CN109386443A - Array type capacity Coupled RF Plasma micro-thruster - Google Patents
Array type capacity Coupled RF Plasma micro-thruster Download PDFInfo
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- CN109386443A CN109386443A CN201811136088.4A CN201811136088A CN109386443A CN 109386443 A CN109386443 A CN 109386443A CN 201811136088 A CN201811136088 A CN 201811136088A CN 109386443 A CN109386443 A CN 109386443A
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- antenna
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- thrust chamber
- plasma
- power supply
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Classifications
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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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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Plasma Technology (AREA)
Abstract
The invention discloses a kind of array type capacity Coupled RF Plasma micro-thrusters, including gas source, valve, antenna, thrust chamber and power supply.Gas source is connected directly with thrust chamber, and valve can be controlled separately each thrust chamber switch, and antenna is wound around outside thrust chamber and connects with power supply.The pocket rocket bulk and overall quality are minimum, and momentum pulse is low, it can be achieved that micro- ox is to the thrust of milli ox magnitude, and average power consumption is low, while can realize precision vector control, are suitably equipped with micro-satellite and keep for high-precision attitude control and relative orbit position.
Description
Technical field:
The present invention is suitable for plasma propulsion technical field, i.e., high integration, low-power consumption, low thrust, micro- momentum it is micro-
Type propulsion system can be applied to micro-satellite (microsatellite, Nano satellite, Pi Weixing) formation flight and composition constellation, especially needle
Design to capacitive couplings radio frequency plasma micromass culture (pocket rocket).
Background technique:
Propulsion system is the key subsystem that spacecraft executes the tasks such as orbit maneuver and special gesture stability, but nearly two
The micro-satellite developed in the world over 10 years is not equipped with propulsion system, or only extremely limited maneuverability nearly all, main
It wants the reason is that the volume and quality of traditional propulsion system are all very big, unsuitable micro-satellite uses.However, with micro-satellite
The development of technology and its expansion of application field, more more and more urgent demand is proposed to micromass culture system.Micro-satellite is formed into columns
Flight and composition constellation, can complete the impossible work of large satellite of many complex and expensives, such as form distributed spaceborne load
Wave radar, satellite three-dimensional imaging and high resolution synthetic aperture remote sensing of the earth etc..But above-mentioned task is completed, to inter-satellite
Relative orbit position is kept, high-precision attitude control proposes very high requirement, specific as follows:
First, micro-satellite is small in size, light weight, rotary inertia are small, for pushing away needed for satellite orbit and gesture stability
Power is small and precision prescribed is high, usually micro- wild marjoram milli ox magnitude；
Second, the target of micro-satellite formation flight is to maintain intersatellite relative position rather than absolute position, is needed
Minimum momentum pulse it is very small, generally according to control accuracy requirement with control the period it is different, required momentum pulsating sphere is 10^
9Ns~10^3Ns magnitude；
Third, the supply voltage that micro-satellite is capable of providing is not high, is 3V~12V under normal conditions, highest to be
28V, and general power is generally 1W to tens of watts magnitudes.
Therefore, it is necessary to study high integration, the low function for being suitable for the holding of micro-satellite track, orbit maneuver and gesture stability
Consumption, the miniature propulsion system of low thrust and micro- momentum.
Pocket rocket is a kind of new concept capacitive couplings radio frequency plasma micromass culture technology, belongs to electrothermal micromass culture,
Bulk and overall quality are all very small, and momentum pulse is very low, it can be achieved that thrust of micro- ox to milli ox magnitude, average power consumption
Therefore only 10-100W is very suitable to be equipped with micro-satellite for high-precision attitude control and the holding of relative orbit position.But
The thrust of single tube pocket rocket is excessively small and weak, so that needing multitube parallel when practical application.
Summary of the invention:
In order to solve deficiency of the prior art, the present invention provides a kind of array type capacity coupled RF plasmas
Body micro-thruster --- single side array pocket rocket.
Array type capacity Coupled RF Plasma micro-thruster includes gas source, valve, antenna, thrust chamber and power supply.Battle array
Gas source one end is connected with collection chamber in column capacitive coupling radio frequency plasma micro-thruster, and plasma beam produces in thrust chamber
It is raw, it sprays to form thrust to the other end, needs to be placed in vacuum interior structure vacuum environment in laboratory.
Gas source is connected directly with each thrust chamber, is individually controlled by valve；
Antenna connects with power supply, and is wound around outside thrust chamber, for exciting plasma；
Power supply is 13.56Mhz radio-frequency power supply.
Gas source air inlet end is passed through gas, and the other end is connected with thrust chamber, and using gas is air or inert gas, inertia
Gas includes argon gas, helium, xenon one of which.
In array type capacity Coupled RF Plasma micro-thruster, thrust chamber is 3 × 3 arrays in embodiment；
Optionally, thrust chamber can use 2 × 2,4 × 4 or other specific embodiments.
Gas source using gas can be air, nitrogen or inert gas, and inert gas includes argon gas, helium, xenon etc..
The utility model has the advantages that
The array type capacity Coupled RF Plasma micro-thruster, i.e. single side array pocket rocket bulk and
Overall quality is all very small, in one embodiment, having a size of 100 × 100 × 18 (units: mm).
The array type capacity Coupled RF Plasma micro-thruster belongs to electric propulsion system, with chemical propulsion system phase
Than that will not generate blocking, small size nozzle venturi can be used, realize micro thrust.For accurately controlling micro-satellite posture
When with orbital position, electric propulsion has high specific impulse, the advantage of low thrust, but traditional electric propulsion device needs a large amount of electrical power (1-
2kW), the array type capacity Coupled RF Plasma micro-thruster is low in energy consumption, and in one embodiment, each thrust chamber is flat
Only 10-100W, the micro-satellite for being highly suitable for power limited realize high-precision attitude control and relative orbit position to equal power consumption
Set holding.
Detailed description of the invention:
In order to illustrate more clearly of technical solution of the present invention, briefly introduce below to attached drawing in one embodiment.
Fig. 1 is 3 × 3 array type capacity Coupled RF Plasma micro-thruster structural schematic diagram of single side and three-view diagram
(a- side view, b- front view, c- dorsal view, unit mm).
In Fig. 1: 1- gas source, 2- valve, 3- antenna, 4- thrust chamber, 5- power supply, 6- plasma jet
Wherein plasma jet (6) non-array formula capacitive coupling radio frequency plasma micro-thruster forms component, by
Power supply excitation generates.
Fig. 2 is array type capacity Coupled RF Plasma micro-thruster igniting distribution and dummy satellite steering corresponding relationship
Measuring principle schematic diagram.
Specific embodiment:
Below in conjunction with the drawings and specific embodiments, the present invention will be further described.
Array type capacity Coupled RF Plasma micro-thruster, including gas source, valve, antenna, thrust chamber and power supply.
In such as Fig. 1 embodiment, using 3 × 3 array type capacity Coupled RF Plasma micro-thruster of single side.
Antenna (3) is wound around on thrust chamber (4), capacitive coupling antenna, inductive coupling antenna, LC coupling can be used in antenna
Close antenna, the common plasma antenna such as spiral wave antenna.
Each thrust chamber (4) switch is individually controlled using valve (2).
Single side array type capacity Coupled RF Plasma micro-thruster is placed in vacuum warehouse, vacuumizing makes air pressure to finger
Definite value.
Gas is passed through at gas source (1), gas is air or inert gas.
It opens power supply (5) and adjusts watt level, by power control in 10-100W, generate plasma in thrust chamber and penetrate
It flows (6).
Make it by measurement array type capacity Coupled RF Plasma micro-thruster plane and unidirectional light source projection angle
It realizes and the precision vector of micro-satellite is controlled.
It is high to be applied to micro-satellite below with reference to Fig. 2 specific explanations array type capacity Coupled RF Plasma micro-thruster
Controlling model when precision gesture stability.
When realizing accurate vector controlled, array type capacity Coupled RF Plasma micro-thruster is assembled in satellite mould
In one plane of type, using the normal direction pointer in a unidirectional light source (7) and the plane, single and various combination push away is measured
The angle (Z axis is method line projection) that the pointer projects in the plane when power room is lighted a fire can determine the distribution of two-dimensional points fire and satellite
Corresponding relationship between model steering, finally establishes the essence of two-dimensional planar array formula capacitive coupling radio frequency plasma micro-thruster
True Vector Control Model.
Particular embodiments described above has carried out further detailed description to technical solution of the present invention, all at this
Within the spirit and principle of invention, any modification made, replacement be should all be included in the protection scope of the present invention.
Claims (4)
1. array type capacity Coupled RF Plasma micro-thruster, feature includes: gas source (1), valve (2), antenna (3),
Thrust chamber (4), power supply (5)；
The gas source (1) is connected directly with each thrust chamber (4), is individually controlled by valve (2)；
The antenna (3) connects with power supply (5), and is wound around outside thrust chamber, for exciting plasma；
The power supply is 13.56Mhz radio-frequency power supply.
2. one end is passed through gas according to gas source described in right 1 (1), the other end is connected with thrust chamber (4), and using gas can be with
For air, nitrogen or inert gas.
3. being arranged on the same face of gas source according to thrust chamber described in right 1 (4) in array.
4. according to antenna described in right 1 (3), including capacitive coupling antenna, inductive coupling antenna, inductant-capacitance coupling antenna, helicon
The common plasma antenna such as antenna；
The antenna (3) uses copper, tungsten or other metal materials.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811136088.4A CN109386443A (en) | 2018-09-28 | 2018-09-28 | Array type capacity Coupled RF Plasma micro-thruster |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811136088.4A CN109386443A (en) | 2018-09-28 | 2018-09-28 | Array type capacity Coupled RF Plasma micro-thruster |
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| CN109386443A true CN109386443A (en) | 2019-02-26 |
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| CN201811136088.4A Pending CN109386443A (en) | 2018-09-28 | 2018-09-28 | Array type capacity Coupled RF Plasma micro-thruster |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109751214A (en) * | 2019-03-25 | 2019-05-14 | 哈尔滨工业大学 | A kind of micro-ox level quick response Flied emission thruster that thrust is continuously adjusted on a large scale |
| CN110145446A (en) * | 2019-06-13 | 2019-08-20 | 哈尔滨工业大学 | A kind of micro- ox propulsion device of pulse electrical excitation |
| CN110230581A (en) * | 2019-06-13 | 2019-09-13 | 哈尔滨工业大学 | A kind of micro-ox level ion propulsion device of vortex resonance ionization |
| CN112109924A (en) * | 2020-08-21 | 2020-12-22 | 北京控制工程研究所 | Three-dimensional vector direction array type micro-cathode discharge propulsion system |
| CN112392675A (en) * | 2020-10-23 | 2021-02-23 | 北京精密机电控制设备研究所 | Array type electric heating plasma accelerating device |
| CN113090484A (en) * | 2021-03-30 | 2021-07-09 | 电子科技大学 | Thrust adjusting device of helicon wave plasma electric thruster |
| CN113173266A (en) * | 2021-04-16 | 2021-07-27 | 中国科学院合肥物质科学研究院 | Plasma vector propeller without moving part |
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| CN101941529A (en) * | 2010-09-08 | 2011-01-12 | 北京理工大学 | Layout method for micro attitude and orbit control thruster array |
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| US7827779B1 (en) * | 2007-09-10 | 2010-11-09 | Alameda Applied Sciences Corp. | Liquid metal ion thruster array |
| CN101941529A (en) * | 2010-09-08 | 2011-01-12 | 北京理工大学 | Layout method for micro attitude and orbit control thruster array |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109751214A (en) * | 2019-03-25 | 2019-05-14 | 哈尔滨工业大学 | A kind of micro-ox level quick response Flied emission thruster that thrust is continuously adjusted on a large scale |
| CN110145446A (en) * | 2019-06-13 | 2019-08-20 | 哈尔滨工业大学 | A kind of micro- ox propulsion device of pulse electrical excitation |
| CN110230581A (en) * | 2019-06-13 | 2019-09-13 | 哈尔滨工业大学 | A kind of micro-ox level ion propulsion device of vortex resonance ionization |
| CN110145446B (en) * | 2019-06-13 | 2020-05-12 | 哈尔滨工业大学 | Pulse electrically-excited micro-cow propulsion device |
| CN112109924A (en) * | 2020-08-21 | 2020-12-22 | 北京控制工程研究所 | Three-dimensional vector direction array type micro-cathode discharge propulsion system |
| CN112392675A (en) * | 2020-10-23 | 2021-02-23 | 北京精密机电控制设备研究所 | Array type electric heating plasma accelerating device |
| CN112392675B (en) * | 2020-10-23 | 2022-03-04 | 北京精密机电控制设备研究所 | Array type electric heating plasma accelerating device |
| CN113090484A (en) * | 2021-03-30 | 2021-07-09 | 电子科技大学 | Thrust adjusting device of helicon wave plasma electric thruster |
| CN113090484B (en) * | 2021-03-30 | 2022-02-01 | 电子科技大学 | Thrust adjusting device of helicon wave plasma electric thruster |
| CN113173266A (en) * | 2021-04-16 | 2021-07-27 | 中国科学院合肥物质科学研究院 | Plasma vector propeller without moving part |
| CN113173266B (en) * | 2021-04-16 | 2024-04-09 | 中国科学院合肥物质科学研究院 | Plasma vector propeller without moving parts |
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Application publication date: 20190226 |