CN111114835B - Liquid propellant supply assembly for electric propulsion and electric propulsion system - Google Patents
Liquid propellant supply assembly for electric propulsion and electric propulsion system Download PDFInfo
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- CN111114835B CN111114835B CN201911351525.9A CN201911351525A CN111114835B CN 111114835 B CN111114835 B CN 111114835B CN 201911351525 A CN201911351525 A CN 201911351525A CN 111114835 B CN111114835 B CN 111114835B
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- 239000007788 liquid Substances 0.000 title claims abstract description 93
- 239000003380 propellant Substances 0.000 title claims abstract description 55
- 238000010438 heat treatment Methods 0.000 claims abstract description 34
- 239000011148 porous material Substances 0.000 claims abstract description 32
- 238000004140 cleaning Methods 0.000 claims description 23
- 238000005485 electric heating Methods 0.000 claims description 11
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 5
- 239000010936 titanium Substances 0.000 claims description 5
- 229910052719 titanium Inorganic materials 0.000 claims description 5
- 229920001343 polytetrafluoroethylene Polymers 0.000 claims description 4
- 239000004810 polytetrafluoroethylene Substances 0.000 claims description 4
- -1 polytetrafluoroethylene Polymers 0.000 claims description 3
- 238000011065 in-situ storage Methods 0.000 abstract description 6
- 229910052724 xenon Inorganic materials 0.000 abstract description 6
- FHNFHKCVQCLJFQ-UHFFFAOYSA-N xenon atom Chemical compound [Xe] FHNFHKCVQCLJFQ-UHFFFAOYSA-N 0.000 abstract description 6
- 238000000034 method Methods 0.000 abstract description 5
- 239000002699 waste material Substances 0.000 abstract description 5
- 239000002351 wastewater Substances 0.000 abstract description 5
- 239000007789 gas Substances 0.000 description 29
- 238000002309 gasification Methods 0.000 description 12
- 230000006872 improvement Effects 0.000 description 4
- 239000012528 membrane Substances 0.000 description 4
- 239000000463 material Substances 0.000 description 3
- 239000012466 permeate Substances 0.000 description 3
- 238000010926 purge Methods 0.000 description 3
- 239000000126 substance Substances 0.000 description 3
- 238000009423 ventilation Methods 0.000 description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 230000006837 decompression Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000010304 firing Methods 0.000 description 2
- 230000008676 import Effects 0.000 description 2
- 239000012535 impurity Substances 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000002245 particle Substances 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 229910001220 stainless steel Inorganic materials 0.000 description 2
- 239000010935 stainless steel Substances 0.000 description 2
- 229910000906 Bronze Inorganic materials 0.000 description 1
- 239000002253 acid Substances 0.000 description 1
- 239000000443 aerosol Substances 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 239000010974 bronze Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- KUNSUQLRTQLHQQ-UHFFFAOYSA-N copper tin Chemical compound [Cu].[Sn] KUNSUQLRTQLHQQ-UHFFFAOYSA-N 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 239000011261 inert gas Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000003595 mist Substances 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 230000035699 permeability Effects 0.000 description 1
- 230000021715 photosynthesis, light harvesting Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000010992 reflux Methods 0.000 description 1
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 1
- 229910010271 silicon carbide Inorganic materials 0.000 description 1
- 238000001179 sorption measurement Methods 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
- 238000009834 vaporization Methods 0.000 description 1
- 230000008016 vaporization Effects 0.000 description 1
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Classifications
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- 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
- B64G1/401—Liquid propellant rocket engines
-
- 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
- B64G1/402—Propellant tanks; Feeding propellants
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/30—Use of alternative fuels, e.g. biofuels
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Pipe Accessories (AREA)
- Resistance Heating (AREA)
Abstract
The application discloses a liquid propellant supply assembly for electric propulsion and an electric propulsion system. The liquid propellant supply assembly for electric propulsion comprises: the pipeline, and the heating device, the porous material piece, the waterproof breathable film and the pressure reducing valve which are sequentially arranged on the pipeline and communicated by the pipeline. The invention also provides an electric propulsion system comprising a liquid propellant supply assembly as described above for electric propulsion. The method solves the problems that xenon serving as a propellant in space electric propulsion is high in cost and cannot be applied in a large quantity for a long time, and space waste liquid and waste water carried by an aircraft and liquid available in situ resources cannot be utilized. The micro-flow supply of the liquid propellant is realized, and the micro-flow liquid propellant has the characteristics of high efficiency, high flexibility, wide application range and long service life.
Description
Technical Field
The present application relates to the field of aerospace electric propulsion, and in particular to a liquid propellant supply assembly for electric propulsion and an electric propulsion system.
Background
An electric propulsion system, also known as an electric rocket engine, is a device that generates thrust without relying on chemical combustion. The traditional chemical propulsion system converts chemical energy into mechanical energy through chemical reaction, and the electric propulsion system converts solar energy into electric energy and then converts the electric energy into mechanical energy. Electric propulsion systems are generally divided into three parts: the device comprises a power supply processing unit, a propellant working medium storage and supply unit and a thruster. The propellant is a working medium in electric propulsion, the most widely used propellant at present is inert gas xenon (Xe), the xenon is liquefied and stored in high density under the pressure of 15 megapascals, and the xenon is supplied by decompression and gasification in space.
Xenon, while the best choice for electric propulsion, is limited by price, propellant firing cost and ground firing capability, making it difficult to achieve a large number of applications over a long period of time. The space waste liquid and waste water carried by the aircraft and the liquid available in situ resources can be taken into consideration as space electric propulsion propellants, and the liquid propellants provide a feasible technical approach for electric propulsion, and can also greatly reduce the cost. However, the liquid propellant must be converted into a gaseous working medium for the discharge operation, so that the problem of space-electric propulsion liquid propellant supply must be solved.
In addition, the development of heavy space tasks such as deep space exploration, ultra-deep space exploration, deep space freight transportation and in-situ resource utilization also requires power support of ultra-large thrust and long-service-life electric propulsion, and a long-service-life, high-efficiency and wide-application-range liquid propellant supply assembly is an essential assembly for improving the electric propulsion performance, so that the design of the assembly is urgently needed.
Disclosure of Invention
The main object of the present application is to provide a liquid propellant supply assembly for electric propulsion and an electric propulsion system, so as to solve the problems that xenon as a propellant in space electric propulsion is high in cost, cannot be applied in a large amount for a long time, and space waste liquid, waste water and in-situ resource available liquid carried by an aircraft cannot be utilized.
To achieve the above object, according to one aspect of the present application, there is provided a liquid propellant supply assembly for electric propulsion, comprising: the pipeline, and the heating device, the porous material piece, the waterproof breathable film and the pressure reducing valve which are sequentially arranged on the pipeline and communicated by the pipeline.
Further, the heating device comprises a shell, an electric heating tube and a spiral tube, wherein the electric heating tube and the spiral tube are arranged in the shell, the spiral tube is spirally wound on the outer surface of the electric heating tube, and the spiral tube is communicated with the pipeline.
Further, the porous material piece adopts a titanium-based porous material column.
Further, the waterproof breathable film is made of polytetrafluoroethylene film.
Further, the waterproof and breathable membrane is fixed by a group of annular gaskets and is arranged in the pipeline.
Further, the liquid propellant supply assembly for electric propulsion further comprises: and the liquid filter is arranged on the pipeline and is positioned at one end of the heating device away from the porous material piece.
Further, the liquid propellant supply assembly for electric propulsion further comprises: the gas flow controller is arranged on the pipeline and is positioned at one end of the pressure reducing valve away from the waterproof and breathable film.
Further, the liquid propellant supply assembly for electric propulsion further comprises: the first pipeline cleaning control valve and the second pipeline cleaning control valve are arranged on the pipeline, the first pipeline cleaning control valve is located at one end, far away from the porous material piece, of the heating device, and the second pipeline cleaning control valve is located between the waterproof breathable film and the pressure reducing valve.
To achieve the above object, according to one aspect of the present application, there is provided an electric propulsion system comprising the liquid propellant supply assembly for electric propulsion described above.
The technical scheme of the invention has the following advantages:
the present invention provides a liquid propellant supply assembly for electric propulsion comprising: the pipeline and the heating device, the porous material piece, the waterproof breathable film and the pressure reducing valve which are sequentially arranged on the pipeline and communicated by the pipeline enter the heating device through the pipeline, the heating device heats and gasifies the liquid propellant, the porous material piece realizes the functions of absorbing and dispelling the gas based on the hole-shaped structure in the porous material piece, most of liquid which is not gasified can be adsorbed, the heat exchange is increased, the gasification efficiency is improved, the continuity and the stability of the liquid gasification are ensured, the reverse flow of the gas can be prevented, the utilization rate of the propellant is improved, the waterproof breathable film plays the role of resisting the liquid and ventilation, the gas generated by gasification is enabled to permeate and block the liquid to pass through, and the gas enters the pressure reducing valve to be decompressed and then is discharged through the pipeline to be supplied to the thruster, wherein the liquid propellant can use space waste liquid carried by an aircraft, waste water and liquid with available in-situ resources, the micro-flow supply of the liquid propellant is realized, and the characteristics of high efficiency, high flexibility, wide application range and long service life are achieved.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, are included to provide a further understanding of the application and to provide a further understanding of the application with regard to the other features, objects and advantages of the application. The drawings of the illustrative embodiments of the present application and their descriptions are for the purpose of illustrating the present application and are not to be construed as unduly limiting the present application. In the drawings:
FIG. 1 is a schematic illustration of a liquid propellant supply assembly for electric propulsion provided in accordance with an embodiment of the present invention;
fig. 2 is a schematic structural view of a heating device according to an embodiment of the present invention.
Reference numerals:
1-a pipeline; 2-a heating device; 21-a housing; 22-an electric heating tube; 231-liquid inlet; 232-a liquid outlet; 24-thermometer; 3-a porous material piece; 4-a waterproof breathable film; 5-a pressure reducing valve; 6-a liquid filter; 7-a gas flow controller; 8-a first pipeline cleaning control valve; 9-a second pipeline cleaning control valve.
Detailed Description
In order to make the present application solution better understood by those skilled in the art, the following description will be made in detail and with reference to the accompanying drawings in the embodiments of the present application, it is apparent that the described embodiments are only some embodiments of the present application, not all embodiments. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, shall fall within the scope of the present application.
It should be noted that the terms "first," "second," and the like in the description and claims of the present application and the above figures are used for distinguishing between similar objects and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used may be interchanged where appropriate in order to describe the embodiments of the present application described herein. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
In the present application, the terms "upper", "lower", "left", "right", "front", "rear", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal" and the like indicate an azimuth or a positional relationship based on that shown in the drawings. These terms are used primarily to better describe the present application and its embodiments and are not intended to limit the indicated device, element or component to a particular orientation or to be constructed and operated in a particular orientation.
Also, some of the terms described above may be used to indicate other meanings in addition to orientation or positional relationships, for example, the term "upper" may also be used to indicate some sort of attachment or connection in some cases. The specific meaning of these terms in this application will be understood by those of ordinary skill in the art as appropriate.
Furthermore, the terms "mounted," "configured," "provided," "connected," "coupled," and "sleeved" are to be construed broadly. For example, it may be a fixed connection, a removable connection, or a unitary construction; may be a mechanical connection, or an electrical connection; may be directly connected, or indirectly connected through intervening media, or may be in internal communication between two devices, elements, or components. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art as the case may be.
It should be noted that, in the case of no conflict, the embodiments and features in the embodiments may be combined with each other. The present application will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
As shown in fig. 1, the present application relates to a liquid propellant supply assembly for electric propulsion, comprising: pipeline 1 and set up on pipeline 1 and by pipeline 1 heating device 2, porous material spare 3, waterproof ventilated membrane 4 and relief pressure valve 5 that switch on in proper order.
The working principle of the liquid propellant supply assembly for electric propulsion is as follows: the liquid propellant is heated and gasified by the heating device 2 through the pipeline 1, the porous material piece 3 realizes the functions of absorbing liquid and dispelling air based on the hole-shaped structure in the porous material piece, can absorb most of liquid which is not gasified, increases heat exchange, improves gasification efficiency, ensures the continuity and stability of liquid gasification, can prevent gas reflux, improves the utilization rate of the propellant, and the waterproof breathable film 4 plays the role of resisting liquid and ventilation, so that gas generated by gasification permeates and blocks liquid to pass through, and the gas is discharged through the pipeline 1 to be supplied to a thruster after being decompressed by the decompression valve 5.
The liquid propellant can be used for space waste liquid and waste water carried by the aircraft and liquid with available in-situ resources, so that the micro-flow supply of the liquid propellant is realized, and the device has the characteristics of high efficiency, high flexibility, wide application range and long service life.
The heating device 2 is a device for heating and gasifying a liquid propellant to generate gas, and may be a heating device in the prior art, for example, the heating device is composed of a housing and an electric heating tube disposed in the housing, the electric heating tube may convert electric energy into heat energy, the liquid passes through the electric heating tube to realize heating and gasifying of the liquid propellant in the housing, or the heating device is composed of the housing and a pipeline in the housing, the liquid passes through the pipeline, and a heating medium is disposed in the housing to heat and gasify the liquid propellant in the pipeline. All that is to use the device that can realize above-mentioned function is in the scope of this application request protection, as the preferred of this application embodiment, as shown in fig. 2, provide a high-efficient liquid heating device, this heating device 2 includes casing 21 and electrothermal tube 22 and the spiral pipe of setting in casing 21, spiral pipe spiral coil in electrothermal tube 22's surface, and the both ends of spiral pipe are liquid import 231 and liquid outlet 232 respectively, and liquid import 231 and liquid outlet 232 all communicate with pipeline 1. The inner side surface of the shell 21 is a silicon carbide material layer, so that the heat insulation effect is good, and the heat dissipation can be reduced; the pipe body of the electric heating pipe is made of pure aluminum, so that heat energy converted from electric energy can be quickly transmitted to the spiral pipe; the spiral pipe is spiral, and the spiral structure has prolonged the length and the area of heating of pipeline, makes electrothermal tube 22 and the liquid propellant in the spiral pipe fully contact, and is heated evenly, and the energy dissipation is little, has greatly promoted heating efficiency. A thermometer 24 is also included for measuring the temperature within the heating device.
The porous material 3 is a component with the functions of absorbing and dispelling air, and the porous material can be bronze, stainless steel, nickel or titanium, preferably titanium-based porous material, and has good mechanical property, corrosion resistance and air permeability. The pore diameter adopts coarse pores (more than 50 nm), the porosity is high (more than 60%), the length is 0.9-1.1 mm, the porous material piece 3 can be a porous material column which is matched with the caliber of the pipeline 1, is clamped in the pipeline, or is connected into the pipeline 1 through other tubular connectors, and the connection mode which can be arranged in the pipeline is within the scope of the application protection. The porous material 3 functions in the assembly as follows: the porous material resists flow of liquid into subsequent components; the heat insulation function prevents the heat of the heating device 2 from being lost in the pipeline 1, and improves the heating efficiency; the adsorption liquid increases heat exchange, improves gasification efficiency, and is favorable for keeping the continuity and stability of liquid gasification; unidirectional conductivity, preventing reverse flow of gas and improving the utilization rate of propellant.
The waterproof and breathable film 4 is a component with a waterproof and breathable function, for example, the material of the waterproof and breathable film can be Polytetrafluoroethylene (PTFE) film material, and all the components using the film with the waterproof and breathable functions are within the scope of the application. The liquid is blocked by the waterproof and breathable membrane 4, and the gas is permeated into the subsequent components. As a connection mode of the waterproof and breathable film 4, the waterproof and breathable film can be fixedly compressed by a group of annular gaskets, the annular gaskets are connected into the pipeline 1 by a tubular joint or directly welded into the pipeline 1, and the annular gaskets can be made of titanium sheets.
The pressure reducing valve 5 is a member for reducing pressure of gas generated by vaporization of the liquid propellant, and stably supplies the gas after the pressure reduction.
As a further improvement of the present embodiment, the liquid propellant supply assembly for electric propulsion further comprises: a liquid filter 6 is arranged on the pipeline 1, and the liquid filter 6 is positioned at one end of the heating device 2 away from the porous material member 3.
The liquid propellant is filtered out large-particle impurities by the liquid filter 6 before heating, so that damage to subsequent pipelines and parts/devices is avoided, the maintenance cost of the whole assembly is reduced, and the supply efficiency of the liquid propellant is improved. Preferably, the liquid filter 6 is made of stainless steel.
As a further improvement of the present embodiment, the liquid propellant supply assembly for electric propulsion further comprises: and a gas flow controller 7 arranged on the pipeline 1, wherein the gas flow controller 7 is positioned at one end of the pressure reducing valve 5 far away from the waterproof and breathable membrane 4.
The gas flow controller 7 is used for controlling the supply amount of the gas, and the depressurized gas is supplied to the propeller through the gas flow controller 7.
As a further improvement of the present embodiment, the liquid propellant supply assembly for electric propulsion further comprises: a first pipeline cleaning control valve 8 and a second pipeline cleaning control valve 9 are arranged on the pipeline 1, the first pipeline cleaning control valve 8 is positioned at one end of the heating device 2 far away from the porous material piece 3, and the second pipeline cleaning control valve 9 is positioned between the waterproof breathable film 4 and the pressure reducing valve 5. More preferably, the first line purge control valve 8 is located at the front end of the liquid filter 6. The first pipeline cleaning control valve 8 and the second pipeline cleaning control valve 9 are used for cleaning pipelines, and can reversely clean the liquid filter 6 and the porous material piece 3, so that the blockage is prevented, and the service life is prolonged. The first line purge control valve 8 and the second line purge control valve 9 operate on the following principle: closing all pipeline valves, firstly opening a second pipeline cleaning control valve 9, and introducing atomized acid gas mist into the pipeline; and then opening the first pipeline cleaning control valve 8 to discharge the cleaned aerosol, thereby achieving the cleaning purpose and maintaining the pipeline flow.
The liquid propellant supply assembly for electric propulsion as shown in fig. 1 works as follows:
the liquid propellant flows into the heating device 2 after entering the liquid filter 6 through the pipeline 1 to filter large-particle impurities, the heating device 2 heats and gasifies the liquid propellant, the porous material piece 3 realizes the effect of absorbing liquid and dispelling gas based on the hole-shaped structure in the porous material piece, most of liquid which is not gasified can be absorbed, heat exchange is increased, gasification efficiency is improved, continuous and stability of liquid gasification is guaranteed, gas backflow can be prevented, propellant utilization rate is improved, the waterproof breathable film 4 plays a role in resisting liquid and ventilation, gas generated by gasification permeates and blocks liquid from passing through, the gas enters the gas flow controller 7 after entering the pressure reducing valve 5 for pressure reduction, and the gas is provided for the propeller through the gas flow controller 7 in a set flow. After the shutdown, the first pipeline cleaning control valve 8 and the second pipeline cleaning control valve 9 can be used for cleaning the pipeline, and the liquid filter 6 and the porous material piece 3 are reversely cleaned.
The application also provides an electric propulsion system, comprising the liquid propellant supply assembly for electric propulsion, and further comprising a thruster, wherein the thruster is connected with a pipeline at the rear end of the gas flow controller 7.
The foregoing description is only of the preferred embodiments of the present application and is not intended to limit the same, but rather, various modifications and variations may be made by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application should be included in the protection scope of the present application.
Claims (2)
1. A liquid propellant supply assembly for electric propulsion, comprising: the heating device comprises a shell, an electric heating tube and a spiral tube, wherein the electric heating tube and the spiral tube are arranged in the shell, the spiral tube is spirally coiled on the outer surface of the electric heating tube, and the spiral tube is communicated with the pipeline; the porous material piece is a component with the functions of absorbing and dispelling air, and adopts titanium-based porous material columns; the waterproof and breathable film adopts a polytetrafluoroethylene film, is fixed by a group of annular gaskets and is arranged in the pipeline,
further comprises: a liquid filter disposed on the conduit, the liquid filter being located at an end of the heating device remote from the porous material member;
further comprises: the gas flow controller is arranged on the pipeline and is positioned at one end of the pressure reducing valve away from the waterproof and breathable film;
further comprises: the first pipeline cleaning control valve and the second pipeline cleaning control valve are arranged on the pipeline, the first pipeline cleaning control valve is located at one end, far away from the porous material piece, of the heating device, and the second pipeline cleaning control valve is located between the waterproof breathable film and the pressure reducing valve.
2. An electric propulsion system comprising the liquid propellant supply assembly for electric propulsion of claim 1.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911351525.9A CN111114835B (en) | 2019-12-24 | 2019-12-24 | Liquid propellant supply assembly for electric propulsion and electric propulsion system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911351525.9A CN111114835B (en) | 2019-12-24 | 2019-12-24 | Liquid propellant supply assembly for electric propulsion and electric propulsion system |
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| CN111114835A CN111114835A (en) | 2020-05-08 |
| CN111114835B true CN111114835B (en) | 2023-06-23 |
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