。 Through the above example and test verification as an example, it shows that this system can effectively realize the active control of the surface potential of the spacecraft.
综上所述，以上仅为本发明的较佳实施例而已，并非用于限定本发明的保护范围。凡在本发明的精神和原则之内，所作的任何修改、等同替换、改进等，均应包含在本发明的保护范围之内。 To sum up, the above are only preferred embodiments of the present invention, and are not intended to limit the protection scope of the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included within the protection scope of the present invention.
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