CN113530778A - Coaxial steady state ablation solid propellant pulse plasma thruster - Google Patents
Coaxial steady state ablation solid propellant pulse plasma thruster Download PDFInfo
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- CN113530778A CN113530778A CN202110822748.XA CN202110822748A CN113530778A CN 113530778 A CN113530778 A CN 113530778A CN 202110822748 A CN202110822748 A CN 202110822748A CN 113530778 A CN113530778 A CN 113530778A
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- electrode
- propellant
- power supply
- solid propellant
- plasma thruster
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- 239000004449 solid propellant Substances 0.000 title claims abstract description 27
- 238000002679 ablation Methods 0.000 title claims abstract description 17
- 239000003380 propellant Substances 0.000 claims abstract description 20
- 239000003990 capacitor Substances 0.000 claims abstract description 11
- 230000005672 electromagnetic field Effects 0.000 claims abstract description 7
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 9
- 229910052802 copper Inorganic materials 0.000 claims description 9
- 239000010949 copper Substances 0.000 claims description 9
- 239000000463 material Substances 0.000 claims description 9
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 6
- 229910052782 aluminium Inorganic materials 0.000 claims description 6
- 239000004810 polytetrafluoroethylene Substances 0.000 claims description 6
- 229920001343 polytetrafluoroethylene Polymers 0.000 claims description 6
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 3
- 239000004642 Polyimide Substances 0.000 claims description 3
- NINIDFKCEFEMDL-UHFFFAOYSA-N Sulfur Chemical compound [S] NINIDFKCEFEMDL-UHFFFAOYSA-N 0.000 claims description 3
- 239000002041 carbon nanotube Substances 0.000 claims description 3
- 229910021393 carbon nanotube Inorganic materials 0.000 claims description 3
- 229920000840 ethylene tetrafluoroethylene copolymer Polymers 0.000 claims description 3
- 229920001721 polyimide Polymers 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims description 3
- 229910052717 sulfur Inorganic materials 0.000 claims description 3
- 239000011593 sulfur Substances 0.000 claims description 3
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims description 3
- 229910052721 tungsten Inorganic materials 0.000 claims description 3
- 239000010937 tungsten Substances 0.000 claims description 3
- 230000009286 beneficial effect Effects 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 108091092878 Microsatellite Proteins 0.000 description 2
- 238000010891 electric arc Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000007935 neutral effect Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
Images
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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- Plasma & Fusion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Plasma Technology (AREA)
Abstract
A coaxial steady state ablative solid propellant pulsed plasma thruster, comprising: the ignition device comprises an electromagnet ring, an insulating layer, a central electrode, an insulating medium layer, an ignition electrode, a propellant, an outer electrode, a constant force spring, an ignition power supply, a main discharge capacitor and an electromagnet ring power supply. The coaxial steady-state ablation solid propellant pulse plasma thruster provided by the invention has the following beneficial effects: (1) plasma advances spirally on the surface of the propellant through an electromagnetic field of the electromagnet ring, so that the difference of radial current density can be effectively reduced, and the propulsion performance consistency and the working reliability of the thruster are improved; (2) the outer electrode and the inner electrode are both provided with sawtooth-shaped or triangular tooth electrodes, the conditions required by starting can be effectively reduced according to the tip discharge principle, and the applicability of the thruster is enhanced.
Description
Technical Field
The invention belongs to the technical field of micro-satellite propulsion, and particularly relates to a coaxial steady ablation solid propellant pulse plasma thruster.
Background
The coaxial solid propellant pulse plasma thruster is an electric thruster without a movable part and with high specific impulse, and has wide application value on microsatellites represented by cuboids. The radial ablation rate of the ablation surface of the solid propellant is inconsistent due to the inconsistency of the radial current density and the field intensity gradient in the working process of the thruster, and after the working times exceed a certain value, the phenomena of high ablation rate at the center of the thruster and low ablation rate at the outer diameter are shown, so that the consistency of the propelling performance of the thruster is poor, the reliability of ignition starting is poor, and the applicability of the coaxial solid propellant pulse plasma thruster is greatly limited.
Disclosure of Invention
In order to solve the above problems, the present invention provides a coaxial steady-state ablation solid propellant pulse plasma thruster, comprising: an electromagnet ring, an insulating layer, a central electrode, an insulating medium layer, an ignition electrode, a propellant, an outer electrode, a constant force spring, an ignition power supply, a main discharge capacitor and an electromagnet ring power supply, wherein the electromagnet ring, the insulating layer, the outer electrode, the propellant, the center electrode, the insulating medium layer and the ignition electrode are arranged in the same axial direction from outside to inside, the outer electrodes are respectively connected with the first end of the main discharge capacitor and the positive electrode of the main discharge power supply, the central electrodes are respectively connected with the second end of the main discharge capacitor and the negative electrode of the main discharge power supply, the central electrode is connected with the positive electrode of the ignition power supply, the ignition electrode is connected with the negative electrode of the ignition power supply, the two ends of the electromagnet ring are respectively connected with the positive electrode and the negative electrode of the electromagnet ring power supply, the first end of the constant force spring is connected with the propellant, and the second end of the constant force spring is connected with the outer electrode.
Preferably, the electromagnetic field direction of the electromagnet ring is perpendicular to the section of the outer electrode.
Preferably, the magnetic field strength of the electromagnet ring ranges from 0.5T to 3.0T.
Preferably, the thickness of the insulating layer ranges from 5 mm to 20mm, and the material is PTFE or polyimide.
Preferably, the outer electrode is a circular ring with serrated teeth or triangular teeth.
Preferably, the material of the external electrode is copper or aluminum.
Preferably, the center electrode is a cylinder with serrated teeth or triangular teeth on the head
Preferably, the material of the central electrode is copper or aluminum.
Preferably, the ignition electrode is in the shape of an elongated wire and is made of copper, tungsten or carbon nanotubes.
Preferably, the propellant is annular and is made of PTFE, ETFE or solid sulfur.
The coaxial steady-state ablation solid propellant pulse plasma thruster provided by the invention has the following beneficial effects:
(1) plasma advances spirally on the surface of the propellant through an electromagnetic field of the electromagnet ring, so that the difference of radial current density can be effectively reduced, and the propulsion performance consistency and the working reliability of the thruster are improved.
(2) The outer electrode and the inner electrode are both provided with sawtooth-shaped or triangular tooth electrodes, the conditions required by starting can be effectively reduced according to the tip discharge principle, and the applicability of the thruster is enhanced.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic diagram of a coaxial steady-state ablative solid propellant pulsed plasma thruster provided by the invention;
FIG. 2 is a schematic structural diagram of a main body of a coaxial steady-state ablative solid propellant pulsed plasma thruster provided by the invention;
FIG. 3 is a schematic diagram of an outer electrode structure of a coaxial steady-state ablative solid propellant pulsed plasma thruster provided by the invention;
FIG. 4 is a schematic structural diagram of a central electrode of a coaxial steady-state ablative solid propellant pulsed plasma thruster provided by the invention;
description of the symbols: 1-electromagnet ring, 2-insulating layer, 31-center electrode, 32-insulating medium layer, 33-ignition electrode, 4-propellant, 5-outer electrode, 6-constant force spring, 7-ignition power supply, 8-main discharge power supply, 9-main discharge capacitor and 10-electromagnet ring power supply.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the accompanying drawings in conjunction with the following detailed description. It should be understood that the description is intended to be exemplary only, and is not intended to limit the scope of the present invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
In an embodiment of the present application, as shown in fig. 1 to 4, the present invention provides a coaxial steady-state ablation solid propellant pulsed plasma thruster, comprising: an electromagnet ring 1, an insulating layer 2, a central electrode 31, an insulating medium layer 32, an ignition electrode 33, a propellant 4, an outer electrode 5, a constant force spring 6, an ignition power supply 7, a main discharge power supply 8, a main discharge capacitor 9 and an electromagnet ring power supply 10, wherein the electromagnet ring 1, the insulating layer 2, the outer electrode 5, the propellant 4, the central electrode 31, the insulating medium layer 32 and the ignition electrode 33 are arranged coaxially from outside to inside, the outer electrode 5 is respectively connected with a first end of the main discharge capacitor 9 and a positive electrode of the main discharge power supply 8, the central electrode 31 is respectively connected with a second end of the main discharge capacitor 9 and a negative electrode of the main discharge power supply 8, the central electrode 31 is connected with the positive electrode of the ignition power supply 7, the ignition electrode 33 is connected with the negative electrode of the ignition power supply 7, two ends of the electromagnet ring 1 are respectively connected with the positive electrode and the negative electrode of the electromagnet ring power supply 10, the constant force spring 6 is connected at a first end to the propellant 4 and at a second end to the outer electrode 5.
When the coaxial steady-state ablation solid propellant pulse plasma thruster provided by the invention works, after the ignition power supply 7 starts a signal, the ignition electrode 33 loads voltage to a certain amplitude, and the ignition electrode 33 generates a small amount of excitation electrons. And exciting electrons to generate a small amount of plasma outside the central electrode 31 under a high-voltage surface flashover mechanism, so that the ignition starting process of the thruster is completed. Under the high-voltage driving of the outer electrode 5 and the central electrode 31, a small amount of plasma generated by ignition starting presents a spiral avalanche effect on the surface of the propellant 4, and arc discharge is formed on the surface of the propellant 4. The thermal energy radiated by the arc discharge ablates the propellant 4 to produce a small amount of neutral gas. Under the action of high voltage, neutral gas is ionized into charged particles and accelerated to be sprayed out by an electromagnetic field generated by self induction.
In the embodiment of the present application, the electromagnetic field direction of the electromagnet ring 1 is perpendicular to the cross section of the outer electrode 5.
In the embodiment of the present application, the magnetic field strength of the electromagnet ring 1 ranges from 0.5T to 3.0T.
In the embodiment of the present application, the thickness of the insulating layer 2 ranges from 5 mm to 20mm, and the material is PTFE or polyimide.
In the embodiment of the present application, the outer electrode 5 is a ring with serrated teeth or triangular teeth.
In the embodiment of the present application, the material of the outer electrode 5 is copper or aluminum.
In the embodiment of the present application, the center electrode 31 is a cylinder with serrated teeth or triangular teeth on the head.
In the embodiment of the present application, the material of the central electrode 31 is copper or aluminum.
In the embodiment of the present application, the ignition electrode 33 is an elongated filament made of copper, tungsten or carbon nanotube.
In the embodiment of the present application, the propellant 4 is annular and is made of PTFE, ETFE, or solid sulfur.
The coaxial steady-state ablation solid propellant pulse plasma thruster provided by the invention has the following beneficial effects:
(1) plasma advances spirally on the surface of the propellant through an electromagnetic field of the electromagnet ring, so that the difference of radial current density can be effectively reduced, and the propulsion performance consistency and the working reliability of the thruster are improved;
(2) the outer electrode and the inner electrode are both provided with sawtooth-shaped or triangular tooth electrodes, the conditions required by starting can be effectively reduced according to the tip discharge principle, and the applicability of the thruster is enhanced.
It is to be understood that the above-described embodiments of the present invention are merely illustrative of or explaining the principles of the invention and are not to be construed as limiting the invention. Therefore, any modification, equivalent replacement, improvement and the like made without departing from the spirit and scope of the present invention should be included in the protection scope of the present invention. Further, it is intended that the appended claims cover all such variations and modifications as fall within the scope and boundaries of the appended claims or the equivalents of such scope and boundaries.
Claims (10)
1. A coaxial steady state ablative solid propellant pulsed plasma thruster, comprising: an electromagnet ring (1), an insulating layer (2), a central electrode (31), an insulating medium layer (32), an ignition electrode (33), a propellant (4), an outer electrode (5), a constant force spring (6), an ignition power supply (7), a main discharge power supply (8), a main discharge capacitor (9) and an electromagnet ring power supply (10), wherein the electromagnet ring (1), the insulating layer (2), the outer electrode (5), the propellant (4), the central electrode (31), the insulating medium layer (32) and the ignition electrode (33) are arranged in the same axial direction from outside to inside, the outer electrode (5) is respectively connected with a first end of the main discharge capacitor (9) and a positive electrode of the main discharge power supply (8), the central electrode (31) is respectively connected with a second end of the main discharge capacitor (9) and a negative electrode of the main discharge power supply (8), center electrode (31) are connected the positive pole of ignition power supply (7), ignition electrode (33) are connected the negative pole of ignition power supply (7), the both ends of electromagnetism magnet ring (1) respectively with the positive negative pole of electromagnetism magnet ring power supply (10) is connected, the first end of constant force spring (6) is connected propellant (4) and the second end is connected outer electrode (5).
2. The coaxial steady-state ablative solid propellant pulsed plasma thruster of claim 1, characterized in that the electromagnetic field direction of the electromagnet ring (1) is perpendicular to the cross section of the outer electrode (5).
3. The coaxial steady-state ablative solid propellant pulsed plasma thruster of claim 2, characterized in that the magnetic field strength of the electromagnet ring (1) ranges from 0.5T to 3.0T.
4. The coaxial steady-state ablation solid propellant pulsed plasma thruster as claimed in claim 1, characterized in that the thickness of the insulating layer (2) ranges from 5 to 20mm and the material is PTFE or polyimide.
5. The coaxial steady-state ablation solid propellant pulsed plasma thruster of claim 1, characterized in that the outer electrode (5) is a circular ring with crenellated teeth or triangular teeth.
6. The coaxial steady-state ablation solid propellant pulsed plasma thruster of claim 5, characterized in that the material of the outer electrode (5) is copper or aluminum.
7. The coaxial steady-state ablative solid propellant pulsed plasma thruster of claim 1, characterized in that the central electrode (31) is a cylinder with crenellated or trigonal teeth on the head.
8. The coaxial steady-state ablative solid propellant pulsed plasma thruster of claim 7, characterized in that the material of the central electrode (31) is copper or aluminum.
9. The coaxial steady-state ablative solid propellant pulsed plasma thruster of claim 1, characterized in that the ignition electrode (33) is in the form of an elongated filament made of copper, tungsten or carbon nanotubes.
10. The coaxial steady-state ablation solid propellant pulsed plasma thruster of claim 1, characterized in that the propellant (4) is annular and is made of PTFE, ETFE or solid sulfur.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110822748.XA CN113530778B (en) | 2021-07-21 | 2021-07-21 | Coaxial steady state ablation solid propellant pulse plasma thruster |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110822748.XA CN113530778B (en) | 2021-07-21 | 2021-07-21 | Coaxial steady state ablation solid propellant pulse plasma thruster |
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| Publication Number | Publication Date |
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| CN113530778A true CN113530778A (en) | 2021-10-22 |
| CN113530778B CN113530778B (en) | 2022-08-02 |
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| CN202110822748.XA Active CN113530778B (en) | 2021-07-21 | 2021-07-21 | Coaxial steady state ablation solid propellant pulse plasma thruster |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2008135078A (en) * | 2008-08-27 | 2010-03-10 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" (RU) | TWO-STAGE ANODE LAYER ENGINE (OPTIONS) |
| CN105952603A (en) * | 2016-04-28 | 2016-09-21 | 中国人民解放军国防科学技术大学 | Laser ablation pulsed plasma thruster |
| CN106499604A (en) * | 2016-12-25 | 2017-03-15 | 袁新平 | Reverse electromagnetic push device |
| CN111561431A (en) * | 2020-04-20 | 2020-08-21 | 哈尔滨工业大学 | Heat radiation anode structure for removing condensation product of iodine working medium electric thruster |
-
2021
- 2021-07-21 CN CN202110822748.XA patent/CN113530778B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2008135078A (en) * | 2008-08-27 | 2010-03-10 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" (RU) | TWO-STAGE ANODE LAYER ENGINE (OPTIONS) |
| CN105952603A (en) * | 2016-04-28 | 2016-09-21 | 中国人民解放军国防科学技术大学 | Laser ablation pulsed plasma thruster |
| CN106499604A (en) * | 2016-12-25 | 2017-03-15 | 袁新平 | Reverse electromagnetic push device |
| CN111561431A (en) * | 2020-04-20 | 2020-08-21 | 哈尔滨工业大学 | Heat radiation anode structure for removing condensation product of iodine working medium electric thruster |
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| Publication number | Publication date |
|---|---|
| CN113530778B (en) | 2022-08-02 |
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Effective date of registration: 20211126 Address after: 300384 No. 6 Huake No. 7 Road, Binhai New Area, Tianjin Binhai High-tech Industrial Development Zone Applicant after: The 18th Research Institute of China Electronics Technology Group Corporation Applicant after: CETC Energy Co.,Ltd. Address before: 300384 No. 6 Huake No. 7 Road, Binhai New Area, Tianjin Binhai High-tech Industrial Development Zone Applicant before: The 18th Research Institute of China Electronics Technology Group Corporation |
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Effective date of registration: 20221116 Address after: 300384 No. 6 Huake No. 7 Road, Binhai New Area, Tianjin Binhai High-tech Industrial Development Zone Patentee after: CETC Energy Co.,Ltd. Address before: 300384 No. 6 Huake No. 7 Road, Binhai New Area, Tianjin Binhai High-tech Industrial Development Zone Patentee before: The 18th Research Institute of China Electronics Technology Group Corporation Patentee before: CETC Energy Co.,Ltd. |
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Address after: 300384 No. 6 Huake No. 7 Road, Binhai New Area, Tianjin Binhai High-tech Industrial Development Zone Patentee after: CETC Blue Sky Technology Co.,Ltd. Address before: 300384 No. 6 Huake No. 7 Road, Binhai New Area, Tianjin Binhai High-tech Industrial Development Zone Patentee before: CETC Energy Co.,Ltd. |