CN102678501A - Gallium ion field emission micro-thruster - Google Patents
Gallium ion field emission micro-thruster Download PDFInfo
- Publication number
- CN102678501A CN102678501A CN2012101644191A CN201210164419A CN102678501A CN 102678501 A CN102678501 A CN 102678501A CN 2012101644191 A CN2012101644191 A CN 2012101644191A CN 201210164419 A CN201210164419 A CN 201210164419A CN 102678501 A CN102678501 A CN 102678501A
- Authority
- CN
- China
- Prior art keywords
- capillary
- emission
- gallium
- capillary channel
- emission part
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Links
- CKHJYUSOUQDYEN-UHFFFAOYSA-N gallium(3+) Chemical compound [Ga+3] CKHJYUSOUQDYEN-UHFFFAOYSA-N 0.000 title claims abstract description 11
- 230000001133 acceleration Effects 0.000 claims abstract description 20
- GYHNNYVSQQEPJS-UHFFFAOYSA-N Gallium Chemical compound [Ga] GYHNNYVSQQEPJS-UHFFFAOYSA-N 0.000 claims abstract description 15
- 229910052733 gallium Inorganic materials 0.000 claims abstract description 15
- 229910052751 metal Inorganic materials 0.000 claims abstract description 15
- 239000002184 metal Substances 0.000 claims abstract description 15
- 230000005684 electric field Effects 0.000 claims abstract description 10
- 150000002500 ions Chemical class 0.000 claims abstract description 5
- 239000000463 material Substances 0.000 claims description 6
- 229910001182 Mo alloy Inorganic materials 0.000 claims description 3
- 230000000694 effects Effects 0.000 claims description 3
- 229910000753 refractory alloy Inorganic materials 0.000 claims description 3
- 239000003380 propellant Substances 0.000 abstract description 11
- 238000000034 method Methods 0.000 abstract description 5
- 230000008569 process Effects 0.000 abstract description 4
- 230000008901 benefit Effects 0.000 abstract description 3
- 230000007246 mechanism Effects 0.000 abstract description 2
- 238000002844 melting Methods 0.000 abstract description 2
- 230000008018 melting Effects 0.000 abstract description 2
- 239000003795 chemical substances by application Substances 0.000 description 8
- 229910001338 liquidmetal Inorganic materials 0.000 description 3
- 239000007769 metal material Substances 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 2
- 238000000576 coating method Methods 0.000 description 2
- 240000007673 Origanum vulgare Species 0.000 description 1
- 235000004383 Origanum vulgare subsp. vulgare Nutrition 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910052792 caesium Inorganic materials 0.000 description 1
- TVFDJXOCXUVLDH-UHFFFAOYSA-N caesium atom Chemical compound [Cs] TVFDJXOCXUVLDH-UHFFFAOYSA-N 0.000 description 1
- 239000000356 contaminant Substances 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 229910052738 indium Inorganic materials 0.000 description 1
- APFVFJFRJDLVQX-UHFFFAOYSA-N indium atom Chemical compound [In] APFVFJFRJDLVQX-UHFFFAOYSA-N 0.000 description 1
- 230000008595 infiltration Effects 0.000 description 1
- 238000001764 infiltration Methods 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 239000012212 insulator Substances 0.000 description 1
- VIKNJXKGJWUCNN-XGXHKTLJSA-N norethisterone Chemical compound O=C1CC[C@@H]2[C@H]3CC[C@](C)([C@](CC4)(O)C#C)[C@@H]4[C@@H]3CCC2=C1 VIKNJXKGJWUCNN-XGXHKTLJSA-N 0.000 description 1
- 229920003223 poly(pyromellitimide-1,4-diphenyl ether) Polymers 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 239000011214 refractory ceramic Substances 0.000 description 1
Classifications
-
- 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
- F03H1/0037—Electrostatic ion thrusters
- F03H1/005—Electrostatic ion thrusters using field emission, e.g. Field Emission Electric Propulsion [FEEP]
Landscapes
- 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)
- Electron Sources, Ion Sources (AREA)
Abstract
本发明公开了一种镓离子场发射推进器，包括：发射部，具有毛细通道和毛细尖端；屏蔽部，位于发射部周围，用于屏蔽及保护发射部；加速部，位于所述发射部的前端，并与所述毛细尖端相邻，所述加速部的与所述毛细尖端相对应的位置开设有加速条状栅口，在所述毛细尖端和加速部之间施加有预定电压的电场；存储部，与所述毛细通道相连通，用于存储金属镓，与所述发射部之间具有预定的间距；金属镓通过毛细作用，由所述存储部经由所述毛细通道流到所述毛细尖端，在施加的所述电场的作用下产生离子羽流，从而获得推力。本发明具有如下优点：1)选取金属镓作为推进剂，熔点低降低额外功消耗；2)处理工艺使得推进剂良好浸润，推进剂自动供给；3)结构极大地简化，没有运动机构。
The invention discloses a gallium ion field emission thruster, which comprises: an emission part, which has a capillary channel and a capillary tip; a shielding part, located around the emission part, for shielding and protecting the emission part; an acceleration part, located in the emission part The front end is adjacent to the capillary tip, an accelerating strip-shaped gate is opened in the position corresponding to the capillary tip of the accelerating part, and an electric field of a predetermined voltage is applied between the capillary tip and the accelerating part; The storage part is connected with the capillary channel and used to store metal gallium, and has a predetermined distance from the emission part; the metal gallium flows from the storage part to the capillary through the capillary channel through the capillary action. The tip, under the action of said electric field applied, generates a plume of ions, thereby obtaining thrust. The invention has the following advantages: 1) metal gallium is selected as the propellant, which has a low melting point and reduces extra work consumption; 2) the treatment process makes the propellant well infiltrated, and the propellant is automatically supplied; 3) the structure is greatly simplified, and there is no moving mechanism.
Description
Technical field
The present invention relates to the micro propulsion device of a kind of emitting ions.
Background technique
In recent years, in the space tasks such as gravity field of the earth and space gravitational wave detection, higher requirement is proposed for the little propulsion system of satellite: little momentum, microthrust.Simultaneously harsh restriction is proposed for its power, volume and weight.And an emission electric propulsion device be present numerous electric propulsion device tool advantage and representational scheme.
Though external correlative study mechanism and company's research are early, the design of its emission electric propulsion device all is based on the propellant agent of metal caesium and indium, and dependency structure complicacy and reliability are low, and processes such as concrete design do not provide play-by-play.
Domestic, do not see the bibliographical information that the field emission principle is applied to the slit impeller design, do not see the application report that gallium is used for the electric propulsion device.
Summary of the invention
To the problem that existing technology exists, the object of the present invention is to provide a kind of gallium ion emission propulsion device that uses the liquid metal gallium as propellant agent, can provide and can produce the little ox level of milli wild marjoram thrust.
A kind of gallium ion provided by the invention field emission propulsion device comprises:
Emission part, it is most advanced and sophisticated to have capillary channel and capillary;
Shielding part is positioned at around the emission part, is used to shield said acceleration portion electrons emitted stream;
Acceleration portion is positioned at the front end of said emission part, and adjacent with said capillary tip, and the strip grid mouth is quickened in offering with the most advanced and sophisticated corresponding position of said capillary of said acceleration portion, between said capillary tip and acceleration portion, is applied with the electric field of predetermined voltage;
Memory section is connected with said capillary channel, is used to store gallium;
Gallium flows to said capillary tip by said memory section via said capillary channel through capillarity, under the said effect of electric field that applies, produces the ion plume, thereby obtains thrust.
Preferably, said acceleration portion is the sheet metal of 1 millimeters thick roughly, and said grid mouth is opened in the centre of sheet metal, and said grid mouth section part chamfering tapers off to a point, and said grid oral thermometer face forms smooth surface.
Preferably, said emission part comprises: the two boards shape slug of symmetry constitutes, and between two blocks of sluies, constitutes the microfluxion layer through plated film, thereby forms said capillary channel, on said slug, offers the through hole of said capillary channel of conducting and memory section.
Preferably, the material of said plate-shape metal piece is a refractory alloy.
Preferably, said capillary channel height is 1 μ m roughly, and width is 2～20 millimeters, and the degree of depth is 10～15 millimeters.
Preferably, the material of said memory section is a molybdenum alloy.
The present invention is through cooperating good infiltrating mirror metal material symmetry, and middle pad constitutes the capillary channel of propellant agent with micron order coating structure layer, between capillary channel tip and acceleration portion, applies high voltage electric field, and direct ionization liquid metal gallium produces thrust.Can change channel width as required among the present invention and regulate the propulsion device maximum thrust, regulate the thrust size through changing potential difference.In addition, the present invention also has following advantage:
1) chooses gallium as propellant agent, the consumption of the low reduction of fusing point extra power;
2) treatment process makes propellant agent well soak into, and propellant agent is supplied with automatically;
3) structure is greatly simplified, and does not have motion.
Description of drawings
Fig. 1 is a structural representation of the present invention;
Fig. 2 is the schematic cross-section of Fig. 1.
Embodiment
Like Fig. 1, shown in 2, the present invention includes: emission part 1, acceleration portion 2, memory section 3 and housing 4.Emission part 1, acceleration portion 2 and memory section 3 are installed in the housing 4 through insulator 5.
Emission part 1 has capillary channel 11 and capillary most advanced and sophisticated 12; Acceleration portion 2 is positioned at the front end of emission part 1, and adjacent with capillary most advanced and sophisticated 12, and strip grid mouth 21 is quickened in offering with the most advanced and sophisticated 12 corresponding positions of capillary of acceleration portion 2, between capillary most advanced and sophisticated 12 and acceleration portion 2, is applied with the electric field of predetermined voltage.
The can with cavity 33 31 that the material of memory section 3 is made for the molybdenum alloy material is used to store gallium, offers the passage 32 that is connected with capillary channel 11 on the can.Gallium flows to capillary tip 12 by memory section 3 via passage 32, capillary channel 11 through capillarity, under the predetermined effect of electric field that applies, produces the ion plume, thereby obtains thrust.
In embodiments of the present invention, acceleration portion 2 is the sheet metal of 1 millimeters thick roughly, and grid mouth 21 is opened in the centre of sheet metal 21, and grid mouth 21 section part chamferings taper off to a point, and grid oral thermometer face forms smooth surface.
In embodiments of the present invention; Emission part 1 comprises: the two boards shape slug 13,14 of symmetry constitutes; At two blocks of sluies 13, clamping has coating 15 between 14, thereby form capillary channel 11, on slug 13,14, offer the through hole 16 of conducting capillary channel 11 and memory section 2.The material of plate-shape metal piece 13,14 is a refractory alloy, makes the tip have the good life-span like this.Capillary channel 11 highly is about 1 μ m, and width is 2～20 millimeters, and the degree of depth is 10～15 millimeters.In embodiments of the present invention, capillary channel is about 1 μ m, channel width 8mm, dark 14mm.
In addition, around emission part 1, also be formed with shielding part 7, this shielding part 7 adopts high temperature metallic material to process, and is used to shield acceleration portion 2 electrons emitted stream and bombards emission part 1 and cause emission part 1 intensification to burn.
Periphery at memory section 3 also is provided with heater 6; Heater 6 is used for heating and removes emission part 1 internal surface oxidize contaminants etc.; Be beneficial to the first infiltration of capillary channel 11, and make the propellant agent metal molten, but need not work for fluent metal thermal insulation; Because gallium had cold trend, can not solidify even be lower than melting point yet.In embodiments of the present invention, heater 6 is resistance heater, refractory ceramics heater or Kapton heater.
The present invention is through cooperating good infiltrating mirror metal material symmetry; Middle pad is with the metal-plated rete of micron order thickness; Constitute the capillary channel 11 of propellant agent, between capillary channel 11 tips and acceleration portion, apply high voltage electric field, direct ionization liquid metal gallium produces.Can change channel width as required among the present invention and regulate the propulsion device maximum thrust, regulate the thrust size through changing potential difference, the propeller thrust scope is at 0.1 μ N～1000 μ N.
Claims (6)
1. a gallium ion field emission propulsion device is characterized in that, comprising:
Emission part, it is most advanced and sophisticated to have capillary channel and capillary;
Acceleration portion is positioned at the front end of said emission part, and adjacent with said capillary tip, and the strip grid mouth is quickened in offering with the most advanced and sophisticated corresponding position of said capillary of said acceleration portion, between said capillary tip and acceleration portion, is applied with the electric field of predetermined voltage;
Shielding part is positioned at around the emission part, is used to shield said acceleration portion electrons emitted stream;
Memory section is connected with said capillary channel, is used to store gallium, and has predetermined spacing between the said emission part;
Gallium flows to said capillary tip by said memory section via said capillary channel through capillarity, under the said effect of electric field that applies, produces the ion plume, thereby obtains thrust.
2. gallium ion as claimed in claim 1 field emission propulsion device; It is characterized in that said acceleration portion is the sheet metal of 1 millimeters thick roughly, said grid mouth is opened in the centre of sheet metal; Said grid mouth section part chamfering tapers off to a point, and said grid oral thermometer face forms smooth surface.
3. gallium ion as claimed in claim 1 field emission propulsion device; It is characterized in that; Said emission part comprises: the two boards shape slug of symmetry constitutes; Between two blocks of sluies, constitute the microfluxion layer, thereby form said capillary channel, on said slug, offer the through hole of said capillary channel of conducting and memory section through plated film.
4. emission propulsion device in gallium ion as claimed in claim 3 field is characterized in that the material of said plate-shape metal piece is a refractory alloy.
5. emission propulsion device in gallium ion as claimed in claim 4 field is characterized in that, said capillary channel height is 1 μ m roughly, and width is 2～20 millimeters, and the degree of depth is 10～15 millimeters.
6. emission propulsion device in gallium ion as claimed in claim 1 field is characterized in that the material of said memory section is a molybdenum alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012101644191A CN102678501A (en) | 2012-05-24 | 2012-05-24 | Gallium ion field emission micro-thruster |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012101644191A CN102678501A (en) | 2012-05-24 | 2012-05-24 | Gallium ion field emission micro-thruster |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102678501A true CN102678501A (en) | 2012-09-19 |
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ID=46810917
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012101644191A Pending CN102678501A (en) | 2012-05-24 | 2012-05-24 | Gallium ion field emission micro-thruster |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102678501A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103244310A (en) * | 2013-05-07 | 2013-08-14 | 中国科学院力学研究所 | Propellant management system for liquid metal ion propeller |
| CN107091210A (en) * | 2017-05-18 | 2017-08-25 | 西安交通大学 | A kind of pulsed plasma thruster based on capillary discharging |
| EP4276306A1 (en) * | 2022-05-12 | 2023-11-15 | ENPULSION GmbH | Ion source |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009137583A2 (en) * | 2008-05-06 | 2009-11-12 | Massachusetts Institute Of Technology | Method and apparatus for a porous metal electrospray emitter |
| US20100018185A1 (en) * | 2007-02-21 | 2010-01-28 | Snecma | Emitter for ionic thruster |
| US7827779B1 (en) * | 2007-09-10 | 2010-11-09 | Alameda Applied Sciences Corp. | Liquid metal ion thruster array |
-
2012
- 2012-05-24 CN CN2012101644191A patent/CN102678501A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100018185A1 (en) * | 2007-02-21 | 2010-01-28 | Snecma | Emitter for ionic thruster |
| US7827779B1 (en) * | 2007-09-10 | 2010-11-09 | Alameda Applied Sciences Corp. | Liquid metal ion thruster array |
| WO2009137583A2 (en) * | 2008-05-06 | 2009-11-12 | Massachusetts Institute Of Technology | Method and apparatus for a porous metal electrospray emitter |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103244310A (en) * | 2013-05-07 | 2013-08-14 | 中国科学院力学研究所 | Propellant management system for liquid metal ion propeller |
| CN103244310B (en) * | 2013-05-07 | 2015-07-29 | 中国科学院力学研究所 | A kind of for the angle of rake propellant management system, propellant control system of liquid metal ion |
| CN107091210A (en) * | 2017-05-18 | 2017-08-25 | 西安交通大学 | A kind of pulsed plasma thruster based on capillary discharging |
| CN107091210B (en) * | 2017-05-18 | 2018-12-04 | 西安交通大学 | A kind of pulsed plasma thruster based on capillary discharging |
| EP4276306A1 (en) * | 2022-05-12 | 2023-11-15 | ENPULSION GmbH | Ion source |
| WO2023217449A1 (en) * | 2022-05-12 | 2023-11-16 | Enpulsion Gmbh | Ion source |
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Application publication date: 20120919 |