CN112224450B - Low-voltage electrospray emission device - Google Patents
Low-voltage electrospray emission device Download PDFInfo
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- CN112224450B CN112224450B CN202011130185.XA CN202011130185A CN112224450B CN 112224450 B CN112224450 B CN 112224450B CN 202011130185 A CN202011130185 A CN 202011130185A CN 112224450 B CN112224450 B CN 112224450B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
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Abstract
The invention discloses a low-voltage electrospray emission device, which comprises a supply device, an emission device, an accelerating device and a magnetic field device, wherein the supply device comprises a power supply unit, a power supply unit and a power supply unit, and the accelerating device comprises a power supply unit, a power supply unit and a power supply unit, and the power supply unit comprises a power supply unit, a power supply unit and a power supply unit, wherein the power supply unit comprises: the supply device is internally provided with magnetic ionic liquid serving as propellant, and the emission device is connected with the supply device and is used for emitting the magnetic ionic liquid in the form of particle beams; the accelerating device is positioned on an emission path of the particle beam and used for accelerating the particle beam; the magnetic field device is provided with a coil capable of generating a uniform magnetic field, wherein the direction of the uniform magnetic field is the same as the emission direction of the particle beam, and the particle beam is wrapped by the uniform magnetic field. By adopting the magnetic ionic liquid as a propellant and additionally arranging the uniform magnetic field in the electrospray thruster, the starting voltage can be greatly reduced, the working range can be effectively expanded, and the thrust density can be improved.
Description
Technical Field
The invention relates to the technical field of space propulsion, in particular to a low-voltage electrospray emission device.
Background
An electrospray thruster is an electrostatic thruster which takes conductive liquid as propellant, utilizes an electrostatic field to extract or generate charged liquid drops/ions in the propellant and accelerate the charged liquid drops/ions, and the basic composition and the working principle of the electrospray thruster are shown in fig. 1. A strong electrostatic field is applied between the extraction pole and the emitter, and the liquid propellant on the emitter bends at the top end of the emitter under the action of electrostatic force, fluid pressure, surface tension and viscous force to form a Taylor cone. Subsequently, the propellant at the tip of the taylor cone will form a charged liquid or ions under the influence of electrostatic forces. Under the action of electrostatic field, the charged liquid drops or ions are ejected from the extraction accelerating electrode, and then thrust is obtained.
From the structural composition of the electrospray thruster, the electrospray thruster mainly comprises an emitting device and a propellant supply device, wherein the emitting device comprises an emitting electrode (an emitting electrode array) and an extracting electrode (two electrodes, one extracting electrode and one accelerating electrode). Early electrospray thrusters often used a dielectric medium or a liquid metal as a propellant, so that the thrusters had a high starting voltage (5 kv) and large power consumption, and were not favorable for long-time operation of micro-nano satellites. In order to adapt to the characteristics of small volume, low electric power and the like of a micro-nano satellite, along with the development of synthesis and preparation of ionic liquid in recent years, the ionic liquid serving as room-temperature molten salt which is liquid at room temperature gradually becomes a main propellant of an electrospray thruster due to the advantages of high conductivity, low vapor pressure, low surface tension and the like.
Electrospray thrusters can be divided into two categories: colloid Thrusters (CT) and Field Emission Electric thrusters (FEEP).
The field emission electric thruster mainly comprises an emitter, an accelerating pole and a neutralizer. Low melting point metals (indium, cesium, etc.) are typically used as propellants and stored in the emitter. During operation, the propellant reservoir is heated, and the propellant melts to a liquid state and is drawn out through capillary action. High-voltage static electricity (6-13 kv) is applied between the accelerating electrode and the emitter, and a strong electric field is generated at the tip of the emitter, so that metal ions overcome surface tension and fly out in an accelerating manner to generate thrust. The thrust of a typical field emission electric thruster is 10-6～3×10-5N, minimum impulse of about 10-9N.s, specific impulse is generally 4X 103～1.2×104s。
The colloid thruster has different propellant and field emission electric thruster. The colloid thruster uses a conductive liquid as a propellant, such as sodium iodide solution, glycerol, etc. The thrust of a typical colloid thruster is 5 multiplied by 10-7～3×10-2N, minimum impulse of 5X 10-7s, specific impulse of 5X 102～1.5×103. The specific impulse of the field emission electric thruster and the colloid thruster is high and the thrust is small, the field emission electric thruster can provide micro impulse, and the colloid thruster can provide large-range thrust and specific impulse. The common disadvantages of both are: the operating voltage is high (-10 kv); low power-push ratio(ii) a The power consumption is large; a neutralizer is needed to mitigate plume contamination; the thruster lifetime is limited by the cathode emitter.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides the low-voltage electrospray emission device which not only can greatly reduce the starting voltage, but also can effectively expand the working range and improve the thrust density.
In order to achieve the above object, the present invention provides a low voltage electrospray emission device, comprising a supply device, an emission device, an acceleration device and a magnetic field device: the supply device is internally provided with magnetic ionic liquid serving as propellant, and the emission device is connected with the supply device and is used for emitting the magnetic ionic liquid in the form of particle beams; the accelerating device is positioned on an emission path of the particle beam and used for accelerating the particle beam; the magnetic field device is provided with a coil capable of generating a uniform magnetic field, wherein the direction of the uniform magnetic field is the same as the emission direction of the particle beam, and the particle beam is wrapped by the uniform magnetic field.
In one embodiment, the emitting device is a porous medium emitter, the accelerating device comprises an extraction electrode and an accelerating electrode, the extraction electrode is positioned between the porous medium emitter and the accelerating electrode, and gaps are arranged between the porous medium emitter and the extraction electrode and between the extraction electrode and the accelerating electrode; and the extraction electrode and the accelerator electrode are respectively provided with a plurality of grid holes, and the emission holes on the porous medium emitter, the grid holes of the extraction electrode and the grid holes of the accelerator electrode are in one-to-one correspondence.
In one embodiment, the magnetic field means comprises a first magnetic field induction coil surrounding the transmitting means.
In one embodiment, the magnetic field apparatus further comprises a second magnetic field induction coil surrounding the space between the extraction pole and the acceleration pole.
In one embodiment, the first magnetic field induction coil and the second magnetic field induction coil are both helmholtz coils.
In one embodiment, the porous medium emitting electrode is a porous material micro-cone array structure or a capillary cone column or a capillary cylinder array structure or a porous material edge type array structure.
In one embodiment, the porous dielectric emitter is made of a conductive material or a dielectric material.
In one embodiment, the extraction pole, the acceleration pole are made of a conductive material, or by sputtering a conductive material on a dielectric material.
In one embodiment, the magnetic ionic liquid is 1-ethyl-3-methylimidazolium tetrachloroferrate.
The low-voltage electrospray emission device provided by the invention has the following beneficial effects:
1. compared with the conventional electrospray thruster, the starting voltage of the electrospray thruster is mostly about 1-2 kv, and the starting voltage can be greatly reduced (by 20-30%) without influencing the emission current by increasing the magnetic field in the low-voltage electrospray emission device.
2. Because the Taylor cone can work in a stable state within a certain flow velocity, voltage and current range, and the working voltage range of the conventional electric spray thruster is too narrow, after a magnetic field is increased in the low-voltage electric spray emission device, the working range of the electric spray thruster can be expanded due to the stabilizing effect of the magnetic field on the Taylor cone;
3. the thrust density of the existing electrospray thruster is low and is only 0.1 muN/muA, and the thrust density of the electrospray thruster can be improved by increasing the acceleration effect of a magnetic field on ferromagnetic particles in the low-voltage electrospray emission device.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a schematic structural diagram of an electrospray thruster in the prior art;
FIG. 2 is a schematic diagram of a low voltage electrospray emission device according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of the magnetic field principle in an embodiment of the present invention;
fig. 4 is a schematic structural diagram of a helmholtz coil according to an embodiment of the present invention.
The reference numbers illustrate: the device comprises a porous medium emitter 1, an extraction pole 2, an acceleration pole 3, a first magnetic field induction coil 4, a second magnetic field induction coil 5, a supply device 6, a coil 7 and a coil support 8.
The implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that all the directional indicators (such as up, down, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.
In addition, the descriptions related to "first", "second", etc. in the present invention are only for descriptive purposes and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; the connection can be mechanical connection, electrical connection, physical connection or wireless communication connection; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In addition, the technical solutions in the embodiments of the present invention may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination of technical solutions should not be considered to exist, and is not within the protection scope of the present invention.
Fig. 2-3 show a low voltage electrospray emitter according to the present disclosure, which includes a supply device 6, an emitter, an accelerator, and a magnetic field device: the supply device 6 is internally provided with magnetic ionic liquid as propellant, and the emission device is connected with the supply device 6 and is used for emitting the magnetic ionic liquid in the form of particle beams; an accelerating device is positioned on an emission path of the particle beam and used for accelerating the particle beam; the magnetic field device is provided with a coil capable of generating a uniform magnetic field, wherein the direction of the uniform magnetic field is the same as the emission direction of the particle beam, and the particle beam is wrapped by the uniform magnetic field, wherein the uniform magnetic field in this embodiment is shown as the solid arrow direction in fig. 3.
The ionic liquid generally refers to room-temperature ionic liquid, also called room-temperature molten salt, is a liquid composed of anions and cations, and generally has the characteristics of high conductivity, negligible vapor pressure (10-9 Pa), low surface tension and wide liquid temperature range (-40-300 ℃). Ionic liquids have particular advantages when used as propellants in electrospray emission devices. The high conductivity enables it to have a higher emission current, and thus a greater thrust; the characteristics of negligible vapor pressure and liquid state maintenance reduce the difficulty of storage and supply of the propellant; the low surface tension allows ionic liquid electrothrusters to have a lower start-up voltage (-1 kv) than field emission electrothrusters and conventional colloid thrusters. In addition, compared with a common colloid thruster, the Ionic liquid electric thrust launching device can more easily achieve a pure ion launching mode (PIR), so that the specific impulse is far higher than that of the latter, and the utilization efficiency of the propellant is higher; and the thrust is smaller, smaller pulse impulse can be achieved, and the attitude and orbit adjustment of the micro-nano satellite can be more accurately carried out. The magnetic ionic liquid in the embodiment refers to an ionic liquid which can generate macroscopic response to an external magnetic field, has a certain magnetization intensity under the action of an external magnetic field, and has the physical and chemical characteristics of common ionic liquids. Compared with an electrospray thruster taking common ionic liquid as propellant, the electrospray thruster taking magnetic ionic liquid as propellant can greatly reduce the working voltage under the condition of not influencing the emission current and the thrust, can expand the working voltage range of the electrospray thruster and can greatly improve the working performance of the electrospray thruster. In the embodiment, the magnetic ionic liquid is used as the propellant, and the uniform magnetic field is additionally arranged in the electrospray thruster, so that the starting voltage can be greatly reduced, the working range can be effectively expanded, and the thrust density can be improved.
In this embodiment, the emitting device is a porous dielectric emitter 1, and specifically, the porous dielectric emitter 1 is a porous material micro-cone array structure, a capillary cone column, a capillary cylinder array structure, or a porous material edge array structure. The porous dielectric emitter 1 is made of a conductor material or a dielectric material, such as quartz glass, borosilicate glass, tungsten, graphite aerogel, etc., and the porous dielectric emitter 1 in the embodiment is preferably a porous material micro-cone array structure.
The accelerating device comprises an extraction electrode 2 and an accelerating electrode 3, wherein the extraction electrode 2 is positioned between the porous medium emitting electrode 1 and the accelerating electrode 3, and intervals are arranged between the porous medium emitting electrode 1 and the extraction electrode 2 and between the extraction electrode 2 and the accelerating electrode 3. The extraction electrode 2 and the acceleration electrode 3 are respectively provided with a plurality of grid holes, the emission holes on the porous medium emitting electrode 1, the grid holes of the extraction electrode 2 and the grid holes of the acceleration electrode 3 are in one-to-one correspondence, namely, the emission holes on the porous medium emitting electrode 1, the grid holes of the extraction electrode 2 and the grid holes of the acceleration electrode 3 which are mutually corresponding are sequentially connected into a straight line, and the ion beams emitted by the emission holes of the porous medium emitting electrode 1 are sequentially sprayed out after passing through the corresponding grid holes of the extraction electrode 2 and the grid holes of the acceleration electrode 3. Wherein, the grid holes on the extraction electrode 2 and the accelerating electrode 3 are round holes. The constraints of the beam current structures of the electrospray emission device on the porous medium emitter 1, the extraction electrode 2 and the acceleration electrode 3, the sizes and the intervals of the grid holes, the porous medium emitter 1, the extraction electrode 2 and the acceleration electrode 3 can be optimally designed, so that the reduction of the performance of the electrospray emission device due to beam current divergence caused by the structure of the single-electrode type emission device is avoided, and the optimization process is a conventional technical means in the field, so that the detailed description is omitted in the embodiment. In this embodiment, the extraction electrode 2 and the acceleration electrode 3 are made of a conductor material, or made by sputtering a conductor material on a dielectric material, the conductor material may be made of a material that is resistant to sputtering and has small thermal strain, such as tungsten, molybdenum, and graphite, the dielectric material may be made of a material such as quartz glass or borosilicate glass, and the coating layer is on the side where ions are not in direct contact with each other, so that the coating layer is prevented from being peeled off due to direct impact of ions. In the embodiment, the working potential of the accelerating electrode 3 is the same as the ground potential on the spacecraft, so that the condition that the beam particles erode the spacecraft due to potential drop generated between the electrospray emission device and the spacecraft is avoided.
In the present embodiment, the magnetic field device includes a first magnetic-field induction coil 4 surrounding the transmitter, and a second magnetic-field induction coil 5 surrounding the gap between the extraction pole 2 and the acceleration pole 3, wherein the first magnetic-field induction coil 4 and the second magnetic-field induction coil 5 are each a helmholtz coil. In this embodiment, the size, the winding diameter, and the number of turns of the first magnetic field induction coil 4 and the second magnetic field induction coil 5 are completely the same, and the first magnetic field induction coil 4 and the second magnetic field induction coil 5 are connected in series to supply the same-direction current during operation, so as to generate a uniform magnetic field or a pulse magnetic field in the central region. Referring to fig. 4, a single helmholtz coil is composed of a coil support 7 and a coil support 8, the coil 7 is made of an enameled copper wire, and the wire diameter and the number of turns are selected according to parameters such as working power, current and required magnetic induction intensity. The coil support 8 is generally made of a dielectric material, and can be made of special engineering materials such as PEEK and the like which are easy to process and have high mechanical strength and excellent performance.
The low voltage electrospray emission device of the present embodiment is further described below with reference to specific examples.
In this example 1-ethyl-3-methylimidazolium tetrachloroferrate-EMIMFeCl4As magnetic ionic liquid, in a pure ion working mode, most of particle beams emitted by an electrospray emission device are in ion clusters ([ EMIMFeCl ]4]nEMIM + or [ EMIMFeCl ]4]nFeCl4-) is present, the magnetic ionic liquid does not show magnetism under the condition of no external magnetic field, and has paramagnetism only under the condition of applying an external magnetic field.
When the electrospray emission device does not work, the Helmholtz coil is not electrified, when the electrospray emission device starts to work, the Helmholtz coil is also electrified to work, a uniform magnetic field is formed in a region between the two parallel coils, at the moment, under the action of an external magnetic field, magnetic metal elements in the magnetic ionic liquid can show paramagnetism, and at the moment, the movement of the magnetic ionic liquid is acted by electrostatic force, fluid pressure, surface tension, viscous force and magnetic field force together.
Under the condition of no magnetic field, the equilibrium state equation of the magnetic ionic liquid on the emitter can be expressed as follows:
Fg-Fst+Fe＝0
in the presence of a magnetic field, the equilibrium equation can be modified as:
Fg-Fst+Fe+Fm＝0
in the formula, FgIs the gravity to which the liquid is subjected, FstIs surface tension, FeIs the electrostatic force to which the liquid is subjected, FmThe magnetic field force is applied to the liquid along the direction of the magnetic induction line.
From the above equation, the larger the magnetic field force in equilibrium, the smaller the required electrostatic force, which depends on the potential difference between the emitter and the extraction electrode 2, given the geometry of the electrospray emitter. The introduction of a magnetic force will therefore reduce the voltage required to operate the electrospray emitter.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (6)
1. A low-voltage electrospray emitter device, comprising a supply device, an emitter device, an accelerator device, and a magnetic field device: the supply device is internally provided with magnetic ionic liquid serving as propellant, and the emission device is connected with the supply device and is used for emitting the magnetic ionic liquid in the form of particle beams; the accelerating device is positioned on an emission path of the particle beam and used for accelerating the particle beam; the magnetic field device is provided with a coil capable of generating a uniform magnetic field, wherein the direction of the uniform magnetic field is the same as the emission direction of the particle beam, and the particle beam is wrapped by the uniform magnetic field, wherein the uniform magnetic field is a uniform magnetic field or a pulse magnetic field;
the emitting device is a porous medium emitting electrode, the accelerating device comprises an extraction electrode and an accelerating electrode, the extraction electrode is positioned between the porous medium emitting electrode and the accelerating electrode, and intervals are arranged between the porous medium emitting electrode and the extraction electrode and between the extraction electrode and the accelerating electrode; the extraction electrode and the accelerator electrode are respectively provided with a plurality of grid holes, and the emission holes on the porous medium emitter, the grid holes of the extraction electrode and the grid holes of the accelerator electrode are in one-to-one correspondence;
the magnetic field device comprises a first magnetic field induction coil surrounding the transmitting device;
the magnetic field device further includes a second magnetic field induction coil surrounding a space between the extraction pole and the acceleration pole.
2. The low voltage electrospray emitter device according to claim 1, wherein said first and second magnetic field induction coils are all Helmholtz coils.
3. The low voltage electrospray emission device according to claim 1 or 2, wherein said porous medium emitting electrode is a porous material micro-cone array structure or a capillary cone column or a capillary cylinder array structure or a porous material edge array structure.
4. A low voltage electrospray emission device according to claim 1 or 2, wherein said porous dielectric emitter is made of a conductive or dielectric material.
5. A low voltage electrospray emission device according to claim 1 or 2, wherein said extraction pole, said acceleration pole are made of a conductive material or by sputtering a conductive material on a dielectric material.
6. A low voltage electrospray emitter according to claim 1 or 2, wherein said magnetic ionic liquid is 1-ethyl-3-methylimidazolium tetrachloroferrate.
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| CN113217318B (en) * | 2021-05-21 | 2022-04-01 | 中国人民解放军国防科技大学 | Electrospray thruster assembly structure and preparation method thereof |
| CN113306746B (en) * | 2021-05-26 | 2022-10-14 | 成都天巡微小卫星科技有限责任公司 | Iodine working medium electric propulsion storage and supply system based on sonic nozzle flow control |
| CN114002634A (en) * | 2021-11-15 | 2022-02-01 | 安徽工程大学 | Calibration device and method for magnetic field-voltage coefficient of multi-channel magnetocardiogram detection system |
| CN116613052B (en) * | 2023-07-19 | 2023-12-19 | 杭州凯莱谱质造科技有限公司 | Electrospray ion source with external magnetic field and mass spectrometer |
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| CN110500250A (en) * | 2019-09-04 | 2019-11-26 | 北京航空航天大学 | A kind of helicon electromagnetism acceleration plasma source |
| CN211397783U (en) * | 2019-06-28 | 2020-09-01 | 中国人民解放军国防科技大学 | Ultra-low rail variable thrust air suction type magnetic plasma thruster |
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| US20190107103A1 (en) * | 2017-10-09 | 2019-04-11 | Phase Four, Inc. | Electrothermal radio frequency thruster and components |
| CN108275288B (en) * | 2017-12-19 | 2020-04-10 | 上海空间推进研究所 | Non-toxic dual-mode micro-propulsion system and working method thereof |
| US11067064B2 (en) * | 2018-02-26 | 2021-07-20 | Massachusetts Institute Of Technology | Propulsion systems including a sublimable barrier |
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| CN110500250A (en) * | 2019-09-04 | 2019-11-26 | 北京航空航天大学 | A kind of helicon electromagnetism acceleration plasma source |
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