CN109630368A - High-power complementary field magnetomotive plasma thruster anode high efficient heat exchanging structure - Google Patents
High-power complementary field magnetomotive plasma thruster anode high efficient heat exchanging structure Download PDFInfo
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- CN109630368A CN109630368A CN201811448865.9A CN201811448865A CN109630368A CN 109630368 A CN109630368 A CN 109630368A CN 201811448865 A CN201811448865 A CN 201811448865A CN 109630368 A CN109630368 A CN 109630368A
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- Prior art keywords
- anode
- heat exchanging
- efficient heat
- exchanging structure
- step part
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Classifications
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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
-
- 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
- F03H1/0081—Electromagnetic plasma thrusters
Abstract
High-power complementary field magnetomotive plasma thruster anode high efficient heat exchanging structure, belongs to spacecraft electric propulsion field of power equipment technology.Anode high efficient heat exchanging structure of the invention, positioned inside are used to increase the deflector of coolant glide path and turbulivity；Anode inner wall be cylindrical body, and increase deflector building inner flow passage, anode water-cooled jacket be thin-wall circular pylon, by corner connection weld complete cooling duct outer side seal and with the cooperation of inner wall, finally constitute entire cooling cavities；The import and export pipeline is connect by welding with anode.The present invention realizes the sealing of anode interior cooling duct by the cooperation between anode inner wall, anode water-cooled jacket and deflector.This anode heat exchange structure design can be under high temperature and pressure, guarantee that the temperature of anode surface is lower, coolant heat-up is larger, reduces the size and complexity of whole thruster, it is easy to dismount, solves the problems, such as that traditional anode design size is larger and heat exchange efficiency is lower.
Description
Technical field
The present invention relates to a kind of high-power complementary field magnetomotive plasma thruster anode high efficient heat exchanging structures, especially suitable
For 50~100kW grades of complementary field magnetomotive plasma propellers, belong to spacecraft electric propulsion power device technology neck
Domain.
Background technique
With the demand of spacecraft application electric propulsion platform and deep space exploration task, China has carried out a variety of electric propulsion technologies
Research, and significant progress is achieved, but in view of the high-power space power system technology in China still in the development stage, the country is to big function
The research of rate MPDT is started late.
Most of power loss of MPD engine in anode, the thermal environment of anode is relatively severe and the structure type of anode and
Size directly determines the shape and size of thruster arc chamber, thus anode design have for thruster performance it is most important
Effect.Anode not yet mature products application record of the China suitable for high-power MPDT.One important spy of MPD work
Point is that electric arc generates ablation to cathode point and anode, and anode power sedimentation is the main performance limiting factor of MPD, 50%-
70% input power is lost in anode.For in, powerful MPD anode it is then even more serious by heat problem.By raised
On the electrode, the cooling row of radiation at this time is far smaller than power sedimentation to the heat of environment to power bring great power settlement action
The heat of generation, electrode temperature sharply increase, it might therefore and damage.Therefore the anode water cooling design of relatively high power MPD must not
It can lack.
Radiation-cooled structure is largely used for the anode construction of MPD thruster in the world, minority takes water-cooling pattern.
Stuttgart University, Germany thruster cools down anode by the way of multichannel water inlet, and test result is preferable.
The anode that existing electric thruster uses is difficult to the long-term operation under high voltage, high-heat environment, in MPD thruster
Reliability and service life are difficult to ensure under portion's electric discharge, heat radiation and the coupling of ion bombardment.Therefore, it develops suitable for high-power
The Novel anode high efficient heat exchanging structure of MPDT reduces anode surface temperature, is the growth requirement of current high-power MPDT.
Summary of the invention
Technical problem solved by the present invention is overcome the deficiencies in the prior art, the present invention provides a kind of high-power additional
Field magnetomotive plasma thruster anode high efficient heat exchanging structure, passes through anode inner wall, anode water-cooled jacket, deflector, cooling
The assemble welding of cavity and the import and export pipeline, it is ensured that anode reliably working at high temperature under high pressure, while by introducing deflector
Coolant flow channel is designed, the defect that traditional through type anode heat exchange structure heat exchange efficiency is low, size is big, the service life is short is compensated for.
The technical solution of the invention is as follows: high-power complementary field magnetomotive plasma thruster anode high efficient heat exchanging knot
Structure, including anode, anode water-cooled jacket, deflector and the import and export pipeline；The anode includes column part and step part, institute
Stating step part is the cone that the outwardly open diameter in column part one end is gradually increased；The anode water-cooled jacket is open circles
Cylinder is socketed on the outside of the step part, and the cooling cavities of sealing is collectively formed with the step part outside wall surface, disengaging
Mouth pipeline is connected to cooling cavities, is provided equipment with coolant and is collectively formed closed-loop path；The step part outside wall surface is fixed
It is connected with the deflector for guiding coolant to flow.
Further, the deflector includes plate sealing together and several notched plates, the sealing plate by cooling cavities every
Disconnected, one side is coolant inlet, and the other side is coolant outlet；The notched plate is placed in what coolant flow in cooling cavities passed through
On access, the notched plate is equipped with the notch at least flowed through for coolant.
Further, the notched plate presses notch side interlaced arrangement, and is circumferentially evenly arranged in outside the step part
Wall surface.
Further, the width of the deflector is the central axis relative to the step part into 3~5 ° of arc length.
Further, the step part outside wall surface is equipped with 1~2mm flat segments in the region cooperated with anode water-cooled jacket,
For being fixedly connected with anode water-cooled jacket.
Further, the anode water-cooled jacket is fixedly connected with the step part outside wall surface, and junction is corner connection weld seam,
Welding method is argon arc welding, electron-bombardment welding or soldering.
Further, the import and export pipeline is fixedly connected with the step part outside wall surface, and junction is plate angle weld seam,
Welding method is electron beam welding or soldering.
Further, the anode water-cooled jacket and the step part outside wall surface with a thickness of 3~5mm.
Further, the column part inner wall, step part outside wall surface and baffle surface are smooth, the cooling chamber
The flow velocity of body internal coolant is 0.5~2kg/s.
Further, the column part, step part, anode water-cooled jacket and the import and export pipeline are all made of of the same race
Material；The coolant is liquid nitrogen, liquid helium or deionized water.
The advantages of the present invention over the prior art are that:
(1) anode high efficient heat exchanging structure of the invention is designed using inner flow passage detour type, guarantees longer transfer path,
Have the preferable capacity of heat transmission, flow resistance is smaller, while guaranteeing that the thermal stress of deflector junction is lower, overall heat exchange effect compared with
It is high.
(2) anode high efficient heat exchanging structure of the invention cooperation is simple and reliable, and using the scheme of welded connecting, it is high to form high temperature resistant
The sealing cooling cavities of pressure, has versatile, applied widely feature, and market application prospect is boundless.
(3) anode heat exchange design of the invention is compact-sized, protects under the premise of guaranteeing reliability and the capacity of heat transmission
Lesser envelope size is held.
(4) anode high efficient heat exchanging structure welding process of the invention and high pressure resistant, inner wall and water-cooled jacket, inlet and outlet
The welding of pipeline and inner wall has fully considered the problems such as technique, structural strength, thermal stress, avoids leaking under high pressure.
(5) the anode high efficient heat exchanging structure of the invention material good using easy processing, thermal conductivity, under the high temperature conditions can be real
Existing high efficient heat exchanging.
Detailed description of the invention
Fig. 1 is cross-sectional view of the invention；
Fig. 2 is the left view of anode inner wall of the present invention；
Fig. 3 is the front view of anode inner wall of the present invention；
Fig. 4 is the left view of anode water-cooled jacket of the present invention.
Specific embodiment
High-power complementary field magnetomotive plasma thruster anode high efficient heat exchanging structure is mainly by anode 1, anode water cooling
Set 2, deflector 3, cooling cavities 4 and the import and export pipeline 5 form.Anode high efficient heat exchanging inside configuration is disposed for increasing cooling
The deflector 3 of agent glide path and turbulivity；Anode 1 is cylindrical body, and increases deflector 3 and construct inner flow passage, anode water-cooled jacket 2
For thin-wall circular pylon, welded by corner connection the outer side seal for completing cooling duct and with the cooperation of inner wall, finally constitute whole
A cooling cavities 4；The import and export pipeline 5 is connect by welding with anode.By between anode 1, anode water-cooled jacket 2 and deflector 3
Welded connecting, realize anode interior cooling duct sealing.
Explanation and specific embodiment with reference to the accompanying drawing, the invention will be further described.
As shown in Figure 1, a kind of high-power complementary field magnetomotive plasma thruster anode high efficient heat exchanging structure, feature
It is to include: anode 1, anode water-cooled jacket 2 and the import and export pipeline 5；
Anode 1 and anode water-cooled jacket 2 are realized by welding seals cooperation, and region between the two constitutes cooling cavities 4, into
Export pipeline 5 guarantees not let out in cooling cavities 4 by realizing coolant disengaging with the welding of the end face of 1 corresponding position of anode
Leak coolant；
Anode 1 is equipped with deflector 3, and the flowing of coolant is guided in cooling cavities 4；
The cooling cavities 4 constituted between coolant channel, with anode 1 and anode water-cooled jacket 2 is equipped in the import and export pipeline 5 to connect
It is logical, realize closed-loop path；
Thruster verifies the functional parameter of anode heat exchange structure when testing, and can meet inside cooling cavities and be passed through
Heat exchange structure weld is not revealed when flow rate is the deionized water of 2kg/s, pressure 4MPa, wall surface crack-free and deformation.It pushes away
When power device works, anode internal surface temperature reaches 500~600K, and anode heat exchange structure, which does not occur ablation, is split up, melt, etc. is heated
Concentration phenomenon, entrance temperature rise reach 10~20K.
To be illustrated that the solution of the present invention more, explanation and specific embodiment are made the present invention further with reference to the accompanying drawing
Description:
As shown in Figure 1, a kind of high-power complementary field magnetomotive plasma thruster anode high efficient heat exchanging structure, including sun
Pole 1, anode water-cooled jacket 2, deflector 3, cooling cavities 4 and the import and export pipeline 5.Anode 1 and anode water-cooled jacket 2 are real by welding
Now sealing cooperation, region between the two constitute cooling cavities 4, and the import and export pipeline 5 passes through the end face weld with 1 corresponding position of anode
It connects and realizes coolant disengaging, while guaranteeing not leak coolant in cooling cavities 4；Anode 1 is equipped with deflector 3, in cooling chamber
The flowing of guidance coolant in body 4；Structure between coolant channel, with anode 1 and anode water-cooled jacket 2 is equipped in the import and export pipeline 5
At cooling cavities 4 be connected to, realize closed-loop path.
Preferably, as shown in Figures 2 and 3, anode 1 is Special-Shaped Surface hollow cylinder, and one end of cylindrical body is equipped with convex
The ladder risen, boring region are high-temperature area, and temperature range is 500~700K.
Preferably, as shown in figure 4, anode water-cooled jacket 2 is hollow thin-wall rotary table, anode water-cooled jacket 2 and anode 1 are matched at both ends
The region of conjunction is equipped with 1~2mm flat segments, for being welded to connect.
It preferably, is fillet welding as shown in Figure 1, anode water-cooled jacket 2 and anode 1 in the welding position of two sides are a and b
Seam, is welded using argon arc welding, electron-bombardment welding and soldering.
It preferably, is pipeline and plate angle weld seam, pipe as shown in Figure 1, the welding position of the import and export pipeline 5 and anode 1 is c
Hole is only capable of close to outer wall using electron beam welding and soldering.
Preferably, as shown in Figure 1, anode water-cooled jacket 2 and 1 thinnest part thickness of anode are not less than 3mm, to guarantee integral solder
Resistance to pressure afterwards, maximum can bear internal pressure greater than 4MPa.
Preferably, as shown in Fig. 2, deflector 3 is designed as curved surface, the width of plate is 3~5 ° relative to center,
It is circumferentially uniformly distributed in cylindrical body simultaneously.
Preferably, as shown in Figure 1, anode 1 and deflector 3 thereon are without tip design, reduce flow resistance, in cooling cavities 4
Portion's coolant designs flow velocity is 0.5~2kg/s.
Preferably, as shown in Fig. 2, anode 1 offers the channel of the import and export pipeline 5, and about horizontal symmetrical at 20~40 °
It places.
Preferably, as shown in Figure 1, anode 1, anode water-cooled jacket 2 and the import and export pipeline 5 to be all made of thermal conductivity preferably same
Kind material, such as red copper.
Preferably, as shown in Figure 1, liquid nitrogen, liquid helium or deionized water can be used in anode coolant.
Anode high efficient heat exchanging structure of the invention is designed using inner flow passage detour type, guarantees longer transfer path, is had
The standby preferable capacity of heat transmission, flow resistance is smaller, while guaranteeing that the thermal stress of 3 junction of deflector is lower, and overall heat exchange effect is higher,
The anode high efficient heat exchanging structure of the invention material good using easy processing, thermal conductivity, can realize high efficient heat exchanging under the high temperature conditions.
Anode heat exchange design of the invention is compact-sized, maintains under the premise of guaranteeing reliability and the capacity of heat transmission
Lesser envelope size, anode high efficient heat exchanging structure cooperation of the invention is simple and reliable, using the scheme of welded connecting, forms resistance to height
The sealing cooling cavities of warm high pressure, has versatile, applied widely feature, and market application prospect is boundless.
Anode high efficient heat exchanging structure welding process of the invention and high pressure resistant, inner wall and water-cooled jacket, inlet/outlet pipe
The welding of road and inner wall has fully considered the problems such as technique, structural strength, thermal stress, avoids leaking under high pressure.
The content that description in the present invention is not described in detail belongs to the well-known technique of those skilled in the art.
Claims (10)
1. high-power complementary field magnetomotive plasma thruster anode high efficient heat exchanging structure, it is characterised in that: including anode
(1), anode water-cooled jacket (2), deflector (3) and the import and export pipeline (5)；The anode (1) includes column part and stage portion
Point, the step part is the cone that the outwardly open diameter in column part one end is gradually increased；The anode water-cooled jacket (2)
It for hollow cylinder, is socketed on the outside of the step part, and collectively forms the cooling of sealing with the step part outside wall surface
Cavity (4), the import and export pipeline (5) are connected to cooling cavities (4), are provided equipment with coolant and are collectively formed closed-loop path；It is described
Step part outside wall surface is fixedly connected with the deflector (3) for guiding coolant to flow.
2. high-power complementary field magnetomotive plasma thruster anode high efficient heat exchanging structure according to claim 1,
Be characterized in that: the deflector (3) includes plate sealing together and several notched plates, and the sealing plate separates cooling cavities (4),
One side is coolant inlet, and the other side is coolant outlet；The notched plate is placed in the interior coolant flow warp of cooling cavities (4)
On access, the notched plate is equipped with the notch at least flowed through for coolant.
3. high-power complementary field magnetomotive plasma thruster anode high efficient heat exchanging structure according to claim 2,
Be characterized in that: the notched plate is circumferentially evenly arranged in the step part outside wall surface by notch side interlaced arrangement.
4. high-power complementary field magnetomotive plasma thruster anode high efficient heat exchanging structure according to claim 3,
Be characterized in that: the width of the deflector (3) is the central axis relative to the step part into 3~5 ° of arc length.
5. high-power complementary field magnetomotive plasma thruster anode high efficient heat exchanging structure according to claim 1,
Be characterized in that: the step part outside wall surface the region cooperated with anode water-cooled jacket (2) be equipped with 1~2mm flat segments, for
Anode water-cooled jacket (2) are fixedly connected.
6. high-power complementary field magnetomotive plasma thruster anode high efficient heat exchanging structure according to claim 1,
Be characterized in that: the anode water-cooled jacket (2) is fixedly connected with the step part outside wall surface, and junction is corner connection weld seam, welding
Method is argon arc welding, electron-bombardment welding or soldering.
7. high-power complementary field magnetomotive plasma thruster anode high efficient heat exchanging structure according to claim 1,
Be characterized in that: the import and export pipeline (5) is fixedly connected with the step part outside wall surface, and junction is plate angle weld seam, welding
Method is electron beam welding or soldering.
8. high-power complementary field magnetomotive plasma thruster anode high efficient heat exchanging structure according to claim 1,
Be characterized in that: the anode water-cooled jacket (2) and the step part outside wall surface with a thickness of 3~5mm.
9. high-power complementary field magnetomotive plasma thruster anode high efficient heat exchanging structure according to claim 1,
It is characterized in that: the column part inner wall, step part outside wall surface and deflector (3) smooth surface, the cooling cavities (4)
The flow velocity of internal coolant is 0.5~2kg/s.
10. high-power complementary field magnetomotive plasma thruster anode high efficient heat exchanging structure according to claim 1,
Be characterized in that: the column part, step part, anode water-cooled jacket (2) and the import and export pipeline (5) are all made of material of the same race
Material；The coolant is liquid nitrogen, liquid helium or deionized water.
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| CN201811448865.9A CN109630368A (en) | 2018-11-28 | 2018-11-28 | High-power complementary field magnetomotive plasma thruster anode high efficient heat exchanging structure |
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| CN201811448865.9A CN109630368A (en) | 2018-11-28 | 2018-11-28 | High-power complementary field magnetomotive plasma thruster anode high efficient heat exchanging structure |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110360073A (en) * | 2019-07-19 | 2019-10-22 | 北京航空航天大学 | A kind of electric thruster anode gas distribution device |
| CN111022275A (en) * | 2019-12-23 | 2020-04-17 | 北京航空航天大学 | Anode structure of magnetic plasma thruster and magnetic plasma thruster |
| CN111779645A (en) * | 2020-05-26 | 2020-10-16 | 北京控制工程研究所 | Cathode spiral heat exchange structure of high-power additional field magnetomotive plasma thruster |
| CN114017275A (en) * | 2021-11-29 | 2022-02-08 | 中国科学院合肥物质科学研究院 | Superconducting magnetic plasma propeller heat pipe cooling structure |
| CN115217732A (en) * | 2022-07-29 | 2022-10-21 | 兰州空间技术物理研究所 | Heat dissipation device of high-power Hall thruster |
| CN115217732B (en) * | 2022-07-29 | 2024-05-10 | 兰州空间技术物理研究所 | High-power Hall thruster heat dissipation device |
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| US20080134663A1 (en) * | 2005-03-02 | 2008-06-12 | Tsuyoshi Totani | Heat Transfer Thruster |
| CN101777391A (en) * | 2009-12-31 | 2010-07-14 | 中国科学院等离子体物理研究所 | Faraday shield helium cooling pipe structure |
| CN107218187A (en) * | 2017-06-12 | 2017-09-29 | 北京航空航天大学 | A kind of anode water-cooling structure of magnetic plasma propeller |
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2018
- 2018-11-28 CN CN201811448865.9A patent/CN109630368A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080134663A1 (en) * | 2005-03-02 | 2008-06-12 | Tsuyoshi Totani | Heat Transfer Thruster |
| CN101777391A (en) * | 2009-12-31 | 2010-07-14 | 中国科学院等离子体物理研究所 | Faraday shield helium cooling pipe structure |
| CN107218187A (en) * | 2017-06-12 | 2017-09-29 | 北京航空航天大学 | A kind of anode water-cooling structure of magnetic plasma propeller |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110360073A (en) * | 2019-07-19 | 2019-10-22 | 北京航空航天大学 | A kind of electric thruster anode gas distribution device |
| CN111022275A (en) * | 2019-12-23 | 2020-04-17 | 北京航空航天大学 | Anode structure of magnetic plasma thruster and magnetic plasma thruster |
| CN111779645A (en) * | 2020-05-26 | 2020-10-16 | 北京控制工程研究所 | Cathode spiral heat exchange structure of high-power additional field magnetomotive plasma thruster |
| CN114017275A (en) * | 2021-11-29 | 2022-02-08 | 中国科学院合肥物质科学研究院 | Superconducting magnetic plasma propeller heat pipe cooling structure |
| US11781535B2 (en) | 2021-11-29 | 2023-10-10 | Hefei Institutes Of Physical Science, Chinese Academy Of Sciences | Cooling structure of heat pipe for superconducting magneto plasma dynamic thruster |
| CN115217732A (en) * | 2022-07-29 | 2022-10-21 | 兰州空间技术物理研究所 | Heat dissipation device of high-power Hall thruster |
| CN115217732B (en) * | 2022-07-29 | 2024-05-10 | 兰州空间技术物理研究所 | High-power Hall thruster heat dissipation device |
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