CN102146902A - High-frequency and high-voltage single electrode plasma thruster - Google Patents
High-frequency and high-voltage single electrode plasma thruster Download PDFInfo
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- CN102146902A CN102146902A CN2010101071947A CN201010107194A CN102146902A CN 102146902 A CN102146902 A CN 102146902A CN 2010101071947 A CN2010101071947 A CN 2010101071947A CN 201010107194 A CN201010107194 A CN 201010107194A CN 102146902 A CN102146902 A CN 102146902A
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Abstract
The invention discloses a high-frequency and high-voltage single electrode plasma thruster. The high-frequency and high-voltage single electrode plasma thruster comprises a point electrode, a gas ejection pipe, a high-frequency and high-voltage power supply and the like, and is characterized in that: the high-frequency and high-voltage point electrode is arranged on the central line of the gas ejection pipe; the gas ejection pipe is fixed on an insulation material with a gas inlet channel; a source gas enters the gas ejection pipe through a gas channel in the insulation material and is ejected outward through a gas ejection pipe opening; the high-voltage point electrode is also fixed on the insulation material and connected with the high-frequency and high-voltage power supply; the other end of the high-frequency and high-voltage power supply is grounded; after a line is conducted, a high-frequency and high-voltage electric field is formed at the end of the point electrode and the gas around ionization is punctured so as to form a plasma ejected outward through a spout; and the plasma produces a reverse thrust at the same time. The system is arranged on a space vehicle so as to thrust the space vehicle in the space.
Description
Technical field
The present invention relates to a kind of high-frequency and high-voltage single electrode plasma propulsion device, refer in particular to the plasma generator that single electrode forms discharge, be installed on the astrovehicle and can be used at the space propultion astrovehicle.
Background technique
Aircraft adopts the required propelling dosage that carries of electric propulsion system less than the employing chemical propulsion system, thereby carry-on useful load is increased, or prolongs the life-span of aircraft.
Electric propulsion both can be used as the basic propulsion system of aircraft, also can be used as secondary propulsion system (SPS), and the track of for example satellite orbit rising and adjustment, drag compensation, position maintenance and terrestrial space and interplanetrary flight such as enters at task.Research electric propulsion more widely at present can be divided into electric heating type, electromagnetic type and electrostatic three types.The electric heating type propulsion device is divided into three kinds of resistance heating, arc heating and microwave heatings; Electromagnetic propeller is divided into pulsed plasma propulsion device and steady-state plasma propulsion device; Static advances and is called ion propulsion again.
At present the electrode in the electric propulsion substantially all is that negative electrode and anode occur in pairs, exists circuit complicated, electrode erosion, problem such as efficient is low, and angle of rake reliability and working life be the key issue that needs solution always.Compact structure, consume that working medium is few, the propulsion device of working stability and long service life becomes the focus of research, develops new notion and new propulsion mode can promote the development of space flight Push Technology, thereby has the important engineering application prospect.
The present invention has introduced a kind of high-frequency and high-voltage single electrode plasma propulsion device, is that a kind of structure is simpler, is easier to install and more high efficiency a kind of novel plasma propulsion device.
Summary of the invention
In order to achieve the above object, the object of the present invention is to provide a kind of high-frequency and high-voltage single electrode plasma propulsion device, comprise a point electrode, air jet pipe, high-frequency and high-voltage power supply etc., it is characterized by: a high-frequency and high-voltage point electrode is installed on the air jet pipe center line, this air jet pipe is fixed on the insulating material that is provided with gas-entered passageway, source of the gas gas is to enter into air jet pipe by the gas channel in the insulating material, and is outwards sprayed by the jet mouth of pipe; The high pressure point electrode also is fixed on the insulating material, and be connected with a high voltagehigh frequency power supply, the other end of this high voltagehigh frequency power supply is connected with ground, after circuit is connected, form high-frequency and high-voltage electric field and the gas of breakdown potential from every side in the end of point electrode, form the plasma that outwards sprays by spout, this plasma can produce a deboost simultaneously, and this system is installed on the astrovehicle and can be used at the space propultion astrovehicle.
Described a kind of high-frequency and high-voltage single electrode plasma propulsion device, comprise a point electrode, air jet pipe, high-frequency and high-voltage power supply etc., it is characterized by: this point electrode is to be made by copper or tungsten metallic rod, is to be fixed on the insulating material, and the diameter at its most advanced and sophisticated position is less than 1 millimeter.
Described a kind of high-frequency and high-voltage single electrode plasma propulsion device comprises a point electrode, air jet pipe, high-frequency and high-voltage power supply etc., and it is characterized by: the discharge frequency scope of this high-frequency and high-voltage power supply is the 1-30 Kilohertz, and the voltage of disruptive discharge is greater than 30,000 volts.
Described a kind of high-frequency and high-voltage single electrode plasma propulsion device comprises a point electrode, air jet pipe, high-frequency and high-voltage power supply etc., and it is characterized by: this air jet pipe is to be fixed on the insulating material, and heart position is a point electrode therein.
Described a kind of high-frequency and high-voltage single electrode plasma propulsion device, comprise a point electrode, air jet pipe, high-frequency and high-voltage power supply etc., it is characterized by: be provided with gas-entered passageway in this insulating material, an end of this gas-entered passageway and gas source pipe connect, and the other end and air jet pipe connect.
Described a kind of high-frequency and high-voltage single electrode plasma propulsion device, comprise a point electrode, air jet pipe, high-frequency and high-voltage power supply etc., it is characterized by: after circuit is connected, form high-frequency and high-voltage electric field and the gas of breakdown potential in the end of point electrode, form the plasma line that outwards sprays by spout from every side.
The invention provides a kind of high-frequency and high-voltage single electrode plasma propulsion device, compare with the double electrodes plasma propeller, its advantage is: (1), because be single electrode, avoided the electrode heat loss that double electrodes brought, so its promotion efficient is higher; (2), because be single electrode, its electrode structure is simpler, and equipment is easy to install; (3) consumption working medium is few, an electrodeless ablation.
Predominant use of the present invention is: as the auxiliary propulsion of astrovehicle.
Embodiment
Fig. 1 is a kind of high-frequency and high-voltage single electrode plasma of the present invention propeller structure schematic representation.
See also Fig. 1, a high-frequency and high-voltage point electrode 107 is installed on the center line of an air jet pipe 105, this air jet pipe 105 is fixed on the insulating materials 104 that is provided with inlet channel, the gas of source of the gas 101 is to enter into air jet pipe 105 by the gas passage 109 in the insulating materials 104, and outwards sprayed by the jet mouth of pipe, be provided with gas flow switch 102 at gas pipeline; High pressure point electrode 107 also is fixed on the insulating materials 104, and is connected with a high voltagehigh frequency power supply 108, and the other end of this high voltagehigh frequency power supply 108 is connected with ground. After circuit is connected, form high-frequency and high-voltage electric field and the gas of breakdown potential from every side in the end of point electrode 107, form the plasma 106 that outwards sprays by spout, this plasma can produce a deboost simultaneously, and this system is installed on the spacecraft and can be used at the space propultion spacecraft.
The discharge frequency scope of this high-frequency and high-voltage power supply 108 is 1-30 Kilohertzs, and the voltage of disruptive discharge is greater than 30,000 volts.
This high-frequency and high-voltage point electrode 107 is to be made by copper or tungsten metallic rod, and the diameter at its most advanced and sophisticated position is less than 1 millimeter; This insulating material 104 is to be made by poly-PTFE; This air jet pipe is to be made by quartz tube.
Invention has been described in conjunction with specific embodiments with reference to the accompanying drawings above, yet, need to prove, for a person skilled in the art, under the situation that does not break away from the spirit and scope of the present invention, can make many changes and modification to the foregoing description, these changes and modification all drop in the claim restricted portion of the present invention.
Claims (6)
1. the invention discloses a kind of high-frequency and high-voltage single electrode plasma propulsion device, comprise a point electrode, air jet pipe, high-frequency and high-voltage power supply etc., it is characterized by: a high-frequency and high-voltage point electrode is installed on the air jet pipe center line, this air jet pipe is fixed on the insulating material that is provided with gas-entered passageway, source of the gas gas is to enter into air jet pipe by the gas channel in the insulating material, and is outwards sprayed by the jet mouth of pipe; The high pressure point electrode also is fixed on the insulating material, and is connected with a high voltagehigh frequency power supply, and the other end of this high voltagehigh frequency power supply is connected with ground; After circuit is connected, form high-frequency and high-voltage electric field and the gas of breakdown potential from every side in the end of point electrode, form the plasma that outwards sprays by spout, this plasma can produce a deboost simultaneously, and this system is installed on the astrovehicle and can be used at the space propultion astrovehicle.
2. a kind of high-frequency and high-voltage single electrode plasma propulsion device as claimed in claim 1, comprise a point electrode, air jet pipe, high-frequency and high-voltage power supply etc., it is characterized by: this point electrode is to be made by copper or tungsten metallic rod, be to be fixed on the insulating material, the diameter at its most advanced and sophisticated position is less than 1 millimeter.
3. a kind of high-frequency and high-voltage single electrode plasma propulsion device as claimed in claim 1, comprise a point electrode, air jet pipe, high-frequency and high-voltage power supply etc., it is characterized by: the discharge frequency scope of this high-frequency and high-voltage power supply is the 1-30 Kilohertz, and the voltage of disruptive discharge is greater than 30,000 volts.
4. a kind of high-frequency and high-voltage single electrode plasma propulsion device as claimed in claim 1 comprises a point electrode, air jet pipe, high-frequency and high-voltage power supply etc., and it is characterized by: this air jet pipe is to be fixed on the insulating material, and heart position is a point electrode therein.
5. a kind of high-frequency and high-voltage single electrode plasma propulsion device as claimed in claim 1, comprise a point electrode, air jet pipe, high-frequency and high-voltage power supply etc., it is characterized by: be provided with gas-entered passageway in this insulating material, an end of this gas-entered passageway and gas source pipe connect, and the other end and air jet pipe connect.
6. a kind of high-frequency and high-voltage single electrode plasma propulsion device as claimed in claim 1, comprise a point electrode, air jet pipe, high-frequency and high-voltage power supply etc., it is characterized by: after circuit is connected, form high-frequency and high-voltage electric field and the gas of breakdown potential in the end of point electrode, form the plasma line that outwards sprays by spout from every side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010101071947A CN102146902A (en) | 2010-02-09 | 2010-02-09 | High-frequency and high-voltage single electrode plasma thruster |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2010101071947A CN102146902A (en) | 2010-02-09 | 2010-02-09 | High-frequency and high-voltage single electrode plasma thruster |
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| CN102146902A true CN102146902A (en) | 2011-08-10 |
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| CN2010101071947A Pending CN102146902A (en) | 2010-02-09 | 2010-02-09 | High-frequency and high-voltage single electrode plasma thruster |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103917779A (en) * | 2011-09-09 | 2014-07-09 | 斯奈克玛公司 | Electric propulsion system with stationary plasma thrusters |
| CN104773307A (en) * | 2015-04-30 | 2015-07-15 | 中国科学院宁波材料技术与工程研究所 | Approximate-light-speed particle moving method and system |
| CN104843198A (en) * | 2015-04-03 | 2015-08-19 | 湘潭大学 | Radioactive material with alpha particle cascade decay, propelling plant adopting same and lotus seed propeller |
| CN107476945A (en) * | 2017-09-22 | 2017-12-15 | 中国科学院合肥物质科学研究院 | A kind of high-frequency and high-voltage electromagnetism microwave antigravity propulsion system |
| CN113357109A (en) * | 2021-06-30 | 2021-09-07 | 哈尔滨工业大学 | Ignition device of radio frequency ion thruster |
-
2010
- 2010-02-09 CN CN2010101071947A patent/CN102146902A/en active Pending
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103917779A (en) * | 2011-09-09 | 2014-07-09 | 斯奈克玛公司 | Electric propulsion system with stationary plasma thrusters |
| CN103917779B (en) * | 2011-09-09 | 2017-06-20 | 斯奈克玛公司 | Electric propulsion system with stationary plasma thruster |
| CN104843198A (en) * | 2015-04-03 | 2015-08-19 | 湘潭大学 | Radioactive material with alpha particle cascade decay, propelling plant adopting same and lotus seed propeller |
| CN104773307A (en) * | 2015-04-30 | 2015-07-15 | 中国科学院宁波材料技术与工程研究所 | Approximate-light-speed particle moving method and system |
| CN107476945A (en) * | 2017-09-22 | 2017-12-15 | 中国科学院合肥物质科学研究院 | A kind of high-frequency and high-voltage electromagnetism microwave antigravity propulsion system |
| CN107476945B (en) * | 2017-09-22 | 2023-08-11 | 中国科学院合肥物质科学研究院 | High-frequency high-voltage electromagnetic microwave antigravity propulsion system |
| CN113357109A (en) * | 2021-06-30 | 2021-09-07 | 哈尔滨工业大学 | Ignition device of radio frequency ion thruster |
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Application publication date: 20110810 |