CN111114835A - A liquid propellant supply assembly for electric propulsion and electric propulsion system - Google Patents
A liquid propellant supply assembly for electric propulsion and electric propulsion system Download PDFInfo
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- CN111114835A CN111114835A CN201911351525.9A CN201911351525A CN111114835A CN 111114835 A CN111114835 A CN 111114835A CN 201911351525 A CN201911351525 A CN 201911351525A CN 111114835 A CN111114835 A CN 111114835A
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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
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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
- B64G1/402—Propellant tanks; Feeding propellants
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- 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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Abstract
本申请公开了一种用于电推进的液体推进剂供给组件及电推进系统。该用于电推进的液体推进剂供给组件包括：管路以及依次设置在所述管路上且由所述管路导通的加热装置、多孔材料件、防水透气膜和减压阀。本发明还提供了包括上述用于电推进的液体推进剂供给组件的电推进系统。本申请解决了空间电推进中氙气作为推进剂成本高、无法长期大量应用、以及而飞行器自身携带的空间废液、废水及原位资源可用的液体不能得以利用的问题。实现了液体推进剂的微流量供给，具有效率高、灵活度高、适用范围宽和长寿命的特点。
The present application discloses a liquid propellant supply assembly for electric propulsion and an electric propulsion system. The liquid propellant supply assembly for electric propulsion includes: a pipeline, a heating device, a porous material piece, a waterproof gas-permeable membrane and a pressure reducing valve, which are sequentially arranged on the pipeline and communicated by the pipeline. The present invention also provides an electric propulsion system comprising the above-described liquid propellant supply assembly for electric propulsion. The present application solves the problems of high cost of xenon gas as a propellant in space electric propulsion, the inability to be used in large quantities for a long time, and the inability to utilize the space waste liquid, waste water and in-situ resources available liquid carried by the aircraft itself. The micro-flow supply of liquid propellant is realized, and it has the characteristics of high efficiency, high flexibility, wide application range and long life.
Description
Technical Field
The application relates to the field of aerospace electric propulsion, 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 can generate 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 sections: 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 at high density under the pressure of 15 MPa, and is decompressed and gasified in space, so that the xenon is supplied.
Xenon, although the best choice for electric propulsion, is difficult to achieve for long periods of mass use due to limitations in price, propellant launch cost and ground launch capability. The space waste liquid, the waste water and the liquid which can be used by the in-situ resource carried by the aircraft can be considered as the propellant for space electric propulsion, the liquid propellant provides a feasible technical approach for the electric propulsion, and the cost can be greatly reduced. However, the liquid propellant must be converted into a gaseous working medium for discharge operation, and therefore the problem of spatially electrically propelling the liquid propellant supply must be solved.
In addition, the development of important space tasks such as deep space exploration, ultra-deep space exploration, deep space freight transportation and in-situ resource utilization also needs power support of ultra-large thrust and long-life electric propulsion, and a liquid propellant supply assembly with long service life, high efficiency and wide application range is an indispensable key assembly for improving the electric propulsion performance, and the assembly is urgently needed to be designed at present.
Disclosure of Invention
The main objective of the present application is to provide a liquid propellant supply assembly and an electric propulsion system for electric propulsion, so as to solve the problems that xenon gas as a propellant in space electric propulsion has high cost and cannot be used in large quantities for a long time, and space waste liquid, waste water and available liquid of in-situ resources 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 set gradually heating device, porous material spare, waterproof ventilated membrane and relief pressure valve on the pipeline and by the pipeline switches on.
Further, the heating device comprises a shell, and an electric heating tube and a spiral tube which are arranged in the shell, wherein 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.
Furthermore, the waterproof breathable film is a polytetrafluoroethylene film.
Further, the waterproof breathable film 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: the liquid filter is arranged on the pipeline and is positioned at one end, far away from the porous material piece, of the heating device.
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, far away from the waterproof and breathable film, of the pressure reducing valve.
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, 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.
In order to achieve the above object, according to one aspect of the present application, there is provided an electric propulsion system including the above liquid propellant supply assembly for electric propulsion.
The technical scheme of the invention has the following advantages:
the invention provides a liquid propellant supply assembly for electric propulsion, comprising: the liquid propellant enters the heating device from the pipeline and is heated and gasified by the heating device, the porous material piece realizes the functions of liquid absorption and gas expelling based on the internal porous structure of the porous material piece, most of the 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 gas backflow can be prevented, the propellant utilization rate is improved, the waterproof breathable film has the functions of liquid blocking and gas permeation, the gas generated by the gasification can permeate and block the liquid from passing through, 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 the space waste liquid, the waste water and the liquid which can be used by the self-carried aircraft, and the micro-flow supply of the liquid propellant is realized, the device has the characteristics of high efficiency, high flexibility, wide application range and long service life.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, serve to provide a further understanding of the application and to enable other features, objects, and advantages of the application to be more apparent. The drawings and their description illustrate the embodiments of the invention and do not limit it. In the drawings:
FIG. 1 is a schematic diagram of a liquid propellant supply assembly for electric propulsion according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a heating device provided in an embodiment of the present invention.
Reference numerals:
1-pipeline; 2-a heating device; 21-a housing; 22-electric heating tubes; 231-liquid inlet; 232-liquid outlet; 24-a thermometer; 3-a piece of porous material; 4-waterproof breathable film; 5-a pressure reducing valve; 6-liquid filter; 7-a gas flow controller; 8-a first line purge control valve; 9-second line purge control valve.
Detailed Description
In order to make the technical solutions better understood by those skilled in the art, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only partial embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
It should be noted that the terms "first," "second," and the like in the description and claims of this application and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It should be understood that the data so used may be interchanged under appropriate circumstances such that embodiments of the application described herein may be used. 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 this application, the terms "upper", "lower", "left", "right", "front", "rear", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings. These terms are used primarily to better describe the present application and its embodiments, and are not used to limit the indicated devices, elements or components to a particular orientation or to be constructed and operated in a particular orientation.
Moreover, some of the above terms may be used to indicate other meanings besides the orientation or positional relationship, for example, the term "on" may also be used to indicate some kind of attachment or connection relationship 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," "disposed," "provided," "connected," and "sleeved" are to be construed broadly. For example, it may be a fixed connection, a removable connection, or a unitary construction; can 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 above terms in the present application can be understood by those of ordinary skill in the art as appropriate.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
As shown in fig. 1, the present application relates to a liquid propellant supply assembly for electric propulsion comprising: the pipeline 1 and set up in proper order on pipeline 1 and by heating device 2, porous material piece 3, waterproof ventilated membrane 4 and relief pressure valve 5 of pipeline 1 switch on.
The working principle of the liquid propellant supply assembly for electric propulsion is as follows: liquid propellant gets into heating device 2 by pipeline 1, by heating device 2 heating gasification, porous material spare 3 realizes the effect that the imbibition is driven gas based on its inside poroid structure, can adsorb most not by the liquid of gasification, the heat exchange has been increased, the gasification efficiency has been promoted, liquid gasification's continuation and stability have been guaranteed, and can prevent that gas is palirrhea, improve the propellant utilization ratio, waterproof ventilated membrane 4 plays the ventilative effect of liquid blocking, the gas that makes gasification production sees through and blocks liquid and pass through, make gas get into decompression valve 5 and supply the thruster through pipeline 1 discharge after decompressing.
The liquid propellant can use space waste liquid, waste water and available liquid of in-situ resources carried by the aircraft, micro-flow supply of the liquid propellant is realized, and the liquid propellant has the characteristics of high efficiency, high flexibility, wide application range and long service life.
The heating device 2 is a device which has a function of heating liquid propellant and gasifying the liquid propellant to generate gas, and can adopt a heating device in the prior art, for example, the heating device comprises a shell and an electric heating pipe arranged in the shell, the electric heating pipe can convert electric energy into heat energy, the liquid runs through the shell side, the heating and gasification of the liquid propellant in the shell are realized through the electric heating pipe, or the heating device comprises the shell and a pipeline in the shell, the liquid runs through the pipeline side, and the shell is internally provided with a heating medium which can heat and gasify the liquid propellant in the pipeline. In the scope of the claimed invention, as a preferred embodiment of the present invention, as shown in fig. 2, an efficient liquid heating device is provided, in which the heating device 2 includes a housing 21, and an electrothermal tube 22 and a spiral tube disposed in the housing 21, the spiral tube spirally winds the outer surface of the electrothermal tube 22, two ends of the spiral tube are respectively a liquid inlet 231 and a liquid outlet 232, and the liquid inlet 231 and the liquid outlet 232 are both communicated with the pipeline 1. The surface of the inner side of the shell 21 is a silicon carbide material layer, so that the heat insulation effect is good, and the heat loss can be reduced; the tubular body of the electric heating tube is made of pure aluminum, so that heat energy converted from electric energy can be quickly conducted to the spiral tube; the spiral pipe is spiral, and the helical structure has prolonged the length and the heated area of pipeline, makes electrothermal tube 22 fully contact with the liquid propellant in the spiral pipe, and it is even to be heated, and 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 piece 3 is a component with the functions of absorbing liquid and expelling gas, the material of the porous material can be bronze, stainless steel, nickel or titanium, and preferably titanium-based porous material, so that the porous material piece has better mechanical property, corrosion resistance and air permeability. The aperture adopts the macropore (> 50nm), high porosity (> 60%), length 0.9 ~ 1.1mm, above-mentioned porous material piece 3 can be for the porous material post that suits with 1 bore of pipeline, the block is in the pipeline, or in inserting pipeline 1 through other tubular joints, all can be with its connected mode of setting in the pipeline all in the scope that this application claims protection. The function of the piece of cellular material 3 in the assembly is as follows: the porous material blocks flow to prevent liquid from flowing into the subsequent part; the heat insulation effect is realized, so that the heat loss of the heating device 2 in the pipeline 1 is avoided, and the heating efficiency is improved; the heat exchange is increased by adsorbing the liquid, the gasification efficiency is improved, and the continuity and the stability of the liquid gasification are favorably maintained; and the unidirectional conductivity prevents gas from flowing backwards, and improves the utilization rate of the propellant.
The waterproof breathable film 4 is a member with waterproof and breathable functions, for example, the material thereof may be Polytetrafluoroethylene (PTFE) film material, and the use of a film assembly with waterproof and breathable functions is within the scope of the present application. The liquid is blocked by the waterproof gas-permeable membrane 4 and the gas permeate flows into the subsequent component. As a connection mode of the waterproof breathable film 4, the waterproof breathable film can be fixedly pressed by a group of annular gaskets and connected into the pipeline 1 through 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 the pressure of the gas generated by vaporizing the liquid propellant, and stably supplies the gas after reducing the pressure.
As a further refinement of this 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 far away from the porous material piece 3.
The liquid propellant passes through the filtering of liquid filter 6 filtering large granule impurity before heating, avoids causing the harm to follow-up pipeline and part/device, reduces the maintenance cost of whole subassembly, improves liquid propellant's supply efficiency. Preferably, the liquid filter 6 is made of stainless steel.
As a further refinement of this embodiment, the liquid propellant supply assembly for electric propulsion further comprises: and the gas flow controller 7 is arranged on the pipeline 1, and 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 rate controller 7 controls the supply amount of the gas, and the gas after pressure reduction is supplied to the propeller through the gas flow rate controller 7.
As a further refinement of this 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 which are arranged on the pipeline 1, wherein 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 optionally, a first line purge control valve 8 is located at the front end of the liquid filter 6. First pipeline washing control valve 8 and second pipeline washing control valve 9 are used for the pipeline clearance, but reverse washing liquid filter 6 and porous material piece 3 prevent to block up, have increased life. The working principle of the first and second line purge control valves 8 and 9 is as follows: closing all pipeline valves, firstly opening a second pipeline cleaning control valve 9, and introducing atomized acid aerosol into the pipeline; then, the first pipeline cleaning control valve 8 is opened to discharge the cleaning gas mist, so that the cleaning purpose is achieved, and the pipeline circulation is kept.
The working principle of the liquid propellant feed assembly for electric propulsion as shown in fig. 1 is as follows:
liquid propellant flows into heating device 2 after getting into 6 filtering large granule impurities of liquid filter by pipeline 1, heat gasification by heating device 2, porous material spare 3 realizes the effect that the imbibition is driven angry based on its inside cavernous structure, can adsorb most liquid that is not gasified, the heat exchange has been increased, the gasification efficiency has been promoted, the continuation and the stability of liquid gasification have been guaranteed, and can prevent that gas is palirrhea, improve the propellant utilization ratio, waterproof ventilated membrane 4 plays the ventilative effect of liquid blocking, make the gas that gasification produced permeate through and block liquid and pass through, make gas get into gas flow controller 7 after getting into pressure reducing valve 5 and reducing pressure, offer the propeller with the settlement flow through gas flow controller 7. After the machine is stopped, the first pipeline cleaning control valve 8 and the second pipeline cleaning control valve 9 can be used for cleaning the pipelines and reversely cleaning the liquid filter 6 and the porous material piece 3.
The application also provides an electric propulsion system, which comprises the liquid propellant supply assembly for electric propulsion and a thruster, wherein the thruster is connected with a pipeline at the rear end of the gas flow controller 7.
The above description is only a preferred embodiment of the present application and is not intended to limit the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.
Claims (9)
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| Application Number | Priority Date | Filing Date | Title |
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| 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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| 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 true CN111114835A (en) | 2020-05-08 |
| CN111114835B CN111114835B (en) | 2023-06-23 |
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