CN111664070B - Metal wire explosion enhanced micro-capillary pulse plasma thruster - Google Patents
Metal wire explosion enhanced micro-capillary pulse plasma thruster Download PDFInfo
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- CN111664070B CN111664070B CN202010749023.8A CN202010749023A CN111664070B CN 111664070 B CN111664070 B CN 111664070B CN 202010749023 A CN202010749023 A CN 202010749023A CN 111664070 B CN111664070 B CN 111664070B
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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 metal wire explosion enhanced microcapillary pulse plasma thruster. The metal wire explosion enhanced type microcapillary pulse plasma thruster comprises an anode nozzle; a capillary cavity mounted on one side of the anode nozzle; a trigger electrode disposed on the capillary cavity; the cathode base is arranged on one side of the capillary cavity far away from the anode nozzle, and a middle hole is formed in the center of the cathode base; a wire having one end extending through the central bore and into the capillary cavity. The metal wire explosion enhanced microcapillary pulse plasma thruster provided by the invention has the advantages of small volume and wide range of expandable output element impulse.
Description
Technical Field
The invention relates to the technical field of miniature electric thrusters, in particular to a metal wire explosion enhanced microcapillary pulse plasma thruster.
Background
The pulse plasma thruster is a pulse plasma device which generates plasma based on spark plug discharge, thereby causing a main energy storage capacitor to discharge to form an electric arc to ablate the surface of a propellant, and the vaporized and decomposed propellant is ejected under the action of electromagnetic force and aerodynamic force to generate thrust. The pulse plasma thruster is mainly used for tasks such as rotation elimination of a micro-nano satellite, orbit positioning (orbit insertion), long-term on-orbit (orbit maintenance), orbit and position adjustment, attitude control, formation flying, orbit unloading and the like. With the continuous development of the aerospace technology, the electric propulsion technology is becoming one of the signs for measuring the advancement of the related satellite platforms. The micro-pulse plasma thruster can generate small and accurate discretization element impulse and meet the requirements of different task parameters. With the increase of the micro on-track time and the increase of the complexity of the executed task, higher requirements are often put on the total impulse and the element impulse adjusting range of the propulsion system. The method further improves the total impact under the condition of keeping the advantages of simple structure, light weight, high specific impact and the like of the propulsion system, and has important significance for the micro-pulse plasma thruster.
The conventional micro pulse plasma thruster generally needs surface discharge triggering of a semiconductor spark plug, and the service life of the spark plug is limited by the problems of large complexity, carbon deposition and the like of an external triggering system, so that the short service life of the system is influenced; in addition, the existing pulse plasma propulsion technology has the problems of small impulse of an output element, narrow range, low total impulse, low efficiency and the like.
Therefore, there is a need to provide a new wire explosion enhanced microcapillary pulsed plasma thruster to solve the above technical problems.
Disclosure of Invention
The invention solves the technical problem of providing a metal wire explosion enhanced microcapillary pulse plasma thruster with small volume and strong output element impulse expansion capability.
In order to solve the technical problem, the metal wire explosion enhanced micro-capillary pulse plasma thruster provided by the invention comprises:
an anode nozzle;
a capillary cavity mounted on one side of the anode nozzle;
a trigger electrode disposed on the capillary cavity;
the cathode base is arranged on one side of the capillary cavity far away from the anode nozzle, and a middle hole is formed in the center of the cathode base;
a wire having one end extending through the central bore and into the capillary cavity.
Preferably, both ends of the capillary cavity are provided with internal threads, the anode nozzle and the cathode base are provided with external threads, and the anode nozzle, the capillary cavity and the cathode base are tightly connected through threads.
Preferably, the trigger electrode is located close to the cathode base, the distance between the trigger electrode and the cathode base is in millimeter order, and the gap between the trigger electrode and the cathode base forms a trigger edge surface.
Preferably, a metal wire sheath ceramic tube is installed in the central hole, and the metal wire penetrates through the metal wire sheath ceramic tube.
Preferably, one side of the cathode base is provided with a wire feeding mechanism, and the wire feeding mechanism is matched with the metal wire.
Preferably, the capillary cavity is made of polytetrafluoroethylene.
Preferably, the lower end of the metal wire is connected with a metal wire driving circuit, and the metal wire driving circuit is used for enhancing the electric explosion effect of the metal wire.
Preferably, the bottom side of the cathode base is connected with a cathode lead, the bottom side of the anode nozzle is connected with an anode nozzle lead, and the cathode lead and the anode nozzle are connected with the same main discharge capacitor.
Preferably, the bottom side of the trigger electrode is connected with a trigger electrode lead, and the trigger electrode lead is connected with a trigger circuit to form creeping discharge and realize stable triggering of the capillary cavity.
Compared with the related technology, the metal wire explosion enhanced type microcapillary pulse plasma thruster provided by the invention has the following beneficial effects:
the invention provides a metal wire explosion enhanced microcapillary pulse plasma thruster, which generates initial plasma by the discharge along the surface of a micro gap between a trigger electrode and a cathode base to induce main gap discharge; after the main gap discharge is formed, the metal wire discharge loop is conducted to induce the metal wire explosion; the original spark plug structure is replaced by a micro-gap triggering mode, so that the volume of the device is greatly reduced; the output unit impulse can be obviously enhanced by metal wire explosion, and the output range of single unit impulse can be flexibly expanded by adjusting the length of the metal wire, so that the requirements of different tasks on unit impulse during long-term in-orbit operation of the micro-nano satellite are met.
Drawings
FIG. 1 is a schematic structural diagram of a wire explosion enhanced micro-capillary pulsed plasma thruster in accordance with a preferred embodiment of the present invention;
reference numbers in the figures: 1. the device comprises an anode nozzle, 2, a capillary cavity, 3, a trigger electrode, 4, a cathode base, 5, a metal wire sheath ceramic tube, 6, a wire feeding mechanism, 7, a metal wire, 8, a metal wire driving circuit, 9, a cathode lead, 10, a trigger electrode lead, 11 and an anode nozzle lead.
Detailed Description
The invention is further described with reference to the following figures and embodiments.
Referring to fig. 1, the wire explosion enhanced microcapillary pulsed plasma thruster includes:
an anode nozzle 1;
the capillary cavity 2 is arranged on one side of the anode nozzle 1;
the trigger electrode 3 is arranged on the capillary cavity 2;
the cathode base 4 is installed on one side, away from the anode nozzle 1, of the capillary cavity 2, and a middle hole is formed in the center of the cathode base 4;
a wire 7, one end of said wire 7 extending through said central aperture and into said capillary cavity 2.
The both ends of capillary cavity 2 all are provided with the internal thread, anode nozzle 1 with be provided with the external screw thread on the negative pole base 4, anode nozzle 1 capillary cavity 2 with negative pole base 4 passes through screw thread zonulae occludens.
The trigger electrode 3 is located at a position close to the cathode base 4, the distance between the trigger electrode 3 and the cathode base 4 is millimeter magnitude, and a gap between the trigger electrode 3 and the cathode base 4 forms a trigger edge surface.
And a metal wire sheath ceramic tube 5 is arranged in the middle hole, and the metal wire 7 penetrates through the metal wire sheath ceramic tube 5.
One side of the cathode base 4 is provided with a wire feeding mechanism 6, and the wire feeding mechanism 6 is matched with the metal wire 7.
The capillary cavity 2 is made of polytetrafluoroethylene materials, and under the ablation effect of the high-temperature high-density electric arc, the materials are continuously subjected to phase change and decomposition to enter the cavity, so that the pressure inside the cavity is increased, the plasma continuously moves towards the nozzle under the action of pressure gradient, and finally is sprayed outwards to generate thrust.
The lower end of the metal wire 7 is connected with a metal wire driving circuit 8, and the metal wire driving circuit 8 is used for enhancing the electric explosion effect of the metal wire 7.
The bottom side of the cathode base 4 is connected with a cathode lead 9, the bottom side of the anode nozzle 1 is connected with an anode nozzle lead 11, and the cathode lead 9 and the anode nozzle are connected with the same main discharge capacitor.
The bottom side of the trigger electrode 3 is connected with a trigger electrode lead 10, the trigger electrode lead 10 is connected with a trigger circuit, creeping discharge is formed, and stable triggering of the capillary cavity is realized.
The working principle of the metal wire explosion enhanced microcapillary pulse plasma thruster provided by the invention is as follows:
1. applying trigger high-voltage pulse to the trigger electrode 3 to induce the generation of creeping discharge in the trigger gap;
2. plasma generated by the gap creeping discharge is triggered to move towards the anode nozzle 1 under the action of electric field force, and creeping discharge is induced to occur in the capillary cavity 2; after the inner part of the capillary cavity 2 is formed by surface discharge, the electric energy stored by the energy storage capacitor is released through the cathode lead 9 and the anode nozzle lead 11, so that a discharge channel gradually forms high-temperature high-density plasma electric arcs; the capillary cavity 2 is made of polytetrafluoroethylene materials, and under the ablation action of the high-temperature high-density electric arc, the polytetrafluoroethylene materials are continuously subjected to phase change and decomposition to enter the cavity, so that the pressure inside the cavity is increased, the plasma continuously moves towards the nozzle under the action of pressure gradient, and finally is sprayed outwards to generate thrust;
3. when a discharge channel of the capillary cavity 2 is formed, the end part of the metal wire is communicated with the anode nozzle 1, the stored energy of the metal wire driving circuit 8 is released to the metal wire, the metal wire is induced to explode, and plasma is sprayed outwards; the high-speed high-density high-mass-density metal plasma is sprayed outwards through the anode nozzle to generate a reverse thrust, so that the impulse of an output element of the thruster can be obviously increased.
Compared with the related technology, the metal wire explosion enhanced type microcapillary pulse plasma thruster provided by the invention has the following beneficial effects:
the invention provides a metal wire explosion enhanced microcapillary pulse plasma thruster, which generates initial plasma by the discharge along the surface of a micro gap between a trigger electrode and a cathode base to induce main gap discharge; after the main gap discharge is formed, the metal wire discharge loop is conducted to induce the metal wire explosion; the original spark plug structure is replaced by a micro-gap triggering mode, so that the volume of the device is greatly reduced; the output unit impulse can be obviously enhanced by metal wire explosion, and the output range of single unit impulse can be flexibly expanded by adjusting the length of the metal wire, so that the requirements of different tasks on unit impulse during long-term in-orbit operation of the micro-nano satellite are met.
The above description is only an embodiment of the present invention, and not intended to limit the scope of the present invention, and all modifications of equivalent structures and equivalent processes, which are made by using the contents of the present specification and the accompanying drawings, or directly or indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (6)
1. The utility model provides a little capillary pulse plasma thrustor of wire explosion enhancement mode which characterized in that includes:
an anode nozzle;
a capillary cavity mounted on one side of the anode nozzle;
a trigger electrode disposed on the capillary cavity;
the cathode base is arranged on one side of the capillary cavity far away from the anode nozzle, and a middle hole is formed in the center of the cathode base;
a wire having one end extending through the central bore and into the capillary cavity;
the trigger electrode is positioned close to the cathode base, the distance between the trigger electrode and the cathode base is millimeter magnitude, and a gap between the trigger electrode and the cathode base forms a trigger edge surface;
one side of the cathode base is provided with a wire feeding mechanism, and the wire feeding mechanism is matched with the metal wire;
the bottom side of the trigger electrode is connected with a trigger electrode lead wire, and the trigger electrode lead wire is connected with a trigger circuit to form creeping discharge and realize stable triggering of the capillary cavity.
2. The metal wire explosion enhancement type microcapillary pulse plasma thruster according to claim 1, wherein internal threads are arranged at both ends of the capillary cavity, external threads are arranged on the anode nozzle and the cathode base, and the anode nozzle, the capillary cavity and the cathode base are tightly connected through threads.
3. The metal wire explosion enhancement type microcapillary pulse plasma thruster according to claim 1, wherein a metal wire sheath ceramic tube is installed in the central hole, and the metal wire penetrates through the metal wire sheath ceramic tube.
4. The metal wire explosion enhanced microcapillary pulsed plasma thruster according to claim 1, wherein the capillary cavity is made of polytetrafluoroethylene material.
5. The metal wire explosion enhancement type microcapillary pulse plasma thruster according to claim 1, wherein the lower end of the metal wire is connected with a metal wire driving circuit, and the metal wire driving circuit is used for enhancing the electric explosion effect of the metal wire.
6. The metal wire explosion enhancement type micro-capillary pulse plasma thruster according to claim 1, wherein a cathode lead is connected to the bottom side of the cathode base, an anode nozzle lead is connected to the bottom side of the anode nozzle, and the cathode lead and the anode nozzle are connected to the same main discharge capacitor.
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| CN112582884B (en) * | 2020-11-05 | 2022-03-08 | 西安交通大学 | Gas switch structure based on low-working-coefficient low-jitter triggering |
| CN112682286A (en) * | 2020-12-11 | 2021-04-20 | 中国电子科技集团公司第十二研究所 | High-reliability hollow cathode structure for electric propulsion |
| CN113623159A (en) * | 2021-09-18 | 2021-11-09 | 西安交通大学 | Propellant automatic supply device of coaxial vacuum arc propeller |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2468543C1 (en) * | 2011-08-01 | 2012-11-27 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Казанский национальный исследовательский технический университет им. А.Н. Туполева-КАИ" (КНИТУ-КАИ) | Method for organisation of working process in chamber of laser rocket engine, and laser rocket engine |
| RU2612312C1 (en) * | 2015-11-13 | 2017-03-06 | Федеральное государственное бюджетное образовательное учреждение высшего образования "Юго-Западный государственный университет" (ЮЗГУ) | Artificial satellite |
| CN107061210A (en) * | 2017-05-18 | 2017-08-18 | 西安交通大学 | It is a kind of that the pulsed plasma thruster accelerated is mixed based on electrothermal and electromagnetic |
| CN110630460A (en) * | 2019-10-17 | 2019-12-31 | 北京航空航天大学 | Segmented anode high specific impulse pulse plasma thruster |
-
2020
- 2020-07-30 CN CN202010749023.8A patent/CN111664070B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2468543C1 (en) * | 2011-08-01 | 2012-11-27 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Казанский национальный исследовательский технический университет им. А.Н. Туполева-КАИ" (КНИТУ-КАИ) | Method for organisation of working process in chamber of laser rocket engine, and laser rocket engine |
| RU2612312C1 (en) * | 2015-11-13 | 2017-03-06 | Федеральное государственное бюджетное образовательное учреждение высшего образования "Юго-Западный государственный университет" (ЮЗГУ) | Artificial satellite |
| CN107061210A (en) * | 2017-05-18 | 2017-08-18 | 西安交通大学 | It is a kind of that the pulsed plasma thruster accelerated is mixed based on electrothermal and electromagnetic |
| CN110630460A (en) * | 2019-10-17 | 2019-12-31 | 北京航空航天大学 | Segmented anode high specific impulse pulse plasma thruster |
Non-Patent Citations (2)
| Title |
|---|
| 毛细管型脉冲等离子体推力器研究现状综述;王亚楠，丁卫东，程乐，李悦，孙安邦;《电工技术学报》;20181024;全文 * |
| 水中裸铜丝与镀膜铜丝电***积分光谱与;韩若愚，吴佳玮，周海滨，邱爱慈;《电工技术学报》;20171023;全文 * |
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