CN116146443B - Low-pressure discharge breakdown suppression assembly of high-power Hall thruster - Google Patents
Low-pressure discharge breakdown suppression assembly of high-power Hall thruster Download PDFInfo
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- CN116146443B CN116146443B CN202211533337.XA CN202211533337A CN116146443B CN 116146443 B CN116146443 B CN 116146443B CN 202211533337 A CN202211533337 A CN 202211533337A CN 116146443 B CN116146443 B CN 116146443B
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- 230000015556 catabolic process Effects 0.000 title claims abstract description 24
- 230000001629 suppression Effects 0.000 title claims abstract description 14
- 239000000919 ceramic Substances 0.000 claims abstract description 38
- 239000002184 metal Substances 0.000 claims description 15
- 239000000835 fiber Substances 0.000 claims description 13
- 238000004804 winding Methods 0.000 claims description 3
- 230000000149 penetrating effect Effects 0.000 claims description 2
- 238000007789 sealing Methods 0.000 claims description 2
- 238000000605 extraction Methods 0.000 claims 2
- 230000002093 peripheral effect Effects 0.000 claims 1
- 238000002955 isolation Methods 0.000 abstract description 14
- 230000005764 inhibitory process Effects 0.000 abstract description 4
- 230000007613 environmental effect Effects 0.000 abstract description 3
- 238000009413 insulation Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 230000005389 magnetism Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000005507 spraying Methods 0.000 description 2
- 238000009423 ventilation Methods 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 229910052909 inorganic silicate Inorganic materials 0.000 description 1
- 150000002500 ions Chemical class 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
Classifications
-
- 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
The invention discloses a low-pressure discharge breakdown suppression component of a high-power Hall thruster, which comprises a bottom plate, wherein an inner magnetic core is arranged in the middle of the upper surface of the bottom plate, an inner coil is wound on the outer wall of the inner magnetic core, an upper pole shoe is arranged at the top of the inner magnetic core and the inner coil, an outer coil is arranged at the outer side of the bottom plate, an outer pole shoe is arranged at the outer side of the outer coil and the top of the outer pole shoe, a discharge channel with an annular groove structure is arranged between the inner coil and the outer coil, a spoke-structure magnetic screen is arranged in the discharge channel, the spoke-structure magnetic screen comprises an outer magnetic screen ring, an inner magnetic screen ring arranged on the inner ring of the outer magnetic screen ring, and a plurality of spoke handles for radially connecting and fixing the outer magnetic screen ring and the inner magnetic screen ring, an inner isolation ceramic ring is coaxially sleeved outside the inner magnetic screen ring above the spoke handle, and an outer isolation ceramic ring is coaxially nested in the inner ring of the outer magnetic screen ring above the spoke handle. The invention can effectively avoid the risk of low-pressure discharge of the Hall thruster, and simultaneously realize the inhibition of the influence of environmental plasma, so that the low-pressure discharge breakdown is inhibited.
Description
Technical Field
The invention relates to the technical field of spacecraft propulsion, in particular to a low-pressure discharge breakdown suppression component of a high-power Hall thruster.
Background
The high-power Hall electric propulsion has the advantages of high thrust ratio, high specific impulse, long service life and the like, is an indispensable power technology for large space tasks in the future, and is highly valued for vigorous development in aerospace countries such as Mei Ruo and the like. Compared with an ion thruster (30 mN/kW), a magnetic plasma power propulsion (10 mN/kW), a variable-ratio magnetic plasma propulsion (25 mN/kW) and other electric thrusters, the Hall thruster has the highest pushing power ratio, reaches 45-66mN/kW, and is the first choice for meeting future tasks.
The high-power Hall thruster has larger size, the size of 50kW exceeds 0.5m, the ceramic discharge chamber is difficult to realize engineering integrated ceramic discharge chambers such as a middle-power Hall thruster due to the severe requirements of process technology and a forced heat environment, therefore, a sectional ceramic discharge chamber is usually adopted, the discharge chamber does not wrap an anode, directly falls on the anode and is fixed through a compression ring, a large-size metal ceramic composite discharge chamber is formed, so that a plurality of gaps are formed, the gaps become larger under the action of a power heat load of tens of kilowatts, a gas leakage potential path is formed, and a local low-pressure environment is formed, so that the gas potential path (gas leakage) is formed.
Meanwhile, because of the large size of the thruster, a larger current and a larger number of turns of exciting coil are required to obtain the magnetic field strength required by the stable discharge of the discharge chamber, and the larger current requires thicker exciting wire to be able to withstand high current. This results in high power hall thrusters having very high mass and volume, and these excitation wires contain a large amount of adhesive which can outgas in a vacuum environment, further contributing to the formation of localized low air pressure. So that the solution is needed.
Disclosure of Invention
Therefore, the invention aims to solve the technical problems, and provides a low-pressure discharge breakdown suppression component of a high-power Hall thruster.
The technical scheme of the invention is as follows: a high power hall thruster low pressure discharge breakdown suppression assembly comprising: the bottom plate, the middle part sets up interior magnetic core above the bottom plate, the winding inner coil on the inner magnetic core outer wall, interior magnetic core, inner coil top set up the pole shoe, the bottom plate outside sets up outer coil, outer pole shoe top set up outer magnetic pole, be equipped with the discharge channel of annular groove structure between inner coil and the outer coil, set up spoke structure magnetism screen in the discharge channel, spoke structure magnetism screen includes outer magnetic screen ring, sets up the interior magnetic screen ring and a plurality of will of outer magnetic screen ring and the radial fixed spoke handle of being connected of interior magnetic screen ring and interior magnetic screen ring, spoke handle top the interior magnetic screen ring outside establishes the inner isolation ceramic ring with the axle sleeve, the coaxial nested outer isolation ceramic ring of outer magnetic screen ring inner circle of spoke handle top, inner isolation ceramic ring, outer isolation ceramic ring top set up annular ceramic fiber paper, set up the anode assembly above the ceramic fiber paper, the bottom plate bottom surface sets up the thrust ware shell, thrust ware top the thrust ware shell sets up the thrust ware shell, thrust ware end and the fixed metallic mesh is passed through the thrust collar, the thrust ware is set up around the fixed air compressor is in the axial pressure plate.
In the above technical scheme, every spoke handle middle part all sets up countersunk head through-hole up along the axis direction, every countersunk head through-hole top is just right set up the through-hole on the ceramic fiber paper, and the bolt passes from bottom to top in proper order countersunk head through-hole, through-hole back with the screw hole threaded connection that the corresponding position of anode assembly bottom was seted up is fixed.
In the technical scheme, the anode component is sprayed with insulating ceramics towards the magnetic screen side of the spoke structure.
In the technical scheme, the spoke handle is a long slat.
In the technical scheme, the edge of the outer ring of the upper pole shoe is provided with a plurality of axial exhaust holes I along the circumferential direction; the outer pole shoe is provided with a plurality of radial exhaust holes II along the circumferential direction.
According to the technical scheme, the bottom plate is provided with the annular groove along the circumferential direction, the bottom of the annular groove is provided with the annular through hole along the circumferential direction, the discharge channel is communicated with the bottom of the bottom plate through the annular groove and the annular through hole, the lower end of the outer magnetic screen ring is axially inserted into the annular groove and is nested into the outer ring of the annular groove to be fixed, and the lower end of the inner magnetic screen ring is axially inserted into the annular groove and is nested into the inner ring of the annular groove to be fixed.
In the above technical scheme, the outer edge of the outer magnetic screen ring and the inner edge of the inner magnetic screen ring are provided with a plurality of through ventilation holes along the circumferential direction.
The technical scheme of the invention has the following advantages:
(1) According to the invention, by arranging the ceramic fiber paper, the leakage path from the leakage to the tail part of the thruster is blocked, so that the ceramic part of the discrete discharge chamber can be realized;
(2) The exhaust hole is arranged, so that the influence of air outlet is weakened, and the hidden trouble caused by low air pressure is avoided;
(3) According to the invention, through the design of the multi-layer isolation net, the risk of existence of low air pressure at the tail part is reduced, the air discharge is promoted, and the risk of low air pressure is reduced;
(4) According to the invention, the anode component faces the magnetic screen side of the spoke structure for ceramic spraying, so that the insulativity is enhanced, and the inhibition of spark breakdown is further improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic cross-sectional view of the whole structure of embodiment 1 of the present invention;
FIG. 2 is a schematic top view of the upper pole piece structure of embodiment 1 of the present invention;
FIG. 3 is a schematic front view of the outer pole piece structure of embodiment 1 of the present invention;
fig. 4 is a schematic top view of a spoke structure of the magnetic screen according to embodiment 1 of the present invention.
Reference numerals illustrate:
the magnetic screen comprises a 1-upper pole shoe, a 2-inner coil, a 3-spoke structure magnetic screen, a 4-inner isolation ceramic ring, 5-ceramic fiber paper, a 6-anode component, a 7-outer isolation ceramic ring, an 8-outer coil, a 9-outer pole shoe, a 10-thruster shell, an 11-metal net, a 12-metal pressing plate, a 13-bottom plate, a 14-inner magnetic core, a 15-bolt, a 31-outer magnetic screen ring, a 32-inner magnetic screen ring, a 33-spoke handle, a 51-through hole, a 91-exhaust hole II, a 101-exhaust hole, a 102-exhaust hole I131-annular groove, a 132-annular through hole, a 301-vent hole and a 331-countersunk through hole.
Detailed Description
The following description of the embodiments of the present invention will be made apparent and fully in view of the accompanying drawings, in which some, but not all embodiments of the invention are shown. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present invention, it should be noted that the terms "first," "second," and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
In addition, the technical features of the different embodiments of the present invention described below may be combined with each other as long as they do not collide with each other.
Example 1:
referring to fig. 1-4, a low-pressure discharge breakdown suppression assembly of a high-power hall thruster includes: the bottom plate 13, the middle part sets up interior magnetic core 14 above the bottom plate 13, winding inner coil 2 on the inner magnetic core 14 outer wall, interior magnetic core 14, inner coil 2 top set up pole shoe 1, the bottom plate 13 outside sets up outer coil 8, outer coil 8 outside sets up outer pole shoe 9, outer coil 8, outer pole shoe 9 top set up outer magnetic pole, be equipped with annular groove structure's discharge channel between inner coil 2 and the outer coil 8, set up spoke structure magnetic screen 3 in the discharge channel, spoke structure magnetic screen 3 includes outer magnetic screen ring 31, sets up the interior magnetic screen ring 32 and a plurality of will outer magnetic screen ring 31 and the radial fixed spoke handle 33 of interior magnetic screen ring 32, the outer coaxial outer isolation ceramic ring 7 of outer magnetic screen ring 31 inner circle of spoke handle 33 top, inner isolation ceramic ring 4, outer ceramic screen ring 7 sets up annular ceramic screen ring 5, the thrust force transducer is in the bottom plate 10, the bottom plate 10 can be realized, the thrust force transducer is in the bottom plate 10 is set up to the fixed air pressure plate 10, and the bottom plate 10 can be reduced the axial thrust system is set up to the bottom plate 10, and the bottom plate 10 can be fixed to the bottom plate 13 is set up to the axial thrust force transducer. The metal pressing plate 12 is a strip-shaped pressing plate, and is used for pressing four sides of the metal mesh, then a second layer of metal mesh is pressed on the other side of the pressing plate, then a second group of four new pressing plates are added, the second layer of metal mesh is pressed, and the other layer of metal mesh is pressed, and the metal mesh and the pressing plates are arranged at intervals to form a stacked three-dimensional assembly structure with multiple layers of metal mesh separated by a plurality of metal pressing plates, and the four sides of the assembly are all provided with through holes and are fixed on the thruster through screws. Wherein the spacing of the metal mesh is the thickness of the press plate, on the order of 1-2 mm.
In the above embodiment, an inner isolation ceramic ring, ceramic fiber paper and an outer isolation ceramic ring are arranged between the anode assembly and the spoke handle, so that a plugging of a submerged passage for air leakage of anode air supply to the tail of the thruster is formed, wherein the whole magnetic device with a spoke structure is in a radial shape of a wheel, and cannot completely wrap the anode air supply assembly, so that a passage for air flow of the anode air supply to the tail of the thruster exists; simultaneously, the upper pole shoe and the outer pole shoe are provided with exhaust holes, so that the exhaust speed of the inner exciting coil and the outer exciting coil after air is exhausted is improved; the closed tail shell is transformed, a multi-layer net structure is arranged, so that a path of tail gas pumped by a vacuum system is smooth, space plasma can be restrained from entering, and the risk of low air pressure is reduced; and synchronously, insulating ceramic spraying is carried out on the anode towards the magnetic screen side of the spoke structure, so that insulation is enhanced. The above components are specially designed to realize the suppression of spark breakdown, and the thruster shell is arranged at the tail part of the thruster, in this case, when the air leakage and the air outlet on the upper part enter the space at the tail part of the thruster and are blocked by the shell, a low-pressure cavity is formed, and the high-voltage of approximately kilovolts is needed to be loaded by combining the high-power thruster, so that the spark breakdown and the spark discharge can occur. Because two main factors of forming discharge breakdown are air pressure and insulation distance, namely pd value, in order to avoid breakdown, the air pressure is reduced as much as possible, and high vacuum is formed; meanwhile, the insulation distance is increased, the breakdown value is further increased, the inhibition of the influence of environmental plasma can be effectively realized, and the low-pressure discharge breakdown is inhibited.
In the above embodiment, the middle portion of each spoke handle 33 is provided with an upward countersunk through hole 331 along the axial direction, the ceramic fiber paper 5 opposite to the top of each countersunk through hole 331 is provided with a through hole 51, and the bolts 15 sequentially pass through the countersunk through holes 331 and the through holes 51 from bottom to top and are then screwed and fixed with threaded holes formed in corresponding positions at the bottom of the anode assembly 6.
In the above embodiment, the anode component 6 is sprayed with insulating ceramic towards the side of the magnetic screen 3 of the spoke structure, so that insulation is enhanced, and the ignition breakdown can be restrained.
In the above embodiment, the spoke 33 is preferably a long slat.
In the above embodiment, the outer ring edge of the upper pole shoe 1 is provided with a plurality of axial exhaust holes 102 along the circumferential direction; the outer pole shoe 9 is provided with a plurality of radial exhaust holes II 91 along the circumferential direction, and the upper pole shoe and the outer pole shoe are provided with exhaust holes, so that the exhaust speed of the gas after the gas is exhausted is improved.
In the above embodiment, the bottom plate 13 is provided with the annular groove 131 along the circumferential direction, the bottom of the annular groove 131 is provided with the annular through hole 132 along the circumferential direction, the discharge channel is communicated with the bottom of the bottom plate 13 through the annular groove 131 and the annular through hole 132, the lower end of the outer magnetic screen ring 31 is axially inserted into the annular groove 131 and is nested in the outer ring of the annular groove 131 for fixation, and the lower end of the inner magnetic screen ring 32 is axially inserted into the annular groove 131 and is nested in the inner ring of the annular groove 131 for fixation.
In the above embodiment, preferably, the outer edge of the outer magnetic screen ring 31 and the inner edge of the inner magnetic screen ring 32 are provided with a plurality of ventilation holes 301 penetrating in the axial direction along the circumferential direction.
In addition, the invention is based on ceramic fiber paper technology, namely inorganic silicate materials, can resist high temperature (more than 1400 ℃), and is non-conductive; the processing of the refractory fiber has the outstanding characteristics of flexibility, sealing effect and the like through extrusion; the design is characterized in that the ceramic fiber paper is introduced, the exhaust holes and the multilayer isolation net are arranged, and the anode component is locally sprayed, so that the risk of low air pressure is avoided, and meanwhile, the inhibition of the influence of environmental plasma is realized, so that the discharge breakdown of the low air pressure is inhibited.
It is apparent that the above examples are given by way of illustration only and are not limiting of the embodiments. Other variations or modifications of the above teachings will be apparent to those of ordinary skill in the art. It is not necessary here nor is it exhaustive of all embodiments. While still being apparent from variations or modifications that may be made by those skilled in the art are within the scope of the invention.
Claims (7)
1. The utility model provides a high-power hall thruster low pressure discharge breakdown suppression subassembly which characterized in that includes: bottom plate (13), middle part sets up interior magnetic core (14) above bottom plate (13), winding inner coil (2) on inner magnetic core (14) outer wall, inner magnetic core (14), inner coil (2) top set up pole shoe (1), the bottom plate (13) outside sets up outer coil (8), outer pole shoe (9) are set up outside outer pole shoe (8), outer pole shoe (9) top set up outer magnetic pole, be the discharge channel that is equipped with annular groove structure between inner coil (2) and outer coil (8), set up spoke structure magnetic screen (3) in the discharge channel, spoke structure magnetic screen (3) include outer magnetic screen ring (31), set up outer magnetic screen ring (32) of outer magnetic screen ring (31) inner circle and a plurality of will outer magnetic screen ring (31) and inner magnetic screen ring (32) are along radial connection fixed spoke handle (33), the outer coaxial with the axle sleeve of spoke screen ring (32) outside of spoke handle (33) top is established inner ring (4), ceramic inner ring (7) outer ceramic screen ring (31) is nested in the ceramic fiber (7), the ceramic fiber paper (5) is provided with an anode assembly (6), the bottom surface of the bottom plate (13) is provided with a thruster shell (10), the upper end of the thruster shell (10) is fixedly connected with the periphery of the bottom plate (13) in a sealing manner, the lower end of the thruster shell (10) is provided with an extraction opening (101), the extraction opening (101) is axially provided with a plurality of metal nets (11), and the metal nets (11) are fixed on the thruster shell (10) through metal pressing plates (12).
2. The low-pressure discharge breakdown suppression assembly of the high-power Hall thruster according to claim 1, wherein an upward countersunk through hole (331) is formed in the middle of each spoke handle (33) along the axial direction, a through hole (51) is formed in the ceramic fiber paper (5) which is right above each countersunk through hole (331), and a bolt (15) sequentially passes through the countersunk through holes (331) and the through holes (51) from bottom to top and is in threaded connection with a threaded hole formed in a position corresponding to the bottom of the anode assembly (6).
3. The low-pressure discharge breakdown suppression assembly of the high-power Hall thruster according to claim 1, wherein the anode assembly (6) is coated with insulating ceramics towards the magnetic screen (3) side of the spoke structure.
4. The low-pressure discharge breakdown suppressing assembly of a high-power hall thruster as claimed in claim 1, wherein said spoke (33) is a long strip.
5. The low-pressure discharge breakdown suppression assembly of the high-power Hall thruster according to claim 1, wherein a plurality of axial exhaust holes I (102) are formed in the peripheral direction of the outer ring edge of the upper pole shoe (1); the outer pole shoe (9) is provided with a plurality of radial exhaust holes (91) along the circumferential direction.
6. The low-pressure discharge breakdown suppression assembly of the high-power Hall thruster according to claim 1, wherein the bottom plate (13) is provided with an annular groove (131) along the circumferential direction, the bottom of the annular groove (131) is provided with an annular through hole (132) along the circumferential direction, the discharge channel is communicated with the bottom of the bottom plate (13) through the annular groove (131) and the annular through hole (132), the lower end of the outer magnetic screen ring (31) is axially inserted into the annular groove (131) and is nested in the outer ring of the annular groove (131) for fixation, and the lower end of the inner magnetic screen ring (32) is axially inserted into the annular groove (131) and is nested in the inner ring of the annular groove (131) for fixation.
7. The low-pressure discharge breakdown suppression assembly of the high-power hall thruster according to claim 6, wherein a plurality of vent holes (301) penetrating axially are formed in the outer edge of the outer magnetic screen ring (31) and the inner edge of the inner magnetic screen ring (32) along the circumferential direction.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211533337.XA CN116146443B (en) | 2022-12-01 | 2022-12-01 | Low-pressure discharge breakdown suppression assembly of high-power Hall thruster |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211533337.XA CN116146443B (en) | 2022-12-01 | 2022-12-01 | Low-pressure discharge breakdown suppression assembly of high-power Hall thruster |
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| CN116146443B true CN116146443B (en) | 2023-10-24 |
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| CN109209804A (en) * | 2018-10-23 | 2019-01-15 | 哈尔滨工业大学 | A kind of magnetic cup of hall thruster/discharge channel integral structure |
| CN112412721A (en) * | 2020-11-10 | 2021-02-26 | 北京航空航天大学 | Closable grid system with diaphragm valve |
| CN114412739A (en) * | 2022-02-24 | 2022-04-29 | 兰州空间技术物理研究所 | High-power Hall thruster magnetic circuit assembly |
| CN114658623A (en) * | 2022-03-11 | 2022-06-24 | 上海易推动力科技有限公司 | Integrated magnetic screen anode structure for low-power Hall thruster |
| CN114738219A (en) * | 2022-05-20 | 2022-07-12 | 西北工业大学 | micro-Newton thrust ECR ion thruster grid assembly |
| CN115387975A (en) * | 2022-08-30 | 2022-11-25 | 兰州空间技术物理研究所 | Novel iodine working medium storage tank for electric propulsion |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10308377B2 (en) * | 2011-05-03 | 2019-06-04 | Massachusetts Institute Of Technology | Propellant tank and loading for electrospray thruster |
| US11067064B2 (en) * | 2018-02-26 | 2021-07-20 | Massachusetts Institute Of Technology | Propulsion systems including a sublimable barrier |
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2022
- 2022-12-01 CN CN202211533337.XA patent/CN116146443B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109209804A (en) * | 2018-10-23 | 2019-01-15 | 哈尔滨工业大学 | A kind of magnetic cup of hall thruster/discharge channel integral structure |
| CN112412721A (en) * | 2020-11-10 | 2021-02-26 | 北京航空航天大学 | Closable grid system with diaphragm valve |
| CN114412739A (en) * | 2022-02-24 | 2022-04-29 | 兰州空间技术物理研究所 | High-power Hall thruster magnetic circuit assembly |
| CN114658623A (en) * | 2022-03-11 | 2022-06-24 | 上海易推动力科技有限公司 | Integrated magnetic screen anode structure for low-power Hall thruster |
| CN114738219A (en) * | 2022-05-20 | 2022-07-12 | 西北工业大学 | micro-Newton thrust ECR ion thruster grid assembly |
| CN115387975A (en) * | 2022-08-30 | 2022-11-25 | 兰州空间技术物理研究所 | Novel iodine working medium storage tank for electric propulsion |
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| CN116146443A (en) | 2023-05-23 |
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