CN114291298A - Bismuth working medium electric propulsion supply system based on filamentous propellant - Google Patents
Bismuth working medium electric propulsion supply system based on filamentous propellant Download PDFInfo
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- CN114291298A CN114291298A CN202111573151.2A CN202111573151A CN114291298A CN 114291298 A CN114291298 A CN 114291298A CN 202111573151 A CN202111573151 A CN 202111573151A CN 114291298 A CN114291298 A CN 114291298A
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- bismuth
- induction heating
- propellant
- working medium
- supply system
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- 229910052797 bismuth Inorganic materials 0.000 title claims abstract description 117
- JCXGWMGPZLAOME-UHFFFAOYSA-N bismuth atom Chemical compound [Bi] JCXGWMGPZLAOME-UHFFFAOYSA-N 0.000 title claims abstract description 117
- 239000003380 propellant Substances 0.000 title claims abstract description 26
- 238000010438 heat treatment Methods 0.000 claims abstract description 89
- 230000006698 induction Effects 0.000 claims abstract description 69
- 238000002309 gasification Methods 0.000 claims abstract description 23
- 230000000903 blocking effect Effects 0.000 claims abstract description 22
- 238000009423 ventilation Methods 0.000 claims abstract description 15
- 230000007246 mechanism Effects 0.000 claims abstract description 12
- 239000012071 phase Substances 0.000 claims abstract description 9
- 239000007790 solid phase Substances 0.000 claims abstract description 4
- 239000000463 material Substances 0.000 claims description 10
- 230000009471 action Effects 0.000 claims description 4
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims description 4
- 229910052721 tungsten Inorganic materials 0.000 claims description 4
- 239000010937 tungsten Substances 0.000 claims description 4
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims description 3
- 229910010293 ceramic material Inorganic materials 0.000 claims description 3
- 229910052750 molybdenum Inorganic materials 0.000 claims description 3
- 239000011733 molybdenum Substances 0.000 claims description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 2
- 229910002804 graphite Inorganic materials 0.000 claims description 2
- 239000010439 graphite Substances 0.000 claims description 2
- 239000012530 fluid Substances 0.000 claims 7
- 239000007789 gas Substances 0.000 description 8
- 238000009834 vaporization Methods 0.000 description 5
- 230000008016 vaporization Effects 0.000 description 5
- 238000013461 design Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 229910052751 metal Inorganic materials 0.000 description 4
- 239000002184 metal Substances 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000008018 melting Effects 0.000 description 2
- 238000002844 melting Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 241000857945 Anita Species 0.000 description 1
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 1
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000005253 cladding Methods 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 238000009833 condensation Methods 0.000 description 1
- 230000005494 condensation Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005674 electromagnetic induction Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000007792 gaseous phase Substances 0.000 description 1
- 239000007770 graphite material Substances 0.000 description 1
- PNDPGZBMCMUPRI-UHFFFAOYSA-N iodine Chemical compound II PNDPGZBMCMUPRI-UHFFFAOYSA-N 0.000 description 1
- 229910052749 magnesium Inorganic materials 0.000 description 1
- 239000011777 magnesium Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000012552 review Methods 0.000 description 1
- 239000004449 solid propellant Substances 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 230000004584 weight gain Effects 0.000 description 1
- 235000019786 weight gain Nutrition 0.000 description 1
- 229910052724 xenon Inorganic materials 0.000 description 1
- FHNFHKCVQCLJFQ-UHFFFAOYSA-N xenon atom Chemical compound [Xe] FHNFHKCVQCLJFQ-UHFFFAOYSA-N 0.000 description 1
- 229910052725 zinc Inorganic materials 0.000 description 1
- 239000011701 zinc Substances 0.000 description 1
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- General Induction Heating (AREA)
Abstract
The invention relates to a bismuth working medium electric propulsion supply system based on a filamentous propellant in the technical field of electric propulsion propellant supply systems, which comprises a bismuth wire storage box, a wire feeding mechanism, a bismuth working medium gasification device and an induction heating power supply; bismuth wires are coiled in the bismuth wire storage box, the bismuth working medium gasification device comprises a blocking cover A, an induction heating coil, an induction heating supporting cylinder, a blocking cover B and a ventilation guide pipe, the induction heating coil is wound on the induction heating supporting cylinder and is electrically connected with an induction heating power supply, the blocking cover A and the blocking cover B are hermetically connected to two ends of the induction heating supporting cylinder, and the ventilation guide pipe is hermetically communicated with the blocking cover B; the bismuth wire coiled in the bismuth wire storage box is driven by the self-plugging cover A to enter the cavity of the induction heating supporting cylinder through the traction of the wire feeding mechanism, and the bismuth wire is changed from a solid phase to a gas phase in an induction heating mode and is output through the ventilation catheter. The invention adopts an induction heating mode, the heating mode is more concentrated and efficient, the structure is simpler, and the complexity of a working medium supply system is reduced.
Description
Technical Field
The invention relates to the technical field of electric propulsion propellant supply systems, in particular to a filamentous bismuth working medium Hall electric propulsion supply system.
Background
The electric propulsion is a propulsion technology which utilizes electric energy to heat or ionize working media to generate plasma and accelerates a propellant through the electric energy to generate thrust, and has the characteristics of higher specific impulse, small thrust, repeatable starting and long service life. At present, gas working media such as xenon and the like are mainly adopted as propellants in an electric propulsion system, and the electric propulsion system is applied to high-power electric propulsion and has low cost performance due to high price and low storage density compared with metal propellants. At present, research and ground tests on solid propellant working media such as magnesium, zinc, iodine, bismuth and the like have been carried out at home and abroad, wherein the bismuth working media have the highest atomic mass, the lowest ionization energy, the largest ionization cross section and the highest storage density, are low in price and become suitable working media for the ultrahigh specific impulse anode layer Hall thruster.
The melting point of the metal propellant working medium is high, and great difficulty is brought to the design and the realization of a working medium supply system. In the existing technical scheme of propellant supply, bismuth working medium is mostly heated and liquefied by a storage tank and then gasified by a gasification device and conveyed to an electric thruster. In 2005, the paper published by Anita senguta et al in 29 th international conference on electrical propulsion entitled "review of ultra high specific impulse anode layer project: double-Layer Bismuth working medium ultrahigh Specific Impulse Anode Layer Thruster (An Overview of the VHITAL Program: A Two-Stage Bismuth Fed Very High Specific Impulse thrust With Anode Layer), Bismuth is heated and liquefied in a storage tank, and is conveyed to An atomizer through a micro pump at certain pressure and flow to be atomized and then conveyed to the Thruster. The problems brought by the prior art are that: bismuth is easy to form compounds with other metals when being heated, the heating mode is easy to cause the temperature of the storage box to be unevenly distributed so as to cause incomplete evaporation, and the selection of bismuth storage box materials and the heating design are difficult; besides, the bismuth in the storage tank is integrally heated with high power, the conveying pipeline is long, and the pipeline needs to maintain a long heating section; meanwhile, the bismuth storage tank propellant is powdery at present and is not beneficial to space application.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a bismuth working medium electric propulsion supply system based on a filamentous propellant.
The bismuth working medium electric propulsion supply system based on the filamentous propellant comprises a bismuth wire storage box, a wire feeding mechanism, a bismuth working medium gasification device and an induction heating power supply;
bismuth wires are coiled in the bismuth wire storage box, the bismuth working medium gasification device comprises a blocking cover A, an induction heating coil, an induction heating supporting cylinder, a blocking cover B and a ventilation guide pipe, the induction heating coil is wound on the induction heating supporting cylinder, the induction heating coil is electrically connected with an induction heating power supply, the blocking cover A and the blocking cover B are hermetically connected to two ends of the induction heating supporting cylinder, and the ventilation guide pipe is hermetically communicated with the blocking cover B;
the bismuth wire that spirals in the bismuth wire storage box passes through wire feeding mechanism's traction drive certainly blanking cover A gets into in the cavity of induction heating supporting cylinder, the bismuth wire is in under the effect of the alternating magnetic field that induction heating coil produced through the vortex heat that produces become the gaseous phase by the solid phase, gaseous steam bismuth passes through the pipe of ventilating is exported.
In some embodiments, the system further comprises a pressure sensor and a thermocouple, wherein the pressure sensor and the thermocouple are used for detecting the pressure and the temperature of the steam bismuth in the pipeline output from the vent hole conduit and providing feedback from time to time.
In some embodiments, the heat tracing pipe is wrapped on a circulation pipeline of the vapor bismuth, and the vapor bismuth in the pipeline is continuously insulated by the heat tracing pipe so as to keep a vapor state.
In some embodiments, the induction heating support cylinder is a high temperature resistant ceramic material.
In some embodiments, the material of the cap a and the cap B is graphite.
In some embodiments, the material of the airway tube is molybdenum.
In some embodiments, the bismuth working medium gasification device further comprises a heating sleeve, the heating sleeve is arranged in the induction heating supporting cylinder, and the bismuth wire passes through an inner cavity of the heating sleeve and is heated into steam bismuth.
In some embodiments, the material of the heating sleeve is tungsten.
In some embodiments, the ventilation device further comprises a hall thruster, the hall thruster is communicated with the ventilation conduit through two parallel pipelines, the two parallel pipelines are coated with the pipeline heat tracing band, and the two parallel pipelines are provided with control valves.
In some embodiments, the control valve further comprises a throttle valve, and the throttle valve is mounted on a pipeline between the control valve and the hall thruster.
Compared with the prior art, the invention has the following beneficial effects:
1. according to the bismuth working medium gasification device based on induction heating, the heating principle adopts an induction heating mode, the heating mode is more concentrated and efficient, the heating structure is simpler, and the complexity of a working medium supply system is reduced.
2. According to the invention, through the optimized design of the bismuth working medium gasification device, the transformation rate of bismuth working medium gasification is increased, and the working efficiency is improved.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic diagram of a bismuth working medium supply system based on a filamentous propellant according to the present invention;
FIG. 2 is a schematic structural diagram of an embodiment of an induction heating bismuth working medium gasification device according to the present invention;
FIG. 3 is a schematic structural diagram of another embodiment of the bismuth working medium gasification device for induction heating according to the present invention;
FIG. 4 is a schematic diagram of a bismuth working medium Hall electric propulsion supply system based on a filamentous propellant.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
Example 1
The invention provides a bismuth working medium electric propulsion supply system based on a filamentous propellant, which comprises a bismuth wire storage box 1, a wire feeding mechanism 2, a bismuth working medium gasification device 3 and an induction heating power supply 4, as shown in a figure 1-2. Bismuth wires 11 are coiled in the bismuth wire storage box 1, and the wire diameter of the bismuth wires 11 is selected to be 0.2-2 mm according to needs. The bismuth wire 11 spirally arranged in the bismuth wire storage box 1 is connected with the wire feeding mechanism 2 after being led out, the wire feeding mechanism 2 provides corresponding bismuth wire supply speed according to downstream load requirements, wherein the wire feeding mechanism 2 can be a stepping motor, the type of the stepping motor, such as the type, the size, the step angle and the like of the stepping motor, is selected according to the load requirements and requirements, further, a vacuum collector can be adopted at the downstream to collect and supply condensed bismuth steam at the downstream of the system, the weight gain of bismuth condensation is measured, the relationship between the bismuth wire feed speed and the bismuth mass flow is calculated quantitatively, and the operation parameters of the stepping motor are controlled in an open loop mode.
The bismuth working medium gasification device 3 is an electromagnetic induction heating device and comprises a blocking cover A12, an induction heating coil 13, an induction heating support cylinder 14, a blocking cover B16 and a ventilation conduit 17. The induction heating coil 13 is wound on the induction heating supporting cylinder 14 and is electrically connected with the induction heating power supply 4, the induction heating coil 13 generates an alternating magnetic field through alternating current input by the induction heating power supply 4, and the power of the induction heating coil is obtained through experiments. The induction heating supporting cylinder is preferably made of high-temperature-resistant ceramic materials, has high mechanical property and dimensional stability at high temperature, and has good heat-insulating property. The two ends of the induction heating supporting cylinder 14 are respectively connected with a blocking cover A12 and a blocking cover B16 in a sealing mode, wherein the blocking cover A12 is used as an inlet port of a bismuth wire to form dynamic sealing with the bismuth wire 11, the end cover B is used as an outlet end of vapor bismuth in a gas phase, preferably, the end cover A12 and the end cover B16 are both made of graphite materials, and the thermal stability is good. One end of the airway tube 17 is sealingly connected to the flow passage of the cap B16 and preferably one end of the airway tube 17 extends into the flow passage of the cap B16 and the vaporized bismuth flows through the airway tube 17 to the downstream load. Preferably, the temperature of the bismuth vapor is higher than 800 ℃, and the material of the ventilation catheter 17 is high-temperature resistant metal material molybdenum.
The working principle of the invention is as follows: the bismuth wire 11 coiled in the bismuth wire storage box 1 enters the cavity of the induction heating supporting cylinder 14 from the port of the blocking cover A12 through the traction drive of the wire feeding mechanism 2, the induction heating coil 13 generates an alternating magnetic field under the action of alternating current provided by the induction power supply 4, the bismuth wire 11 generates eddy heat under the action of the alternating magnetic field, the eddy heat enables the bismuth wire 11 to be changed from a solid phase to a gas phase, and then vapor bismuth in the gas phase is output through the ventilation catheter 17 and flows to a downstream load. In the above process, the melting point of bismuth is 271.4 ℃, the vaporization temperature is 935.93 ℃ when the vaporization pressure is 200Pa, and the vaporization temperature is 1052.09 ℃ when the vaporization pressure is 1000 Pa. The induction heating temperature of the bismuth gas is set to be 1300-1800 ℃ so as to complete liquid-gas two-phase change of the bismuth wire in the heating area, and the liquefaction area is small enough and provides enough temperature for supporting the vaporization rate and the downstream flow pressure.
Compared with the problem that the heating principle of the bismuth working medium gasification device based on induction heating adopts an induction heating mode, the heating mode is more concentrated and efficient, the heating structure is simpler, and the complexity of a working medium supply system is reduced.
Preferably, a pressure sensor 5 and a thermocouple 6 are installed at the outlet end of the ventilation duct 17, and the pressure and the temperature of the bismuth vapor are measured in real time through the pressure sensor 5 and the thermocouple 6 to provide real-time feedback.
Furthermore, the outlet end of the ventilation conduit 17 and a downstream pipeline thereof are coated with a conduit heat tracing band 18, the specific heat tracing temperature setting range of the conduit heat tracing band 18 can be 900-1100 ℃, so that the bismuth working medium at the outlet and the downstream of the outlet thereof is in a gas phase state, and a condensed phase is prevented from being formed inside the propeller.
Example 2
The embodiment 2 is formed on the basis of the embodiment 1, and the conversion rate of bismuth working medium gasification is improved and the working efficiency is improved through the optimized design of the bismuth working medium gasification device. Specifically, the method comprises the following steps:
as shown in fig. 3, an induction heating cylinder 15 is further disposed in the bismuth working medium gasification device 3, the induction heating cylinder 15 is made of metal, preferably tungsten, which is a high temperature resistant material, the induction heating cylinder 15 is disposed in the induction heating support cylinder 14, and the induction heating cylinder 15 is preferably made of tungsten, which is a high temperature resistant material. Through the wire feeding mechanism 2, the bismuth wire 11 enters the inner cavity of the induction heating cylinder 15 from the inlet of the blocking cover A12, after the induction heating coil 13 is introduced with alternating current with a certain frequency, the induction heating cylinder 15 generates induction current under the action of an alternating magnetic field, the eddy current is utilized to heat the induction heating cylinder 15 to 1200-1300 ℃, the heated induction heating cylinder 15 heats the bismuth wire 11 in the inner cavity, the bismuth wire is rapidly liquefied and gasified in the heating area, and the bismuth steam is conveyed to a downstream load through the ventilation guide pipe 17 after being formed.
Example 3
The embodiment 3 is formed on the basis of the embodiment 1 or the embodiment 2, and provides a working medium supply system scheme facing a bismuth working medium hall electric propulsion system, in particular to an ultrahigh specific-impulse anode layer thruster, which is shown in fig. 4, and specifically:
on the basis of the technical solutions of embodiment 1 or embodiment 2, air supply pipelines with different air flow rates are respectively added to the cathode and the anode of the hall thruster, as shown in fig. 4, a control valve 7 and a throttling element 8 are arranged in each pipeline, and the temperature in the system pipeline is still maintained by a cladding pipeline heat tracing band 18, and the implementation steps are as follows:
firstly, heating by a pipeline heat tracing band 18, carrying out system heat tracing on a pipeline, and finishing primary preheating of the system;
secondly, opening the control valve 7 to complete the exhaust of residual gas in the system;
and thirdly, starting the induction power supply 4, carrying out induction heating through the bismuth working medium gasification device 3, heating the inner cavity temperature of the induction heating cylinder 15 in the bismuth working medium gasification device 3 to the preset temperature of 1300-1800 ℃ according to the preset power, then starting the stepping motor 2 to work, supplying the bismuth wires 11 to the bismuth working medium gasification device, and starting outputting steam bismuth at the downstream.
The pressure sensor 5 and the thermocouple 6 detect the temperature of the bismuth steam, the throttling element 8 controls the input flow of the cathode and the anode of the Hall thruster 10, the rotating speed of the stepping motor 2 is adjusted in real time according to feedback data, and then the supply speed of the bismuth wire 11 is controlled so as to adjust the supply flow of bismuth.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A bismuth working medium electric propulsion supply system based on a filamentous propellant is characterized by comprising a bismuth wire storage box (1), a wire feeding mechanism (2), a bismuth working medium gasification device (3) and an induction heating power supply (4);
bismuth wires (11) are coiled in the bismuth wire storage box (1), the bismuth working medium gasification device (3) comprises a blocking cover A (12), an induction heating coil (13), an induction heating support cylinder (14), a blocking cover B (16) and an air duct (17), the induction heating coil (13) is wound on the induction heating support cylinder (14), the induction heating coil (13) is electrically connected with the induction heating power supply (4), the blocking cover A (12) and the blocking cover B (16) are hermetically connected to two ends of the induction heating support cylinder (14), and the air duct (17) is hermetically communicated with the blocking cover B (16);
the bismuth wire (11) which is coiled in the bismuth wire storage box (1) is driven to enter the cavity of the induction heating supporting cylinder (14) through the traction of the wire feeding mechanism (2), the bismuth wire (11) is changed from a solid phase to a gas phase through generated eddy heat under the action of an alternating magnetic field generated by the induction heating coil (13), and vapor bismuth of the gas phase is output through the ventilation guide pipe (17).
2. The bismuth working fluid electric propulsion supply system based on filamentous propellant as claimed in claim 1, further comprising a pressure sensor (5) and a thermocouple (6), wherein the pressure sensor (5) and the thermocouple (6) are used for detecting the pressure and the temperature of the steam bismuth in the pipeline output from the vent conduit (17) and providing feedback from time to time.
3. The bismuth working fluid electric propulsion supply system based on filamentous propellant as claimed in claim 1, further comprising a conduit heat tracing band (18), wherein the conduit heat tracing band (18) is coated on the flow pipeline of the vapor bismuth, and the vapor bismuth in the pipeline is continuously kept warm through the conduit heat tracing band (18) to keep the vapor state.
4. The bismuth working fluid electric propulsion supply system based on filamentous propellant as claimed in claim 1, characterized in that the induction heating support cylinder (14) is a high temperature resistant ceramic material.
5. The bismuth working fluid electric propulsion supply system based on filamentous propellant as claimed in claim 1, characterized in that the material of the cap a (12) and the cap B (16) is graphite.
6. The bismuth working fluid electric propulsion supply system based on filamentous propellant as claimed in claim 1, characterized in that the material of the vent duct (17) is molybdenum.
7. The bismuth working medium electric propulsion supply system based on the filamentous propellant as claimed in any one of claims 1 to 6, wherein the bismuth working medium gasification device (3) further comprises a heating sleeve (15), the heating sleeve (15) is arranged in the induction heating support cylinder (14), and the bismuth wire (11) passes through the inner cavity of the heating sleeve (15) and is heated into steam bismuth.
8. The bismuth working fluid electric propulsion supply system based on filamentous propellant as claimed in claim 7, characterized in that the material of the heating sleeve (15) is tungsten.
9. The bismuth working medium electric propulsion supply system based on the filamentous propellant as claimed in claim 7, further comprising a Hall thruster (10), wherein the Hall thruster (10) is communicated with the ventilation conduit (17) through two parallel pipelines, the two parallel pipelines are coated with the pipeline heat tracing band (18), and the two parallel pipelines are provided with control valves (7).
10. The bismuth working fluid electric propulsion supply system based on filamentous propellant as claimed in claim 9, further comprising a throttle valve (8), wherein the throttle valve (8) is installed on the pipeline between the control valve (7) and the hall thruster (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111573151.2A CN114291298B (en) | 2021-12-21 | 2021-12-21 | Bismuth working medium electric propulsion supply system based on filament propellant |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111573151.2A CN114291298B (en) | 2021-12-21 | 2021-12-21 | Bismuth working medium electric propulsion supply system based on filament propellant |
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| CN114291298B CN114291298B (en) | 2024-03-29 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US6609363B1 (en) * | 1999-08-19 | 2003-08-26 | The United States Of America As Represented By The Secretary Of The Air Force | Iodine electric propulsion thrusters |
| US20050086926A1 (en) * | 2003-10-24 | 2005-04-28 | Michigan Technological University | Thruster apparatus and method |
| US20170036784A1 (en) * | 2014-04-18 | 2017-02-09 | Japan Aerospace Exploration Agency | Vapor jet system |
| CN107031869A (en) * | 2016-01-22 | 2017-08-11 | 波音公司 | The method and system promoted in space for spacecraft |
| US20190107103A1 (en) * | 2017-10-09 | 2019-04-11 | Phase Four, Inc. | Electrothermal radio frequency thruster and components |
| US20200025183A1 (en) * | 2018-06-13 | 2020-01-23 | Cu Aerospace, Llc | Fiber-fed advanced pulsed plasma thruster (fppt) |
| WO2020117354A2 (en) * | 2018-09-28 | 2020-06-11 | Phase Four, Inc. | Optimized rf-sourced gridded ion thruster and components |
| CN113306746A (en) * | 2021-05-26 | 2021-08-27 | 成都天巡微小卫星科技有限责任公司 | Iodine working medium electric propulsion storage and supply system based on sonic nozzle flow control |
-
2021
- 2021-12-21 CN CN202111573151.2A patent/CN114291298B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6609363B1 (en) * | 1999-08-19 | 2003-08-26 | The United States Of America As Represented By The Secretary Of The Air Force | Iodine electric propulsion thrusters |
| US20050086926A1 (en) * | 2003-10-24 | 2005-04-28 | Michigan Technological University | Thruster apparatus and method |
| US20170036784A1 (en) * | 2014-04-18 | 2017-02-09 | Japan Aerospace Exploration Agency | Vapor jet system |
| CN107031869A (en) * | 2016-01-22 | 2017-08-11 | 波音公司 | The method and system promoted in space for spacecraft |
| US20190107103A1 (en) * | 2017-10-09 | 2019-04-11 | Phase Four, Inc. | Electrothermal radio frequency thruster and components |
| US20200025183A1 (en) * | 2018-06-13 | 2020-01-23 | Cu Aerospace, Llc | Fiber-fed advanced pulsed plasma thruster (fppt) |
| WO2020117354A2 (en) * | 2018-09-28 | 2020-06-11 | Phase Four, Inc. | Optimized rf-sourced gridded ion thruster and components |
| CN113306746A (en) * | 2021-05-26 | 2021-08-27 | 成都天巡微小卫星科技有限责任公司 | Iodine working medium electric propulsion storage and supply system based on sonic nozzle flow control |
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| CN114291298B (en) | 2024-03-29 |
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