CN105626410A - Plume neutralizer of space electric thruster - Google Patents
Plume neutralizer of space electric thruster Download PDFInfo
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- CN105626410A CN105626410A CN201510996242.5A CN201510996242A CN105626410A CN 105626410 A CN105626410 A CN 105626410A CN 201510996242 A CN201510996242 A CN 201510996242A CN 105626410 A CN105626410 A CN 105626410A
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- radiator
- neutralizer
- well heater
- pore plate
- apical pore
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0087—Electro-dynamic thrusters, e.g. pulsed plasma thrusters
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
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- Plasma & Fusion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Plasma Technology (AREA)
Abstract
The invention discloses a plume neutralizer of a space electric thruster. The neutralizer comprises an ignition electrode, a top hole plate, a heater, a heat shielding cylinder, an emitting body and a support pipe; the emitting body is mounted in the support pipe; the top hole plate shields out of the emitting body, and is fixedly connected with the support pipe; the heater is mounted out of the support pipe opposite to the emitting body; a heating area covers the whole emitting body; the heater is wrapped with an insulation ceramic layer; the heat shielding cylinder covers the heater, and forms gaps with the heater and the insulation ceramic layer; the ignition electrode is mounted at the downstream of the top hole plate, and forms a gap with a small hole of the top hole plate; and a center hole of the ignition electrode is coaxial with the small hole of the top hole plate. The neutralizer generates a lot of electrons through a hot electron ionized gas discharge mode; continuously emitted electrons are high in density; after the gas discharge is stabilized, the self-heating can be performed to maintain discharge, so that the system power consumption is saved; the equivalent potential is low; the effective acceleration voltage of the thruster is higher; and the specific impulse of the thruster is high.
Description
Technical field
The invention belongs to space industry, concrete, it relates to a kind of space electric thruster plume neutralizer, it is applicable to the plume neutralization of the electric thruster such as Huo Er, ion, microwave and Flied emission.
Background technology
Electricity advances has very high efflux velocity, relative chemical advances to be had than the remarkable feature leapt high, can be widely used in spacecraft Orbit Transformation, track maintenance, gesture stability, without towing control, survey of deep space promote mainly into etc. task, significantly save propelling agent, increase the spacecraft life-span or reduce delivery demand. Along with the development of spacemarching, electricity advances commercial applications from the 90's of last century, it is successfully applied to up to a hundred spacecrafts, electricity has been advanced the significant factor as Space dynamics analysis competition, survey of deep space and commercial applications by the spacefaring nations such as U.S., Europe, Russia, day, they are the gordian technique of Future Spacecraft depending on electric propulsion technology, Application Areas comprises the gesture stability of spacecraft, drag compensation, position keep, Orbit Transformation and wartime track motor-driven with reorientate. The electric thruster such as Huo Er, ion, microwave plasma and Flied emission are that current space is applied relatively extensively, studied more several thrusters. Their principle of work is similar, it is all first propelling agent is ionized as ion, then by high-voltage electric field acceleration ion, its high velocity spray is gone out and produce reactive force, the ion needs outside offer stream of electrons neutralization produced is provided, the plume that thruster is sprayed is electric neutrality, avoids spacecraft charged.
The Large Spacecraft such as manned space station are caught a cold the bringing out of the factors such as thick plasma body and secondary electron in middle low orbit environment, and the use of large-scale high pressure photovoltaic solar battle array, can cause the inequality charging that spacecraft surface is serious. Electricity propelling neutralizer can as a low-power plasma body source, the plasma body bridge of a low resistance is set up between spacecraft surface and space plasma, form a charge discharging resisting passage, control spacecraft is relative to the current potential of space environment, it is ensured that the safety of the extravehicular activity with spacefarer is run in space station.
The principle of work of traditional vacuum electronic technology field electron source is similar to electric thruster neutralizer, all must work under vacuum conditions, reaches working temperature heat of emission electronics by outside power supply heating radiator, and the electric field relying on external high voltage to be formed draws electronics. But, in vacuum electronic source, the transmitter current of up to ten thousand hours life-span product is generally microampere or milliampere level, it is necessary to is operated in vacuum tightness and is better than 1 �� 10-4The ultra-high vacuum environment of Pa, transmitter current reaches several amperes or product needed thousands of volt high pressure of tens amperes and the lasting power supply of thousands of watts, and ejected electron current equivalence current potential is higher. The thruster in space electric propulsion field must lead to the propellant medium into certain flow when working, and ground experiment environment vacuum tightness is generally 5 �� 10-3About Pa, the local vacuum tightness of thruster reaches several hundred to upper kPa, and emitter material is had certain pollution by propelling agent, and therefore the electron source in vacuum electronics technology field is not suitable for space electric propulsion system and uses.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of space electric thruster plume neutralizer, adopt a kind of novel texture, the mode discharged by thermoelectron ionized gas produces a large amount of electronics, continue ejected electron current density height, can certainly heat sustain discharge after geseous discharge is stable, save system power dissipation; Equivalent potential is low, and the effective acceleration voltage of thruster is higher, and the ratio of thruster is leapt high; Can be used for the neutralization of the plume of the electric thruster such as Huo Er, ion, microwave and Flied emission, complete the space propultion tasks such as the Orbit Transformation of the spacecrafts such as satellite, gesture stability and drag compensation; The large-scale low rail spacecrafts such as space station can also be used for, as plasma body contactor control surface current potential, ensure spacecraft safety.
For solving the problems of the technologies described above, embodiments of the invention provide a kind of space electric thruster plume neutralizer, neutralizer comprises igniter, apical pore plate, well heater, thermoshield cylinder, radiator and supporting tube, radiator is arranged on the inside of supporting tube, apical pore plate gear and is fixedly connected with supporting tube outside radiator, well heater is arranged on outside corresponding with the radiator position of supporting tube, the coated whole radiator in heating zone, and well heater is wrapped with dielectric ceramic layer; Thermoshield barrel cover is located at well heater outside, and and be provided with gap between well heater and dielectric ceramic layer thereof, reduce thermal conduction, improve radioprotective efficiency, igniter is arranged on the downstream of apical pore plate, and and be provided with gap between the aperture of apical pore plate, the centre hole of igniter is coaxial with the aperture of apical pore plate.
Wherein, described neutralizer is gas discharge type electron source, and Working environment vacuum tightness is better than 5 �� 10-3Pa��
Wherein, described radiator adopts the electronic emission material of low effusion work content.
Wherein, described radiator is the one in oxide compound radiator, barium tungsten radiator or lanthanum boride radiator.
Wherein, described thermoshield cylinder adopts high temperature material preparation, such as molybdenum, tantalum, niobium, titanium.
Wherein, described well heater adopt high temperature material, such as tungsten, tantalum.
Wherein, igniting is very open or closed, it is necessary to other parts insulation, keep suitable distance with apical pore plate 2 simultaneously, igniter can apply positive voltage and form local highfield, be beneficial to electronics extraction.
In the present invention, gas working medium must adopt the propelling agent identical with Huo Er or ion thruster main discharge room to be working medium, strictly control water, oxygen etc. are to emitter material oxious component content, the high purity rare gas elementes such as preferred xenon and krypton, radiator working temperature maintains mode, necessarily after ionization of gas, the energy transformation that ion moves to radiator by electric field attracts is as main energy sources, if temperature work is continued after cannot keeping electric discharge, a certain proportion of heating power can be retained as energy supplement, the heating power of general sustain discharge is the 10��30% of ignition process heating power.
The useful effect of the technique scheme of the present invention is as follows:
May be used for the neutralization of the plume of the electric thruster such as space Huo Er, ion, microwave and Flied emission, avoid spacecraft is produced harmful effect, improve system efficiency and reliability, complete the space propultion tasks such as the Orbit Transformation of spacecraft, gesture stability and drag compensation, save propelling agent, it is to increase the operation on orbit time of China's satellite. The neutralizer of the present invention can also as plasma body contactor, for the surface potential ACTIVE CONTROL of the Large Spacecraft such as space station at space motion, prevent the electric charge accumulation of local, spacecraft surface from causing static discharge, ensure that spacecraft docking, cosmonaut go out the movable safety such as cabin.
Accompanying drawing explanation
Fig. 1 is the structural representation of a kind of space of embodiment of the present invention electric thruster plume neutralizer.
Fig. 2 is the structural representation of a kind of space of embodiment of the present invention electric thruster plume neutralizer embodiment.
Fig. 3 is the principle of work figure of a kind of space of embodiment of the present invention electric thruster plume neutralizer.
In figure, 1: igniter; 2: apical pore plate, 3: well heater; : 4: thermoshield cylinder; 5: radiator; 6: supporting tube; N: neutral ion; I+: ion; E-: electronics;
Embodiment
For making the technical problem to be solved in the present invention, technical scheme and advantage clearly, it is described in detail below in conjunction with the accompanying drawings and the specific embodiments.
Embodiment 1
As shown in Figure 1, neutralizer comprises igniter 1, apical pore plate 2, well heater 3, thermoshield cylinder 4, radiator 5 and supporting tube 6, radiator 5 is arranged on the inside of supporting tube 6, apical pore plate 2 keeps off outside radiator 5 and is fixedly connected with supporting tube 6, well heater 3 is arranged on outside corresponding with radiator 5 position of supporting tube 6, the coated whole radiator 5 in heating zone, well heater 3 is wrapped with dielectric ceramic layer, it is outside that thermoshield cylinder 4 is located at well heater 3, and and be provided with gap between well heater 3 and dielectric ceramic layer thereof, reduce thermal conduction, improve radioprotective efficiency, igniter 1 is arranged on the downstream of apical pore plate 2, and and be provided with gap between the aperture of apical pore plate 2, the centre hole of igniter 1 is coaxial with the aperture of apical pore plate, the emitter material of neutralizer adopts barium tungsten radiator, supporting tube and thermoshield cylinder adopt tungsten, apical pore plate adopts tungsten, well heater adopts tungsten filament, well heater pottery adopts electrophoresis alumina-ceramic, igniter adopts stainless material, cylinder enclosed formula structure, the distance of igniter and apical pore plate is 3mm.
Neutralizer test adopts triode mode to work, and principle of work figure is shown in Fig. 3, and Working environment vacuum tightness is not less than 5 �� 10-3Pa. When xenon working medium flow is 0.15��0.4mg/s, heating power 40��70W, when striking voltage is 50��300V, heat neutralizer electric discharge in 4��7 minutes, launch electronic current to realize when reaching 2��3A from heating steady operation (heater power can be closed completely), it is possible to meet in the hall thruster of power 660W or ion thruster plume and needs.
Embodiment 2
As shown in Figure 1, neutralizer comprises igniter 1, apical pore plate 2, well heater 3, thermoshield cylinder 4, radiator 5 and supporting tube 6, radiator 5 is arranged on the inside of supporting tube 6, apical pore plate 2 keeps off outside radiator 5 and is fixedly connected with supporting tube 6, well heater 3 is arranged on outside corresponding with radiator 5 position of supporting tube 6, the coated whole radiator 5 in heating zone, well heater 3 is wrapped with dielectric ceramic layer; It is outside that thermoshield cylinder 4 is located at well heater 3, and and be provided with gap between well heater 3 and dielectric ceramic layer thereof, reduce thermal conduction, improve radioprotective efficiency, igniter 1 is arranged on the downstream of apical pore plate 2, and and be provided with gap between the aperture of apical pore plate 2, the centre hole of igniter 1 is coaxial with the aperture of apical pore plate. The emitter material of hollow cathode adopts oxide compound emitter material, supporting tube, apical pore plate and thermoshield cylinder adopt molybdenum, apical pore plate adopts tungsten, well heater adopts tungsten filament, well heater pottery adopts electrophoresis alumina-ceramic, igniter adopts Stainless Steel Wire, annulus Open architecture, and the distance of igniter and apical pore plate is 2mm.
Neutralizer test adopts triode mode to work, and principle of work figure is shown in Fig. 3, and Working environment vacuum tightness is not less than 5 �� 10-3Pa. When xenon working medium flow is 0.05��0.1mg/s, heating power 30��35W, when striking voltage is 50��100V, heat neutralizer electric discharge in 2��4 minutes, transmitting electronic current reaches 0.3��1A and realizes steady operation, can meeting the hall thruster of power 50��100W or ion thruster plume and needs, well heater need to provide 5��8W to supplement power, keeps radiator temperature.
Embodiment 3
As shown in Figure 1, neutralizer comprises igniter 1, apical pore plate 2, well heater 3, thermoshield cylinder 4, radiator 5 and supporting tube 6, radiator 5 is arranged on the inside of supporting tube 6, apical pore plate 2 keeps off outside radiator 5 and is fixedly connected with supporting tube 6, well heater 3 is arranged on outside corresponding with radiator 5 position of supporting tube 6, the coated whole radiator 5 in heating zone, well heater 3 is wrapped with dielectric ceramic layer; It is outside that thermoshield cylinder 4 is located at well heater 3, and and be provided with gap between well heater 3 and dielectric ceramic layer thereof, reduce thermal conduction, improve radioprotective efficiency, igniter 1 is arranged on the downstream of apical pore plate 2, and and be provided with gap between the aperture of apical pore plate 2, the centre hole of igniter 1 is coaxial with the aperture of apical pore plate. The emitter material of neutralizer adopts lanthanum hexaborane radiator (LaB6), supporting tube adopts tantalum, thermoshield cylinder adopts tungsten, apical pore plate adopts tungsten, well heater adopts tungsten filament, well heater pottery adopts high temperature sintering alumina-ceramic, and igniter adopts molybdenum, cylinder enclosed formula structure, and the distance of igniter and apical pore plate is 5mm.
Neutralizer test adopts triode mode to work, and principle of work figure is shown in Fig. 3, and Working environment vacuum tightness is not less than 5 �� 10-3Pa. When xenon working medium flow is 0.8��1.5mg/s, heating power 120��200W, when striking voltage is 150��300V, heat neutralizer electric discharge in 6��8 minutes, launch electronic current and realize steady operation when reaching 6��17A, can meet in the hall thruster of power 2000��4500W or ion thruster plume and needs, when launching electronic current lower than 8A, need well heater to provide the supplementary power of 15��20W, keep radiator temperature.
Embodiment 4
As shown in Figure 1, neutralizer comprises igniter 1, apical pore plate 2, well heater 3, thermoshield cylinder 4, radiator 5 and supporting tube 6, radiator 5 is arranged on the inside of supporting tube 6, apical pore plate 2 keeps off outside radiator 5 and is fixedly connected with supporting tube 6, well heater 3 is arranged on outside corresponding with radiator 5 position of supporting tube 6, the coated whole radiator 5 in heating zone, well heater 3 is wrapped with dielectric ceramic layer, it is outside that thermoshield cylinder 4 is located at well heater 3, and and be provided with gap between well heater 3 and dielectric ceramic layer thereof, reduce thermal conduction, improve radioprotective efficiency, igniter 1 is arranged on the downstream of apical pore plate 2, and and be provided with gap between the aperture of apical pore plate 2, the emitter material of the centre hole of igniter 1 and the aperture coaxial hollow negative electrode of apical pore plate adopts barium tungsten radiator, supporting tube adopts tantalum, igniter and apical pore plate adopt molybdenum, well heater adopts tungsten, heater insulation pottery adopts high temperature sintering alumina-ceramic, igniter adopts molybdenum, cylinder enclosed formula structure, the distance of igniter and apical pore plate is 5mm.
Neutralizer test adopts triode mode to work, and principle of work figure is shown in Fig. 3, and Working environment vacuum tightness is not less than 5 �� 10-3Pa. When xenon working medium flow is 0.8��1.5mg/s, heating power 90��150W, when striking voltage is 150��300V, heat neutralizer electric discharge in 6��8 minutes, launch electronic current to realize when reaching 8��17A from heating steady operation, can meet in the hall thruster of power 2000��4500W or ion thruster plume and needs.
Neutralizer test adopts triode mode to work (Fig. 3), and when xenon working medium flow is 0.8��1.5mg/s, vacuum tightness is not less than 5 �� 10-3Pa. Heating power 90��150W, when striking voltage is 150��300V, heats neutralizer electric discharge in 6��8 minutes, launch when electronic current reaches 6��17A and realize steady operation, can meet in the hall thruster of power 2000��4500W or ion thruster plume and needs, it is not necessary to supplement power.
Above specific embodiments of the invention are described. It is understood that the present invention is not limited to above-mentioned particular implementation, those skilled in the art can make various distortion or amendment within the scope of the claims, and this does not affect the flesh and blood of the present invention.
Claims (7)
1. a space electric thruster plume neutralizer, it is characterized in that, neutralizer comprises igniter, apical pore plate, well heater, thermoshield cylinder, radiator and supporting tube, radiator is arranged on the inside of supporting tube, apical pore plate gear and is fixedly connected with supporting tube outside radiator 5, well heater is arranged on outside corresponding with the radiator position of supporting tube, the coated whole radiator in heating zone, and well heater is wrapped with dielectric ceramic layer; Thermoshield barrel cover is located at well heater outside, and and be provided with gap between well heater and dielectric ceramic layer thereof, reduce thermal conduction, improve radioprotective efficiency, igniter is arranged on the downstream of apical pore plate, and and be provided with gap between the aperture of apical pore plate, the centre hole of igniter is coaxial with the aperture of apical pore plate.
2. space electric thruster plume neutralizer according to right 1, it is characterised in that, described neutralizer is gas discharge type electron source, and Working environment vacuum tightness is better than 5 �� 10-3Pa��
3. space electric thruster plume neutralizer according to right 1, it is characterised in that, described radiator adopts the electronic emission material of low effusion work content.
4. space electric thruster plume neutralizer according to right 1, it is characterised in that, described radiator is the one in oxide compound radiator, barium tungsten radiator or lanthanum boride radiator.
5. space electric thruster plume neutralizer according to right 1, it is characterised in that, described thermoshield cylinder adopts high temperature material preparation.
6. space electric thruster plume neutralizer according to right 1, it is characterised in that, described well heater adopts high temperature material.
7. space electric thruster plume neutralizer according to right 1, it is characterised in that, light a fire very open or closed, must insulate with other parts, keep suitable distance with apical pore plate 2 simultaneously, igniter can apply positive voltage and form local highfield, be beneficial to electronics and draw.
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106438251A (en) * | 2016-11-09 | 2017-02-22 | 哈尔滨工业大学 | Novel hollow cathode thruster |
| CN106567813A (en) * | 2016-10-09 | 2017-04-19 | 上海空间推进研究所 | Integral high-temperature heating device |
| CN107762754A (en) * | 2017-11-20 | 2018-03-06 | 北京千乘探索科技有限公司 | A kind of integral packaging structure suitable for micro- electric thruster |
| CN108335957A (en) * | 2017-12-22 | 2018-07-27 | 兰州空间技术物理研究所 | A kind of gas discharge electron source based on hot cathode |
| CN108696979A (en) * | 2018-04-24 | 2018-10-23 | 台州学院 | A kind of plasma igniter |
| CN110374829A (en) * | 2019-06-11 | 2019-10-25 | 上海空间推进研究所 | Nano particle Flied emission thruster |
| CN111895389A (en) * | 2020-07-24 | 2020-11-06 | 西北工业大学 | Device and method for organizing metal powder through stable combustion |
| CN111954361A (en) * | 2020-08-14 | 2020-11-17 | 哈尔滨工业大学 | Integrated power supply circuit and power supply method for tethered satellite hollow cathode |
| CN112502927A (en) * | 2020-10-29 | 2021-03-16 | 中国科学院合肥物质科学研究院 | Plume corrosion prevention device for superconducting magnetic plasma propeller |
| CN112628099A (en) * | 2020-12-14 | 2021-04-09 | 兰州空间技术物理研究所 | Plume shielding shell of high-power ion thruster and manufacturing method thereof |
| CN112696328A (en) * | 2020-12-11 | 2021-04-23 | 中国电子科技集团公司第十二研究所 | High-reliability hollow cathode structure for electric propulsion |
| CN113357114A (en) * | 2021-07-19 | 2021-09-07 | 哈尔滨工业大学 | Main cathode assembly structure applied to thruster and assembly method thereof |
| CN113357109A (en) * | 2021-06-30 | 2021-09-07 | 哈尔滨工业大学 | Ignition device of radio frequency ion thruster |
| CN114320801A (en) * | 2021-12-28 | 2022-04-12 | 哈尔滨工业大学 | Cold cathode capable of being started quickly |
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Cited By (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106567813A (en) * | 2016-10-09 | 2017-04-19 | 上海空间推进研究所 | Integral high-temperature heating device |
| CN106438251A (en) * | 2016-11-09 | 2017-02-22 | 哈尔滨工业大学 | Novel hollow cathode thruster |
| CN106438251B (en) * | 2016-11-09 | 2019-01-04 | 哈尔滨工业大学 | Novel hollow cathode thruster |
| CN107762754A (en) * | 2017-11-20 | 2018-03-06 | 北京千乘探索科技有限公司 | A kind of integral packaging structure suitable for micro- electric thruster |
| CN108335957A (en) * | 2017-12-22 | 2018-07-27 | 兰州空间技术物理研究所 | A kind of gas discharge electron source based on hot cathode |
| CN108335957B (en) * | 2017-12-22 | 2020-01-10 | 兰州空间技术物理研究所 | Gas discharge electron source based on hot cathode |
| CN108696979A (en) * | 2018-04-24 | 2018-10-23 | 台州学院 | A kind of plasma igniter |
| CN108696979B (en) * | 2018-04-24 | 2020-04-10 | 台州学院 | Plasma igniter |
| CN110374829A (en) * | 2019-06-11 | 2019-10-25 | 上海空间推进研究所 | Nano particle Flied emission thruster |
| CN111895389A (en) * | 2020-07-24 | 2020-11-06 | 西北工业大学 | Device and method for organizing metal powder through stable combustion |
| CN111954361A (en) * | 2020-08-14 | 2020-11-17 | 哈尔滨工业大学 | Integrated power supply circuit and power supply method for tethered satellite hollow cathode |
| CN111954361B (en) * | 2020-08-14 | 2022-10-28 | 哈尔滨工业大学 | Integrated power supply circuit and power supply method for rope-tied satellite hollow cathode |
| CN112502927A (en) * | 2020-10-29 | 2021-03-16 | 中国科学院合肥物质科学研究院 | Plume corrosion prevention device for superconducting magnetic plasma propeller |
| CN112502927B (en) * | 2020-10-29 | 2021-09-17 | 中国科学院合肥物质科学研究院 | Plume corrosion prevention device for superconducting magnetic plasma propeller |
| CN112696328A (en) * | 2020-12-11 | 2021-04-23 | 中国电子科技集团公司第十二研究所 | High-reliability hollow cathode structure for electric propulsion |
| CN112628099A (en) * | 2020-12-14 | 2021-04-09 | 兰州空间技术物理研究所 | Plume shielding shell of high-power ion thruster and manufacturing method thereof |
| CN112628099B (en) * | 2020-12-14 | 2022-03-04 | 兰州空间技术物理研究所 | Plume shielding shell of high-power ion thruster and manufacturing method thereof |
| CN113357109A (en) * | 2021-06-30 | 2021-09-07 | 哈尔滨工业大学 | Ignition device of radio frequency ion thruster |
| CN113357114A (en) * | 2021-07-19 | 2021-09-07 | 哈尔滨工业大学 | Main cathode assembly structure applied to thruster and assembly method thereof |
| CN114320801A (en) * | 2021-12-28 | 2022-04-12 | 哈尔滨工业大学 | Cold cathode capable of being started quickly |
| CN114320801B (en) * | 2021-12-28 | 2022-07-01 | 哈尔滨工业大学 | Cold cathode capable of being started quickly |
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