CN107882702A - Rafael nozzle formula magnetic confinement hollow cathode - Google Patents
Rafael nozzle formula magnetic confinement hollow cathode Download PDFInfo
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- CN107882702A CN107882702A CN201711003634.2A CN201711003634A CN107882702A CN 107882702 A CN107882702 A CN 107882702A CN 201711003634 A CN201711003634 A CN 201711003634A CN 107882702 A CN107882702 A CN 107882702A
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- Prior art keywords
- negative electrode
- top plate
- hollow cathode
- electrode top
- pole
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Classifications
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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
- F03H1/0006—Details applicable to different types of plasma thrusters
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Plasma Technology (AREA)
Abstract
Rafael nozzle formula magnetic confinement hollow cathode, is related to space industry, in order to solve the problems, such as performance and life-span that the structure of existing hollow cathode can reduce hollow cathode.Cathode tube is cased with outer tube outside, and the bottom of cathode tube is provided with negative electrode top plate, and the bottom of outer tube, which is provided with to touch, holds pole, and negative electrode top plate and the tactile center for holding pole are equipped with aperture, is tapered gradual-enlargement type passage by negative electrode top plate to the tactile pore channels for holding pole.The present invention is applied to hollow cathode.
Description
Technical field
The present invention relates to space industry, and in particular to a kind of hollow cathode.
Background technology
Hollow cathode is widely used in hollowing technology with its excellent characteristic.Hollow cathode divides in ion thruster
Zuo Wei not main cathode and averager negative electrode.Main cathode is formed to produce original electron ionizing collision center gas in arc chamber
Plasma, averager negative electrode produces electron stream prevents ion beam current from making spacecraft charging to neutralize ion beam current.Hall pushes away
Only need hollow cathode be used as electron source and averager simultaneously in power device, often use two hollow cathodes mutual during practical application
For backup.Spacecraft can produce charge accumulated, induced discharge, to alleviate in spacecraft after prolonged space motion
Charging phenomenon reduces spacecraft current potential, it is necessary to which the Plasma contact device using hollow cathode as critical piece discharges electronics.In electricity
In dynamics tether and spatial tether electromagnetic force propeller, charge-exchange is carried out using Plasma contact device and space.
Existing hollow cathode is divided into heater hollow cathode and without heater hollow cathode, and the structure of existing hollow cathode is such as
Shown in Fig. 1, the design principle of total is operated in the environment for meeting certain air pressure and voltage's distribiuting for emitter, is maintained
Operating temperature and can ensure emitter transmitting electronics can successfully export.Cathode tube is arranged on for this cylindrical type emitter
Bottom, it is close to negative electrode bore and top plate, cathode tube top plate is provided with aperture, ensures there is hyperbar, negative electrode bottom of the tube in emitter
Outside is tied with heater strip and is used to heat during start-up course and activates emitter, and no heater hollow cathode is compared with existing hollow cathode
Cancel heater, the ignition discharge of negative electrode is directly realized by by high-voltage pulse gas breakdown, held by staying foraminate outside to touch
Pole top plate, to apply high voltage and export plasma.
Under existing hollow cathode structure, because the presence of cathode aperture makes plasma circulation road sudden contraction, negative electrode is caused
Hole front end produces large area vortex, and kinetic energy rejection, energetic plasma is detained here can also make more high-temperature plasmas
Bombardment corrosion emitter end and negative electrode top plate, while cause the loss of plasma.Plume plasma is due to by electric field
Acting on minus plate and touching the regional divergence held between step for power and the radial component of itself repulsion is propagated, equally cause etc. from
Son loss and the corrosion that pole and negative electrode top plate are held to touching.The right-angle structure being exposed in hollow cathode in plasma jet is vulnerable to height
The intense bombardment corrosion of energy plasma.Above each point makes the hydraulic performance decline and service life reduction of hollow cathode.
The content of the invention
Performance and the life-span that can reduce hollow cathode the invention aims to solve the structure of existing hollow cathode
Problem, so as to provide Rafael nozzle formula magnetic confinement hollow cathode.
Rafael nozzle formula magnetic confinement hollow cathode of the present invention, including outer tube 1, cathode tube 2, touch hold pole 3 and the moon
Pole top plate 4；
Outer tube 1 is cased with outside cathode tube 2, the bottom of cathode tube 2 is provided with negative electrode top plate 4, and the bottom of outer tube 1, which is provided with to touch, holds pole 3,
Negative electrode top plate 4 and the tactile center for holding pole 3 are equipped with aperture, are tapered gradual-enlargement type by negative electrode top plate 4 to the tactile pore channels for holding pole 3
Passage 5.
Preferably, in addition to permanent magnet 6；Permanent magnet 6 be arranged on outer tube 1, cathode tube 2, negative electrode top plate 4 and touch hold pole 3
In the chamber enclosed, and positioned at the end of chamber.
Preferably, in addition to insulating barrier 7；Insulating barrier 7 is arranged on the inwall of chamber.
Preferably, negative electrode top plate 4 and touch to hold and be provided with insulating ceramics stage casing 8, the center in insulating ceramics stage casing 8 between pole 3
Provided with aperture, negative electrode top plate 4, insulating ceramics stage casing 8 and the tactile tapered gradual-enlargement type passage 5 of keyhole formation for holding pole 3.
Preferably, in addition to annulus 9 and thermal insulation layer 10；
Thermal insulation layer 10 is provided with cathode tube 2, thermal insulation layer 10 is contacted by annulus 9 with negative electrode top plate 4, the bottom of emitter 11
Alignd with the bottom of thermal insulation layer 10, make to leave gap between emitter 11 and negative electrode top plate 4 by annulus 9.
Beneficial effects of the present invention：The present invention uses tapered gradual-enlargement type passage, ensure that and is sent out in hollow cathode start-up course
Beam air pressure inside is high, while makes plasma stream smooth flow under the guiding of passage, avoids existing hollow cathode structure
Middle energetic plasma to cathode construction bombardment corrosion and plasma loss, improve hollow cathode overall performance,
Reduce hollow cathode corrosion, add the service life of hollow cathode.
Brief description of the drawings
Fig. 1 is the structural representation of the existing heater hollow cathode in background technology；
Wherein, 12 be heat shielding, and 13 be heater, and 14 be cathode aperture；
Fig. 2 is the structural representation of the existing no heater hollow cathode in background technology；
Wherein, 15 be plasma；
Fig. 3 is the structural representation without the Rafael nozzle formula magnetic confinement hollow cathode of annulus；
Fig. 4 is the structural representation of the Rafael nozzle formula magnetic confinement hollow cathode with annulus.
Embodiment
Embodiment one：Present embodiment is illustrated with reference to Fig. 3 and Fig. 4, the daraf(reciprocal of farad) that described in present embodiment
Jet tube magnetic confinement hollow cathode, including outer tube 1, cathode tube 2, touch hold pole 3 and negative electrode top plate 4；
Outer tube 1 is cased with outside cathode tube 2, the bottom of cathode tube 2 is provided with negative electrode top plate 4, and the bottom of outer tube 1, which is provided with to touch, holds pole 3,
Negative electrode top plate 4 and the tactile center for holding pole 3 are equipped with aperture, are tapered gradual-enlargement type by negative electrode top plate 4 to the tactile pore channels for holding pole 3
Passage 5.Also include permanent magnet 6 in present embodiment；Permanent magnet 6 be arranged on outer tube 1, cathode tube 2, negative electrode top plate 4 and touch hold pole 3
In the chamber enclosed, and positioned at the end of chamber.
Tapered configuration makes the propellant air pressure inside emitter be maintained at one higher in hollow cathode start-up course
Level, divergent structure cause the plasma stream drawn inside emitter extraction smoother in passage.In hollow cathode
End is set with O-shaped permanent magnet, and the radial velocity of plasma is perpendicular to O-shaped magnet interior parallel magnetic field, and plasma is parallel
Spinned under the constraint in magnetic field motion so that plasma stream is largely bound in passage area, the high energy plasma such as reduces
Corrosion of the body to conduit wall.
Air-flow is entered inside emitter 11 through the feed channel that circulates by gas distributor 16, and tapered segment structure each contributes to
Be internally formed high-pressure area in emitter 11, while apply high voltage pulse on pole 3 touching to hold, touch hold pole 3 and negative electrode top plate 4 it
Between region in produce high voltage field, propelling gas (generally Xe, Ar gas) shape in the presence of highfield of hyperbar state
Enter stable discharging state into disruptive discharge, then by a series of processes, under hollow cathode steady-working state, divergent segment leads to
Road contributes to smooth guide plasma jet to flow out.
In present embodiment, insulating ceramics stage casing 8 is a part for tapered flaring passage, and ceramics bombard in high energy plasma
There is down corrosion resistant advantage, while avoid touching and hold pole 3 and the short circuit of negative electrode top plate 4.Held touching on the inside of pole 3, outside negative electrode top plate 4
Side, the inwall of outer tube 1, the outer wall of stop sleeve 17 apply coatings and form insulating barrier, avoid permanent magnet from making two parts short-circuit, while forever
Magnet should meet the magnetic susceptibility variation very little under 500 DEG C of hot environments, and parallel magnetic field can be formed in passage using permanent magnet,
Plasma stream is spinned motion in the presence of parallel magnetic field around magnetic field, reduces the radial velocity component of plasma stream.
The design of tapered flaring passage and the use of high temperature resistant permanent magnet each contribute to reduce energetic plasma to hollow
The bombardment corrosion of cathode assembly, extend the service life of hollow cathode and improve the combination property of hollow cathode.
In present embodiment, in addition to annulus 9 and thermal insulation layer 10；Thermal insulation layer 10 is provided with cathode tube 2, thermal insulation layer 10 passes through
Annulus 9 is contacted with negative electrode top plate 4, and the bottom of emitter 11 is alignd with the bottom of thermal insulation layer 10, by annulus 9 make emitter 11 with
Gap is left between negative electrode top plate 4.
Make to leave gap between emitter 11 and negative electrode top plate 4 by annulus 9, so as to expansion space, found by emulating,
This design emitter air pressure inside can be higher, so as to more convenient igniting, reduces to touch and holds the extremely upper magnitude of voltage applied, and then subtract
The power of few accessory power.Thruster is mainly used on satellite, reduces power, and it is extremely important to mitigate weight.Therefore annulus 9
Great significance for design.
Fig. 3 is so that without heater hollow cathode structure, to be illustrated, for heater, the hollow cathode present invention is equally applicable.
It is obvious to a person skilled in the art that the invention is not restricted to the details of above-mentioned one exemplary embodiment, Er Qie
In the case of without departing substantially from spirit or essential attributes of the invention, the present invention can be realized in other specific forms.Therefore, no matter
From the point of view of which point, embodiment all should be regarded as exemplary, and be nonrestrictive, the scope of the present invention is by appended power
Profit requires rather than described above limits, it is intended that all in the implication and scope of the equivalency of claim by falling
Change is included in the present invention.
Claims (5)
1. Rafael nozzle formula magnetic confinement hollow cathode, it is characterised in that including outer tube (1), cathode tube (2), touch hold pole (3) and
Negative electrode top plate (4)；
Outer tube (1) is cased with outside cathode tube (2), the bottom of cathode tube (2) is provided with negative electrode top plate (4), and the bottom of outer tube (1), which is provided with, touches
Pole (3) is held, negative electrode top plate (4) and the tactile center for holding pole (3) are equipped with aperture, by negative electrode top plate (4) to the tactile aperture for holding pole (3)
Passage is tapered gradual-enlargement type passage (5).
2. Rafael nozzle formula magnetic confinement hollow cathode according to claim 1, it is characterised in that also including permanent magnet
(6)；
Permanent magnet (6) be arranged on outer tube (1), cathode tube (2), negative electrode top plate (4) and touch hold in the chamber that pole (3) encloses, and
Positioned at the end of chamber.
3. Rafael nozzle formula magnetic confinement hollow cathode according to claim 2, it is characterised in that also including insulating barrier
(7)；
Insulating barrier (7) is arranged on the inwall of chamber.
4. Rafael nozzle formula magnetic confinement hollow cathode according to claim 1, it is characterised in that the negative electrode top plate
(4) and touch to hold and be provided with insulating ceramics stage casing (8) between pole (3), the center of insulating ceramics stage casing (8) is provided with aperture, negative electrode top plate
(4), insulating ceramics stage casing (8) and the tactile tapered gradual-enlargement type passage (5) of keyhole formation for holding pole (3).
5. Rafael nozzle formula magnetic confinement hollow cathode according to claim 1, it is characterised in that also including annulus (9)
With thermal insulation layer (10)；
Thermal insulation layer (10) is provided with cathode tube (2), thermal insulation layer (10) is contacted by annulus (9) with negative electrode top plate (4), emitter
(11) bottom is alignd with the bottom of thermal insulation layer (10), makes to leave between emitter (11) and negative electrode top plate (4) by annulus (9)
Gap.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711003634.2A CN107882702A (en) | 2017-10-24 | 2017-10-24 | Rafael nozzle formula magnetic confinement hollow cathode |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711003634.2A CN107882702A (en) | 2017-10-24 | 2017-10-24 | Rafael nozzle formula magnetic confinement hollow cathode |
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| CN107882702A true CN107882702A (en) | 2018-04-06 |
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| CN201711003634.2A Pending CN107882702A (en) | 2017-10-24 | 2017-10-24 | Rafael nozzle formula magnetic confinement hollow cathode |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111038741A (en) * | 2019-12-31 | 2020-04-21 | 哈尔滨工业大学 | Hectowatt-level aerospace electric propulsion hollow cathode structure |
| CN111120234A (en) * | 2019-12-19 | 2020-05-08 | 上海航天控制技术研究所 | Graphite high-temperature cathode device for electric 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 |
| CN113775496A (en) * | 2021-03-01 | 2021-12-10 | 陈晓彬 | Electromagnetic fluid vortex power device |
| CN115750252A (en) * | 2023-01-03 | 2023-03-07 | 国科大杭州高等研究院 | Working medium-free cathode and Hall thruster and space equipment comprising same |
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| CN102522298A (en) * | 2011-12-30 | 2012-06-27 | 电子科技大学 | Oval sheet beam electron gun |
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| CN104696180A (en) * | 2014-12-29 | 2015-06-10 | 中国空间技术研究院 | Magnetic field regulation type large-area microcavity discharge plasma micro-thruster for liquid working substances |
| CN105609395A (en) * | 2015-12-28 | 2016-05-25 | 哈尔滨工业大学 | Novel hollow cathode |
| WO2016149082A1 (en) * | 2015-03-15 | 2016-09-22 | Aerojet Rocketdyne, Inc. | Hall thruster with exclusive outer magnetic core |
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Patent Citations (6)
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| CN102497721A (en) * | 2011-11-29 | 2012-06-13 | 北京大学 | Plasma device with double-hollow cathode and double-hollow cathode and applications |
| CN102522298A (en) * | 2011-12-30 | 2012-06-27 | 电子科技大学 | Oval sheet beam electron gun |
| CN103311066A (en) * | 2013-06-03 | 2013-09-18 | 哈尔滨工业大学 | Emitter with inner core for self-held hollow cathode of spacecraft |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111120234A (en) * | 2019-12-19 | 2020-05-08 | 上海航天控制技术研究所 | Graphite high-temperature cathode device for electric thruster |
| CN111120234B (en) * | 2019-12-19 | 2021-02-23 | 上海航天控制技术研究所 | Graphite high-temperature cathode device for electric thruster |
| CN111038741A (en) * | 2019-12-31 | 2020-04-21 | 哈尔滨工业大学 | Hectowatt-level aerospace electric propulsion hollow cathode structure |
| CN113775496A (en) * | 2021-03-01 | 2021-12-10 | 陈晓彬 | Electromagnetic fluid vortex power device |
| 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 |
| CN113357114B (en) * | 2021-07-19 | 2022-05-06 | 哈尔滨工业大学 | Main cathode assembly structure applied to thruster and assembly method thereof |
| CN115750252A (en) * | 2023-01-03 | 2023-03-07 | 国科大杭州高等研究院 | Working medium-free cathode and Hall thruster and space equipment comprising same |
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Application publication date: 20180406 |
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