CN107387347B - Hollow cathode thruster for cube satellite - Google Patents
Hollow cathode thruster for cube satellite Download PDFInfo
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- CN107387347B CN107387347B CN201710590882.5A CN201710590882A CN107387347B CN 107387347 B CN107387347 B CN 107387347B CN 201710590882 A CN201710590882 A CN 201710590882A CN 107387347 B CN107387347 B CN 107387347B
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- snorkel
- hollow cathode
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- thruster
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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
- F03H1/0081—Electromagnetic plasma thrusters
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- Combustion & Propulsion (AREA)
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- Plasma & Fusion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Plasma Technology (AREA)
Abstract
For the hollow cathode thruster of cube satellite, it is related to thruster field, structure is complicated in order to solve existing electric propulsion system, can not directly minimize the problem on 1U.The gas being passed through in the snorkel of hollow cathode of the invention is discharge gas and electronegative gas.The present invention is using electronegative gas as main propulsive working medium, high-density plasma environment is formed in hollow cathode thruster internal discharge using discharge gas, wherein electronics decomposes electronegative gas, form anion, anion accelerates outward under potential effect inside hollow cathode thruster, generates high specific impulse propulsion efficiency.The present invention is suitable for cube satellite.
Description
Technical field
The present invention relates to thruster fields.
Background technique
In moonlet classification, Nano satellite quality is 1~10kg, and the quality of skin satellite is 0.1~1kg.Cube satellite
It (CubeSat) is a kind of new concept skin satellite specification, for quality in 1kg or so, structure size is 10cm × 10cm × 10cm
Square, also known as 1U (a cube satellite unit).Several cube satellite units are assembled into Nano satellite again.Cube is defended
Star has the characteristics that simple structure, small in size, light weight, at low cost, the lead time is short low with launch cost, and in space, demonstration is tested
It demonstrate,proves and there is broad development prospect using space, temporal resolution etc. that cube satellite network improves earth observation.
Currently, cube satellite in orbit when gesture stability utilize the strong magnetic meter of miniature three axis, miniature momenttum wheel and magnetic
The micromodules such as torquer constitute attitude control system, complete to control the three-axis stabilization of satellite.The another kind control attitude of satellite
Method be to adjust the control attitude of satellite by propeller, while propeller is also responsible for the task that the track of satellite maintains.For
The satellite propulsion system for executing pose adjustment and orbit maneuver task, can choose cold air propulsion system and electric propulsion system.It is cold
Gas propeller structure is simple, and the thrust that can be generated is big, but is compared to electric propulsion, and the specific impulse of cold air propeller is small, i.e., singly
Jet velocity caused by the propellant of position weight flow is smaller.Under conditions of carrying phase homogenous quantities propellant, electric propulsion
Total punching can always be rushed much larger than cold gas-driven, extend the in-orbit life-span of satellite substantially.But existing hall thruster, ion push away
The structure of the electric propulsion systems such as power device and pulsed plasma thruster is more complicated, can not directly minimize on 1U.
Summary of the invention
The purpose of the present invention is to solve existing electric propulsion system, structure is complicated, can not directly minimize on 1U
Problem, to provide the hollow cathode thruster for being used for cube satellite.
A kind of hollow cathode thruster for cube satellite of the present invention leads in the snorkel of hollow cathode
The gas entered is discharge gas and electronegative gas.
For hollow cathode as hall thruster, the electron source and averager of ion thruster, structure is simple, small in size, again
It measures light, low in energy consumption, can directly utilize existing electric propulsion gas storage system and power-supply system, and relative to cold air propulsion system
For, hollow cathode thruster can generate higher specific impulse, be ideal cube star thruster.But hollow cathode is made
For electron source, ion can not direct out ejection, and the thrust of generation is small, therefore the invention proposes one kind not to change cathode knot
Under the premise of structure and power supply mode, using electronegative gas as main propulsive working medium, using discharge gas in hollow cathode thruster
Internal discharge forms high-density plasma environment, and wherein electronics decomposes electronegative gas, forms anion, anion is in sky
Potential effect is lower inside the thruster of the heart-yin pole accelerates outward, generates high specific impulse propulsion efficiency.
Another hollow cathode thruster for being used for cube satellite of the present invention, the hollow cathode thruster include
Pedestal 1, snorkel, emitter 4, anode tube 5 and anode plate 6；
Snorkel includes the first snorkel 2 and the second snorkel 3；First snorkel 2 passes through pedestal 1 and the second snorkel 3
Conducting, 5 sets of anode tube outside the second snorkel 3, one end of one end of anode tube 5 and the second snorkel 3 is each attached to pedestal 1
On, the other end build-in of anode tube 5 has an anode plate 6, and the center of anode plate 6 is equipped with throttle orifice 6-1, the second snorkel 3 it is another
End build-in has emitter 4；Emitter 4 is connect with power supply cathode, and anode plate 6 is connect with power supply anode；
The gas being passed through in snorkel is discharge gas and electronegative gas.
Preferably, discharge gas and electronegative gas individually store, and respectively flow into snorkel by a flowmeter control
Flow.
Preferably, discharge gas and electronegative gas pass through a flowmeter control stream by setting ratio mixing storage
Enter the flow of snorkel.
Preferably, discharge gas is inert gas.
Preferably, electronegative gas O2Or F2。
Preferably, the material of pedestal 1 is ceramics, and the material of the first snorkel 2 is stainless steel, the second snorkel 3 and sun
The material of pole pipe 5 is silica, and the material of emitter 4 is C 12 A 7.
Preferably, emitter 4 passes sequentially through pure titanium silicon carbide-copper conductive material and first of 3 side wall of the second snorkel
Snorkel 2 is connect with power supply cathode.
Preferably, anode plate 6 is connect by the stainless steel material of 5 side wall of anode tube with power supply anode.
Preferably, pure titanium silicon carbide-copper conductive material is Filamentous, band-like or tubular.
The beneficial effects of the present invention are: the structure of hollow cathode thruster is simple, light weight, cube satellite can satisfy
To the rigors of spatial volume and load-carrying quality；The small power consumption of hollow cathode thruster simultaneously, transmitting temperature is high, Neng Gou
Relatively large power is obtained under low-power；Thruster specific impulse is capable of increasing using electric propulsion, increases effective load of cube satellite
Lotus and prolong the service life；Using electronegative gas, anion is generated inside hollow cathode thruster, is accelerated to spray, be increased
Thrust and specific impulse.
Detailed description of the invention
Fig. 1 is the structural schematic diagram described in specific embodiment one for the hollow cathode thruster of cube satellite；
Fig. 2 is cathode and power supply cathode connection schematic diagram in specific embodiment two；
Wherein, 3-1 is band-like stainless steel material；
Fig. 3 is the anode supply positive pole connection schematic diagram in specific embodiment two；
Fig. 4 is the structural schematic diagram of the conductive filament in specific embodiment three；
Fig. 5 is the structural schematic diagram of the conductive strips in specific embodiment three；
Fig. 6 is the structural schematic diagram of the conductive tube in specific embodiment three；
Fig. 7 is the first plenum system schematic diagram of the hollow cathode thruster in specific embodiment four；
Fig. 8 is second of plenum system schematic diagram of the hollow cathode thruster in specific embodiment four.
Specific embodiment
Specific embodiment 1: illustrating present embodiment in conjunction with Fig. 1, defended described in present embodiment for cube
The hollow cathode thruster of star, the hollow cathode thruster include pedestal 1, snorkel, emitter 4, anode tube 5 and anode plate 6；
Snorkel includes the first snorkel 2 and the second snorkel 3；First snorkel 2 passes through pedestal 1 and the second snorkel 3
Conducting, 5 sets of anode tube outside the second snorkel 3, one end of one end of anode tube 5 and the second snorkel 3 is each attached to pedestal 1
On, the other end build-in of anode tube 5 has an anode plate 6, and the center of anode plate 6 is equipped with throttle orifice 6-1, the second snorkel 3 it is another
End build-in has emitter 4；Emitter 4 is connect with power supply cathode, and anode plate 6 is connect with power supply anode；In snorkel
The gas being passed through is discharge gas and electronegative gas.
The material of pedestal 1 is ceramics, and the material of the first snorkel 2 is stainless steel, the material of the second snorkel 3 and anode tube 5
Material is silica, and the material of emitter 4 is C 12 A 7.
Discharge gas is passed through in snorkel, as cathode launching electronics gas occurs between the anode and the cathode for emitter
Body electric discharge, forms high-density plasma；Electronegative gas is passed through in snorkel, electronegative gas is in cathode and anode gap
It is decomposed by electronics, while adsorbing electronics as anion, under anode potential effect, part anion accelerates to spray throttle orifice,
Generate progradation.
Since electronegative gas has stronger oxidisability, the second snorkel 3 uses silica material with anode tube
Material, can be anti-oxidant, prevents gas leakage using interference fit using tantalum platinum between the first snorkel 2 and the second snorkel 3.Anode
Gas leakage is prevented using interference fit using tantalum platinum between pipe 5 and ceramic base 1.Emitter is C 12 A 7 material, the material
Material has a degree of inoxidizability while can emit certain electron current density.Anode plate, which uses, has antioxygen
The conductive polymer material for the property changed, prevents anode to be oxidized.
Specific embodiment 2: illustrating present embodiment in conjunction with Fig. 2 and Fig. 3, present embodiment is to specific implementation
Be described further described in mode one for the hollow cathode thruster of cube satellite, in present embodiment, emitter 4 according to
The secondary pure titanium silicon carbide-copper conductive material for passing through 3 side wall of the second snorkel and the first snorkel 2 are connect with power supply cathode.
Anode plate 6 is connect by the stainless steel material of 5 side wall of anode tube with power supply anode.
The electric discharge of hollow cathode thruster needs for emitter 4 to connect with power supply cathode, thus by the first snorkel 2 and
Conductive material is connected between emitter.Have after being decomposed due to electronegative gas compared with strong oxidizing property, conductive material is using tool
There is pure titanium silicon carbide-copper conductive material of good oxidation resistance, the first snorkel 2 of stainless steel material is connect with emitter.
Since anode tube is earth silicon material, will be connected between anode plate and positive pole with conducting wire.Since outside does not need to examine
Consider the strong oxidizing property of electronegative gas, therefore outer conductive material, to antioxidative of less demanding, present embodiment is not using
Become rusty Steel material, is compressed band-like stainless steel material using the bolt 1-1 of non-magnetic stainless steel, which claims
It is attached on anode tube body, is welded on anode plate for stainless steel conductive strips 5-1, stainless steel conductive strips 5-1.
Specific embodiment 3: illustrating present embodiment in conjunction with fig. 4 to fig. 6, present embodiment is to specific implementation
Hollow cathode thruster described in mode two for cube satellite is described further, in present embodiment, pure titanium silication
Carbon-copper conductive material is Filamentous, band-like or tubular.
Using pure titanium silicon carbide-copper conductive material with good oxidation resistance between the first snorkel 2 and emitter
Proceed to conduction, conductive material can use three kinds of shapes.The first is filiform, referred to as conductive filament, as shown in figure 4, such side
Case can save material, while playing and being connected between the first snorkel 2 and emitter；Second to be band-like, referred to as conductive strips,
As shown in figure 5, such scheme can reduce the same current density of electric current, prevent from fusing, while increasing conductive strips service life；Scheme
Three be tubular, referred to as conductive tube, as shown in fig. 6, tubular conductive strips can further decrease electric current current density, further increasing makes
Use the service life.
Specific embodiment 4: illustrating present embodiment in conjunction with Fig. 7 and Fig. 8, present embodiment is to specific implementation
Hollow cathode thruster described in mode three for cube satellite is described further, in present embodiment, in hollow yin
The extremely internal gas to discharge uses inert gas, and such as Xe, Ar and Kr, and electronegative gas has O2, F2Deng.
There are two types of the plenum systems of the hollow cathode thruster of present embodiment, as shown in Figure 7 and Figure 8 respectively.Fig. 7 is electricity
Negativity gas separates preservation with discharge gas, controls the flow being passed into hollow cathode thruster by two flowmeters.It should
Scheme can first be passed through inert gas, it is established that hollow cathode discharge, then be passed through electronegative gas, using electronics by electronegativity gas
Body dissociation ionization forms anion, while can also realize the different ratio of discharge lag gas and electronegative gas.Fig. 8 is will
Electronegative gas mixes storage by setting ratio with discharge gas, and it is stream that flowmeter control, which is passed into hollow cathode thruster,
Amount, the program can reduce by an air accumulator, increase the payload of cube satellite.
It is obvious to a person skilled in the art that invention is not limited to the details of the above exemplary embodiments, Er Qie
In the case where 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, the present embodiments are to be considered as illustrative and not restrictive, and the scope of the present invention is by appended power
Benefit requires rather than above description limits, it is intended that all by what is fallen within the meaning and scope of the equivalent elements of the claims
Variation is included within the present invention.
Claims (9)
1. being used for the hollow cathode thruster of cube satellite, which is characterized in that the gas being passed through in the snorkel of hollow cathode
Body is discharge gas and electronegative gas；
The hollow cathode thruster includes pedestal (1), snorkel, emitter (4), anode tube (5) and anode plate (6)；
Snorkel includes the first snorkel (2) and the second snorkel (3)；First snorkel (2) passes through pedestal (1) and the second ventilation
Manage (3) conducting, anode tube (5) cover the second snorkel (3) outside, one end of anode tube (5) and one end of the second snorkel (3) are equal
It is fixed on pedestal (1), the other end build-in of anode tube (5) has anode plate (6), and the center of anode plate (6) is equipped with throttle orifice (6-
1), the other end build-in of the second snorkel (3) has emitter (4)；Emitter (4) is connect with power supply cathode, anode plate (6)
It is connect with power supply anode.
2. the hollow cathode thruster according to claim 1 for cube satellite, which is characterized in that the electric discharge gas
Body and electronegative gas individually store, and the flow of snorkel is respectively flowed by a flowmeter control.
3. the hollow cathode thruster according to claim 1 for cube satellite, which is characterized in that the electric discharge gas
Body and electronegative gas flow into the flow of snorkel by a flowmeter control by setting ratio mixing storage.
4. the hollow cathode thruster according to claim 1 for cube satellite, which is characterized in that discharge gas is
Inert gas.
5. the hollow cathode thruster according to claim 1 for cube satellite, which is characterized in that electronegative gas
For O2Or F2。
6. the hollow cathode thruster according to claim 1 for cube satellite, which is characterized in that pedestal (1)
Material is ceramics, and the material of the first snorkel (2) is stainless steel, and the material of the second snorkel (3) and anode tube (5) is dioxy
SiClx, the material of emitter (4) are C 12 A 7.
7. the hollow cathode thruster for cube satellite according to claim 1 or 6, which is characterized in that the hair
Beam (4) pass sequentially through the second snorkel (3) side wall pure titanium silicon carbide-copper conductive material and the first snorkel (2) and power supply
Power cathode connection.
8. the hollow cathode thruster for cube satellite according to claim 1 or 6, which is characterized in that the sun
Pole plate (6) is connect by the stainless steel material of anode tube (5) side wall with power supply anode.
9. the hollow cathode thruster according to claim 7 for cube satellite, which is characterized in that the pure titanium silicon
Change carbon-copper conductive material is Filamentous, band-like or tubular.
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| CN201710590882.5A CN107387347B (en) | 2017-07-19 | 2017-07-19 | Hollow cathode thruster for cube satellite |
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| CN201710590882.5A CN107387347B (en) | 2017-07-19 | 2017-07-19 | Hollow cathode thruster for cube satellite |
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| CN107387347B true CN107387347B (en) | 2019-02-19 |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108317062A (en) * | 2017-12-22 | 2018-07-24 | 兰州空间技术物理研究所 | A kind of mixing thruster |
| CN108571431B (en) * | 2018-04-13 | 2019-07-23 | 哈尔滨工业大学 | A kind of mechanical support structure of magnetic focusing hall thruster hollow cathode |
| CN109236594B (en) * | 2018-09-14 | 2020-08-25 | 哈尔滨工业大学 | Low-power magnetized electric propulsion hollow cathode thruster |
| CN110145446B (en) * | 2019-06-13 | 2020-05-12 | 哈尔滨工业大学 | Pulse electrically-excited micro-cow propulsion device |
| CN111637029B (en) * | 2020-05-12 | 2021-09-07 | 北京控制工程研究所 | Segmented composite structure magnetic plasma power thruster cathode and preparation method thereof |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105609395A (en) * | 2015-12-28 | 2016-05-25 | 哈尔滨工业大学 | Novel hollow cathode |
| CN106438251A (en) * | 2016-11-09 | 2017-02-22 | 哈尔滨工业大学 | Novel hollow cathode thruster |
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| FR2950114B1 (en) * | 2009-09-17 | 2012-07-06 | Snecma | HALL EFFECT ENGINE WITH COOLING OF THE INTERNAL CERAMIC |
| US8875485B2 (en) * | 2010-04-06 | 2014-11-04 | The George Washington University | Micro-cathode thruster and a method of increasing thrust output for a micro-cathode thruster |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105609395A (en) * | 2015-12-28 | 2016-05-25 | 哈尔滨工业大学 | Novel hollow cathode |
| CN106438251A (en) * | 2016-11-09 | 2017-02-22 | 哈尔滨工业大学 | Novel hollow cathode thruster |
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Application publication date: 20171124 Assignee: Shanghai Yili Technology Co.,Ltd. Assignor: HARBIN INSTITUTE OF TECHNOLOGY Contract record no.: X2021230000047 Denomination of invention: Hollow cathode thruster for CubeSat Granted publication date: 20190219 License type: Exclusive License Record date: 20210712 |
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