CN111654967B - Double-jet pulse metal ion plasma propeller - Google Patents
Double-jet pulse metal ion plasma propeller Download PDFInfo
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- CN111654967B CN111654967B CN202010518342.8A CN202010518342A CN111654967B CN 111654967 B CN111654967 B CN 111654967B CN 202010518342 A CN202010518342 A CN 202010518342A CN 111654967 B CN111654967 B CN 111654967B
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05H—PLASMA TECHNIQUE; PRODUCTION OF ACCELERATED ELECTRICALLY-CHARGED PARTICLES OR OF NEUTRONS; PRODUCTION OR ACCELERATION OF NEUTRAL MOLECULAR OR ATOMIC BEAMS
- H05H1/00—Generating plasma; Handling plasma
- H05H1/24—Generating plasma
- H05H1/26—Plasma torches
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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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- 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
- F03H1/0087—Electro-dynamic thrusters, e.g. pulsed plasma thrusters
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Abstract
The invention provides a double-jet pulse metal ion plasma thruster, which comprises: the anode, the inner insulating sleeve, the cathode and the outer insulating sleeve; the anode is columnar, and the two ends of the anode are respectively provided with an anode nozzle and an anode tail end; the inner insulating sleeve is of a cylindrical structure with openings at two ends, is sleeved on the anode, and the inner wall of the inner insulating sleeve is in contact with the outer wall of the anode; the cathode is the tubular structure of both ends open-ended, includes: the discharge end and the anode nozzle are positioned on the same side, the cathode is sleeved on the inner insulating sleeve, and the inner wall of the cathode is in contact with the outer wall of the inner insulating sleeve; the external insulation sleeve is sleeved on the surface of the cathode, and one side of the external insulation sleeve close to the cathode discharge end is made into a horn shape; the non-discharge end of the cathode is connected with a negative high-voltage terminal of an external circuit, and the anode is grounded. In the single pulse discharge process, the obvious visible plasma jet is formed near the cathode and near the anode for propulsion, so that the propulsion performance of the pulse metal ion plasma propeller is effectively improved.
Description
Technical Field
The invention relates to the technical field of microsatellite electromagnetic propulsion systems, in particular to a double-jet pulse metal ion plasma propeller.
Background
In recent years, with the increase of the demand of space exploration tasks in various countries, microsatellites with the characteristics of small volume, light weight, short research period, good economy and the like are rapidly developed. Due to the size and mass limitations of microsatellites, higher demands are placed on the performance of their propulsion systems, and low energy input and high specific impulse output are desired. Electric propulsion systems are gradually replacing traditional chemical propulsion systems due to their structural and functional advantages and become the main propulsion of microsatellite systems. The pulse plasma propeller is an electromagnetic propulsion system, and has the characteristics of simple structure, light weight, high specific impulse and the like, can generate controllable thrust, is very suitable for the propulsion of a microsatellite, and is attracted more and more attention.
Research shows that the vacuum pulse discharge ablation of cathode metal material can generate high ionization degree and supersonic speed (-10)4m/s), high density, directionally ejected metal ion plasma beam. And thus new types of pulsed plasma thrusters using metal ion plasmas as a thrust source have received increasing attention. For such a propeller, it is mainly propelled by the energy of metal ions, and thus it is called a pulsed metal ion plasma propeller. As shown in fig. 1, the conventional pulsed metal ion plasma thruster adopts an electrode structure: inner cathode-insulating sleeve-outer bare metal anode. But most of the generated charged particles enter the metal electrode under the action of the space electric field to form circuit current. Only a small part of charged particles are ejected out of the nozzle of the propeller to form thrust, so that the generated thrust of the propeller is small, and the efficiency is low.
A fully insulated anode electrode structure is proposed in the literature of "Tianjia, Liu Zheng, Zhenwei and Yongjie. Generation characteristics of a metal ion Plasma jet in vacuum discharge [ J ]. Plasma Science and Technology,2018,20: 1-7", and the fully insulated anode electrode structure obstructs the passage of charged particles generated by discharge to a discharge electrode, so that more Plasma is sprayed out along an insulated sleeve, although the density and the propagation speed of a Plasma source are improved by the fully insulated anode, the discharge difficulty is increased by adopting the fully insulated anode electrode structure, the current amplitude of a cathode generated by discharge is reduced, and the Plasma Generation amount is reduced.
At present, all pulsed metal ion plasma thruster structures utilize the plasma near the cathode to form directional jet to provide thrust during discharging, the anode only plays a role of receiving particles from the cathode to form an electric loop, and little people study how to utilize the plasma directional jet near the anode to realize propulsion.
Disclosure of Invention
The embodiment of the invention provides a double-jet pulse metal ion plasma thruster which can improve the density and the jet speed of a plasma thrust source jetted from a thruster nozzle in single pulse discharge on the premise of not influencing the generation of plasma, and solves the technical problems of low density and low energy of the plasma source in the vacuum discharge process, smaller thruster thrust and lower efficiency of the thruster in the background technology.
In order to achieve the purpose, the invention adopts the following technical scheme.
A dual-ejection pulsed metal ion plasma thruster, comprising: an anode 1, an inner insulating sleeve 2, a cathode 3 and an outer insulating sleeve 4;
the anode 1 is columnar, and the two ends of the anode are respectively provided with an anode nozzle 7 and an anode tail end;
the inner insulating sleeve 2 is a cylindrical structure with openings at two ends, is sleeved on the anode 1, and the inner wall of the inner insulating sleeve is in contact with the outer wall of the anode 1;
the cathode 3 is a tubular structure with two open ends, and comprises: the cathode 3 is sleeved on the inner insulating sleeve 2, and the inner wall of the cathode is contacted with the outer wall of the inner insulating sleeve 2;
outer insulating sleeve 4 is both ends open-ended tubular structure, includes: the cathode comprises a cylindrical end and a horn-shaped end 5, wherein the horn-shaped end 5 and an anode nozzle 7 are positioned on the same side, the outer insulating sleeve 4 is sleeved on the cathode 3, and the inner wall of the cylindrical end of the outer insulating sleeve is in contact with the outer wall of the cathode 3;
the non-discharge end of the cathode 3 is connected with an external circuit negative high-voltage terminal, and the anode 1 is grounded.
Preferably, the sum of the distances from the end surface of the inner insulating sleeve 2 positioned at the anode nozzle to the cathode discharge end 6 and the anode nozzle 7 is less than the sum of the distances from the end surface of the inner insulating sleeve 2 positioned at the anode terminal to the cathode non-discharge end and the anode terminal.
Preferably, said cathode discharge end 6 cannot exceed the anode nozzle 7 in axial position.
Preferably, in axial position, the beginning of the flared end of the outer insulating sleeve 4 protrudes beyond the anode spout 7.
Preferably, in axial position, the inner insulating sleeve 2 is located at one end of the anode nozzle 7, protruding beyond the cathode discharge end 6 and the anode nozzle 7.
Preferably, the anode 1 is cylindrical, and the cathode 3, the inner insulating sleeve 2 and the outer insulating sleeve 4 are all cylindrical structures.
Preferably, the inner insulating sleeve 2 and the outer insulating sleeve 4 are made of an insulating material.
Preferably, the cathode 3 is made of a magnetically conductive metal material.
Preferably, the discharge end 6 is in the shape of a bulge, which is wedge-shaped, arc-shaped or cube-shaped.
According to the technical scheme provided by the embodiment of the invention, the embodiment of the invention provides the double-jet pulse metal ion plasma thruster, and the plasma generated by the cathode is blocked and restrained by the small space formed between the inner insulating sleeve and the outer insulating sleeve, so that the directional jet capability of the plasma nearby the cathode is improved; the inner insulating sleeve is arranged on the outer surface of the anode, so that the metal ion density near the anode is improved, and the establishment of positive space potential near the anode is facilitated. On the one hand, the generation of plasma is not affected and the charged particles are hindered from further entering the anode, and on the other hand, a clearly visible plasma jet is formed in the same direction as the cathode in the vicinity of the anode under the action of the higher positive space potential in the vicinity of the anode. Therefore, under the condition of not influencing the discharging difficulty of the propeller, the double plasma jet formed near the cathode and the anode is utilized for propulsion, and the propulsion performance of the pulse plasma propeller is improved.
Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
Fig. 1 is a schematic diagram of a conventional cathode-sleeve-anode structure according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram (anode-sleeve-cathode-sleeve) of a dual-injection pulse metal ion plasma thruster according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of the operation of a dual spray pulse metal ion plasma thruster with dual insulating sleeves according to an embodiment of the present invention;
fig. 4 is a discharge circuit diagram of a dual-injection pulse metal ion plasma thruster according to an embodiment of the present invention;
FIG. 5 is a graph of peak plasma density in a single pulse discharge using a dual spray pulse metal ion plasma thruster with a dual insulating sleeve and a conventional cathode-sleeve-anode configuration, as measured in accordance with an embodiment of the present invention;
FIG. 6 is a graph of the peak plasma propagation velocity for a conventional cathode-sleeve-anode configuration in a single pulse discharge using a dual spray pulse metal ion plasma thruster with a dual insulating sleeve in accordance with an embodiment of the present invention;
fig. 7 is a graph of thrust magnitude measured in a single pulse discharge using a dual spray pulse metal ion plasma thruster with a dual insulating sleeve and a conventional cathode-sleeve-anode configuration in accordance with an embodiment of the present invention.
Reference numerals:
1-an anode; 2-an inner insulating sleeve; 3-a cathode; 4-an outer insulating sleeve; 5-a trumpet-shaped end; 6-discharge end; 7-anode nozzle.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative only for the purpose of explaining the present invention, and are not to be construed as limiting the present invention.
As used herein, the singular forms "a", "an", "the" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof. It will be understood that when an element is referred to as being "connected" or "coupled" to another element, it can be directly connected or coupled to the other element or intervening elements may also be present. Further, "connected" or "coupled" as used herein may include wirelessly connected or coupled. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.
It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
For the convenience of understanding the embodiments of the present invention, the following description will be further explained by taking several specific embodiments as examples in conjunction with the drawings, and the embodiments are not to be construed as limiting the embodiments of the present invention.
An embodiment of the present invention provides a dual-injection pulse metal ion plasma thruster, as shown in fig. 2, including: anode 1, inner insulating sleeve 2, cathode 3 and outer insulating sleeve 4. The anode 1 is cylindrical, and the two ends of the anode are respectively provided with an anode nozzle 7 and an anode tail end; the inner insulating sleeve 2 is a cylindrical structure with two open ends and is sleeved on the outer wall of the anode; the cathode 3 is a cylindrical structure with both ends open, and includes: the discharge end 6 and the anode nozzle 7 are positioned on the same side, and the cathode 3 is sleeved on the outer wall of the inner insulating sleeve 2; outer insulating sleeve 4 is both ends open-ended cylindric structure, includes: the cathode comprises a cylindrical end and a horn-shaped end 5, an external insulation sleeve 4 is sleeved on the outer wall of the cathode 3, and the inner wall of the cylindrical end of the external insulation sleeve is contacted with the outer wall of the cathode 3; the non-discharge end of the cathode 3 is connected with the negative high-voltage terminal of an external circuit, and the anode 1 is grounded.
The sum of the distances from the end surface of the inner insulating sleeve 2 positioned at the anode nozzle to the cathode discharge end 6 and the anode nozzle 7 is smaller than the sum of the distances from the end surface of the inner insulating sleeve 2 positioned at the anode tail end to the cathode non-discharge end and the anode tail end, so that the plasma thruster discharges at one end only.
The outer insulating sleeve 4 is sleeved on the outer wall of the cathode 3, so that radial diffusion of plasma near the cathode can be restrained, the number of metal ions near the cathode is increased, the potential Vc near the cathode is increased, and the spraying performance of the plasma near the cathode is improved. The trumpet-shaped nozzle can further reduce energy loss, thereby improving thrust and system efficiency.
In the axial position, the cathode discharge end 6 cannot go beyond the anode nozzle 7; the initial section of the horn-shaped end of the external insulation sleeve 4 extends out of the anode nozzle 7, and the extension length is 0mm-20 mm; the inner insulating sleeve 2 is located at one end of the anode nozzle 7, extending beyond the cathode discharge end 6 and the anode nozzle 7.
The inner insulating sleeve 2 consists of an insulating material. The cathode 3 is made of iron metal with good magnetic permeability.
In one embodiment of the present invention, the discharge end 6 has a convex shape such as a wedge shape, an arc shape, or a cube shape.
In a particular embodiment of the invention, the diameter of the anode 1 does not exceed 2 mm.
In one embodiment of the invention, the cathode 3 is made of a magnetically conductive metal material and the discharge end 6 is made of a lead material.
In a particular embodiment of the invention, the inner insulating sleeve 2 is made of a ceramic material.
In a particular embodiment of the invention, the outer insulating sleeve 4 is also made of a ceramic material.
For ease of understanding, detailed dimensions of a set of discharge electrodes are given below. The anode 1 is made of copper metal, and the diameter of the anode 1 is 1 mm. The inner insulating sleeve 2 sleeved on the surface of the anode is made of ceramic, and the outer diameter of the inner insulating sleeve is 2 mm. The cathode 3 sleeved on the surface of the inner insulating sleeve 2 is made of lead metal, and the outer diameter of the cathode is 4 mm. The outer insulating sleeve 4 sleeved on the surface of the cathode is made of ceramic, the outer diameter of the cylindrical part of the outer insulating sleeve 4 is 5mm, the axial height of the horn-shaped part is 10mm, and the inner diameter and the outer diameter of the opening are respectively 10mm and 11 mm. In the axial position, the cathode discharge end 6 is flush with the anode nozzle 7; the inner insulating sleeve 2 and the outer insulating sleeve 4 are positioned at the same level of the cylindrical part at one side of the anode nozzle and extend out of the anode nozzle by 2 mm.
Fig. 3 is a schematic diagram of the working mechanism of the dual-injection pulse metal ion plasma thruster with the dual-insulation sleeve. The method comprises the following specific steps: the discharge end 6 of the cathode 3 generates electrons and ions under the action of electron field emission. Then a part of the charged particles is at a positive space potential V near the discharge end 6CAxially spraying out along a gap between the inner insulating sleeve 2 and the outer insulating sleeve 4 under the action to form thrust; the other part moves to the anode under the action of a space electric field, then electrons are absorbed by the anode, metal ions are accumulated near the anode, and a positive space potential V is formed near the anode nozzle 7A. At VAUnder the action, charged particles near the anode nozzle 7 are also axially sprayed out along the inner insulating sleeve 2 to form thrust. Finally, the resultant thrust force formed near the cathode and near the anode propels the vehicle.
The discharge power supply adopts a pulse discharge form whichThe specific discharge circuit is shown in fig. 4. The 220V AC power supply is boosted by a transformer and converted by a voltage doubling rectifying circuit and then is supplied to a capacitor C2And (6) charging. When an ignition pulse is applied to the three-point gap, the three-point gap is conducted through C2The 27 omega resistor, the 220 muH inductor and the vacuum gap form a loop, and the vacuum gap breaks down to generate a discharge phenomenon. The cathode is connected with the high-voltage end of the power supply through a binding post, and the anode is grounded through a lead.
Fig. 5 is a graph of the peak plasma density generated in a single pulse discharge using a dual spray pulse metal ion plasma thruster with dual insulator sleeves and a conventional cathode-insulator sleeve-anode configuration. As can be seen from fig. 5, the peak plasma density generated using the dual spray pulsed metal ion plasma thruster configuration with dual insulating sleeves is increased by a factor of 10.7, which is a significant improvement, compared to the conventional cathode-insulating sleeve-anode configuration. This result demonstrates that the dual spray configuration can achieve a higher density plasma source.
Fig. 6 is a graph of the peak plasma propagation velocity generated in a single pulse discharge using a dual spray pulse metal ion plasma thruster with dual insulating sleeves and a conventional cathode-insulating sleeve-anode configuration. As can be seen from fig. 6, the peak propagation velocity of the plasma generated by the dual spray pulse metal ion plasma thruster structure with the dual insulating sleeves is increased by 1.47 times compared with the conventional cathode-insulating sleeve-anode structure. This result demonstrates that a dual injection configuration with dual insulating sleeves can achieve a more energetic plasma source.
Fig. 7 is a graph of thrust magnitude measured in a single pulse discharge using a dual spray pulse metal ion plasma thruster with a dual insulator sleeve and a conventional cathode-insulator sleeve-anode configuration in accordance with an embodiment of the present invention. As can be seen from fig. 7, the peak thrust value generated by using the dual spray pulse metal ion plasma thruster structure with the dual insulating sleeves is improved by 2.64 times compared with the conventional cathode-insulating sleeve-anode structure. This result demonstrates that a greater thrust can be achieved with a dual spray configuration having dual insulative sleeves.
2 plasma generation effect test after different propeller structures discharge:
in the discharge experiment process, comparative discharge experiment research is carried out on 2 different propeller structures, wherein the 2 propeller structures are a double-jet pulse metal ion plasma propeller structure (anode-sleeve-cathode-sleeve structure) with a double-insulation sleeve and a traditional cathode-insulation sleeve-anode structure.
For a double-injection pulse metal ion plasma thruster structure with double insulating sleeves, the anode 1 adopts copper metal, and the diameter of the anode is 1 mm. The inner insulating sleeve 2 sleeved on the surface of the anode is made of ceramic, and the outer diameter of the inner insulating sleeve is 2 mm. The cathode 3 sleeved on the surface of the inner insulating sleeve 2 is made of lead metal, and the outer diameter of the cathode is 4 mm. The outer insulating sleeve 4 sleeved on the surface of the cathode is made of ceramic, the outer diameter of the cylindrical part is 5mm, the axial height of the horn-shaped part is 10mm, and the inner diameter and the outer diameter are 10mm and 11mm respectively. In the axial position, the cathode discharge end 6 is flush with the anode nozzle 7; the inner insulating sleeve 2 and the outer insulating sleeve 4 are positioned at the same level of the cylindrical part at one side of the anode nozzle and extend out of the anode nozzle by 2 mm. In contrast, for the conventional cathode-insulating sleeve-anode structure, the positions of the cathode and the anode are just opposite to those of the structure of the dual-spray pulse metal ion plasma thruster with the dual-insulating sleeve, the size of the cathode is the same as that of the anode in the structure of the dual-spray pulse metal ion plasma thruster with the dual-insulating sleeve, and the size of the anode is the same as that of the cathode in the structure of the dual-spray pulse metal ion plasma thruster with the dual-insulating sleeve.
The 2 electrode configurations are shown in fig. 1 and 2. The experimental plasma generation results using the above 2 different propeller configurations at a distance of 110mm from the anode nozzle are shown in table 1.
Table 1 plasma and thrust measurements for different propeller configurations
From the parameters in table 1, under the condition of equal discharge voltage, the cathode current amplitude when the anode-sleeve-cathode-sleeve structure is discharged is 130A, and the anode current amplitude is 70A. The anode current amplitude only accounts for 53% of the cathode current amplitude, and analysis shows that the anode current amplitude is caused by the fact that a positive space potential is formed near the anode to prevent subsequent charged particles from entering the anode. For a conventional cathode-insulator sleeve-anode configuration, the anode current accounts for 90% of the cathode current amplitude.
According to the plasma measurement parameters, the density peak value of the plasma jet generated by the discharge of the anode-sleeve-cathode-sleeve structure is highest, and the propagation speed is maximum; compared with the traditional cathode-insulating sleeve-anode, the plasma density peak value, the propagation velocity peak value and the thruster thrust generated by adopting the anode-sleeve-cathode-sleeve structure discharge are respectively improved by 10.7 times, 1.47 times and 2.64 times. In conclusion, the double-jet pulse plasma propeller structure which simultaneously forms plasma jet near the cathode and the anode for propulsion effectively improves the performance of the generated plasma thrust source, including the density and the energy of the plasma and the thrust peak value generated by the propeller.
In summary, the embodiments of the present invention provide a dual-injection pulse metal ion plasma thruster, which utilizes plasma injection formed near the cathode and near the anode in a single pulse discharge process to perform propulsion without affecting the generation of plasma. More plasmas are sprayed out to form a thrust source, and the spraying performance of the plasmas and the propelling performance of the propeller are improved.
Those of ordinary skill in the art will understand that: the figures are merely schematic representations of one embodiment, and the blocks or flow diagrams in the figures are not necessarily required to practice the present invention.
The embodiments in the present specification are described in a progressive manner, and the same and similar parts among the embodiments are referred to each other, and each embodiment focuses on the differences from the other embodiments. In particular, for apparatus or system embodiments, since they are substantially similar to method embodiments, they are described in relative terms, as long as they are described in partial descriptions of method embodiments. The above-described embodiments of the apparatus and system are merely illustrative, and the units described as separate parts may or may not be physically separate, and the parts displayed as units may or may not be physical units, may be located in one place, or may be distributed on a plurality of network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the solution of the present embodiment. One of ordinary skill in the art can understand and implement it without inventive effort.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (9)
1. A double-jet pulse metal ion plasma thruster comprises an anode (1), an inner insulating sleeve (2) and a cathode (3), and is characterized by further comprising an outer insulating sleeve (4);
the anode (1) is columnar, and the two ends of the anode are respectively provided with an anode nozzle (7) and an anode tail end;
the inner insulating sleeve (2) is of a cylindrical structure with openings at two ends, is sleeved on the anode (1), and the inner wall of the inner insulating sleeve is in contact with the outer wall of the anode (1);
the cathode (3) is a tubular structure with two open ends, and comprises: the cathode (3) is sleeved on the inner insulating sleeve (2), and the inner wall of the cathode is contacted with the outer wall of the inner insulating sleeve (2);
outer insulating sleeve (4) are both ends open-ended tubular structure, include: the cathode comprises a cylindrical end and a horn-shaped end (5), wherein the horn-shaped end (5) and an anode nozzle (7) are positioned on the same side, the outer insulating sleeve (4) is sleeved on the cathode (3), and the inner wall of the cylindrical end of the outer insulating sleeve is contacted with the outer wall of the cathode (3);
the non-discharge end of the cathode (3) is connected with an external circuit negative high-voltage terminal, and the anode (1) is grounded.
2. The thruster according to claim 1, wherein the sum of the distances from the end surface of the inner insulating sleeve (2) located at the anode nozzle to the cathode discharge end (6) and the anode nozzle (7) respectively is smaller than the sum of the distances from the end surface of the inner insulating sleeve (2) located at the anode end to the cathode non-discharge end and the anode end respectively.
3. A thruster according to claim 2, characterized in that the cathode discharge end (6) cannot pass beyond the anode nozzle (7) in the axial position.
4. A thruster according to claim 3, characterized in that the starting section of the flared end of the outer insulating sleeve (4) projects, in an axial position, beyond the anode spout (7).
5. A thruster according to claim 3 or 4, characterized in that the inner insulating sleeve (2) is located at one end of the anode nozzle (7) in an axial position, projecting beyond the cathode discharge end (6) and the anode nozzle (7).
6. The thruster according to claim 1, characterized in that the anode (1) is cylindrical and the cathode (3), the inner insulating sleeve (2) and the outer insulating sleeve (4) are all cylindrical structures.
7. The thruster according to claim 1, characterized in that the inner insulating sleeve (2) and the outer insulating sleeve (4) are made of insulating material.
8. The thruster according to claim 1, characterized in that the cathode (3) is made of a magnetically conductive metal material.
9. A thruster according to claim 1, characterized in that the discharge end (6) is of convex shape, wedge-shaped, arc-shaped or cube-shaped.
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Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4821509A (en) * | 1985-06-10 | 1989-04-18 | Gt-Devices | Pulsed electrothermal thruster |
| US7518085B1 (en) * | 2003-05-30 | 2009-04-14 | Alameda Applied Sciences Corp. | Vacuum arc plasma thrusters with inductive energy storage driver |
| CN102869181A (en) * | 2012-09-05 | 2013-01-09 | 北京交通大学 | Electrode structure and electrode fixing structure for plasma thruster |
| US9242747B1 (en) * | 2011-11-18 | 2016-01-26 | Cu Aerospace, Llc | Space thruster using robust microcavity discharge and advanced propellants |
| CN108194294A (en) * | 2017-12-22 | 2018-06-22 | 北京交通大学 | Coaxial-type anodized insulation type pulsed plasma thruster |
| CN109578233A (en) * | 2018-10-12 | 2019-04-05 | 北京交通大学 | A kind of ablative-type protective coating pulsed plasma thruster based on multianode electrode structure |
| CN110043436A (en) * | 2019-06-05 | 2019-07-23 | 中国人民解放军国防科技大学 | Expanding type self-magnetic field magnetic plasma thruster |
| WO2019241489A1 (en) * | 2018-06-13 | 2019-12-19 | Cu Aerospace, Llc | Fiber-fed advanced pulsed plasma thruster (fppt) |
| CN110615122A (en) * | 2019-10-30 | 2019-12-27 | 哈尔滨工业大学 | Multi-ring micro-cathode electric arc thruster |
| CN110630460A (en) * | 2019-10-17 | 2019-12-31 | 北京航空航天大学 | Segmented anode high specific impulse pulse plasma thruster |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070045248A1 (en) * | 2003-05-30 | 2007-03-01 | Jochen Schein | Vacuum arc plasma thrusters with inductive energy storage driver |
-
2020
- 2020-06-09 CN CN202010518342.8A patent/CN111654967B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4821509A (en) * | 1985-06-10 | 1989-04-18 | Gt-Devices | Pulsed electrothermal thruster |
| US7518085B1 (en) * | 2003-05-30 | 2009-04-14 | Alameda Applied Sciences Corp. | Vacuum arc plasma thrusters with inductive energy storage driver |
| US9242747B1 (en) * | 2011-11-18 | 2016-01-26 | Cu Aerospace, Llc | Space thruster using robust microcavity discharge and advanced propellants |
| CN102869181A (en) * | 2012-09-05 | 2013-01-09 | 北京交通大学 | Electrode structure and electrode fixing structure for plasma thruster |
| CN108194294A (en) * | 2017-12-22 | 2018-06-22 | 北京交通大学 | Coaxial-type anodized insulation type pulsed plasma thruster |
| WO2019241489A1 (en) * | 2018-06-13 | 2019-12-19 | Cu Aerospace, Llc | Fiber-fed advanced pulsed plasma thruster (fppt) |
| CN109578233A (en) * | 2018-10-12 | 2019-04-05 | 北京交通大学 | A kind of ablative-type protective coating pulsed plasma thruster based on multianode electrode structure |
| CN110043436A (en) * | 2019-06-05 | 2019-07-23 | 中国人民解放军国防科技大学 | Expanding type self-magnetic field magnetic plasma thruster |
| CN110630460A (en) * | 2019-10-17 | 2019-12-31 | 北京航空航天大学 | Segmented anode high specific impulse pulse plasma thruster |
| CN110615122A (en) * | 2019-10-30 | 2019-12-27 | 哈尔滨工业大学 | Multi-ring micro-cathode electric arc thruster |
Non-Patent Citations (5)
| Title |
|---|
| Discharge and metallic plasma generation characteristics of an insulated anode with a micropore;Jia Tian et al.;《Phys. Plasmas》;20190213;第26卷;第23511-1—023511-8页 * |
| Generation characteristics of a metal ion plasma jet in vacuum discharge;jia tian et al.;《Plasma Science and Technology》;20180706;第1-5页 * |
| 真空弧推力器技术研究;吴先明等;《真空与低温》;20171230;第23卷(第6期);第331-335页 * |
| 真空弧推力器构型设计发展现状;李啸天等;《真空与低温》;20180227;第24卷(第1期);第9-14页 * |
| 面向微小卫星推进应用的脉冲等离子体特性研究;崔伟胜;《中国博士学位论文全文数据库 工程科技II辑》;20200115(第01期);C031-85 * |
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