CN104696180B - Magnetic field regulation type liquid phase working fluid large area microcavity discharge plasma micro-thruster - Google Patents
Magnetic field regulation type liquid phase working fluid large area microcavity discharge plasma micro-thruster Download PDFInfo
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- CN104696180B CN104696180B CN201410837625.3A CN201410837625A CN104696180B CN 104696180 B CN104696180 B CN 104696180B CN 201410837625 A CN201410837625 A CN 201410837625A CN 104696180 B CN104696180 B CN 104696180B
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- microcavity
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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
- F03H1/0012—Means for supplying the propellant
-
- 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
- F03H1/0093—Electro-thermal plasma thrusters, i.e. thrusters heating the particles in a plasma
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- Combustion & Propulsion (AREA)
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- Plasma & Fusion (AREA)
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- Plasma Technology (AREA)
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Abstract
Magnetic field regulation type liquid phase working fluid large area microcavity discharge plasma micro-thruster, propellant working medium feed mechanism diffuses into the liquid propellant in liquid propellant storage tank in electric discharge microcavity, the hole that described electric discharge microcavity is not waited by a diameter is constituted through sheet metal and insulation dielectric, insulation dielectric is clipped between two neighboring sheet metal, and two neighboring sheet metal constitutes an electrode pair；The sheet metal and insulation dielectric composition daraf(reciprocal of farad) that spout of electric discharge microcavity end, wherein, insulation dielectric constitutes the contraction section and expansion segment of your spout of daraf(reciprocal of farad), the throat of your spout of anode metal piece composition daraf(reciprocal of farad), it constitutes an electrode pair with your the cathodic metal piece in nozzle divergence section exit positioned at daraf(reciprocal of farad)；At least provided with an electrode pair on the horizontal segment of your spout of daraf(reciprocal of farad), external power source module provides periodically exchange or direct current high voltage pulses voltage, and be connected to using wire in each electrode pair, and annular permanent magnet is sleeved on the outside of the tube wall of above-mentioned electric discharge microcavity.
Description
Technical field
The present invention relates to a kind of liquid phase working fluid large area microcavity discharge plasma space micromass culture based on magnetic field modulation
Device, be particularly suitable for use in space tiny spacecraft to high integration, low-power consumption, accurate momentum, high specific impulse micromass culture system work
Demand.
Background technology
Flourishing for this century micro-nano satellite is come to the active demand that space minimizes platform micromass culture technology.Into
After 21 century, micro-nano satellite networking technology develops rapidly, increasingly mature, and this causes micro-nano satellite to complete traditional large satellite work(
While energy, with more the advantage that the cycle is short, risk is low, radiation pattern is flexible, expansibility is strong.Due to micro-nano satellite volume
Small, light weight, rotary inertia are small, small for satellite orbit and thrust needed for gesture stability, reproducible, it is desirable to which precision is high, and one
As be milli ox magnitude, or even to micro- ox magnitude；Excellent micro-thruster should also have wider thrust range concurrently, different to adapt to
Task application demand.Meanwhile, the target of micro-nano satellite formation flight is to maintain intersatellite relative position, is respectively defended without being to maintain
The absolute position of star, it is therefore desirable to minimum momentum pulse it is very small, to meet control system high-precision requirement.Therefore study suitable
Kept together in micro-nano satellite track, the high integration of orbit maneuver and gesture stability, low-power consumption, accurate momentum, high specific impulse
Small propulsion system is the inevitable requirement of micro-nano satellite development and the key link for concerning success or failure.
Compared to chemical micromass culture, electric propulsion has the advantages that low cost, high specific impulse, thrust is small, control accuracy is high, can be significantly
Reduce the carrying amount of propellant and increase Satellite Payloads, or do not reduce propellant and greatly prolong the working life of satellite,
Thus as one of most potential micromass culture mode.Micro- electric propulsion device is divided into electrothermal, electrostatic and electromagnetic type.Electric heating
The propeller that declines is pollution-free, however, it would be possible to use any propellant, cost is low, but its specific impulse is very low, there is leakage problem.
Electrostatic micro-thruster has field-effect electrostatic propeller, colloid micro-thruster, ion micro-thruster, Hall micro-thruster.But it is quiet
Electric-type micro-thruster generally needs high operating voltage (kV magnitudes) or larger power (hectowatt magnitude), has exceeded micro-
The supply capacity of Nano satellite, also limits its application in terms of microminiature micro-nano satellite.Such as pulse of electromagnetic type micro-thruster
Plasma propulsion device proper mass is larger, there is also plume contamination problem, and pushes away work(than not high.
So far, the constraint of quality and power to propulsion system causes the electric propulsion mode of micro-nano satellite main with electric heating
Based on formula.Traditional electric resistor heating type micromass culture systems face specific impulse is small, the low outstanding problem of the efficiency of heating surface, radio frequency discharge electric heating
Decline and promote and with the deficiency that energy utilization efficiency is low, wall surface ablation is big, the size of micro- electric arc generator can not also expire
Less than sufficient centimetre of process requirements.These unfavorable factors limit application of the above-mentioned propulsion system on micro-nano satellite.Compared to it
Under, microcavity discharge plasma propulsion is the Novel electric heating micromass culture technology that a kind of utilization micro discharge technology is developed.It is micro-
Cavity discharging, is a kind of novel non-equilibrium high-pressure glow discharge, it is only necessary to low-down voltage (hundreds of volts) or input
Power (the hundred milliwatt orders of magnitude), by the collision and electric field of plasma and neutral gas to used in the acceleration of ion, heating
Working medium gas, then sprayed by certain nozzle structure, produces thrust, thus for improve the performance of propulsion system open it is new
Approach.Illinois, America stands the calculating plasma laboratory of the state university in electric propulsion laboratory and Texas of university
Propose the design (as shown in Figure 1) of microcavity discharge micro-nano satellite propeller and in USAF central science research foundation earliest
Corresponding research work is carried out under subsidy<R.L.Burton et al.Development of the MCD thruster
for nanosat propulsion,Proceedings of the 57th Joint Army Navy NASAAir Force
Propulsion Meeting,Colorado Springs,Colorado,2010；M.de Chadenedes et
al.Advances in microcavity discharge thruster technology,Proceedings of the
46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference,Nashville,TN,2010>.Exist at present
, there is many outstanding problems in the microcavity discharge plasma propeller ground, constrain thrust, specific impulse and energy efficiency enters one
Step, which is improved, to be improved：(1) due to the big surface-to-volume ratio of microdischarge cavities, substantial amounts of energy loss occurs in solid wall and waited
Sheaths region on gas ions interface, serious reduction propellant working medium heating and the energy utilization efficiency promoted.(2) due to etc.
Gas ions and the strong coupling of cold propellant gas stream, charged ion are mainly distributed on discharge cavities or spout internal, very
The thrust just contributed by charged particle is extremely limited.(3) single pair of electrode structure machining area is smaller, and discharge stability is not high, when
Ionizing efficiency is limited when propellant flow rate is larger, and a large amount of gas-phase working mediums, which can not effectively discharge, ionizes heating, causes the work of propeller
Matter utilization ratio is relatively low.(4) requirement of the gaseous propellant to quality flow control accuracy is higher, while storage of higher pressures is needed, meeting
Take the volume and quality of tiny spacecraft.Based on above mentioned problem, the specific impulse of current microcavity discharge plasma micro-thruster is only
It is 100-200s, energy efficiency less than 60%, Solid rocket engine precision is not high.
The content of the invention
The technology of the present invention solves problem：Overcome under traditional microcavity discharge plasma micro-thruster specific impulse, can dose-effect
Rate is low, the low bottleneck of Solid rocket engine precision, proposes a kind of liquid phase working fluid large area microcavity discharge plasma based on magnetic field modulation
Body micro-thruster, is compared by the comprehensive regulation of a variety of outside control conditions and the realization height of distributing rationally of various new parts
The micro-nano satellite of punching, long-life and high control precision is promoted.
The present invention technical solution be：Magnetic field regulation type liquid phase working fluid large area microcavity discharge plasma micromass culture
Device, including propeller body, permanent magnet and external power source module；Propeller body construction includes liquid propellant storage tank, promotes
Agent working medium feed mechanism, sheet metal, insulation dielectric and Rafael nozzle；
Propellant working medium feed mechanism controlled medium flow simultaneously sprays the liquid propellant formation in liquid propellant storage tank
Mist is diffused into electric discharge microcavity, and sheet metal and insulation dielectric structure are run through in the hole that described electric discharge microcavity is not waited by a diameter
Into insulation dielectric is clipped between two neighboring sheet metal, and two neighboring sheet metal constitutes an electrode pair；Electric discharge microcavity end
Sheet metal and insulation dielectric composition daraf(reciprocal of farad) your spout, wherein, insulation dielectric constitutes contraction section and the expansion of daraf(reciprocal of farad) your spout
Section, the throat of your spout of anode metal piece composition daraf(reciprocal of farad), itself and the cathodic metal positioned at your nozzle divergence section exit of daraf(reciprocal of farad)
Piece constitutes an electrode pair；At least provided with an electrode pair on the horizontal segment of your spout of daraf(reciprocal of farad), external power source module provides the cycle
Sexual intercourse stream or direct current high voltage pulses voltage, and be connected to using wire in each electrode pair, annular permanent magnet is sleeved on above-mentioned
On the outside of the tube wall of electric discharge microcavity.
It regard said external power module and propeller body construction as a propulsion unit, multiple identical propulsion units
Dot matrix is lined up, the set of permanent magnets of outside suit annular fills insulation into multi-cavity propeller between permanent magnet and each propulsion unit
Material.
The present invention has the beneficial effect that compared with prior art：
(1) large area is obtained under relatively low power input power surface density using compound multiple electrode structure surface-discharge
Discharge plasma, and the higher-order of oscillation of electric discharge can be reduced, the stability of electric discharge is improved, it is big when overcoming propellant flow rate larger
Amount gas-phase working medium, which can not effectively discharge, ionizes heating, the low bottleneck of propeller working medium utilization ratio；
(2) the outside axial magnetic field modulation optimization produced using round ring magnet is significantly reduced discharge voltage and strengthens electricity
From process, regulate and control microcavity discharge plasma discharge transport property, improve the contribution that charged particle is improved to propulsive performance；
(3) liquid propellant by working medium feed mechanism enter to discharge microcavity spread speed it is slower than gaseous propellant very
Many, propellant flow rate control is more easy, can realize more high-precision to the specific impulse of micro-nano satellite propeller, thrust and micro impulse
The operational control of degree；Secondly, liquid propellant mass density is big, without high pressure tank, can save propeller and micro-nano is defended
The volume and weight of star；
(4) microcavity discharge plasma microdriver meets micro-nano satellite to promoting system using MEMS technology processing and manufacturing
System weight, volume, the rigors of power；
(5) working medium feed mechanism makes liquid propellant enter electric discharge microcavity with mist, thereby increases liquid propulsion
Agent and sparking electrode, the contact area of plasma, are more beneficial for the heating of propellant and improve discharging efficiency.
(6) by multiple propeller module integrated combinations formation multi-cavity propeller of same model, thrust can be realized larger
In the range of regulation, applied to the propulsion task of different thrust requirements, ability is obtained with thrust continuously adjustabe.
Brief description of the drawings
Fig. 1 tradition microcavity discharge propeller schematic diagrames
Fig. 2 is single propulsion unit schematic diagram of the invention；
Fig. 3 a, 3b are that multi-cavity propeller of the present invention arranges two kinds of schematic diagrames.
Embodiment
As shown in Fig. 2 a kind of magnetic field regulation type liquid phase working fluid large area microcavity discharge plasma micro-thruster of the invention,
Including propeller body construction, permanent magnet 9 and external power source module 6；Propeller body construction includes liquid propellant storage tank 8,
Propellant working medium feed mechanism 7, sheet metal (anode 1, negative electrode 2), dielectric 3 and Rafael nozzle 4；
Wherein, the internal memory of liquid propellant storage tank 8 contains the liquid propellant (ethanol, water etc.) of effumability, working medium feeding
Mechanism 7 includes the micro-valve door and the capillary injection atomizer for being atomized liquid refrigerant of a controlled medium flow, and liquid is pushed away
Enter agent to diffuse into electric discharge microcavity and realize spraying treatment.Under space environment, liquid working substance is pressed into by capillary injection atomizer
Capillary causes high-speed jet, and drop is ejected to form liquid mist with imperceptible particle, and the port of export can be diffused into automatically
For in the electrode space of vacuum.The hole that described electric discharge microcavity is not waited by a diameter (from tens microns to hundreds of microns) is run through
Sheet metal (copper, nickel, platinum, tungsten etc.) and insulation dielectric 3 (mica, ceramics, lucite etc.) are constituted, and insulation dielectric 3 is pressed from both sides
Between two neighboring sheet metal, two neighboring sheet metal constitutes an electrode pair；Dielectric 3 is used to prevent from waiting electric discharge to occur
Except other positions between electrode intracavity electrode.
Above-mentioned two sheet metal and the insulation dielectric being clipped between two sheet metals 3 are referred to as an electric discharge device, pushed away
Enter the multiple electric discharge devices of device body interior to be placed in parallel, the sheet metal of electric discharge microcavity end and insulation dielectric composition daraf(reciprocal of farad) that spray
Mouth 4, wherein, insulation dielectric constitutes the contraction section and expansion segment of your spout 4 of daraf(reciprocal of farad), anode metal piece composition daraf(reciprocal of farad) that spout 4
Throat, itself and the cathodic metal piece positioned at your spout 4 of daraf(reciprocal of farad) expansion segment exit constitute an electrode pair；Daraf(reciprocal of farad) that spout 4
Horizontal segment at least provided with an electrode pair.
The low pressure constant-direct current output that space device solar cell is converted to by external power source module 6 is converted to week
Phase sexual intercourse stream or direct current high voltage pulses voltage, and be connected to using wire on the binding post of anode 1 and negative electrode 2, in two metals
Electric discharge produces plasma 5 between plate electrode, and its discharge scenario has with pore size, electrode spacing, air pressure and size of current
Close.The external power source of each electrode pair connection is connected in parallel, and is put with identical amplitude and frequency by the control of external trigger circuit
Electricity produces plasma.Due to electric discharge microcavity aperture very little, only need relatively low voltage just can maintain to produce stabilization between two electrodes
Electric discharge, obtain gas temperature and electron density all higher plasmas, and the electric discharge of unit is heated by multiple electrodes
Effect, by the Rafael nozzle (there is typical contraction section, confinement section and expansion segment) of end, after the expansion of downstream expansion segment
Flow at high speed is presented, the propulsion of spacecraft is realized by effective reaction force.Multiple electric discharge unit parallel arrangements, which are constituted, to be promoted
Array, realizes the auto-adjustment control of thrust, annular permanent magnet 9 (magnet is Nd-Fe-B permanent magnet, also can for samarium cobalt magnet,
The permanent magnets such as alnico magnet ferrite lattice) it is sleeved on the outside of the tube wall of above-mentioned electric discharge microcavity, produce consistent with air flow direction
Axial magnetic field, significantly reduce discharge voltage and strengthen ionization process, regulation and control charged particle along it is parallel be axially moved, so as to pray
Pray the purpose of modulation discharge process and plasma transport process.
As shown in Figure 3 a, 3 b, using said external power module 6 and propeller body construction and it is used as a propulsion unit
10, multiple identical propulsion units line up dot matrix, and for the ease of controlling the work of propulsion unit, possible propulsion unit arranges shape
Formula includes annular and Two-Dimensional Moment formation.The composition multi-cavity propeller of permanent magnet 9 of outside suit annular, permanent magnet 9 is with each pushing away
Enter fill insulant between unit.
Unspecified part of the present invention belongs to general knowledge as well known to those skilled in the art.
Claims (2)
1. magnetic field regulation type liquid phase working fluid large area microcavity discharge plasma micro-thruster, it is characterised in that：Including propeller
Body construction, permanent magnet (9) and external power source module (6)；Propeller body construction includes liquid propellant storage tank (8), promotes
Agent working medium feed mechanism (7), sheet metal, insulation dielectric (3) and Rafael nozzle (4)；Wherein, in direct-current discharge condition
Under, sheet metal respectively constitutes the anode (1) existed in pairs, negative electrode (2)；
Propellant working medium feed mechanism (7) controlled medium flow simultaneously spreads the liquid propellant in liquid propellant storage tank (8)
Enter in the microcavity that discharges, the hole that described electric discharge microcavity is not waited by a diameter is constituted through sheet metal and insulation dielectric (3), absolutely
Edge dielectric (3) is clipped between two neighboring sheet metal, and two neighboring sheet metal constitutes an electrode pair；Electric discharge microcavity end
Sheet metal and insulation dielectric (3) composition daraf(reciprocal of farad) that spout (4), wherein, insulation dielectric (3) constitutes daraf(reciprocal of farad) that spout (4)
Contraction section and expansion segment, the throat of your spout of anode metal piece composition daraf(reciprocal of farad) (4), its with positioned at your spout (4) expansion segment of daraf(reciprocal of farad)
The cathodic metal piece in exit constitutes an electrode pair；At least provided with an electrode pair on the horizontal segment of your spout (4) of daraf(reciprocal of farad), outside
Portion's power module (6) provides periodically exchange or direct current high voltage pulses voltage, and be connected to using wire in each electrode pair, ring
The permanent magnet (9) of shape is sleeved on the outside of the tube wall of above-mentioned electric discharge microcavity.
2. magnetic field regulation type liquid phase working fluid large area microcavity discharge plasma micro-thruster according to claim 1, its
It is characterised by：It regard said external power module (6) and propeller body construction as a propulsion unit (10), multiple identicals
Propulsion unit lines up dot matrix, and annular permanent magnet (9) the composition multi-cavity propeller of outside suit, permanent magnet (9) promotes list with each
Fill insulant between member.
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| CN105704903B (en) * | 2016-03-16 | 2019-03-05 | 北京交通大学 | A kind of discharge electrode structure that the vacuum plasma based on magnetic fields generates |
| CN107975462B (en) * | 2016-10-21 | 2020-06-19 | 南京理工大学 | Electric heating micro thruster |
| CN107620652B (en) * | 2016-10-28 | 2020-04-14 | 湖北航天化学技术研究所 | Multi-pulse thrust-adjustable solid propeller |
| CN108612599B (en) * | 2016-12-10 | 2020-09-08 | 中国科学院大连化学物理研究所 | Liquid-electric combined space thruster |
| CN106704132A (en) * | 2017-01-12 | 2017-05-24 | 安徽工程大学 | Ferroelectric micro-plasma propeller |
| FR3066557B1 (en) * | 2017-05-16 | 2019-05-10 | Safran Aircraft Engines | DEVICE FOR CONTROLLING PROPELLANT FLUID FLOW RATE FOR ELECTRIC PROPELLER |
| CN107061210B (en) * | 2017-05-18 | 2018-12-04 | 西安交通大学 | A kind of pulsed plasma thruster accelerated based on electrothermal and electromagnetic mixing |
| CN107165794B (en) * | 2017-06-12 | 2019-10-01 | 北京航空航天大学 | A kind of adjustable low-power hall thruster with magnetic screening effect in magnetic field |
| CN107882702A (en) * | 2017-10-24 | 2018-04-06 | 哈尔滨工业大学 | Rafael nozzle formula magnetic confinement hollow cathode |
| CN111173698B (en) * | 2018-11-09 | 2021-01-05 | 哈尔滨工业大学 | Liquid working medium plasma thruster based on microwave enhancement |
| CN109779781B (en) * | 2019-03-15 | 2020-06-02 | 常熟理工学院 | Magnetic fluid control spray pipe for improving thrust of pulse detonation engine |
| CN114135457B (en) * | 2021-11-30 | 2023-03-14 | 中国工程物理研究院电子工程研究所 | Ion propeller |
| CN114337349B (en) * | 2021-12-30 | 2022-08-26 | 哈尔滨工业大学 | Pulse power source for simulating solar wind |
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| US6449941B1 (en) * | 1999-04-28 | 2002-09-17 | Lockheed Martin Corporation | Hall effect electric propulsion system |
| CN102305200B (en) * | 2011-07-12 | 2013-01-23 | 中北大学 | Pulsed plasma thruster with water working medium |
| CN102878040A (en) * | 2011-07-15 | 2013-01-16 | 葛泓杉 | Magnetically controlled plasma power generation booster |
| FR2985292B1 (en) * | 2011-12-29 | 2014-01-24 | Onera (Off Nat Aerospatiale) | PLASMIC PROPELLER AND METHOD FOR GENERATING PLASMIC PROPULSIVE THRUST |
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