CN104696180A - Magnetic field regulation type large-area microcavity discharge plasma micro-thruster for liquid working substances - Google Patents
Magnetic field regulation type large-area microcavity discharge plasma micro-thruster for liquid working substances Download PDFInfo
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- CN104696180A CN104696180A CN201410837625.3A CN201410837625A CN104696180A CN 104696180 A CN104696180 A CN 104696180A CN 201410837625 A CN201410837625 A CN 201410837625A CN 104696180 A CN104696180 A CN 104696180A
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- microcavity
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- electrode pair
- thruster
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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
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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
- F03H1/0081—Electromagnetic 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
- F03H1/0093—Electro-thermal plasma thrusters, i.e. thrusters heating the particles in a plasma
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
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- General Engineering & Computer Science (AREA)
- Plasma Technology (AREA)
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Abstract
A magnetic field regulation type large-area microcavity discharge plasma micro-thruster for liquid working substances is characterized in that a propellant working substance feeding mechanism diffuses a liquid propellant in a liquid propellant storage tank into a discharge microcavity, the discharge microcavity comprises metal sheets and insulation dielectrics, a hole with unequal diameters penetrates through the metal sheets, the insulation dielectrics are clamped between two adjacent metal sheets, and every two adjacent metal sheets form one electrode pair; a Laval-cavity nozzle is formed by the metal sheet at the tail end of the discharge microcavity and the corresponding insulation dielectrics, the insulation dielectrics constitute a contraction section and an expansion section of the Laval-cavity nozzle, an anode metal sheet constitutes the throat part of the Laval-cavity nozzle, and the anode metal sheet and a cathode metal sheet located at an outlet of the expansion section of the Laval-cavity nozzle constitute one electrode pair; at least one electrode pair is arranged at the horizontal section of the Laval-cavity nozzle; an external power supply module provides periodic alternating-current or direct-current high-voltage pulse voltage and is connected to every electrode pair by wires; a ring-shaped permanent magnet is mounted on the outer side of the pipe wall of the discharge microcavity in a sleeving manner.
Description
Technical field
The present invention relates to a kind of liquid phase working fluid large size microcavity discharge plasma space micro-thruster based on magnetic field modulation, be specially adapted to the work requirements of space tiny spacecraft to high integration, low power consumption, accurately momentum, high specific impulse micromass culture system.
Background technique
The flourish of micro-nano satellite in this century is come to the active demand of space miniaturization platform micromass culture technology.After entering 21 century, the develop rapidly of micro-nano satellite networking technology, increasingly mature, this makes micro-nano satellite while completing traditional large satellite function, the advantage that the cycle that has more is short, risk is low, radiation pattern is flexible, expansibility is strong.Because micro-nano satellite volume is little, quality is light, rotary inertia is little, for satellite orbit and gesture stability required thrust little, reproducible, precision prescribed is high, is generally milli ox magnitude, even arrives micro-ox magnitude; Excellent micro-thruster also should have wider thrust range concurrently, to adapt to different task application demands.Meanwhile, the target of micro-nano satellite formation flight maintains intersatellite relative position, instead of keep the absolute position of each satellite, and the minimum momentum pulse therefore needed is very little, to meet control system high-precision requirement.Therefore research be suitable for that micro-nano satellite track keeps, the high integration of orbit maneuver and gesture stability, low power consumption, accurate momentum, high specific impulse small propulsion system be the inevitable requirement that micro-nano satellite develops and the key link concerning success or failure.
Compare chemical micromass culture, electric propulsion has that low cost, high specific impulse, thrust are little, control accuracy advantages of higher, the carrying amount of propellant agent can be greatly reduced and increase Satellite Payloads, or do not reduce propellant agent and greatly extend the operating life of satellite, thus become one of the most potential micromass culture mode.Micro-electric propulsion device is divided into electric heating type, electrostatic and electromagnetic type.Electric heating type micro-thruster is pollution-free, and can use any propellant agent in principle, cost is low, but its specific impulse is very low, there is leakage problem.Electrostatic micro-thruster has field effect electrostatic propulsion device, colloid micro-thruster, ion micro-thruster, Hall micro-thruster.But electrostatic micro-thruster generally needs high operating voltage (kV magnitude) or larger power (hectowatt magnitude), has exceeded the supply capacity of micro-nano satellite, also just limit its application in microminiature micro-nano satellite.Electromagnetic type micro-thruster is as comparatively large in pulse plasma propulsion device proper mass, also there is plume contamination problem, and it is higher than not to push away merit.
So far, quality and the constraint of power to propulsion system make the electric propulsion mode of micro-nano satellite mainly based on electric heating type.The outstanding problems such as traditional electric resistor heating type micromass culture systems face specific impulse is little, the efficiency of heating surface is low, radio frequency discharge electric heating type micromass culture has again the deficiency that energy utilization efficiency is low, wall surface ablation is large, the process requirements below the size of micro-electric arc generator also cannot meet centimetre.These unfavorable factors limit the application of above-mentioned propulsion system on micro-nano satellite.By contrast, microcavity discharge plasma propulsion be a kind of utilize micro discharge technical development and come Novel electric heating micromass culture technology.Microcavity discharge, it is a kind of non-equilibrium high-pressure glow discharge of novelty, only need low-down voltage (hundreds of volt) or input power (the hundred milliwatt orders of magnitude), by the collision of plasma and neutral gas and the acceleration of electric field to ion used, heating working medium gas, again by the ejection of certain nozzle structure, produce thrust, thus be that the performance improving propulsion system opens new approach.The calculating plasma laboratory that Illinois, America founds the state university in electric propulsion laboratory and Texas of university proposes the angle of rake design of microcavity discharge micro-nano satellite (as shown in Figure 1) the earliest and carried out corresponding research work <R.L.Burtonet al.Development of the MCD thruster for nanosat propulsion under USAF central science fellowship is subsidized, Proceedingsof the 57th Joint Army Navy NASA Air Force Propulsion Meeting, ColoradoSprings, Colorado, 2010, M.de Chadenedes et al.Advances in microcavitydischarge thruster technology, Proceedings of the 46thAIAA/ASME/SAE/ASEE Joint Propulsion Conference, Nashville, TN, 2010>.The microcavity discharge plasma propeller ground at present, there is many outstanding problems, constrain thrust, improving further of specific impulse and energy efficiency is improved: (1) is due to the large surface-to-volume ratio of microdischarge cavities, a large amount of energy losses occurs in the sheath layer region on solid wall and plasma interface, the serious energy utilization efficiency reducing the heating of propellant agent working medium and advance.(2) due to plasma and the strong coupling of cold propellant gas stream, charged ion is mainly distributed in discharge cavities or spout internal, and the thrust really contributed by charged particle is very limited.(3) single less to electrode structure machining area, discharge stability is not high, and when propellant flow rate is larger, ionizing efficiency is limited, and a large amount of gas-phase working medium effectively cannot discharge and ionize heating, causes angle of rake working medium utilization ratio lower.(4) requirement of gas propellant to quality flow control accuracy is higher, needs storage of higher pressures simultaneously, can take volume and the quality of tiny spacecraft.Based on the problems referred to above, the specific impulse of current microcavity discharge plasma micro-thruster is only 100-200s, energy efficiency less than 60%, and Solid rocket engine precision is not high.
Summary of the invention
Technology of the present invention is dealt with problems and is: under overcoming the specific impulse of traditional microcavity discharge plasma micro-thruster, energy efficiency is low, the bottleneck that Solid rocket engine precision is low, propose a kind of liquid phase working fluid large size microcavity discharge plasma micro-thruster based on magnetic field modulation, realize high specific impulse by distributing rationally of the comprehensive regulation of multiple external control condition and various new parts, the micro-nano satellite of long lifetime and high control precision advances.
Technical solution of the present invention is: magnetic field regulation type liquid phase working fluid large size microcavity discharge plasma micro-thruster, comprises propulsion device body, permanent magnet and external power supply module; Propulsion device body structure comprises liquid propellant storage tank, propellant agent working medium feed mechanism, tinsel, dielectrics and Rafael nozzle;
Liquid propellant formation spraying in liquid propellant storage tank also diffuses in electric discharge microcavity by propellant agent working medium feed mechanism controlled medium flow, tinsel is run through in the hole that described electric discharge microcavity is not waited by a diameter and insulation dielectric is formed, insulation dielectric is clipped between adjacent two tinsels, and adjacent two tinsels form an electrode pair; The tinsel of electric discharge microcavity end and insulation dielectric composition daraf(reciprocal of farad) that spout, wherein, insulation dielectric forms contraction section and the extending section of your spout of daraf(reciprocal of farad), the throat of your spout of anode metal sheet composition daraf(reciprocal of farad), it forms an electrode pair with the cathodic metal sheet being positioned at daraf(reciprocal of farad) that nozzle divergence section outlet port; The horizontal segment of your spout of daraf(reciprocal of farad) at least arranges an electrode pair, and external power supply module provides and periodically exchanges or direct current high voltage pulses voltage, and utilizes wire to be connected on each electrode pair, and the permanent magnet of annular is sleeved on outside the tube wall of above-mentioned electric discharge microcavity.
Using said external power module and propulsion device body structure as a propulsion unit, multiple identical propulsion unit lines up dot matrix, the permanent magnet composition multi-cavity propulsion device of outside suit annular, fill insulant between permanent magnet and each propulsion unit.
The present invention compared with prior art beneficial effect is:
(1) compound multiple electrode structure surface discharge is adopted to obtain large-area discharge plasma under lower power supply input power surface density, and the high frequency oscillation of electric discharge can be reduced, improve the stability of electric discharge, overcome propellant flow rate larger time a large amount of gas-phase working medium cannot effectively discharge ionization heating, the bottleneck that propulsion device working medium utilization ratio is low;
(1) the outside axial magnetic field modulation adopting round ring magnet to produce is optimized and is significantly reduced discharge voltage and strengthen ionization process, and regulation and control microcavity discharge plasma discharge transport property, improves the contribution that charged particle improves propulsive performance;
(2) liquid propellant by working medium feed mechanism enter to discharge microcavity diffusion speed much slower than gas propellant, it is more easy that propellant flow rate controls, and can realize controlling the more high-precision operation of the specific impulse of micro-nano satellite propulsion device, thrust and micro impulse; Secondly, liquid propellant density of mass is large, without the need to high pressure tank, can save the volume and weight of propulsion device and micro-nano satellite;
(3) microcavity discharge plasma microdriver adopts MEMS technology manufacturing to meet the rigors of micro-nano satellite to propulsion system weight, volume, power;
(4) working medium feed mechanism makes liquid propellant enter electric discharge microcavity with mist, thereby increases the area of contact of liquid propellant and sparking electrode, plasma, is more conducive to the heating of propellant agent and improves discharging efficiency.
(5) multiple propeller module integrated combinations of same model are formed multi-cavity propulsion device, the adjustment of thrust in a big way can be realized, be applied to the propelling task of different thrust requirements, there is thrust continuously adjustabe and obtain ability.
Accompanying drawing explanation
Fig. 1 tradition microcavity discharge propulsion device schematic diagram
Fig. 2 is the single propulsion unit schematic diagram of the present invention;
Fig. 3 a, 3b are that multi-cavity propulsion device of the present invention arranges two kinds of schematic diagram.
Embodiment
As shown in Figure 2, a kind of magnetic field of the present invention regulation type liquid phase working fluid large size microcavity discharge plasma micro-thruster, comprises propulsion device body structure, permanent magnet 9 and external power supply module 6; Propulsion device body structure comprises liquid propellant storage tank 8, propellant agent working medium feed mechanism 7, tinsel (anode 1, negative electrode 2), dielectrics 3 and Rafael nozzle 4;
Wherein, the liquid propellant (ethanol, water etc.) of effumability is stored in liquid propellant storage tank 8, micro-valve that working medium feed mechanism 7 comprises a controlled medium flow and the capillary injection atomizer be atomized by liquid refrigerant, diffuse into electric discharge microcavity and realize spraying process by liquid propellant.Under space environment, liquid working substance is pressed into capillary tube and causes high-speed jet by capillary injection atomizer, and drop is out formed liquid mist with imperceptible particle jetting, and automatically can be diffused into outlet end is in the electrode space of vacuum.Tinsel (copper, nickel, platinum, tungsten etc.) is run through in the hole that described electric discharge microcavity is not waited by a diameter (from tens microns to hundreds of micron) and insulation dielectric 3 (mica, pottery, plexiglass etc.) is formed, insulation dielectric 3 is clipped between adjacent two tinsels, and adjacent two tinsels form an electrode pair; Dielectrics 3 occurs at other position between electrode intracavity electrode for the electric discharge such as preventing.
Above-mentioned two tinsels and the insulation dielectric 3 be clipped between two tinsels are called an electric discharge device, the parallel placement of the multiple electric discharge device of propulsion device body interior, the tinsel of electric discharge microcavity end and insulation dielectric composition daraf(reciprocal of farad) that spout 4, wherein, insulation dielectric forms contraction section and the extending section of your spout 4 of daraf(reciprocal of farad), the throat of your spout 4 of anode metal sheet composition daraf(reciprocal of farad), it forms an electrode pair with the cathodic metal sheet being positioned at daraf(reciprocal of farad) that spout 4 extending section outlet port; The horizontal segment of your spout 4 of daraf(reciprocal of farad) at least arranges an electrode pair.
The low pressure constant-direct current that space device solar cell is converted to by external power supply module 6 exports to be converted to and periodically exchanges or direct current high voltage pulses voltage, and utilize wire to be connected on the wiring terminal of anode 1 and negative electrode 2, between two tinsel electrodes, electric discharge produces plasma 5, and its discharge scenario is relevant with pore size, electrode spacing, air pressure and size of current.The external power supply that each electrode pair connects is connected in parallel, and produces plasma with identical amplitude and frequency by the electric discharge of external trigger control circui.Because electric discharge microcavity aperture is very little, only need lower voltage just can maintain between two electrodes and produce stable electric discharge, obtain gas temperature and all higher plasma of electron density, and through the electric discharge heat effect of multiple electrode pair unit, through the Rafael nozzle (there is typical contraction section, confinement section and extending section) of end, after downstream extending section expands, present flow at high speed, realize the propelling of astrovehicle by effective reaction force.Multiple electric discharge units parallel arrangement forms propelling array, realize the auto-adjustment control of thrust, (magnet is Nd-Fe-B permanent magnet to the permanent magnet 9 of annular, also can be the permanent magnet such as samarium cobalt magnet, alnico magnet ferrite lattice) outside the tube wall that is sleeved on above-mentioned electric discharge microcavity, produce the axial magnetic field consistent with air flow direction, remarkable reduction discharge voltage also strengthens ionization process, control strip charged particle along parallel axial motion, thus prays the object of modulation discharge process and plasma transport process.
As shown in Figure 3, using said external power module 6 and propulsion device body structure and as a propulsion unit 10, multiple identical propulsion unit lines up dot matrix, and for the ease of controlling the work of propulsion unit, possible propulsion unit spread pattern comprises ring and Two-Dimensional Moment formation.The permanent magnet 9 of outside suit annular forms multi-cavity propulsion device, fill insulant between permanent magnet 9 and each propulsion unit.
The 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 size microcavity discharge plasma micro-thruster, is characterized in that: comprise propulsion device body structure, permanent magnet (9) and external power supply module (6); Propulsion device body structure comprises liquid propellant storage tank (8), propellant agent working medium feed mechanism (7), tinsel, dielectrics (3) and Rafael nozzle (4); Wherein, under direct-current discharge condition, tinsel forms the anode (1), the negative electrode (2) that exist in pairs respectively;
Liquid propellant in liquid propellant storage tank (8) also diffuses in electric discharge microcavity by propellant agent working medium feed mechanism (7) controlled medium flow, tinsel is run through in the hole that described electric discharge microcavity is not waited by a diameter and insulation dielectric (3) is formed, insulation dielectric is clipped between adjacent two tinsels, and adjacent two tinsels form an electrode pair; The tinsel of electric discharge microcavity end and insulation dielectric composition daraf(reciprocal of farad) that spout (4), wherein, insulation dielectric forms contraction section and the extending section of your spout (4) of daraf(reciprocal of farad), the throat of your spout (4) of anode metal sheet composition daraf(reciprocal of farad), it forms an electrode pair with the cathodic metal sheet being positioned at daraf(reciprocal of farad) that spout (4) extending section outlet port; The horizontal segment of your spout (4) of daraf(reciprocal of farad) at least arranges an electrode pair, external power supply module (6) provides and periodically exchanges or direct current high voltage pulses voltage, and utilizing wire to be connected on each electrode pair, the permanent magnet (9) of annular is sleeved on outside the tube wall of above-mentioned electric discharge microcavity.
2. magnetic field according to claim 1 regulation type liquid phase working fluid large size microcavity discharge plasma micro-thruster, it is characterized in that: using said external power module (6) and propulsion device body structure as a propulsion unit (10), multiple identical propulsion unit lines up dot matrix, permanent magnet (9) the composition multi-cavity propulsion device of outside suit annular, fill insulant between permanent magnet (9) and each propulsion unit.
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105704903A (en) * | 2016-03-16 | 2016-06-22 | 北京交通大学 | Discharging electrode structure generated by vacuum plasmas based on magnetic field effects |
| CN106704132A (en) * | 2017-01-12 | 2017-05-24 | 安徽工程大学 | Ferroelectric micro-plasma propeller |
| 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 |
| CN107165794A (en) * | 2017-06-12 | 2017-09-15 | 北京航空航天大学 | A kind of adjustable low-power hall thruster with magnetic screening effect in magnetic field |
| CN107620652A (en) * | 2016-10-28 | 2018-01-23 | 湖北航天化学技术研究所 | A kind of multiple-pulse adjustable thrust Solid propeller |
| CN107882702A (en) * | 2017-10-24 | 2018-04-06 | 哈尔滨工业大学 | Rafael nozzle formula magnetic confinement hollow cathode |
| CN107975462A (en) * | 2016-10-21 | 2018-05-01 | 南京理工大学 | Electric heating microthruster |
| CN108612599A (en) * | 2016-12-10 | 2018-10-02 | 中国科学院大连化学物理研究所 | A kind of liquid-electricity interblock space thruster |
| CN109779781A (en) * | 2019-03-15 | 2019-05-21 | 常熟理工学院 | The magnetic fluid for improving pulse detonation engine thrust controls jet pipe |
| CN110799751A (en) * | 2017-05-16 | 2020-02-14 | 赛峰飞机发动机公司 | Device for regulating the flow of a propellant fluid for an electric thruster |
| CN111173698A (en) * | 2018-11-09 | 2020-05-19 | 哈尔滨工业大学 | Liquid working medium plasma thruster based on microwave enhancement |
| CN114135457A (en) * | 2021-11-30 | 2022-03-04 | 中国工程物理研究院电子工程研究所 | Ion propeller |
| CN114337349A (en) * | 2021-12-30 | 2022-04-12 | 哈尔滨工业大学 | Pulse power source for simulating solar wind |
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Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105704903A (en) * | 2016-03-16 | 2016-06-22 | 北京交通大学 | Discharging electrode structure generated by vacuum plasmas based on magnetic field effects |
| 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 |
| CN107975462A (en) * | 2016-10-21 | 2018-05-01 | 南京理工大学 | Electric heating microthruster |
| CN107620652A (en) * | 2016-10-28 | 2018-01-23 | 湖北航天化学技术研究所 | A kind of multiple-pulse adjustable thrust 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 |
| CN108612599A (en) * | 2016-12-10 | 2018-10-02 | 中国科学院大连化学物理研究所 | A kind of liquid-electricity interblock space thruster |
| CN106704132A (en) * | 2017-01-12 | 2017-05-24 | 安徽工程大学 | Ferroelectric micro-plasma propeller |
| CN110799751A (en) * | 2017-05-16 | 2020-02-14 | 赛峰飞机发动机公司 | Device for regulating the flow of a propellant fluid for an electric thruster |
| 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 |
| 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 |
| CN107165794A (en) * | 2017-06-12 | 2017-09-15 | 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 |
| CN111173698A (en) * | 2018-11-09 | 2020-05-19 | 哈尔滨工业大学 | Liquid working medium plasma thruster based on microwave enhancement |
| CN109779781A (en) * | 2019-03-15 | 2019-05-21 | 常熟理工学院 | The magnetic fluid for improving pulse detonation engine thrust controls jet pipe |
| 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 |
| CN114135457A (en) * | 2021-11-30 | 2022-03-04 | 中国工程物理研究院电子工程研究所 | Ion propeller |
| CN114337349A (en) * | 2021-12-30 | 2022-04-12 | 哈尔滨工业大学 | Pulse power source for simulating solar wind |
| 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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