CN112761917B - Multi-ring Hall thruster magnetic circuit thermal protection device - Google Patents
Multi-ring Hall thruster magnetic circuit thermal protection device Download PDFInfo
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- CN112761917B CN112761917B CN202110197226.5A CN202110197226A CN112761917B CN 112761917 B CN112761917 B CN 112761917B CN 202110197226 A CN202110197226 A CN 202110197226A CN 112761917 B CN112761917 B CN 112761917B
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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
- F03H1/0081—Electromagnetic plasma thrusters
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Abstract
The utility model provides a many ring hall thrustor magnetic circuit heat protector, contains cylindric negative pole heat shield and N annular discharge passage heat shield by making of low emission material, and cylindric negative pole heat shield and N annular discharge passage heat shield are arranged from inside to outside with one heart, and cylindric negative pole heat shield links to each other with the annular discharge passage heat shield of inlayer, and two adjacent annular discharge passage heat shields are connected as an organic wholely, and every annular discharge passage heat shield is open-top, and the dicyclo structure that the bottom links to each other. The magnetic circuit temperature of the multi-ring Hall thruster can be effectively reduced, and the reliability and the stability are further improved.
Description
Technical Field
The invention relates to a thermal protection device, in particular to a magnetic circuit thermal protection device of a multi-ring Hall thruster.
Background
With the rapid development of spacecraft power supply technology and the successful application of full electric propulsion satellites, the characteristics of high specific impulse, high efficiency, long service life and the like of electric propulsion compared with the traditional chemical propulsion are gradually highlighted. However, since its small thrust limits the applicable range of tasks, it is currently applied more to the position maintenance task of the satellite. At the present stage, the development of space stations and large satellite platforms in China and the future tasks of deep space exploration, lunar exploration engineering and the like all put forward the requirement of high thrust to a propulsion system, so that the Hall thruster inevitably develops towards the direction of high power and high thrust in the future. For a high-power hall thruster, in order to improve the capability of a magnetic field to restrain electrons, the volume of an internal non-through-flow part needs to be greatly increased. The effective flow area of the high-power Hall thruster is greatly reduced, the thrust density is low due to the hollow effect, and the application of the traditional Hall thruster in the field of high-power electric propulsion is greatly limited. Therefore, the concentric multi-ring nested Hall thruster is provided, the discharge channel of the concentric multi-ring nested Hall thruster consists of a plurality of coaxial rings, the hollow cathode is positioned on the central axis, the flow area of the Hall thruster is increased to the maximum extent, the volume and the weight are effectively reduced under the same power level, and the thrust density is increased. However, compared with the traditional single-ring hall thruster, the concentric multi-ring nested hall thruster has the defects of insufficient technical maturity, the problems of mutual interference, coupling and the like exist between a plurality of channels, particularly, the heat generation of a structural part between two adjacent channels is serious, and the heat dissipation environment is severe, so that a magnetic circuit structure between two channels is in a high-temperature radiation environment, the magnetic conductivity of the magnetic circuit structure is influenced by the overhigh temperature of the magnetic circuit structure, the normal discharge process of a magnetic field and the thruster in the channels is further influenced, and therefore a specific thermal protection structure is required to actively control the temperature of the magnetic circuit, and the temperature of the magnetic circuit structure is reduced, so that the reliability and the stability of the multi-ring hall thruster are improved.
Disclosure of Invention
The invention provides a magnetic circuit thermal protection device of a multi-ring Hall thruster, aiming at overcoming the defects of the prior art, and the magnetic circuit thermal protection device can effectively reduce the temperature of the magnetic circuit of the multi-ring Hall thruster, so that the reliability and the stability are improved.
The utility model provides a many ring hall thrustor magnetic circuit heat protector, contains cylindric negative pole heat shield and N annular discharge channel heat shield by making of low emission material, cylindric negative pole heat shield and N annular discharge channel heat shield from inside to outside arrange with one heart, cylindric negative pole heat shield links to each other with the annular discharge channel heat shield of inlayer, two adjacent annular discharge channel heat shields are connected as an organic wholely, every annular discharge channel heat shield is open-top, and the dicyclo structure that the bottom links to each other, wherein N is greater than or equal to 2, and is the integer.
Compared with the prior art, the invention has the beneficial effects that:
the thermal protection device adopts the technical idea that a high-temperature area and a low-temperature sensitive area (magnetic circuit structure) in the thruster are physically separated through an integrally formed low-emissivity material structure, so that the temperature of a high-temperature part is shielded and is not transmitted to the temperature sensitive part, and the purpose of protecting the magnetic circuit is achieved.
The magnetic circuit thermal protection structure of the multi-ring Hall thruster has an integrated structure, is simple to assemble, is made of low-emissivity materials, isolates a high-temperature component from a magnetic circuit structure in the working process of the Hall thruster, prevents the high-temperature component from transferring the temperature to the magnetic circuit structure, and can effectively reduce the temperature of the magnetic circuit, so that the reliability and the stability of the multi-ring Hall thruster are improved.
The technical scheme of the invention is further explained by combining the drawings and the embodiment:
drawings
Fig. 1 is a schematic perspective view of a magnetic circuit thermal protection device of a double-ring hall thruster;
FIG. 2 is a front view of a magnetic circuit thermal protection device of the double-ring Hall thruster;
FIG. 3 is a half sectional view of a magnetic circuit thermal protection device of the double-ring Hall thruster;
FIG. 4 is a schematic perspective view of another magnetic circuit thermal protection device of the double-ring Hall thruster;
FIG. 5 is a front view of another magnetic circuit thermal protection device of the double-ring Hall thruster;
FIG. 6 is a half sectional view of another magnetic circuit thermal protection device of the double-ring Hall thruster;
FIG. 7 shows a temperature simulation result of a magnetic path-free thermal protection structure of the double-ring Hall thruster;
FIG. 8 is a temperature simulation result of a magnetic circuit thermal protection device of a double-ring Hall thruster;
fig. 9 is a temperature simulation result of another double-ring hall thruster magnetic circuit thermal protection device.
Detailed Description
Referring to fig. 1 and 4, the multi-ring hall thruster magnetic circuit heat protection device according to the embodiment includes a cylindrical cathode heat shield 1 and N annular discharge channel heat shields 2, which are made of low emission materials, and are integrally arranged, the cylindrical cathode heat shield 1 and the N annular discharge channel heat shields 2 are concentrically arranged from inside to outside, the cylindrical cathode heat shield 1 is connected with the annular discharge channel heat shield 2 at the innermost layer, two adjacent annular discharge channel heat shields 2 are integrally connected, each annular discharge channel heat shield 2 is a double-ring structure with an open top and a connected bottom, where N is greater than or equal to 2 and is an integer.
The heat shield device which is integrally formed is adopted, so that the structure is simple and easy to realize. Gaps among structural components of the thruster are maximized, a heat shield is additionally arranged on the premise of not changing the size of a structural component of the thruster, the heat shield is made of low-emission materials, and the whole structure is light and good in reliability. Typically the low emissive material is a metallic titanium alloy material. The high-temperature radiation of the discharge channel is favorably shielded on the premise of fully utilizing the intermediate space between the magnetic screen and the ceramic channel in the thruster, so that the temperature of the magnetic circuit structure is effectively reduced.
The heat conduction structure leads heat flow to the outside of the thruster through the contact of the structural parts, an additional structural part with good heat conductivity is required to be assembled with the thruster, the required space is large, and the heat flow is blocked by adopting a material with low emissivity, namely the heat flow in the thruster is shielded to a structure which is not afraid of heat, so that temperature sensitive parts are protected, the required space is small, and the structure and the weight of the thruster are not influenced.
Furthermore, the thickness of the cylindrical cathode heat shield 1 and the thickness of the inner annular shield 2-1 and the outer annular shield 2-2 of the annular discharge channel heat shield 2 are both 0.3-0.7 mm. Preferably, the thickness is 0.5 mm. The surfaces of the cylindrical cathode screen 1 and the annular discharge channel heat screen 2 are polished to reduce the radiance, the appropriate thickness is favorable for heat dissipation, and the temperature of the magnetic circuit structure is reduced.
Based on the above, the cylindrical cathode heat shield 1 is connected with the annular discharge channel heat shield 2 of the innermost layer and the tops of the two adjacent annular discharge channel heat shields 2 through the connecting sheets 3 uniformly distributed in the circumferential direction. Through the connection of connection piece for magnetic circuit heat protector formula structure as an organic whole, simple structure can effectively reduce the magnetic circuit temperature again. Usually, the material of the connecting piece is a metal titanium alloy material.
As an embodiment, as shown in figures 1-3, the inner ring screen 2-1 and the outer ring screen 2-2 of the outmost ring-shaped discharge channel heat screen 2 have the same height, and the outer side surface of the outer ring screen is provided with connecting pieces 3 which are uniformly distributed in the circumferential direction. So arranged, the main reasons are the complete shielding of the high temperature components and the symmetry of the structure. In addition, considering that if all high-temperature components are shielded to a certain extent and are not beneficial to the overall heat dissipation of the thruster, and the saturation condition of the outermost ring magnetic circuit is not serious, the sensitivity to the temperature is low, in order to fully exert the low sensitivity of the outermost ring magnetic circuit structure to the temperature and increase the heat dissipation area and improve the overall heat dissipation capacity of the multi-ring hall thruster, a second implementation scheme is provided, as shown in fig. 4-6, the height of an outer ring screen 2-2 of the outermost ring discharge channel heat screen is reduced and the arrangement of an outermost ring connecting sheet 3 is omitted on the basis of the first implementation mode, so that the high temperature on the wall surface of the outermost ring discharge channel can be dissipated through the outermost ring magnetic circuit structure with low temperature sensitivity, and the increase of the overall heat dissipation capacity of the multi-ring hall thruster is facilitated.
Each annular discharge channel heat shield 2 is a double-ring groove with a closed bottom. Therefore, the double functions of the U-shaped annular groove, the groove bottom and the connecting sheet can be formed, so that the effective heat dissipation and the assembly of parts such as the anode are ensured, and the integrated manufacture of the magnetic circuit heat protection device is also ensured.
In general, the bottom of each double-ring groove is provided with a mounting hole 2-3 for mounting an anode structure, and the shape can be circular. The top of the heat shield is connected with the adjacent heat shields into a whole through four connecting pieces 3 which are uniformly distributed in the circumferential direction, the lower surface of each connecting piece 3 is flush with the end surface of each magnetic pole, a connecting and mounting hole 2-4 is formed in the middle of each connecting piece, and the magnetic circuit heat protection device can be fixed on the thruster through bolts.
In another embodiment, as shown in fig. 4-6, the outer annular shield 2-2 of the outermost annular discharge channel heat shield 2 has a height less than the height of the inner annular shield 2-1. In consideration of the fact that the heat dissipation capacity of the multi-ring Hall thruster structural member is increased and the saturation condition of the outermost ring magnetic circuit is not serious, the advantages of large volume and large heat dissipation area of the outermost ring magnetic circuit structure are fully exerted, the outer ring screen of the outermost ring-shaped discharge channel heat screen is shortened to the bottom of the discharge channel, and meanwhile, the arrangement of connecting pieces is cancelled, as shown in figures 4 and 5. The design of the height of the outer ring screen mainly considers the position of the magnetic circuit structure where magnetic saturation easily occurs, and the outer ring screen can completely wrap the position sensitive to temperature in the outer ring magnetic circuit structure.
Based on above-mentioned dicyclo hall thruster magnetic circuit heat protector, the degree of depth of each annular discharge passage heat shield 2 is along with the shape setting according to the size of concrete hall thruster discharge passage, guarantees that certain clearance is left with the discharge passage bottom surface to the bottom surface of heat shield groove, and this magnetic circuit heat protector only contacts with other structures of hall thruster in the position of top connection piece 3 in the assembling process, and this magnetic circuit heat protector does not do the load spare.
As shown in fig. 3 and 6, the top of each annular discharge channel heat shield 2 is of a stepped structure and is matched with the magnetic structure of the thruster, the diameter and the diameter-changing position are matched with the size of the magnetic structure of the thruster and a certain gap is reserved, and the diameters of the inner and outer annular shields of each annular discharge channel heat shield 2 are matched with the inner and outer diameters of the discharge channel of the thruster and an assembly gap is reserved. Due to the arrangement, the thermal protection device cannot interfere with parts of the thruster in the assembling process, and a gap of at least 0.5mm is reserved, so that sufficient margin is reserved for thermal deformation of materials.
As shown in fig. 7 to 9, taking the double-ring hall thruster as an example, thermal simulation analysis is performed through ANSYS, and compared with the temperature of the magnetic circuit structure of the double-ring hall thruster with the non-magnetic circuit thermal protection device under the same power and the same thermal load setting, the temperature simulation results of the magnetic circuit structures under the three structures are shown in fig. 7 to 9. As shown in fig. 7, the temperature of the magnetic circuit structure of the double-ring hall thruster without the thermal protection structure is 324.51 ℃ -477.4 ℃, and the temperature of the magnetic circuit structure of the double-ring hall thruster adopting the first thermal protection device is 308.7 ℃ -415.39 ℃, as shown in fig. 8; the temperature of the magnetic circuit structure of the double-ring Hall thruster adopting the second thermal protection device is 290.56-453.29 ℃, but the position with the highest magnetic circuit temperature is arranged on the magnetic screen of the outermost ring which is not wrapped by the thermal protection position of the magnetic circuit, the magnetic saturation condition of the position is not serious, so the double-ring Hall thruster is not sensitive to the temperature, the magnetic saturation easily occurs between the inner ring and the two channels, and the temperature of the position which is sensitive to the temperature is only 427.19 ℃ at the highest, the temperature of the magnetic circuit is slightly higher compared with the temperature of the structural magnetic circuit of the first thermal protection device, and the temperature of the magnetic circuit of the double-ring Hall thruster is reduced by 50 ℃ by comparison with the temperature of the magnetic circuit of the double-ring Hall thruster without the thermal protection device, so that the temperature of the magnetic circuit structure of the multi-ring Hall thruster can be greatly reduced, the possibility of thermal failure of the magnetic circuit structure is reduced, and the reliability of the thruster is improved.
The present invention is not limited to the above embodiments, and those skilled in the art can make various changes and modifications without departing from the scope of the invention.
Claims (9)
1. The utility model provides a hot protector of multi-ring hall thruster magnetic circuit which characterized in that: the heat shield comprises a cylindrical cathode heat shield (1) and N annular discharge channel heat shields (2) which are made of low-emission materials, wherein the cylindrical cathode heat shield (1) and the N annular discharge channel heat shields (2) are concentrically arranged from inside to outside, the cylindrical cathode heat shield (1) is connected with the annular discharge channel heat shield (2) at the innermost layer, two adjacent annular discharge channel heat shields (2) are connected into a whole, each annular discharge channel heat shield (2) is of a top opening and a double-ring structure with the bottom connected, N is more than or equal to 2 and is an integer, the diameters of the inner ring shield and the outer ring shield of each annular discharge channel heat shield (2) are matched with the inner diameter and the outer diameter of a thruster discharge channel, and an assembly gap is reserved.
2. The magnetic circuit heat protection device of the multi-ring Hall thruster according to claim 1, wherein the cylindrical cathode heat shield (1) is connected with the annular discharge channel heat shield (2) at the innermost layer and the tops of two adjacent annular discharge channel heat shields (2) through connecting pieces (3) which are uniformly distributed in the circumferential direction.
3. The magnetic circuit thermal protection device of the multi-ring Hall thruster of claim 2, wherein: the inner ring screen (2-1) and the outer ring screen (2-2) of the annular discharge channel heat screen (2) on the outermost layer are the same in height, and connecting pieces (3) are uniformly distributed in the circumferential direction on the outer side surface of the outer ring screen.
4. The magnetic circuit thermal protection device of the multi-ring Hall thruster of claim 3, wherein: each annular discharge channel heat shield (2) is a double-ring groove with a closed bottom.
5. The magnetic circuit thermal protection device of the multi-ring Hall thruster of claim 4, wherein: the top of each annular discharge channel heat shield (2) is of a step structure and is matched with the magnetic circuit structure of the thruster.
6. The magnetic circuit thermal protection device of the multi-ring Hall thruster of claim 2, wherein: the height of the outer annular shield (2-2) of the annular discharge channel heat shield (2) at the outermost layer is lower than that of the inner annular shield (2-1).
7. The magnetic circuit heat protection device of the multi-ring Hall thruster of claim 3 or 6, wherein: the low-emission material is a metal titanium alloy material, and the connecting piece is made of the metal titanium alloy material.
8. The magnetic circuit thermal protection device of the multi-ring Hall thruster of claim 7, wherein: the thickness of the cylindrical cathode heat shield (1) and the thickness of the inner ring shield (2-1) and the outer ring shield (2-2) of the annular discharge channel heat shield (2) are both 0.3-0.7 mm.
9. The magnetic circuit thermal protection device of the multi-ring Hall thruster of claim 4, wherein: and the bottom of each double-ring groove is provided with a mounting hole (2-3) for mounting an anode structure.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110197226.5A CN112761917B (en) | 2021-02-22 | 2021-02-22 | Multi-ring Hall thruster magnetic circuit thermal protection device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110197226.5A CN112761917B (en) | 2021-02-22 | 2021-02-22 | Multi-ring Hall thruster magnetic circuit thermal protection device |
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| CN112761917A CN112761917A (en) | 2021-05-07 |
| CN112761917B true CN112761917B (en) | 2021-09-03 |
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| US8143788B2 (en) * | 2007-08-31 | 2012-03-27 | California Institute Of Technology | Compact high current rare-earth emitter hollow cathode for hall effect thrusters |
| CN105609395B (en) * | 2015-12-28 | 2019-02-01 | 哈尔滨工业大学 | A kind of novel hollow cathode |
| CN109209804B (en) * | 2018-10-23 | 2019-12-03 | 哈尔滨工业大学 | A kind of magnetic cup of hall thruster/discharge channel integral structure |
| CN109667739A (en) * | 2018-12-10 | 2019-04-23 | 兰州空间技术物理研究所 | A kind of RF assistance discharge-type is efficiently cold-started hollow cathode |
| CN111622912B (en) * | 2020-05-22 | 2021-09-28 | 哈尔滨工业大学 | Magnetic circuit design method for adjusting magnetic interface morphology of magnetic conductive column Hall thruster |
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