CN108533469B - Self-heating type working medium supply device for electric propeller and electric propeller - Google Patents
Self-heating type working medium supply device for electric propeller and electric propeller Download PDFInfo
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- CN108533469B CN108533469B CN201810193769.8A CN201810193769A CN108533469B CN 108533469 B CN108533469 B CN 108533469B CN 201810193769 A CN201810193769 A CN 201810193769A CN 108533469 B CN108533469 B CN 108533469B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0093—Electro-thermal plasma thrusters, i.e. thrusters heating the particles in a plasma
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0006—Details applicable to different types of plasma thrusters
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0006—Details applicable to different types of plasma thrusters
- F03H1/0031—Thermal management, heating or cooling parts of the thruster
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- Plasma Technology (AREA)
Abstract
The invention discloses a working medium supply device of a self-heating type electric propeller and an electric propeller, wherein the working medium supply device of the self-heating type electric propeller comprises a working medium storage tank, a flow valve, a first pipeline and a second pipeline; the vertical section of the working medium storage tank is of a groove shape, the flow valve, the first pipeline and the second pipeline are arranged in the groove, the air inlet of the flow valve is communicated with the inside of the working medium storage tank through the first pipeline, and the air outlet of the flow valve is communicated with a discharge cavity arranged in the groove through the second pipeline. The working medium supply device of the self-heating type electric propeller and the electric propeller provided by the invention have the advantages that the power consumption of the electric propeller is reduced, and the problem that steam is easy to condense locally is avoided.
Description
Technical Field
The invention relates to the technical field of aerospace electric propulsion, in particular to a working medium supply device of a self-heating electric propeller and an electric propeller.
Background
With the rapid development of the aerospace propulsion technology, the electric propulsion technology which utilizes the ions generated after the ionization of working medium gas or the jet of plasma to generate the reverse thrust gradually occupies a place in the application of the micro-nano satellite by the advantages of high specific impulse, convenient carrying, light weight and the like. The xenon working medium electric propulsion technology represented by ion propulsion and Hall propulsion is developed more mature, and the high-pressure gas propellant storage system adopted by the propulsion system has the problems of heavy dryness of the storage system, low xenon storage density, large storage tank volume and the like. Based on this, the propulsion technology of solid working media starts to develop, and the more mature solid working media propeller mainly comprises the polytetrafluoroethylene pulse plasma propulsion technology and the emission ion propulsion technology of working media such as indium and the like. At present, the specific impulse and efficiency of the polytetrafluoroethylene pulse plasma propulsion technology are low, the impulse of the transmitted ions is high, but the transmitter channel through which the metal ions pass is easy to block. Under such circumstances, electric propulsion technology to heat sublimable or vaporizable solid materials (e.g., iodine) has become a new research focus in recent years. The electric propeller generally adopts a hollow cathode or a radio frequency discharge mode to generate plasma, a high-pressure propellant storage tank is not needed, so that a plastic container is introduced to store solid working media, the dry weight of a storage system is greatly reduced, the electric propeller has the advantages of high storage density, low cost, strong adaptability and the like, and the service life of a satellite effective load and a satellite propulsion system is prolonged.
When the propeller works, the solid working medium needs to be heated when being sublimated or gasified. In the prior art, a working medium storage tank, a flow control system, a pipeline between the working medium storage tank and the flow control system, and a pipeline between the flow control system and a propeller are respectively wound with a heating belt for heating, and the heating mode has long heating circuit, so that the problems of high power consumption, easy local condensation of steam and the like exist.
Disclosure of Invention
The invention aims to solve the problems of high power consumption and easy local condensation of steam of a solid working medium for heating the electric propeller in the conventional mode.
The invention is realized by the following technical scheme:
a working medium supply device of a self-heating electric propeller comprises a working medium storage tank, a flow valve, a first pipeline and a second pipeline;
the vertical section of the working medium storage tank is of a groove shape, the flow valve, the first pipeline and the second pipeline are arranged in the groove, the air inlet of the flow valve is communicated with the inside of the working medium storage tank through the first pipeline, and the air outlet of the flow valve is communicated with a discharge cavity arranged in the groove through the second pipeline.
Optionally, the horizontal section of the sidewall of the working medium storage tank is circular or regular polygon.
Optionally, the side wall of the working medium storage tank is a heat-resistant plastic shell.
Optionally, the side wall of the groove is a heat-conducting insulating shell.
Optionally, the horizontal cross section of the side wall of the groove is a regular polygon.
Optionally, the working medium supply device of the self-heating electric propeller further comprises at least two automatic propelling structures which are arranged inside the working medium storage tank and uniformly distributed around the groove;
the automatic propelling structure comprises an elastic piece and a partition piece, one end of the elastic piece is fixed to the side face of the working medium storage tank, the other end of the elastic piece abuts against one side of the solid working medium, one end of the partition piece is fixed to the side face of the groove, and the other end of the partition piece abuts against the other side of the solid working medium.
Optionally, the elastic member, the partition member and the central point of the horizontal cross section of the side wall of the groove are located on the same horizontal straight line.
The invention also provides an electric propeller, which comprises a discharge cavity and the self-heating working medium supply device of the electric propeller;
the discharge cavity is arranged in the groove, and the bottom of the discharge cavity is communicated with the air outlet of the flow valve through the second pipeline.
Optionally, the discharge cavity is a hollow cathode discharge cavity, and the side wall of the discharge cavity is a heat conducting conductive shell.
Optionally, the side wall of the discharge cavity is an insulating shell, and a radio frequency antenna is wound on the outer surface of the side wall of the discharge cavity.
Compared with the prior art, the invention has the following advantages and beneficial effects:
the working medium supply device and the electric propeller provided by the invention have the advantages that the conventional heating device is omitted, the working medium storage tank with the vertical section in the shape of the groove is adopted, the flow valve, the pipeline for transporting steam and the discharge cavity are arranged in the groove, and the sublimation or gasification of the solid working medium is realized by utilizing the heat generated by the electrode of the discharge cavity, i.e. extra power is not required to be consumed, so that the power consumption of the electric propeller is greatly reduced, and the heat dissipation of the electric propeller is facilitated. In addition, the solid working medium, the flow control system and the pipeline are integrally heated by utilizing the heat generated by the discharge cavity electrode, and each part does not need to be independently heated, so that the problem that steam is easy to condense locally is avoided. Furthermore, the invention effectively utilizes the heat energy generated by the electric propeller, reduces the volume of the electric propeller, lightens the mass of the electric propeller and reduces the launching cost of the spacecraft on the premise of not changing the function of the electric propeller.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the principles of the invention. In the drawings:
FIG. 1 is a schematic structural view of a vertical section of an electric propulsion apparatus according to an embodiment of the present invention;
FIG. 2 is a schematic structural view of a horizontal section of an electric propulsion apparatus according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of another electrical thruster in vertical section according to an embodiment of the present invention;
FIG. 4 is a schematic structural view of a horizontal section of another electric thruster according to an embodiment of the present invention;
FIG. 5 is a schematic structural view in vertical section of yet another electric propulsion apparatus according to an embodiment of the present invention;
FIG. 6 is a schematic structural view of a horizontal section of another electric propulsion device according to an embodiment of the present invention;
FIG. 7 is a schematic structural view of a vertical section of another electric propulsion apparatus according to an embodiment of the present invention;
fig. 8 is a schematic structural view of a horizontal section of another electric propulsion device according to an embodiment of the present invention.
Reference numbers and corresponding part names in the drawings:
101-working medium storage tank, 102-solid working medium, 103-elastic member, 105-partition member, 106-flow valve, 107-first pipeline, 108-second pipeline, 201-discharge cavity, 202-radio frequency antenna.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to examples and accompanying drawings, and the exemplary embodiments and descriptions thereof are only used for explaining the present invention and are not meant to limit the present invention.
Example 1
The embodiment provides a working medium supply device of a self-heating type electric propeller and an electric propeller, wherein the electric propeller comprises the working medium supply device of the self-heating type electric propeller, and the working medium supply device of the self-heating type electric propeller is used for heating a solid working medium to sublimate or gasify the solid working medium so as to provide working medium gas for the electric propeller. Fig. 1 is a schematic structural view of a vertical section of an electric propeller of the present embodiment, and fig. 2 is a schematic structural view of a horizontal section of the electric propeller of the present embodiment, the electric propeller including a self-heating type electric propeller working medium supply device including a working medium storage tank 101, a flow valve 106, a first pipe 107, and a second pipe 108, and a discharge chamber 201.
Specifically, the working medium storage tank 101 is used for storing a solid working medium 102, and the vertical section of the working medium storage tank is groove-shaped. The solid working medium 102 may be solid iodine or other solid working mediums, which is not limited in this embodiment. Further, the horizontal section of the sidewall of the working medium storage tank 101 may be a circle or a regular polygon, and the sidewall of the working medium storage tank 101 may be a light heat-resistant plastic shell. The horizontal section of the groove side wall can be circular or regular polygon, and the groove side wall can be a heat-conducting insulating shell. In this embodiment, the horizontal cross section of the sidewall of the working medium storage tank 101 and the horizontal cross section of the sidewall of the groove are both regular quadrangles.
The flow valve 106 may be a proportional flow valve, and is configured to adjust the flow rate of the working medium gas entering the discharge cavity 201. The flow valve 106, the first pipeline 107, the second pipeline 108 and the discharge cavity 201 are arranged in the groove, an air inlet of the flow valve 106 is communicated with the inside of the working medium storage tank 101 through the first pipeline 107, and an air outlet of the flow valve 106 is communicated with the discharge cavity 201 through the second pipeline 108. The first conduit 107 may be connected to the bottom of the groove or to the side walls of the groove. In this embodiment, to ensure that the working medium gas entering the first pipe 107 is more uniform, the center line of the groove, the center line of the first pipe 107, the center line of the second pipe 108, and the center line of the discharge chamber 201 coincide.
The discharge cavity 201 is arranged in the groove, and the bottom of the discharge cavity is communicated with the air outlet of the flow valve 106 through the second pipeline 108. In this embodiment, the electric thruster ionizes the solid working medium in a hollow cathode discharge mode, the discharge cavity 201 is a hollow cathode discharge cavity, and the side wall of the discharge cavity is a corrosion-resistant heat conduction conductive shell. The hollow cathode discharge chamber is of a conventional structure and is not described in detail herein. Further, the side wall of the discharge cavity 201 is close to the side wall of the groove, and the distance between the two side walls can be set according to actual conditions, so long as it is ensured that the solid working medium 102 in the working medium storage tank 101 cannot be sublimated or gasified due to the fact that the distance is too large, wherein heat generated by the electrode of the discharge cavity 201 is avoided. In this embodiment, the distance between the sidewall of the discharge chamber 201 and the sidewall of the groove is not more than 2 mm.
When the electric thruster works, electric power is introduced to the electrode of the discharge cavity 201, heat generated by the electrode of the discharge cavity 201 penetrates through the side wall of the groove to enter the working medium storage tank 101, the solid working medium 102 is sublimated or gasified, generated working medium gas enters the discharge cavity 201 through the first pipeline 107, the flow valve 106 and the second pipeline 108, the discharge cavity 201 ionizes the working medium gas through hollow cathode discharge to generate plasma, and the plasma or the led-out ions are ejected out of the discharge cavity 201 to form thrust.
According to the working medium supply device of the self-heating type electric propeller and the electric propeller, the discharge cavity 201 and the working medium supply device of the self-heating type electric propeller are integrated, the vertical section of the working medium storage tank 101 is of a groove shape, the flow valve 106, the first pipeline 107, the second pipeline 108 and the discharge cavity 201 are arranged in the groove, and the sublimation or gasification of solid working medium is realized by utilizing heat generated by the electrodes of the discharge cavity 201 when the electric propeller works. Compared with the prior art, this embodiment has cancelled heating device, and need not to consume extra power, both can realize the sublimation or the gasification of solid-state working medium, and the heat that accessible working medium gasification or sublimation absorption electrode produced realizes again discharge chamber 201's heat dissipation has utilized the heat energy that electric propulsion ware self produced effectively under the prerequisite that does not change electric propulsion ware function, has reduced electric propulsion ware's consumption, has simplified electric propulsion ware's structure, has reduced electric propulsion ware's volume, has alleviateed electric propulsion ware's quality, has reduced spacecraft's emission cost simultaneously. In addition, the first pipeline 107, the flow valve 106 and the second pipeline 108 are all arranged in a hot environment, so that working medium gas flowing through the first pipeline 107, the flow valve 106 and the second pipeline 108 is guaranteed not to be condensed when cooled, and the problem that the pipeline is blocked due to the condensation of the working medium gas is avoided.
Example 2
Fig. 3 is a schematic structural view of a vertical section of the electric propeller of this embodiment, and fig. 4 is a schematic structural view of a horizontal section of the electric propeller of this embodiment. Compared with the electric propeller provided in embodiment 1, the difference is that: the electric propulsion device of the embodiment adopts a radio frequency antenna discharge form, that is, the side wall of the discharge cavity 201 is an insulating shell, and the radio frequency antenna 202 is wound outside the side wall of the discharge cavity 201. The side wall of the discharge cavity 201 may be an insulating casing made of quartz, ceramic, or the like, and the rf antenna 202 may be a metal antenna with good thermal and electrical conductivity. Further, the distance between the radio frequency antenna 202 and the groove side wall can be set according to actual conditions, so long as it is ensured that the solid working medium 102 in the working medium storage tank 101 cannot be sublimated or gasified due to heat generated by the radio frequency antenna 202 due to too large distance. In this embodiment, the distance between the rf antenna 202 and the sidewall of the groove is not greater than 2 mm.
When the propeller works, electric power is introduced to the radio frequency antenna 202, heat generated by the radio frequency antenna 202 penetrates through the side wall of the groove to enter the working medium storage tank 101, the solid working medium 102 is sublimated or gasified, generated working medium gas enters the discharge cavity 201 through the first pipeline 107, the flow valve 106 and the second pipeline 108, inductive coupling discharge through the radio frequency antenna 202 ionizes the working medium gas to generate plasma, and the plasma or the extracted ions are ejected out of the discharge cavity 201 to form thrust.
Example 3
Fig. 5 is a schematic structural view of a vertical section of the electric propeller of the present embodiment, and fig. 6 is a schematic structural view of a horizontal section of the electric propeller of the present embodiment. Compared with the self-heating type electric propeller working medium supply device provided by the embodiment 1, the self-heating type electric propeller working medium supply device is characterized in that: the horizontal section of the side wall of the groove is a regular polygon, and the working medium supply device of the self-heating electric propeller further comprises at least two automatic propelling structures which are arranged inside the working medium storage tank 101 and are uniformly distributed around the groove. The automatic propelling structure is used for automatically propelling the solid working medium 102 to be close to the discharge cavity 201, so that automatic feeding is realized, and the stability of working medium gas is ensured. In this embodiment, the horizontal cross section of the sidewall of the working medium storage tank 101 and the horizontal cross section of the sidewall of the groove are illustrated as a regular quadrangle.
Specifically, the automatic propelling structure comprises an elastic member 103 and a partition 105, one end of the elastic member 103 is fixed on the side surface of the working medium storage tank 101, the other end of the elastic member 103 abuts against one side of the solid working medium 102, one end of the partition 105 is fixed on the side surface of the groove, and the other end of the partition 105 abuts against the other side of the solid working medium 102, namely, the solid working medium 102 abuts against the partition 105 by the thrust exerted by the elastic member 103. The elastic member 103 is used for providing elastic thrust to the solid working medium 102, and may be a spring. The partition 105 is used for forming a gap between the solid working medium 102 and the side wall of the working medium storage tank 101, so that the sublimated or gasified working medium gas can flow into the first pipeline 107 through the gap. Further, the partition 105 may be a corrosion-resistant heat-conductive metal block, and the thickness of the partition in the horizontal direction may be set according to the flow rate of the working medium gas required by the electric propulsion device with different thrusts. In the present embodiment, the thickness of the separator 105 in the horizontal direction is 1 mm to 2 mm. Further, the center points of the horizontal cross sections of the elastic member 103, the partition 105 and the side wall of the groove may be located on the same horizontal straight line, so that the force applied by the elastic member 103 and the partition 105 to the solid working medium 102 is on the same horizontal plane.
When the device provided by the embodiment is adopted to provide working medium gas for the electric propeller, a large solid working medium is divided into a plurality of blocks to be stored in the working medium storage tank 101, and each solid working medium 102 abuts between the elastic part 103 and the separating part 105. The electrodes of the discharge cavity 201 continuously provide heat energy, the solid working medium 102 close to the discharge cavity 201 is firstly sublimated or gasified, along with the consumption of the solid working medium 102, the elastic part 103 enables the solid working medium 102 to be attached to the isolating part 105, the solid working medium 102 is automatically pushed to be close to the discharge cavity 201, the distance between the solid working medium 102 and the discharge cavity 201 is kept unchanged, automatic feeding is realized, and the stability of working medium gas is maintained.
Example 4
Fig. 7 is a schematic structural view of a vertical section of the electric propeller of this embodiment, and fig. 8 is a schematic structural view of a horizontal section of the electric propeller of this embodiment. Compared with the electric propeller provided in embodiment 3, the difference is that: the electric propulsion device of the embodiment adopts a radio frequency antenna discharge form, that is, the side wall of the discharge cavity 201 is an insulating shell, and the radio frequency antenna 202 is wound outside the side wall of the discharge cavity 201. The structure and operation principle of the discharge chamber 201 and the rf antenna 202 can be referred to the description of embodiment 2, and will not be explained in detail here.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are merely exemplary embodiments of the present invention, and are not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (8)
1. A self-heating type working medium supply device of an electric propeller is characterized by comprising a working medium storage tank (101), a flow valve (106), a first pipeline (107) and a second pipeline (108);
the vertical section of the working medium storage tank (101) is of a groove type, the flow valve (106), the first pipeline (107) and the second pipeline (108) are arranged in the groove, the air inlet of the flow valve (106) is communicated with the interior of the working medium storage tank (101) through the first pipeline (107), and the air outlet of the flow valve (106) is communicated with a discharge cavity (201) arranged in the groove through the second pipeline (108);
the horizontal section of the side wall of the groove is a regular polygon, and the working medium supply device of the self-heating electric propeller further comprises at least two automatic propelling structures which are arranged in the working medium storage tank (101) and are uniformly distributed around the groove;
the automatic propelling structure comprises an elastic piece (103) and a partition piece (105), one end of the elastic piece (103) is fixed to the side face of the working medium storage tank (101), the other end of the elastic piece (103) is abutted to one side of the solid working medium (102), one end of the partition piece (105) is fixed to the side face of the groove, and the other end of the partition piece (105) is abutted to the other side of the solid working medium (102).
2. A self-heating electric propeller working medium supply device according to claim 1, characterized in that the horizontal cross section of the working medium tank (101) side wall is circular or regular polygon.
3. The working medium supply device of the self-heating electric propeller as claimed in claim 1, wherein the side wall of the working medium storage tank (101) is a heat-resistant plastic shell.
4. A self-heating electric propeller working medium supply device according to claim 1, wherein the groove side wall is a heat-conductive insulating case.
5. A self-heating electric propeller working medium supply device according to claim 1, characterized in that the elastic member (103), the partition member (105) and the center point of the horizontal cross section of the recess side wall are located on the same horizontal straight line.
6. An electric propulsion device, characterized in that it comprises a discharge chamber (201) and a self-heating electric propulsion device working medium supply device according to any one of claims 1 to 5;
the discharge cavity (201) is arranged in the groove, and the bottom of the discharge cavity is communicated with an air outlet of the flow valve (106) through the second pipeline (108).
7. An electric propulsion device according to claim 6, characterised in that said discharge chamber (201) is a hollow cathode discharge chamber and the side walls of said discharge chamber (201) are a conductive shell.
8. An electric propulsion device according to claim 6, characterized in that the side wall of the discharge chamber (201) is an insulating shell, and the side wall of the discharge chamber (201) is externally wound with a radio frequency antenna (202).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810193769.8A CN108533469B (en) | 2018-03-09 | 2018-03-09 | Self-heating type working medium supply device for electric propeller and electric propeller |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810193769.8A CN108533469B (en) | 2018-03-09 | 2018-03-09 | Self-heating type working medium supply device for electric propeller and electric propeller |
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| CN108533469B true CN108533469B (en) | 2020-01-14 |
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| CN110374830A (en) * | 2019-07-15 | 2019-10-25 | 上海交通大学 | Storage tank is heated in heat radiation suitable for iodine working medium electric propulsion device |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5175996A (en) * | 1990-10-16 | 1993-01-05 | Olin Corporation | Apparatus for propellant flow control at low mass flow rates in zero G environment |
| DE4122755A1 (en) * | 1991-07-10 | 1993-01-21 | Erno Raumfahrttechnik Gmbh | ENGINE FOR SPACING BODIES |
| US6293090B1 (en) * | 1998-07-22 | 2001-09-25 | New England Space Works, Inc. | More efficient RF plasma electric thruster |
| US6336318B1 (en) * | 2000-02-02 | 2002-01-08 | Hughes Electronics Corporation | Ion thruster having a hollow cathode assembly with an encapsulated heater, and its fabrication |
| FR2959534B1 (en) * | 2010-04-29 | 2012-07-13 | Snecma | HALL EFFECT ENGINE WITH REGULATION OF THE TEMPERATURE OF THE CATHODE HEATING DEVICE |
| CN103696919A (en) * | 2013-12-26 | 2014-04-02 | 苏州市牛勿耳关电器科技有限公司 | Electrostatic propeller |
| CN107387348B (en) * | 2017-09-13 | 2019-07-02 | 哈尔滨工业大学 | A kind of a wide range of adjustable plasma microthruster using solid working medium |
| CN107605687B (en) * | 2017-09-28 | 2019-07-02 | 哈尔滨工业大学深圳研究生院 | Low-power electric arc heated propeller |
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