CN109185090A - A kind of Multi-section high-efficient rate pulsed plasma thruster - Google Patents
A kind of Multi-section high-efficient rate pulsed plasma thruster Download PDFInfo
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- CN109185090A CN109185090A CN201811275159.9A CN201811275159A CN109185090A CN 109185090 A CN109185090 A CN 109185090A CN 201811275159 A CN201811275159 A CN 201811275159A CN 109185090 A CN109185090 A CN 109185090A
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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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- 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
- F03H1/0006—Details applicable to different types of plasma thrusters
-
- 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
- F03H1/0006—Details applicable to different types of plasma thrusters
- F03H1/0018—Arrangements or adaptations of power supply systems
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- Chemical & Material Sciences (AREA)
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- General Engineering & Computer Science (AREA)
- Plasma Technology (AREA)
Abstract
A kind of Multi-section high-efficient rate pulsed plasma thruster disclosed by the invention, belongs to micro-nano satellite micromass culture field.The present invention is mainly made of one section of anode, one section of cathode, two sections of anodes, two sections of cathodes, insulating segment, trigger electrode, triggering working medium, energy capacitance set, propellant, clad and external shell.Thruster electrode is divided to two sections, and each segment electrode provides voltage by respective storage capacitor, gross energy is distributed to different capacitors by realization, and it discharges in different location, to which propellant ablation ionization process and plasma accelerator be separated, make more energy for plasma accelerator, can be improved the acceleration efficiency of thruster entirety.Triggering working medium is ionized by trigger electrode ablation and generates a small amount of plasma, makes the breakdown voltage between a segment electrode that the triggering in favor of initial discharge be greatly reduced, and then improve the reliability of thruster work.The present invention is suitable for the application of low-power wiener satellite, meets corresponding task thrust requirements.
Description
Technical field
The present invention relates to a kind of Multi-section high-efficient rate pulsed plasma thrusters, belong to micro-nano satellite micromass culture field.
Background technique
In recent years, with the fast development of space technology, micro-nano satellite because have small in size, low in energy consumption, transmit cycle is short,
The features such as light weight and cost is low, function expansibility is receive more and more attention, has a extensive future.With several micro-nanos
Satellites formation forms big " virtual satellite ", and by the collaborative signal processing between micro-nano satellite, achievable earth observation is led to
Believe the tasks such as navigation, target reconnaissance.Therefore, the mission requirements of micro-nano satellite and flight space environment make its propulsion system need to meet
Claimed below: light-weight, low-power consumption, small in size, thrust is accurate.Traditional Push Technology is because of thrust fineness and thrust output phase
To coarse, it is difficult to meet high-precision thrust requirements.Pulsed plasma thruster have than leaping high, it is simple and compact for structure, control
Make it is convenient, flexible, micro-nano satellite thrust requirements can be can satisfy the steady operation under low-power the features such as.But with Novel electric
The continuous development of Push Technology, the disadvantage that its reliability of traditional pulsed plasma thruster is low, propulsive efficiency is low are gradually shown
Dew.
Summary of the invention
Failure reliability deficiency, energy conversion are easy in order to solve traditional pulse plasma thruster ignition initiation devices
The problems such as low efficiency, a kind of Multi-section high-efficient rate pulsed plasma thruster disclosed by the invention, the technology mainly solved are asked
Topic is: improving pulsed plasma thruster ignition initiation devices reliability and energy conversion efficiency.
The purpose of the present invention is what is be achieved through the following technical solutions.
A kind of Multi-section high-efficient rate pulsed plasma thruster disclosed by the invention, the thruster structure is mainly by one
Section anode, one section of cathode, two sections of anodes, two sections of cathodes, insulating segment, trigger electrode, triggering working medium, energy capacitance set, propellant, packet
Coating and external shell composition.
Thruster is integrally in coaxial structure, and electrode is divided into two sections, and the first segment electrode is mainly used for propellant ablation
Ionization process；Second segment electrode is mainly used for plasma accelerator.First segment electrode is by one section of anode and one section of cathode sets
At one section of anode and one section of cathode are coaxial annulus, and circular ring shape propellant is located at one section of anode annulus and one section of cathode ring
Between, one section of anode annulus is located on the outside of propellant, and one section of cathode ring is located on the inside of propellant.One section of anode and two sections of anodes
Between separated by the insulating segment of circular ring shape.Two sections of anodes are with one section of anode with the annulus of the diameter of axle.Two sections of cathodes are solid cylinder,
Two sections of cathodes pass through one section of cathode inner ring.Influence for two sections of cathodes of isolation to a segment electrode and insulating segment, two sections of cathode externals
It is coated by clad.Clad is successively cased with trigger electrode, triggering working medium, one section of cathode, the trigger electrode, triggering work from the inside to the outside
Matter, one section of cathode collectively constitute ignition initiation devices.One segment electrode, two-section electrode and ignition initiation devices are by respective energy storage electricity
Hold and voltage is provided.It to avoid tail portion from discharging, and is the connection convenient for each segment electrode and external power supply, two sections of yin of thruster tail portion
Pole, clad, trigger electrode, triggering working medium and one section of cathode are stepped.One section of anode, insulating segment and two sections of anodes pass through one end
The external shell of convex is fixed, and realizes the purpose that thruster electrode is isolated with external environment.
Since thruster electrode is divided to two sections, and each segment electrode provides voltage by respective storage capacitor, realizes gross energy
Different capacitors is distributed to, and is discharged in different location, so that propellant ablation ionization process and plasma be accelerated
Journey separates, and makes more energy for plasma accelerator, can be improved the acceleration efficiency of thruster entirety.
Triggering working medium is ionized by trigger electrode ablation and generates a small amount of plasma, makes breakdown voltage between a segment electrode substantially
The triggering in favor of initial discharge is reduced, and then improves the reliability of thruster work.
The working method of a kind of Multi-section high-efficient rate pulsed plasma thruster disclosed by the invention are as follows: firstly, respectively
For a segment electrode, two-section electrode and ignition initiation devices provide voltage storage capacitor charging, due between a segment electrode in vacuum
Under the conditions of lack turn-on condition, can not voluntarily puncture；Due to trigger electrode breakdown voltage very little, puncture prior to a segment electrode, triggering
Electric current ablation between pole and one section of cathode triggers working medium, and the neutral gas that ablation generates ionizes in the electric field, to generate a small amount of
Plasma；The plasma of generation is full of between a segment electrode, the breakdown voltage between a segment electrode is greatly reduced in favor of
The triggering of initial discharge, and then improve the reliability of thruster work.Therefore, puncture to generate high current between a segment electrode,
Electric current ablation propellant generates neutral gas, and under the action of high voltage, the neutral gas that ablation goes out is ionized to plasma
Group；After the plasma of generation is detached from propellant surface, electric field between a segment electrode and self-induction magnetic field under the action of, accelerates edge
Insulating segment is sprayed to two-section electrode；After plasma reaches two-section electrode, since there are high voltage, plasmas between two-section electrode
Group accelerates along axial until being pushed out, generation impulse force again under the action of electric field and self-induction magnetic field.
The utility model has the advantages that
1, the present invention a kind of Multi-section high-efficient rate pulsed plasma thruster is disclosed, by by electrode be divided into two sections and by
Different capacitors provides energy, the different distribution of gross energy is realized, so that propellant ablation ionization process and plasma be added
Fast process separates, to improve the acceleration efficiency of thruster entirety.
2, the present invention discloses a kind of Multi-section high-efficient rate pulsed plasma thruster, has abandoned traditional pulse plasma
The plug ignition starter of thruster ionizes triggering working medium by trigger electrode ablation and generates a small amount of plasma, makes one section
The triggering that interelectrode breakdown voltage is greatly reduced in favor of initial discharge, and then improve the reliability of thruster work.
3, a kind of Multi-section high-efficient rate pulsed plasma thruster disclosed by the invention is suitable for low-power wiener satellite
Application, meet corresponding task thrust requirements, including gesture stability, position is kept, drag compensation etc..
Detailed description of the invention
Fig. 1 Multi-section high-efficient rate pulsed plasma thruster structural schematic diagram
Fig. 2 Multi-section high-efficient rate pulsed plasma thruster front schematic three dimensional views
Fig. 3 Multi-section high-efficient rate pulsed plasma thruster tail portion schematic three dimensional views
Wherein: 1- trigger electrode, 2- trigger working medium, mono- section of cathode of 3-, 4- propellant, 5- insulating segment, 6- external shell, 7- bis-
Section anode, bis- sections of cathodes of 8-, 9- clad, mono- section of anode of 10-, 11- storage capacitor.
Specific embodiment
Objects and advantages in order to better illustrate the present invention with reference to the accompanying drawing do further summary of the invention with example
Explanation.
Embodiment 1:
A kind of Multi-section high-efficient rate pulsed plasma thruster disclosed in the present embodiment, thruster structure is mainly by one section
10, one sections of anode, 3, two sections of cathode anode, 7, two sections of cathodes 8, insulating segment 5, trigger electrode 1, triggering working medium 2, energy capacitance set 11,
Propellant 4, clad 9 and external shell 6 form.
Thruster is integrally in coaxial structure, and electrode is divided into two sections, and the first segment electrode is mainly used for propellant ablation
Ionization process, the second segment electrode are mainly used for plasma accelerator.First segment electrode is by one section of anode 10 and one section of cathode 3
Composition, one section of anode 10 and one section of cathode 3 are the coaxial annulus of brass material, wherein one section of anode 10, internal diameter 9mm, outside
Diameter 10mm, length 25mm, one section of cathode 3, internal diameter 3mm, outer diameter 4mm, length 22mm.4 material of circular ring shape propellant is
Polytetrafluoroethylene (PTFE), internal diameter 4mm, outer diameter 9mm, length 20mm, be located at one section of anode annulus 10 and one section of cathode ring 3 it
Between, one section of anode annulus 10 is located at 4 outside of propellant, and one section of cathode ring 3 is located at 4 inside of propellant.One section of anode 10 and two
It is separated between section anode 7 by the insulating segment 5 of the glass material of circular ring shape, 5 internal diameter of insulating segment is 9mm, outer diameter 10mm, length 5mm.
Two sections of anodes 7 are with one section of anode 10 with the brass material annulus of the diameter of axle, and two sections of 7 internal diameters of anode are 9mm, outer diameter 10mm, length
For 20mm.Two sections of cathodes 8 are the solid cylinder of brass material, and diameter 1mm, length 55mm, two sections of cathodes 8 are across one section
3 inner ring of cathode.For influence of the two sections of cathodes 8 of isolation to a segment electrode and insulating segment 5, by rubber material outside two sections of cathodes 8
Clad 9 coats, and 9 internal diameter of clad is 1mm, outer diameter 2mm, length 38mm.Clad 9 is successively cased with trigger electrode from the inside to the outside
1, working medium 2, one section of cathode 3 are triggered, wherein trigger electrode 1 is the annulus of the red copper material coaxial with anode, internal diameter 2mm, outer diameter
2.5mm, length 27mm, triggering working medium 2 material are polytetrafluoroethylene (PTFE), internal diameter 2.5mm, outer diameter 3mm, length 24mm.Institute
It states trigger electrode 1, triggering working medium 2, one section of cathode 3 and collectively constitutes ignition initiation devices.One segment electrode, two-section electrode and igniting starting
Device provides voltage, energy capacitance set 11 by respective storage capacitor 11, and two main discharge capacitances are 5 μ F, trigger circuit electricity
Holding is 3000pF.It to avoid tail portion from discharging, and is the connection convenient for each segment electrode and external power supply, two sections of yin of thruster tail portion
Pole 8, clad 9, trigger electrode 1, triggering working medium 2 and one section of cathode 3 are stepped, wherein two sections of cathodes 8 are apart from tail portion propellant
10mm is stretched out on 4 surfaces, and clad 9 stretches out 8mm, and trigger electrode 1 stretches out 6mm, and triggering working medium 2 stretches out 4mm, and one section of cathode 3 stretches out
2mm.One section of anode 10, insulating segment 5 and two sections of anodes 7 are fixed by the external shell 6 of one end convex, and realizing keeps thruster electric
The purpose that pole is isolated with external environment, 6 material of external shell are ambroin, and tail portion internal diameter is 10mm, outer diameter 11mm, and inside is deep
For 50mm, front inner diameter 9mm, outer diameter 11mm, internal depth is 2mm, and 6 entire length of external shell is 52mm.
Since thruster electrode is divided to two sections, and each segment electrode provides voltage by respective storage capacitor 11, realizes total energy
Amount distributes to different capacitors, and discharges in different location, so that propellant ablation ionization process and plasma be accelerated
Process separates, and makes more energy for plasma accelerator, can be improved the acceleration efficiency of thruster entirety.
Triggering working medium 2 is ionized by 1 ablation of trigger electrode and generates a small amount of plasma, keeps the breakdown voltage between a segment electrode big
The triggering that width reduces in favor of initial discharge, and then improve the reliability of thruster work.
A kind of working method of Multi-section high-efficient rate pulsed plasma thruster disclosed in the present embodiment are as follows: firstly, point
Not for a segment electrode, two-section electrode and ignition initiation devices provide voltage storage capacitor 11 charge, due between a segment electrode
Lack turn-on condition under vacuum condition, can not voluntarily puncture；Due to 1 breakdown voltage very little of trigger electrode, puncture prior to a segment electrode,
Electric current ablation between trigger electrode 1 and one section of cathode 3 triggers working medium 2, and the neutral gas that ablation generates ionizes in the electric field, to produce
Raw a small amount of plasma；The plasma of generation is full of between a segment electrode, and the breakdown voltage between a segment electrode is greatly reduced
In favor of the triggering of initial discharge, and then improve the reliability of thruster work.Therefore, breakdown is big to generate between a segment electrode
Electric current, electric current ablation propellant generates neutral gas, under the action of high voltage, the neutral gas that ablation goes out be ionized to etc. from
Daughter group；After the plasma of generation is detached from 4 surface of propellant, under the action of electric field between a segment electrode and self-induction magnetic field plus
Speed is sprayed along insulating segment 5 to two-section electrode；After plasma reaches two-section electrode, due between two-section electrode there are high voltage,
Plasma accelerates along axial until being pushed out, generation impulse force again under the action of electric field and self-induction magnetic field.
Above-described specific descriptions have carried out further specifically the purpose of invention, technical scheme and beneficial effects
It is bright, it should be understood that the above is only a specific embodiment of the present invention, the protection model being not intended to limit the present invention
It encloses, all within the spirits and principles of the present invention, any modification, equivalent substitution, improvement and etc. done should be included in the present invention
Protection scope within.
Claims (4)
1. a kind of Multi-section high-efficient rate pulsed plasma thruster, it is characterised in that: the thruster structure is mainly by one section
Anode (10), one section of cathode (3), two sections of anodes (7), two sections of cathodes (8), insulating segment (5), trigger electrode (1), triggering working medium (2),
Energy capacitance set (11), propellant (4), clad (9) and external shell (6) composition；
Thruster is integrally in coaxial structure, and electrode is divided into two sections, and the first segment electrode is mainly used for propellant ablation and ionized
Journey；Second segment electrode is mainly used for plasma accelerator；First segment electrode is by one section of anode (10) and one section of cathode (3) group
At one section of anode (10) and one section of cathode (3) are coaxial annulus, and circular ring shape propellant (4) is located at one section of anode annulus (10)
Between one section of cathode ring (3), one section of anode annulus (10) is located on the outside of propellant (4), and one section of cathode ring (3), which is located at, to push away
On the inside of into agent (4)；It is separated between one section of anode (10) and two sections of anodes (7) by the insulating segment (5) of circular ring shape；Two sections of anodes (7) are
With one section of anode (10) with the annulus of the diameter of axle；Two sections of cathodes (8) are solid cylinder, and two sections of cathodes (8) pass through one section of cathode (3)
Inner ring；Influence for two sections of cathodes (8) of isolation to a segment electrode and insulating segment (5), two sections of cathodes (8) are external by clad (9)
Cladding；Clad (9) is successively cased with trigger electrode (1), triggering working medium (2), one section of cathode (3), the trigger electrode from the inside to the outside
(1), working medium (2) are triggered, one section of cathode (3) collectively constitutes ignition initiation devices；One segment electrode, two-section electrode and igniting starting dress
It sets and provides voltage by respective storage capacitor (11)；It to avoid tail portion from discharging, and is the company convenient for each segment electrode and external power supply
It connects, two sections of cathodes (8), clad (9), trigger electrode (1), triggering working medium (2) and the one section of cathode (3) of thruster tail portion are in ladder
Shape；One section of anode (10), insulating segment (5) and two sections of anodes (7) are fixed by the external shell (6) of one end convex, and realization makes
The purpose that thruster electrode is isolated with external environment.
2. a kind of Multi-section high-efficient rate pulsed plasma thruster as described in claim 1, it is characterised in that: due to thrust
Device electrode is divided to two sections, and each segment electrode provides voltage by respective storage capacitor (11), and realization distributes to gross energy different
Capacitor, and discharge in different location, so that propellant ablation ionization process and plasma accelerator be separated, make more
Energy be used for plasma accelerator, can be improved the acceleration efficiency of thruster entirety.
3. a kind of Multi-section high-efficient rate pulsed plasma thruster as claimed in claim 1 or 2, it is characterised in that: pass through
Trigger electrode (1) ablation ionization triggering working medium (2) generates a small amount of plasma, the breakdown voltage between a segment electrode is greatly reduced with
Conducive to the triggering of initial discharge, and then improve the reliability of thruster work.
4. a kind of Multi-section high-efficient rate pulsed plasma thruster as claimed in claim 1 or 2, it is characterised in that: work
Method is, firstly, a respectively segment electrode, two-section electrode and ignition initiation devices provide storage capacitor (11) charging of voltage,
Due to lacking turn-on condition under vacuum conditions between a segment electrode, can not voluntarily puncture；Very due to trigger electrode (1) breakdown voltage
It is small, puncture prior to a segment electrode, the electric current ablation between trigger electrode (1) and one section of cathode (3) triggers working medium (2), what ablation generated
Neutral gas ionizes in the electric field, to generate a small amount of plasma；The plasma of generation is full of between a segment electrode, makes one
The triggering that breakdown voltage between segment electrode is greatly reduced in favor of initial discharge, and then improve the reliability of thruster work；Cause
This, breakdown is between a segment electrode to generate high current, and electric current ablation propellant (4) generates neutral gas, in the effect of high voltage
Under, the neutral gas that ablation goes out is ionized to plasmoid；After the plasma of generation is detached from propellant (4) surface, one
Accelerate to spray along insulating segment (5) to two-section electrode under the action of electric field and self-induction magnetic field between segment electrode；When plasma reaches
After two-section electrode, since there are high voltages between two-section electrode, plasma is under the action of electric field and self-induction magnetic field again along axis
To acceleration until being pushed out, impulse force is generated.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811275159.9A CN109185090B (en) | 2018-10-26 | 2018-10-26 | Multi-section high-efficiency pulse plasma thruster |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811275159.9A CN109185090B (en) | 2018-10-26 | 2018-10-26 | Multi-section high-efficiency pulse plasma thruster |
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| CN109185090A true CN109185090A (en) | 2019-01-11 |
| CN109185090B CN109185090B (en) | 2019-12-24 |
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| CN201811275159.9A Expired - Fee Related CN109185090B (en) | 2018-10-26 | 2018-10-26 | Multi-section high-efficiency pulse plasma thruster |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109751212A (en) * | 2019-01-28 | 2019-05-14 | 北京交通大学 | Pulse plasma propeller with microporous insulation anode |
| CN110012584A (en) * | 2019-03-22 | 2019-07-12 | 北京交通大学 | Pulse Vacuum arc plasma propeller with segmentation microporous insulation anode |
| CN110630460A (en) * | 2019-10-17 | 2019-12-31 | 北京航空航天大学 | Segmented anode high specific impulse pulse plasma thruster |
| CN111472954A (en) * | 2020-03-25 | 2020-07-31 | 北京交通大学 | Insulating anode cathode arc propeller with auxiliary suspension potential electrode |
| CN111720281A (en) * | 2020-06-24 | 2020-09-29 | 遨天科技(北京)有限公司 | Array coaxial type vacuum arc thruster device |
| CN114001003A (en) * | 2021-10-26 | 2022-02-01 | 北京理工大学 | Double-section coaxial toothed cathode pulse plasma thruster |
| CN114352494A (en) * | 2021-12-15 | 2022-04-15 | 西安航天动力研究所 | Plasma generation device and method based on multi-stage magnetic field and multi-stage spray pipe |
| TWI778706B (en) * | 2021-07-13 | 2022-09-21 | 國立成功大學 | Vacuum cathode arc-induced pulsed thruster |
| US11859599B1 (en) | 2023-06-27 | 2024-01-02 | National Cheng Kung University | Vacuum arc thruster with multi-layer insulation |
| TWI849989B (en) * | 2023-06-20 | 2024-07-21 | 國立成功大學 | A vacuum arc thruster with multi-layer insulation |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109751212A (en) * | 2019-01-28 | 2019-05-14 | 北京交通大学 | Pulse plasma propeller with microporous insulation anode |
| CN110012584A (en) * | 2019-03-22 | 2019-07-12 | 北京交通大学 | Pulse Vacuum arc plasma propeller with segmentation microporous insulation anode |
| CN110630460A (en) * | 2019-10-17 | 2019-12-31 | 北京航空航天大学 | Segmented anode high specific impulse pulse plasma thruster |
| CN111472954A (en) * | 2020-03-25 | 2020-07-31 | 北京交通大学 | Insulating anode cathode arc propeller with auxiliary suspension potential electrode |
| CN111720281A (en) * | 2020-06-24 | 2020-09-29 | 遨天科技(北京)有限公司 | Array coaxial type vacuum arc thruster device |
| TWI778706B (en) * | 2021-07-13 | 2022-09-21 | 國立成功大學 | Vacuum cathode arc-induced pulsed thruster |
| CN114001003A (en) * | 2021-10-26 | 2022-02-01 | 北京理工大学 | Double-section coaxial toothed cathode pulse plasma thruster |
| CN114352494A (en) * | 2021-12-15 | 2022-04-15 | 西安航天动力研究所 | Plasma generation device and method based on multi-stage magnetic field and multi-stage spray pipe |
| TWI849989B (en) * | 2023-06-20 | 2024-07-21 | 國立成功大學 | A vacuum arc thruster with multi-layer insulation |
| US11859599B1 (en) | 2023-06-27 | 2024-01-02 | National Cheng Kung University | Vacuum arc thruster with multi-layer insulation |
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| Publication number | Publication date |
|---|---|
| CN109185090B (en) | 2019-12-24 |
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