CN107651222A - Micro cathode Arcjet - Google Patents
Micro cathode Arcjet Download PDFInfo
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- CN107651222A CN107651222A CN201710893795.7A CN201710893795A CN107651222A CN 107651222 A CN107651222 A CN 107651222A CN 201710893795 A CN201710893795 A CN 201710893795A CN 107651222 A CN107651222 A CN 107651222A
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- 239000000919 ceramic Substances 0.000 claims abstract description 30
- 238000010891 electric arc Methods 0.000 claims abstract description 21
- 238000007747 plating Methods 0.000 claims abstract description 21
- 230000000694 effects Effects 0.000 claims description 17
- 239000002245 particle Substances 0.000 claims description 9
- 230000001141 propulsive effect Effects 0.000 claims description 9
- 239000003380 propellant Substances 0.000 claims description 7
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 6
- 239000011810 insulating material Substances 0.000 claims description 5
- 238000009413 insulation Methods 0.000 claims description 5
- 125000004122 cyclic group Chemical group 0.000 claims description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 3
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 3
- 229920006362 Teflon® Polymers 0.000 claims description 3
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 3
- NRTOMJZYCJJWKI-UHFFFAOYSA-N Titanium nitride Chemical compound [Ti]#N NRTOMJZYCJJWKI-UHFFFAOYSA-N 0.000 claims description 3
- 230000003213 activating effect Effects 0.000 claims description 3
- 229910052799 carbon Inorganic materials 0.000 claims description 3
- 229910052802 copper Inorganic materials 0.000 claims description 3
- 239000010949 copper Substances 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 239000007769 metal material Substances 0.000 claims description 3
- 229910052759 nickel Inorganic materials 0.000 claims description 3
- 239000010936 titanium Substances 0.000 claims description 3
- 229910052719 titanium Inorganic materials 0.000 claims description 3
- 239000000203 mixture Substances 0.000 claims description 2
- 230000007797 corrosion Effects 0.000 abstract description 6
- 238000005260 corrosion Methods 0.000 abstract description 6
- 239000007921 spray Substances 0.000 abstract description 5
- 230000015572 biosynthetic process Effects 0.000 abstract description 3
- 238000005183 dynamical system Methods 0.000 abstract description 3
- 240000000560 Citrus x paradisi Species 0.000 abstract 1
- 238000005516 engineering process Methods 0.000 description 8
- 108091092878 Microsatellite Proteins 0.000 description 4
- 230000008901 benefit Effects 0.000 description 4
- 150000002500 ions Chemical class 0.000 description 4
- 239000010453 quartz Substances 0.000 description 4
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 4
- BSYNRYMUTXBXSQ-UHFFFAOYSA-N Aspirin Chemical compound CC(=O)OC1=CC=CC=C1C(O)=O BSYNRYMUTXBXSQ-UHFFFAOYSA-N 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 230000002730 additional effect Effects 0.000 description 2
- 230000003466 anti-cipated effect Effects 0.000 description 2
- 238000009296 electrodeionization Methods 0.000 description 2
- 230000005284 excitation Effects 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 230000005355 Hall effect Effects 0.000 description 1
- 239000004809 Teflon Substances 0.000 description 1
- 238000002679 ablation Methods 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000005684 electric field Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 239000000686 essence Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000005426 magnetic field effect Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/405—Ion or plasma engines
-
- 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
- F03H1/0081—Electromagnetic plasma thrusters
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Electromagnetism (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Plasma Technology (AREA)
Abstract
The invention belongs to electric thrust field, more particularly to a kind of micro cathode Arcjet applied to micro-nano satellite, is mainly used in the dynamical system compared with grapefruit satellite such as micro-nano satellite.The present invention is for solving the problems, such as existing micro-nano satellite without propulsion system, using vacuum cathode arc discharge principle, devises the electric thruster structure of complete set.The thruster structure mainly forms：1 shell, 2 negative electrode working medium, 3 springs, 4 ceramic cylinders, 5 bases, 6 fixing nuts, 7 clamp nut bolts, 8 anodes, 9 conductive film plating layers, 10 magnetic coils.When reaching predetermined voltage between anode and cathode, cathode protection electric discharge, gradually spread, negative electrode working medium constantly ionizes corrosion, forms stable plasma plume.Plasma plume outwards sprays under additional magnetic fields, reaction thrust needed for formation.Overall structure size of the present invention is small, in light weight.
Description
Technical field
The invention belongs to electric thrust field, more particularly to a kind of micro cathode Arc applied to micro-nano satellite
Device.
Background technology
As the continuous progress of technology, the gradual reduction of technical threshold, micro-nano satellite industry are gradually emerging in the world
Rise, micro-nano satellite technology is considered as the space technology for 21 century most having technology and commercial promise, is not only had to military and national defense
Its own strategic significance, also commercially it will bring revolutionary impact, such as communication, internet, agricultural, education for many industries
Medical treatment etc. industry.Micro-nano satellite is also no longer the product that large-scale or huge state-owned enterprise can just do, and many individual enterprises are even individual
People's start-up group is involved in wherein.
Micro-nano satellite has series of advantages, and small volume, low in energy consumption, the construction cycle is short, possesses capability of fast response.But by
Constrained in by whole star power consumption, weight, volume etc., existing Push Technology can not meet microsatellite dynamical system demand.Meanwhile
It greatly limit the scope of activities and service life of micro-nano satellite, it is impossible to give full play to microsatellite in business, civilian and national defence
The advantage of military aspect.
The fast-developing impetus will be presented in future for micro-nano satellite, and following microsatellite includes to the application demand of electric propulsion：
1. with relative cold air or the high specific impulse advantage of chemical propulsion, propulsion system gross weight is greatly reduced, completes long-life microsatellite
Damping compensation, track lifting, position is kept and the task such as motor-driven, gesture stability, formation flight, transmission error amendment；2. carry
For the accurate momentum of the needs such as attitude regulation and control, position holding；3. relative broad range thrust can quick regulation application demand,
Such as without towing control, precise formation flight.
New solar-system operation is, it is necessary to new technical support.Traditional chemical propulsion system, energy density are low, it is necessary to carry
Substantial amounts of fuel, and propulsion efficiency-cost ratio is low, system reliability is poor, can not meet present spacecraft function needs.It is existing
In new electric propulsion system, most often Hall effect plasma thrust body device and Kaufman ion propeller.Both
Plasma thruster all can not be by simple size and power contracting than constructing the plasma that suitable micro-nano satellite uses
Body electric propulsion device.Because after contracting is than effect, because the physical characteristic of plasma in itself determines that its efficiency can be significantly
Degree declines, and can not also accomplish the miniaturized electronic source averager for being adapted to it to use.In addition, existing electric thruster structure is excessively
It is complicated.
Micro-nano satellite electric propulsion technology is not yet ripe at present, and electric propulsion cost is higher, is difficult to ensure safely, to suitable for micro-
The demand of the electric push system of Nano satellite platform is extremely urgent, and quarter is developed not suitable for the miniaturization electricity thrust structure of micro-nano satellite
Rong Huan.
For example, a kind of electric arc heated formula Helicon wave plasma electric propulsion devices of prior art CN106385756A, including：
Helicon wave plasma excitation antenna, quartz discharge room, sleeve, jet pipe, hollow cathode and anode；Sleeve is one section of straight pipe,
One end closing and perforate, for connecting radio frequency power source, other end jointed anode；Quartz discharge room is located in sleeve, and one end is tight
Sleeve perforate end is pasted, the other end is connected with hollow cathode；Helicon wave plasma excitation antenna is wound, the table outside quartz discharge room
Face；Hollow cathode is located in sleeve, and one end connection quartz discharge room, the other end stretches into the cavity of anode, formed and put with anode
Electrode；Anode one end is connected with sleeve；Anode other end connecting spray nozzle.
In addition, CN106742073A discloses a kind of differential of the arc cathodic discharge micro electric propulsion die, including power supply, inductor wire
Circle, controlling switch, current divider, negative electrode, anode and magnet coil；Power source supplies DC, and measured with current divider, control
Charged during switch closure for inductance coil, instantaneous pressure is produced to the external world when controlling switch disconnects, if external circuitry turns on, to
The external world provides electric current until the electric energy of inductance coil storage discharges completely；Negative electrode and anode are led by discharge breakdown during instantaneous pressure
Logical, ablation cathode surface simultaneously generates plasma, and under the magnetic line of force effect of magnet coil, plasma focus accelerates to spray,
Produce thrust.
The size of prior art is big, has not been able to produce preferable thrust, is not easy to be integrated into micro-nano satellite operation system
In system, and ionize and produce energy of plasma consumption height, pulse stability deficiency, the security of whole system work needs into one
Step improves.
The content of the invention
In order to meet the dynamical system demand of micro-nano satellite, electric thrust miniaturization technologies problem is overcome, simplify engine and reach
Structure, the invention provides a kind of micro cathode Arcjet.
Specifically, the present invention is achieved through the following technical solutions, and it is most of that micro cathode Arcjet mainly includes four：
Negative electrode, anode, magnetosphere, negative electrode working medium push structure.
Micro cathode electric arc propeller, it is integrally a pipe cyclic structure, wherein, shell 1 and the connection of base 5 form one and half
Close tubular structure；Ceramic cylinder 4 is arranged in semiclosed tubular structure, the ceramic cylinder 4 of base 5 composition insulation system, isolates negative and positive
Pole；Negative electrode working medium 2 is connected to form cathode passage with shell 1, together with anode 8, the conductive film plating layer 9 being arranged at the top of ceramic cylinder 4
A complete galvanic circle is formed, conductive film plating layer 9 is playing forearc choked flow, working condition underpass；Place bullet in the lower end of negative electrode 2
Spring 3, the lower end connect base 5 of spring 3, working medium propulsion system are mainly completed by spring 3；Negative electrode working medium 2 connects with shell 1, ceramic cylinder 4
It is freely slidable to meet place；Magnetic coil 10, generation and plumage of the additional magnetic coil 10 for plasma are placed outside the upper end of shell 1
Stream acceleration has gain effect.
One of preferred scheme of the present invention is manhole shape for negative electrode working medium 2, and as propellant working medium, its material can be with
It is the conductive metallic materials such as copper, nickel, titanium.
One of preferred scheme of the present invention is coated in ceramic cylinder 4 close to the side of magnetic coil 10 for conductive film plating layer 9, circular,
Conductive film plating layer can be the functional properties conductivity film layer such as titanium nitride, carbon, TiCN.
One of preferred scheme of the present invention is in cylinder boss shape, top and the inner hole of shell 1 for base 5, using Teflon
The insulating materials such as dragon, with housing combination closed interior structure, interstitial hole passes through for anode rod 8.
One of preferred scheme of the present invention is in shaft-like for anode 8, and upper boss external diameter is slightly larger than bar external diameter, and boss can be consolidated
Determine anode position, bottom is machined with one section of screw thread, is easy to clamp internal structure.
One of preferred scheme of the present invention is placed at the top of thruster for magnetic coil 10, is wrapped in the circular line of housing exterior
Circle, contribute to plasma to be formed and accelerate with charged particle.
One of preferred scheme of the present invention is hollow circuit cylinder cylinder for ceramic cylinder 4, external negative electrode, pole bar of inside activating yang, is played absolutely
Edge acts on, and is clipped between anode boss and base.
One of preferred scheme of present invention space between shell 1 and ceramic cylinder 4 is used to install spring 3, in negative electrode working medium
Continuous propulsive working medium during ionization corrosion.
One of preferred scheme of the present invention is threaded for the bottom of anode 8, coordinates fixing nut 6, for compressing inside
Structure.
One of preferred scheme of the present invention is closely connected for shell 1 with base 5 by six unit bolt nuts 7.
The effect of related each part further comprises：Shell 1 also serves as negative electrode conducting medium simultaneously, and shell 1 is hollow circle
Post boss structure, top small sircle hole are used for connect base 5 as plasma jet, the big circular hole in lower end, and base 5 has insulation
Effect.In addition, base 5 ensures the center of anode 8, and the bottom of anode 8 is threaded, and coordinates fixing nut 6, is used for
Compress internal structure.Negative electrode 2 is cylindrical structure, as propulsive working medium.Ceramic cylinder 4 is used for the upper end position of fixed anode 8, simultaneously
There is insulating effect.And can be slidably between shell 1, and negative electrode 2 and ceramic cylinder 4 outside negative electrode 2.The top of ceramic cylinder 4 has
One layer of conductive film plating layer 9.Place spring 3, the lower end connect base 5 of spring 3 in the lower end of negative electrode 2.Magnetic coil is placed outside the upper end of shell 1
10.Shell 1 is closely connected with base 5 by six unit bolt nuts 7.Shell 1 connects power cathode, and anode 8 connects power anode.
Magnetic coil 10 and anode and cathode use independent electric power system.
The present invention mainly utilizes cathodic vacuum arc principle, when reaching arcing voltage, negative electrode spot between negative electrode 2, anode 8
Point electric discharge produces plasma, and negative electrode working medium 2 constantly ionizes corrosion, forms stable plasma, outer caused by magnetic coil 10
Add under magnetic fields, spray at a high speed, obtain reaction thrust.
When the micro cathode electric propulsion device works, the plasma of ionization is internally produced between cathode electrode 2, the surface of anode 8
Body.Plasma is initially formed in cathode protection, then gradually expands to the lower caused magnetic field of the additional effect of magnetic coil 10.Deng from
Charged particle in daughter accelerates under magnetic fields, finally with high-speed expansion to vacuum, forms plasma plume as shown in the figure
Stream, produce propulsive thrust.
Ionization of the generation from negative electrode working medium 2 of plasma, with the continuous consumption of propellant working medium, negative electrode working medium 2
Constantly pushed ahead under the elastic force effect of spring 3, ensure that propulsive working medium conveys incessantly.
Base 5 uses insulating materials, forms insulation system with ceramic cylinder 4, Structure of the cathode and the anode is separated.
Magnetic coil 10 produces magnetic field in energization working condition, and this externally-applied magnetic field has bright to the work of micro cathode electric propulsion device
Aobvious gain effect.Negative electrode 2 ionizes caused plasma charged particles by magnetic fields, can significantly speed up ion, greatly
Its conevying efficiency is improved greatly, so as to strengthen plasma plume.Charged particle accelerates under magnetic fields, and this is to producing thrust
There is very big contribution.Additional directional magnetic field causes cathode protection to be moved in anticipated orientation, and this guarantees the uniform of cathodic corrosion
Property, add functional reliability.In addition, magnetic field also contributes to negative electrode ionization rate.
Conductive film plating layer 9 positioned at the top of ceramic cylinder 4 is the electric arc startup for preliminary work.Conductive film plating layer 9 is main
Effect is to hinder path, until reaching certain arcing voltage value between anode and cathode, cathode protection is formed, until stablizing electric arc shape
Into.
The present invention includes relative to the advantages of prior art：
(1) overall structure is simple, and shell also serves as conducting medium, and anode and cathode power supply is convenient.Overall weight is lighter, meets micro-
The low weight of the propulsion system of Nano satellite, small size requirement, can produce preferable thrust, be easy to be integrated into micro-nano satellite operation
In system.
(2) conductive film plating layer ensure that the successful ionization of negative electrode working medium under vacuum conditions in the present invention.Magnetic coil produces
Ionization of the electric field for propulsive working medium, plasma acceleration and plasma plume diverging play the role of it is good.Working medium
Propulsion system structure is simple, reliable.Using metal as propellant working medium, ionization produces energy of plasma and consumes low, pulse
Stability is high.
(3) propellant working medium is metal, rather than combustible, ensure that system operational security.Using conductive film plating layer point
Fiery mode, it effectively prevent structural redundancy caused by tradition machinery triggering, spark plug triggering.Sparking mode, in addition, the present invention into
This is relatively low, is easy to quantify to produce.
Brief description of the drawings
Fig. 1 is the interior three-dimensional view of micro cathode electric arc propeller of the present invention, is integrally a pipe cyclic structure.
Fig. 2 is the sectional view of micro cathode electric arc propeller of the present invention, each main element explanation：1- shells, 2- negative electrode working medium,
3- springs, 4- ceramic cylinders, 5- bases, 6- fixing nuts, 7- fastening structures, 8- anodes, 9- conduction film plating layers, 10- magnetic coils.
Embodiment
Below in conjunction with the accompanying drawings and better embodiment is described in further detail to the present invention, but the present invention is not limited to
This：
A kind of micro cathode electric arc propeller of embodiment 1
Micro cathode electric arc propeller, it is integrally a pipe cyclic structure with reference to shown in Fig. 1 and 2, wherein, shell 1 and base
5 connections form a semiclosed tubular structure；Ceramic cylinder 4 is arranged in semiclosed tubular structure, and the ceramic cylinder 4 of base 5 forms absolutely
Edge structure, isolate anode and cathode；Negative electrode working medium 2 is connected to form cathode passage with shell 1, together with anode 8, is arranged at ceramic cylinder 4 and pushes up
The conductive film plating layer 9 in portion forms a complete galvanic circle, and conductive film plating layer 9 is playing forearc choked flow, working condition underpass；
Spring 3, the lower end connect base 5 of spring 3 are placed in the lower end of negative electrode 2, and working medium propulsion system is mainly completed by spring 3；Negative electrode working medium 2 with
Shell 1, the junction of ceramic cylinder 4 are freely slidable；Place magnetic coil 10 outside the upper end of shell 1, additional magnetic coil 10 for etc.
The generation of gas ions and plume accelerate have gain effect.
A kind of micro cathode electric arc propeller of embodiment 2
With reference to shown in Fig. 1 and 2, on the basis of embodiment 1, negative electrode working medium 2 is manhole shape, as propellant work
Matter, its material can be the conductive metallic materials such as copper, nickel, titanium.
Conductive film plating layer 9 is coated in ceramic cylinder 4 close to the side of magnetic coil 10, circular, conductive film plating layer can be titanium nitride,
The functional properties conductivity film layer such as carbon, TiCN.
Base 5 is in cylinder boss shape, top and the inner hole of shell 1, using insulating materials such as Teflons, with housing combination
Closed interior structure, interstitial hole pass through for anode rod 8.
Anode 8 is in shaft-like, and upper boss external diameter is slightly larger than bar external diameter, and boss can be machined with fixed anode position, bottom
One section of screw thread, is easy to clamp internal structure.
Magnetic coil 10 is placed at the top of thruster, is wrapped in the circular coil of housing exterior, is contributed to plasma to be formed
Accelerate with charged particle.
Ceramic cylinder 4 is hollow circuit cylinder cylinder, external negative electrode, pole bar of inside activating yang, plays insulating effect, is clipped in anode boss and bottom
Between seat.
Space is used to install spring 3 between shell 1 and ceramic cylinder 4, the continuous propulsive working medium when negative electrode working medium is ionized and corroded.
The bottom of anode 8 is threaded, and coordinates fixing nut 6, for compressing internal structure.
Shell 1 is closely connected with base 5 by six unit bolt nuts 7.
Present invention mainly utilizes cathodic vacuum arc principle, has reached when between negative electrode 2, anode 8
Arc voltage, cathode protection electric discharge produce plasma, and negative electrode working medium 2 constantly ionizes corrosion, stable plasma is formed, in magnet-wire
Under externally-applied magnetic field effect caused by circle 10, spray at a high speed, obtain reaction thrust.
When the micro cathode electric propulsion device works, the plasma of ionization is internally produced between cathode electrode 2, the surface of anode 8
Body.Plasma is initially formed in cathode protection, then gradually expands to the lower caused magnetic field of the additional effect of magnetic coil 10.Deng from
Charged particle in daughter accelerates under magnetic fields, finally with high-speed expansion to vacuum, forms plasma plume as shown in the figure
Stream, produce propulsive thrust.
Ionization of the generation from negative electrode working medium 2 of plasma, with the continuous consumption of propellant working medium, negative electrode working medium 2
Constantly pushed ahead under the elastic force effect of spring 3, ensure that propulsive working medium conveys incessantly.
Base 5 uses insulating materials, forms insulation system with ceramic cylinder 4, Structure of the cathode and the anode is separated.
Magnetic coil 10 produces magnetic field in energization working condition, and this externally-applied magnetic field has bright to the work of micro cathode electric propulsion device
Aobvious gain effect.Negative electrode 2 ionizes caused plasma charged particles by magnetic fields, can significantly speed up ion, greatly
Its conevying efficiency is improved greatly, so as to strengthen plasma plume.Charged particle accelerates under magnetic fields, and this is to producing thrust
There is very big contribution.Additional directional magnetic field causes cathode protection to be moved in anticipated orientation, and this guarantees the uniform of cathodic corrosion
Property, add functional reliability.In addition, magnetic field also contributes to negative electrode ionization rate.
Conductive film plating layer 9 positioned at the top of ceramic cylinder 4 is the electric arc startup for preliminary work.Conductive film plating layer 9 is main
Effect is to hinder path, until reaching certain arcing voltage value between anode and cathode, cathode protection is formed, until stablizing electric arc shape
Into.
Above-described embodiment is the preferable embodiment of the present invention, but embodiments of the present invention are not by above-described embodiment
Limitation, other any Spirit Essences without departing from the present invention with made under principle change, modification, replacement, combine, simplification,
Equivalent substitute mode is should be, is included within protection scope of the present invention.
Claims (10)
1. micro cathode electric arc propeller, it is integrally a pipe cyclic structure, it is characterised in that shell (1) and base (5) connection shape
Into a semiclosed tubular structure；Ceramic cylinder (4) is arranged in semiclosed tubular structure, base (5) ceramic cylinder (4) composition insulation
Structure, isolate anode and cathode；Negative electrode working medium (2) is connected to form cathode passage with shell (1), together with anode (8), is arranged at ceramic cylinder
(4) the conductive film plating layer (9) at the top of forms a complete galvanic circle, and conductive film plating layer (9) is playing forearc choked flow, and work shape
State underpass；Spring (3) is placed in negative electrode (2) lower end, and spring (3) lower end connect base (5), working medium propulsion system is mainly by spring
(3) complete；Negative electrode working medium (2) and shell (1), ceramic cylinder (4) junction are freely slidable；Placed outside shell (1) upper end
Magnetic coil (10), generation and plume of the additional magnetic coil (10) for plasma accelerate have gain effect.
2. micro cathode electric arc propeller according to claim 1, it is characterised in that negative electrode working medium (2) is manhole shape,
As propellant working medium, its material can be the conductive metallic materials such as copper, nickel, titanium.
3. micro cathode electric arc propeller according to claim 1, it is characterised in that conductive film plating layer (9) is coated in ceramic cylinder
(4) close to magnetic coil (10) side, circular, conductive film plating layer can be the functional properties conductivity film such as titanium nitride, carbon, TiCN
Layer.
4. micro cathode electric arc propeller according to claim 1, it is characterised in that base (5) is in cylinder boss shape, top
With shell (1) inner hole, using insulating materials such as Teflons, with housing combination closed interior structure, interstitial hole is used for anode
Bar (8) passes through.
5. micro cathode electric arc propeller according to claim 4, it is characterised in that anode (8) is in shaft-like, outside upper boss
Footpath is slightly larger than bar external diameter, and boss can be with fixed anode position, and bottom is machined with one section of screw thread, is easy to clamp internal structure.
6. micro cathode electric arc propeller according to claim 1, it is characterised in that magnetic coil (10) is placed in thruster top
Portion, the circular coil of housing exterior is wrapped in, contributes to plasma to be formed and accelerate with charged particle.
It is 7. according to claim 4, it is characterised in that ceramic cylinder (4) is hollow circuit cylinder cylinder, external negative electrode, pole of inside activating yang
Bar, insulating effect is played, be clipped between anode boss and base.
8. micro cathode electric arc propeller according to claim 1, it is characterised in that empty between shell (1) and ceramic cylinder (4)
Gap is used to install spring (3), the continuous propulsive working medium when negative electrode working medium is ionized and corroded.
9. micro cathode electric arc propeller according to claim 1, it is characterised in that anode (8) bottom is threaded, and is matched somebody with somebody
Fixing nut (6) is closed, for compressing internal structure.
10. micro cathode electric arc propeller according to claim 1, it is characterised in that shell (1) passes through six with base (5)
Individual unit bolt nut (7) closely connects.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710893795.7A CN107651222A (en) | 2017-09-28 | 2017-09-28 | Micro cathode Arcjet |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710893795.7A CN107651222A (en) | 2017-09-28 | 2017-09-28 | Micro cathode Arcjet |
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| Publication Number | Publication Date |
|---|---|
| CN107651222A true CN107651222A (en) | 2018-02-02 |
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ID=61116935
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| Application Number | Title | Priority Date | Filing Date |
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| CN201710893795.7A Pending CN107651222A (en) | 2017-09-28 | 2017-09-28 | Micro cathode Arcjet |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108194295A (en) * | 2017-12-28 | 2018-06-22 | 西安航天动力研究所 | A kind of triggerless electrode that can reduce vacuum arc thruster starting the arc energy |
| CN110486243A (en) * | 2019-09-11 | 2019-11-22 | 哈尔滨工业大学 | A kind of micro cathode electric arc propulsion system |
| CN110594114A (en) * | 2019-09-04 | 2019-12-20 | 北京航空航天大学 | Bipolar multimode micro-cathode arc thruster |
| CN110615122A (en) * | 2019-10-30 | 2019-12-27 | 哈尔滨工业大学 | Multi-ring micro-cathode electric arc thruster |
| CN110641740A (en) * | 2019-10-30 | 2020-01-03 | 哈尔滨工业大学 | Micro-cathode arc propeller |
| CN111516905A (en) * | 2019-02-02 | 2020-08-11 | 中国科学院宁波材料技术与工程研究所 | Mars flying method and device |
| CN112373728A (en) * | 2020-10-26 | 2021-02-19 | 哈尔滨工业大学 | Combined electric propulsion device for space gravitational wave detection and control method |
| CN113027718A (en) * | 2021-04-17 | 2021-06-25 | 中国人民解放军国防科技大学 | Micro-cathode arc propulsion system based on igniter |
| CN113401373A (en) * | 2020-12-07 | 2021-09-17 | 中国科学院微小卫星创新研究院 | Nut separating mechanism |
| CN113716074A (en) * | 2021-11-04 | 2021-11-30 | 北京理工大学 | Satellite with electric propulsion system |
| CN115045816A (en) * | 2022-06-28 | 2022-09-13 | 大连理工大学 | Double-anode micro-cathode arc propulsion device |
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| CN115045816A (en) * | 2022-06-28 | 2022-09-13 | 大连理工大学 | Double-anode micro-cathode arc propulsion device |
| CN116588355A (en) * | 2023-06-12 | 2023-08-15 | 上海易推动力科技有限公司 | Cathode propulsion system for micro-nano satellite |
| CN116588355B (en) * | 2023-06-12 | 2024-03-12 | 上海易推动力科技有限公司 | Cathode propulsion system for micro-nano satellite |
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