CN114291298B - Bismuth working medium electric propulsion supply system based on filament propellant - Google Patents
Bismuth working medium electric propulsion supply system based on filament propellant Download PDFInfo
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- CN114291298B CN114291298B CN202111573151.2A CN202111573151A CN114291298B CN 114291298 B CN114291298 B CN 114291298B CN 202111573151 A CN202111573151 A CN 202111573151A CN 114291298 B CN114291298 B CN 114291298B
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- bismuth
- induction heating
- working medium
- blanking cover
- supply system
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- 229910052797 bismuth Inorganic materials 0.000 title claims abstract description 115
- JCXGWMGPZLAOME-UHFFFAOYSA-N bismuth atom Chemical compound [Bi] JCXGWMGPZLAOME-UHFFFAOYSA-N 0.000 title claims abstract description 115
- 239000003380 propellant Substances 0.000 title claims abstract description 23
- 238000010438 heat treatment Methods 0.000 claims abstract description 93
- 230000006698 induction Effects 0.000 claims abstract description 66
- 238000002309 gasification Methods 0.000 claims abstract description 25
- 230000007246 mechanism Effects 0.000 claims abstract description 12
- 239000012071 phase Substances 0.000 claims abstract description 12
- 238000009423 ventilation Methods 0.000 claims abstract description 12
- 238000007789 sealing Methods 0.000 claims abstract description 6
- 239000007790 solid phase Substances 0.000 claims abstract description 4
- 239000000463 material Substances 0.000 claims description 9
- 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
- 239000000126 substance Substances 0.000 claims 2
- 238000004378 air conditioning Methods 0.000 claims 1
- 238000013461 design Methods 0.000 description 5
- 238000009834 vaporization Methods 0.000 description 5
- 230000008016 vaporization Effects 0.000 description 5
- 235000017166 Bambusa arundinacea Nutrition 0.000 description 4
- 235000017491 Bambusa tulda Nutrition 0.000 description 4
- 241001330002 Bambuseae Species 0.000 description 4
- 235000015334 Phyllostachys viridis Nutrition 0.000 description 4
- 239000011425 bamboo Substances 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
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000008018 melting Effects 0.000 description 2
- 238000002844 melting Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000001105 regulatory effect Effects 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
- 229910052770 Uranium Inorganic materials 0.000 description 1
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 description 1
- 230000015572 biosynthetic process Effects 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
- 239000007770 graphite material Substances 0.000 description 1
- 238000009413 insulation Methods 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
- 238000000034 method Methods 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000004449 solid propellant Substances 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 230000007704 transition 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
Landscapes
- General Induction Heating (AREA)
Abstract
The invention relates to a bismuth working medium electric propulsion supply system based on a filament propellant, which belongs to the technical field of electric propulsion propellant supply systems and comprises a bismuth filament 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 blanking cover A, an induction heating coil, an induction heating supporting cylinder, a blanking cover B and an air duct, the induction heating coil is wound on the induction heating supporting cylinder and is electrically connected with an induction heating power supply, the blanking cover A and the blanking cover B are connected to two ends of the induction heating supporting cylinder in a sealing mode, and the air duct is communicated with the blanking cover B in a sealing mode; bismuth wires spiraling in the bismuth wire storage box enter the cavity of the induction heating support cylinder from the blanking cover A through traction drive of the wire feeding mechanism, and the bismuth wires are changed from solid phase to gas phase through induction heating and output through the ventilation catheter. The invention adopts an induction heating mode, the heating mode is more centralized 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 filament 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 medium to generate plasma and accelerates propellant by the electric energy to generate thrust, and has the characteristics of higher than impulse, small thrust, repeatable start and long service life. At present, the electric propulsion system mainly adopts gas working media such as xenon as propellant, and has low cost performance when being applied to high-power electric propulsion because of high price and lower storage density than metal propellant. At present, research and ground tests on solid propellant working media such as magnesium, zinc, iodine, bismuth and the like are carried out at home and abroad, wherein the bismuth working medium has the highest atomic mass, lowest ionization energy, highest ionization cross section and highest storage density, is low in price, and becomes a proper working medium for the ultra-high specific impulse anode layer Hall thruster.
The metal propellant working medium has high melting point, which brings great difficulty to design and realization of the working medium supply system. In the existing propellant supply technical scheme, most of the propellant is bismuth working medium which is heated and liquefied by a storage tank and then gasified by a gasification device to be conveyed to an electric thruster. In 2005, anita Sengupta et al, U.S. reviewed the ultra high specific impulse anode layer project in the 29 th International electric Propulsion conference paper: double-layer bismuth working medium ultra-high specific impulse anode layer thruster (An Overview of the VHITAL Program: A Two-Stage Bismuth Fed Very High Specific Impulse Thruster With Anode Layer) adopts bismuth to heat and liquefy in a storage tank, and the bismuth is conveyed to an atomizer through a micropump at a certain pressure and flow rate to be atomized and then to the thruster. The problems brought by the prior art are: the bismuth is easy to form a compound with other metals when heated, and the heating mode is easy to cause incomplete evaporation due to uneven temperature distribution of the storage tank, so that the selection and heating design of the bismuth storage tank material are difficult; besides, the whole heating power of the storage tank bismuth is larger, the conveying pipeline is longer, and the pipeline needs to keep a longer heating section; meanwhile, the bismuth storage tank propellant is in powder form at present, which 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 filament-shaped propellant.
The bismuth working medium electric propulsion supply system based on the filament propellant comprises a bismuth filament 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 blanking cover A, an induction heating coil, an induction heating supporting cylinder, a blanking cover B and an air duct, the induction heating coil is wound on the induction heating supporting cylinder and is electrically connected with an induction heating power supply, the blanking cover A and the blanking cover B are connected to two ends of the induction heating supporting cylinder in a sealing mode, and the air duct is communicated with the blanking cover B in a sealing mode;
the bismuth wire coiled in the bismuth wire storage box enters the cavity of the induction heating support cylinder from the blanking cover A through traction drive of the wire feeding mechanism, the bismuth wire is changed into a gas phase from a solid phase through generated vortex heat under the action of an alternating magnetic field generated by the induction heating coil, and the vapor bismuth in the gas phase is output through the ventilation catheter.
In some embodiments, a pressure sensor and thermocouple are included for detecting the pressure and temperature of the bismuth vapor in the tubing output from the vent conduit, providing real-time feedback.
In some embodiments, the device further comprises a conduit heat tracing band, wherein the conduit heat tracing band is coated on the flow pipeline of the steam bismuth, and the steam bismuth in the pipeline is continuously insulated through the conduit heat tracing band to keep the steam state.
In some embodiments, the induction heating support cylinder is a high temperature resistant ceramic material.
In some embodiments, the material of the plug a and the plug 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, wherein the heating sleeve is arranged in the induction heating support 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 device further comprises a hall thruster, the hall thruster is communicated with the ventilation catheter through two parallel pipelines, the catheter heat tracing belt is covered on the two parallel pipelines, and the control valve is installed on the two parallel pipelines.
In some embodiments, a throttle valve is also included, the throttle valve being mounted on the 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 centralized 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 optimal design of the bismuth working medium gasification device, the conversion rate of bismuth working medium gasification is improved, and the working efficiency is improved.
Drawings
Other features, objects and advantages of the present invention will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a schematic diagram of a bismuth working medium supply system based on a filament-like propellant in accordance with the present invention;
FIG. 2 is a schematic structural diagram of an embodiment of an induction heating bismuth working medium gasification device of the present invention;
FIG. 3 is a schematic structural diagram of another embodiment of an induction heating bismuth working medium gasification device of the present invention;
fig. 4 is a schematic diagram of a bismuth working medium hall electric propulsion supply system based on a filiform 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 present invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present invention.
Example 1
The invention provides a bismuth working medium electric propulsion supply system based on a filament propellant, which is shown in figures 1-2 and comprises a bismuth filament 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 spirally arranged in the bismuth wire storage box 1, and the wire diameter of the bismuth wires 11 is 0.2-2 mm according to the requirement. The bismuth wire 11 spirally installed in the bismuth wire storage box 1 is led out and then connected with the wire feeding mechanism 2, the wire feeding mechanism 2 provides corresponding bismuth wire feeding speed according to downstream load demand, wherein the wire feeding mechanism 2 can be a stepping motor, the type of the stepping motor, such as the motor type, the size and the stepping angle, is selected according to the load demand and the demand, further, a vacuum collector can be adopted downstream to collect the bismuth steam condensed in the downstream of the supply system, the weight gain of bismuth condensation is measured, and the relation between the bismuth wire feeding speed and the bismuth mass flow is quantitatively calculated so as to open loop control the operation parameters of the stepping motor.
The bismuth working medium gasification device 3 is an electromagnetic induction heating device and comprises a blanking cover A12, an induction heating coil 13, an induction heating supporting cylinder 14, a blanking cover B16 and an air duct 17. The induction heating coil 13 is wound on the induction heating support 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 induction heating coil power is obtained through experiments. The induction heating support cylinder is preferably a high-temperature-resistant ceramic material, has high mechanical property and dimensional stability at high temperature, and has good heat insulation performance. The two ends of the induction heating support cylinder 14 are respectively and hermetically connected with the blanking cover A12 and the blanking cover B16, wherein the blanking cover A12 is used as a port into which bismuth wires enter to form dynamic seal with the bismuth wires 11, the end cover B is used as an outlet end of vapor bismuth in a gas phase, and preferably, the blanking cover A12 and the end cover B16 are both made of graphite materials, so that the thermal stability is good. One end of the vent conduit 17 is sealingly connected to the flow passage of the plug B16, preferably one end of the vent conduit 17 extends into the flow passage of the plug B16, and the bismuth vapor flows through the vent conduit 17 to the downstream load. Preferably, the material of the ventilation duct 17 is molybdenum, which is a high temperature resistant metal material, because the bismuth vapor temperature is higher than 800 ℃.
The working principle of the invention is as follows: the bismuth wire 11 spiraling in the bismuth wire storage box 1 is driven by the traction of the wire feeding mechanism 2, the bismuth wire enters the cavity of the induction heating support cylinder 14 from the port of the plug A12, the induction heating coil 13 generates an alternating magnetic field under the action of alternating current provided by the induction heating power supply 4, the bismuth wire 11 generates eddy current heat under the action of the alternating magnetic field, the eddy current heat enables the bismuth wire 11 to be changed from a solid phase to a gas phase, and then steam 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 was 271.4 ℃, the corresponding vaporization temperature was 935.93 ℃ when the vaporization pressure was 200Pa, and the corresponding vaporization temperature was 1052.09 ℃ when the vaporization pressure was 1000 Pa. The induction heating temperature of the bismuth gas is set to 1300-1800 ℃ to complete the liquid-gas two-phase transition of the bismuth wire in the heating area, and the liquefying area is small enough to provide a temperature sufficient to support the vaporization rate and the downstream flow pressure.
Compared with the prior art that two phases of liquefaction and gasification of the bismuth working medium are completed in different areas of the storage tank and the gasification device by adopting a heating belt or a heating pipeline direct heating mode, the problem that the design of a heating structure of the storage tank heating and gasification device is complex is solved.
Preferably, a pressure sensor 5 and a thermocouple 6 are arranged at the outlet end of the ventilation catheter 17, and the pressure and the temperature of bismuth steam are measured in real time through the pressure sensor 5 and the thermocouple 6, so that real-time feedback is provided.
Further, the outlet end of the ventilation duct 17 and the downstream pipeline thereof are covered with the duct heat tracing band 18, and the specific heat tracing temperature setting range of the duct heat tracing band 18 can be 900-1100 ℃, so that bismuth working medium at the outlet and downstream of the outlet presents a gas phase form, and the formation of condensed phase inside the propeller is prevented.
Example 2
The embodiment 2 is formed on the basis of the embodiment 1, and improves the conversion rate of bismuth working medium gasification and improves the working efficiency by optimizing the design of the bismuth working medium gasification device. Specifically:
as shown in fig. 3, the bismuth working medium gasification device 3 is further provided with an induction heating cylinder 15, the induction heating cylinder 15 is made of metal, preferably high temperature resistant material tungsten, the induction heating cylinder 15 is arranged in the induction heating supporting cylinder 14, and the induction heating cylinder 15 is made of high temperature resistant material tungsten. Through wire feeding mechanism 2, bismuth wire 11 gets into induction heating section of thick bamboo 15's inner chamber from the entry of blanking cover A12, and induction heating coil 13 lets in the alternating current of certain frequency, and induction heating section of thick bamboo 15 produces the induction current under the effect of alternating magnetic field, utilizes vortex heating induction heating section of thick bamboo 15 to 1200-1300 ℃, and the induction heating section of thick bamboo 15 after the heating heats bismuth wire 11 in the inner chamber, and the bismuth wire is liquefied and gasified rapidly in the zone of heating, forms bismuth steam after being carried to the low reaches load by ventilation catheter 17.
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 for a bismuth working medium hall electric propulsion system, particularly for an ultra-high specific impulse anode layer thruster, as shown in fig. 4, specifically:
on the basis of the technical solutions of embodiment 1 or embodiment 2, air supply pipelines with different air flows to the cathode and the anode of the hall thruster are respectively added, as shown in fig. 4, a control valve 7 and a throttling element 8 are arranged in each pipeline, and the temperature is still kept in the system pipeline through a cladding conduit heat tracing belt 18, and the implementation steps are as follows:
firstly, heating by a conduit heat tracing belt 18, carrying out system heat tracing on a conduit, and completing preliminary preheating of the system;
secondly, opening a control valve 7 to complete the exhaust of residual gas in the system;
and starting the induction heating power supply 4, performing 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 1300-1800 ℃ according to preset power, starting the stepping motor 2 to work, feeding the bismuth wire 11 into the bismuth working medium gasification device, and starting outputting steam bismuth at the downstream.
The pressure sensor 5 and the thermocouple 6 detect the bismuth steam temperature, the throttling element 8 controls the cathode and anode input flow of the Hall thruster 10, the rotating speed of the stepping motor 2 is regulated in real time according to feedback data, and the feeding speed of the bismuth wire 11 is further controlled, so that the bismuth feeding flow is regulated.
In the description of the present application, it should 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 the orientations or positional relationships illustrated in the drawings, merely to facilitate description of the present application and simplify the description, and do not indicate or imply that the devices or elements being referred to must have a specific orientation, be configured and operated in a specific orientation, and are not to be construed as limiting the present application.
The foregoing describes specific embodiments of the present invention. It is to be understood that the invention is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the invention. The embodiments of the present application and features in the embodiments may be combined with each other arbitrarily without conflict.
Claims (6)
1. The bismuth working medium electric propulsion supply system based on the filiform propellant is characterized by comprising a bismuth filament 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 blanking cover A (12), an induction heating coil (13), an induction heating support cylinder (14), a blanking 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 an induction heating power supply (4), the blanking cover A (12) and the blanking cover B (16) are connected to the two ends of the induction heating support cylinder (14) in a sealing mode, and the air duct (17) is communicated with the blanking cover B (16) in a sealing mode;
the bismuth wire (11) spiraling in the bismuth wire storage box (1) enters the cavity of the induction heating support cylinder (14) from the blanking cover A (12) through traction drive of the wire feeding mechanism (2), the bismuth wire (11) is changed into a gas phase from a solid phase through the generated eddy current heat under the action of an alternating magnetic field generated by the induction heating coil (13), and the vapor bismuth in the gas phase is output through the ventilation catheter (17);
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;
the heating sleeve (15) is made of tungsten;
the device also comprises a conduit heat tracing belt (18), wherein the conduit heat tracing belt (18) is coated on a flow pipeline of the steam bismuth, and the steam bismuth in the pipeline is continuously insulated through the conduit heat tracing belt (18) to keep a steam state;
the novel high-pressure air-conditioning device is characterized by further comprising a Hall thruster (10), wherein the Hall thruster (10) is communicated with the ventilation catheter (17) through two parallel pipelines, the catheter heat tracing belt (18) is wrapped on the two parallel pipelines, and the control valve (7) is arranged on the two parallel pipelines.
2. The bismuth working medium electric propulsion supply system based on the filiform propellant according to 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 bismuth vapor in the pipeline output from the ventilation catheter (17) and providing real-time feedback.
3. Bismuth working substance electric propulsion supply system based on filiform propellant according to claim 1, characterized in that the induction heating support cylinder (14) is a high temperature resistant ceramic material.
4. The bismuth working medium electric propulsion supply system based on the filiform propellant according to claim 1, wherein the material of the blanking cover a (12) and the blanking cover B (16) is graphite.
5. Bismuth working substance electric propulsion supply system based on a filiform propellant according to claim 1, characterized in that the material of the ventilation duct (17) is molybdenum.
6. The bismuth working medium electric propulsion supply system based on the filiform propellant according to claim 1, further comprising a throttle valve (8), wherein the throttle valve (8) is installed on a 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 |
Applications Claiming Priority (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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| CN114291298B true 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 |
| CN107031869A (en) * | 2016-01-22 | 2017-08-11 | 波音公司 | The method and system promoted in space for spacecraft |
| 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 |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7059111B2 (en) * | 2003-10-24 | 2006-06-13 | Michigan Technological University | Thruster apparatus and method |
| JP6586657B2 (en) * | 2014-04-18 | 2019-10-09 | 国立研究開発法人宇宙航空研究開発機構 | Steam injection system |
| US20190107103A1 (en) * | 2017-10-09 | 2019-04-11 | Phase Four, Inc. | Electrothermal radio frequency thruster and components |
| US10570892B2 (en) * | 2018-06-13 | 2020-02-25 | Cu Aerospace, Llc | Fiber-fed advanced pulsed plasma thruster (FPPT) |
-
2021
- 2021-12-21 CN CN202111573151.2A patent/CN114291298B/en active Active
Patent Citations (4)
| 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 |
| CN107031869A (en) * | 2016-01-22 | 2017-08-11 | 波音公司 | The method and system promoted in space for spacecraft |
| 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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