CN110145446B - Pulse electrically-excited micro-cow propulsion device - Google Patents
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- CN110145446B CN110145446B CN201910510644.8A CN201910510644A CN110145446B CN 110145446 B CN110145446 B CN 110145446B CN 201910510644 A CN201910510644 A CN 201910510644A CN 110145446 B CN110145446 B CN 110145446B
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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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Abstract
A pulse electrically excited micro-cow propulsion device belongs to the technical field of plasma micro-propulsion. The invention solves the problems that the ionization adjusting means of the existing thruster is single, the high-efficiency stable work of large-range adjustment cannot be met, and the requirement on quick response in the satellite non-dragging control cannot be met. The discharge chamber main part is the barrel-shaped structure, through-hole, first annular channel and second annular channel have coaxially been seted up on the base, the inner skleeve insert establish in first annular channel and with the base rigid coupling, the outer sleeve insert establish in the second annular channel and with the base rigid coupling, all around being equipped with the coil on the outer wall that lies in the discharge chamber outside on every sleeve, microwave input unit insert establish in the through-hole and with the base rigid coupling, and the microwave input unit is gone up the one end that lies in the discharge chamber and has set firmly annular microwave antenna coaxially, still set up a plurality of air feed holes that quantity and a plurality of air feed unit are the same on the base, and a plurality of air feed unit corresponds through a plurality of air feed holes intercommunication with the discharge chamber.
Description
Technical Field
The invention relates to a pulse electrically-excited micro-cow propulsion device, and belongs to the technical field of plasma micro-propulsion.
Background
Compared with a chemical system, the electric propulsion system has the advantages of higher thrust, low thrust and the like, less fuel is needed for completing the same task, the cost is reduced, the speed increment is larger, the electric propulsion system can work for a longer time, and the space mission at a longer distance becomes practical. The electric thruster is a core subunit of an electric propulsion system, can be divided into three major categories, namely an electric heating type, an electrostatic type and an electromagnetic type according to different propellant acceleration modes, wherein an electrostatic ion thruster accelerates charged particles by using an electrostatic field, a reaction force generated by a high-speed ejected ion beam is the thrust of the thruster, an electron cyclotron resonance thruster (ECRIT) belongs to the ion thruster, a magnetic field placing strategy realizes a magnetic mirror effect, when the charged particles in the center of the magnetic mirror move to two sides, the charged particles are reflected to the center by the magnetic mirror force, the plasma is restrained by the magnetic field, the electron restraining capability is improved, and the ionization rate of a working medium is improved; the ECRIT has a cathode-free discharge scheme, avoids cathode ablation, has the characteristics of long service life, high specific impact, simple structure and the like, and is suitable for being used as a main propulsion device of a deep space detector.
With the continuous progress of aerospace technology, in order to meet the requirements of future scientific research, technical verification, satellite communication, deep space exploration and military missions, the application of the plasma propulsion unit in future aerospace will become more and more extensive, the requirements on the aspects of spacecraft attitude control, height control, orbit accuracy and the like will be higher, and micro-propulsion and variable thrust are one of the future development directions.
The prior electron cyclotron resonance thruster structure has the following problems: in order to achieve the lower limit of the thrust, the size of a discharge chamber is required to be miniaturized, the surface-to-volume ratio is increased, the problem that the plasma electron wall surface in the thruster is lost and the like is caused, and the conventional thruster is single in ionization adjusting means and cannot meet the problem of efficient and stable operation of large-range adjustment.
Disclosure of Invention
The invention provides a pulse electrically-excited micro-Newton propulsion device, which aims to solve the problems that the ionization adjusting means of the existing thruster is single, the high-efficiency stable work of large-range adjustment cannot be met, and the requirement on quick response in satellite non-towing control cannot be met.
The technical scheme adopted by the invention for solving the technical problems is as follows:
a pulse electro-magnetic micro-cow propulsion device comprises a discharge chamber, an inner sleeve, an outer sleeve, a microwave input unit and a plurality of air supply units, wherein the discharge chamber comprises a discharge chamber main body, a base fixedly connected to one end of the discharge chamber main body and a grid accelerating unit fixedly connected to the other end of the discharge chamber main body, the discharge chamber main body is of a cylindrical structure, a through hole, a first annular channel and a second annular channel are coaxially formed in the base, the inner sleeve is inserted into the first annular channel and fixedly connected with the base, the outer sleeve is inserted into the second annular channel and fixedly connected with the base, a coil is wound on the outer wall of each sleeve outside the discharge chamber, the microwave input unit is inserted into the through hole and fixedly connected with the base, an annular microwave antenna is coaxially fixedly arranged at one end of the microwave input unit, which is located in the discharge chamber, and a plurality of air supply holes with the same number as the plurality of air supply units, and the plurality of gas supply units are correspondingly communicated with the discharge chamber through a plurality of gas supply holes.
Furthermore, the grid accelerating unit comprises a screen and an accelerating grid, wherein the screen is arranged close to the microwave input unit, the potential of the screen is a positive potential, and the potential of the accelerating grid is a negative potential.
Furthermore, the diameters of a plurality of second lead-out holes formed in the accelerating grid are smaller than the diameters of a plurality of first lead-out holes formed in the screen grid.
Further, the current of the coils wound on the inner sleeve is smaller than that of the coils wound on the outer sleeve, and the current directions of the two groups of coils are opposite.
Further, a plurality of air supply holes are arranged on the outer side of the outer sleeve.
Furthermore, the number of the plurality of air supply holes is 20, and the air supply holes are uniformly distributed on the base.
Furthermore, the main body of the discharge chamber is a stainless steel cylinder, the length of the stainless steel cylinder is less than or equal to 20mm, the base is a steel base, and the inner sleeve and the outer sleeve are made of DT4C type soft iron materials.
Compared with the prior art, the invention has the following effects:
1. in the process of realizing thrust miniaturization, under the action of the magnetic circuit unit, a small amount of charged electrons in a motion state are subjected to the lorentz force centripetal force to form electron cyclotron motion, and the electrons are bound in the discharge chamber due to the magnetic mirror effect. The microwave input unit is directly contacted with the discharge area, microwaves are transmitted into the discharge chamber without reservation, once the frequency of the electromagnetic waves reaches the frequency of the gyration angle, electrons can absorb the microwave energy to the maximum extent and collide with neutral gas, and the neutral gas is ionized to generate plasma. In the process, the stable discharge can be realized under the low-pressure and low-flow condition, and the discharge mechanism is based on microwave and electron cyclotron coupling, so that the requirement on quick response in the satellite drag-free control is met. The discharge cavity is small, the air pressure is low, the lower thrust lower limit can be achieved compared with the existing thruster, and a low-power electric propulsion product is achieved in the field of microsatellites.
2. The discharge chamber adopts miniaturized cylindrical cavity in this application, and the linear polarization electromagnetic wave that enters into in the discharge chamber can be decomposed into two circular polarization waves that the direction of rotation is opposite, and wherein the electron cyclotron wave is in the right-handed polarized wave frequency range. The electrons gain energy from the electric field through a non-collision heating mechanism, constantly in the direction perpendicular to the magnetic field. After the electrons are accelerated by the microwave, if the energy of the electrons is higher than the first ionization energy of neutral ions, the electrons collide with the neutral gas to ionize the neutral gas to form plasma. However, because the radius of the cavity is small, the maximum cutoff wavelength (namely, the cutoff wavelength of the fundamental mode) in each transmission mode calculated according to the method is smaller than the working wavelength of the microwave thruster, at the moment, the electromagnetic field is in a sine oscillation wave state of in-situ vibration, the electromagnetic waves are not transmitted forwards any more and are in the cutoff state, and by utilizing the characteristic, the discharge volume is adjusted, so that the beneficial effect can be generated on the ion source beam.
3. The microwave input is completed by directly exposing an annular microwave antenna in the electron cyclotron resonance cavity, an electric field intensity equipotential line generated by the annular microwave antenna is better parallel to a magnetic line of force in the electron cyclotron resonance region, a magnetic field and microwave matching result is closer to a calculation result, and a corresponding electron capacitation index is maximum. Meanwhile, the surface area of the annular microwave antenna is smaller, and the collision loss of plasma on the wall surface of the antenna can be effectively reduced. In addition, the problem of difficult microwave transmission is solved by the exposure of the antenna, and energy is directly absorbed by electrons to achieve extremely high microwave plasma absorption rate.
4. The utility model provides a magnetic circuit unit is realized by pulsed electric excitation, and the magnetic field that the iron sleeve part that stretches into in the cavity produced is inhomogeneous, forms the magnetic mirror effect, and when the charged particle at magnetic mirror center moved to both sides, by magnetic mirror power restraint reflection back center, the motion region of charged particle just is restricted between the magnetic mirror, can effectively prolong the electron at the dwell time of discharge chamber, reduces the loss of electron and wall collision, improves working medium ionization rate.
5. The pulse type electric excitation changes the magnetic field intensity by adjusting the current, removes the constraint of single magnetic field intensity brought by a permanent magnet in the prior art, and realizes the adjusting mode of variable thrust. Under the condition that the air supply flow is changed in a large range, the current is changed, the magnetic field intensity and the position are changed along with the change, and the size and the position of an electron cyclotron resonance surface generated by matching with microwaves are changed. The size and the position of the resonance surface are used for measuring the discharge scale of the device. The resonance surface is enlarged, the discharge scale is obviously increased, the gas ion movement area is adjustable, and the working medium utilization rate can be effectively improved. The extraction of ion beams can be influenced by the change of the position of the electron cyclotron resonance surface, the closer the distance between the resonance surface and the grid is, the easier the extraction of gas ions is, the thrust is increased along with the extraction of the gas ions, and meanwhile, the more serious corrosion problem can be caused; conversely, the shorter the distance, the more difficult the gas ion extraction, the less the thrust, and the better the erosion problem.
In addition, this application has expressed very big superiority under the further discharge chamber size condition that reduces, and the processing degree of difficulty that millimeter level permanent magnetism device reduces again is great, and the magnetic conduction sleeve processing degree of difficulty among the electric excitation device is less, and the section of thick bamboo wall can be accomplished thinly, reaches lower thrust lower limit.
Drawings
FIG. 1 is a main cross-sectional schematic view of the present application;
FIG. 2 is a schematic right view of a microwave input unit;
FIG. 3 is a schematic diagram of the position simulation of the resonance surface generated when the inner coil current is 10A;
fig. 4 is a schematic diagram of the position simulation of the resonance surface generated when the inner coil current is 4A.
Detailed Description
The first embodiment is as follows: the present embodiment is described with reference to fig. 1 to 4, a pulse electro-magnetic micro-cow propulsion device, which includes a discharge chamber 1, an inner sleeve 2, an outer sleeve 3, a microwave input unit 4 and a plurality of gas supply units 5, wherein the discharge chamber 1 includes a discharge chamber main body 11, a base 12 fixedly connected to one end of the discharge chamber main body 11, and a grid accelerating unit 13 fixedly connected to the other end of the discharge chamber main body 11, the discharge chamber main body 11 is a cylindrical structure, the base 12 is coaxially provided with a through hole, a first annular channel and a second annular channel, the inner sleeve 2 is inserted into the first annular channel and fixedly connected to the base 12, the outer sleeve 3 is inserted into the second annular channel and fixedly connected to the base 12, a coil 6 is wound around an outer wall of each sleeve located outside the discharge chamber 1, the microwave input unit 4 is inserted into the through hole and fixedly connected to the base 12, and an annular microwave antenna 41 is coaxially fixed to one end of the microwave input unit 4 located inside the discharge chamber 1, the base 12 is further provided with a plurality of air supply holes 12-1, the number of the air supply holes is the same as that of the air supply units 5, and the air supply units 5 are correspondingly communicated with the discharge chamber 1 through the air supply holes 12-1.
The inner sleeve, the outer sleeve and the coil 6 wound on the inner sleeve form an electric excitation adjusting unit which is positioned at the front end of the discharge chamber 1 and generates a time-varying magnetic field by supplying power to the coil 6;
the grid accelerating unit 13 is positioned at the rear end of the discharge area, and ions are accelerated to be sprayed out to generate thrust and are neutralized with electrons emitted by a neutralizer of the thruster; a stable working medium airflow is provided for the thruster through the air supply unit 5;
and the microwave supply unit acquires pulse microwaves with a certain frequency from the microwave power supply and provides microwave input to the thruster.
The main area in the discharge chamber 1 is an electron cyclotron resonance area 7 generated by the cooperation of the electric excitation adjusting unit and the microwave input unit 4.
The electromagnetic induction type microwave plasma discharge lamp is characterized in that a time-varying magnetic field which responds to electric excitation and is generated by supplying power to a coil 6 wound on an inner sleeve and an outer sleeve is formed, a magnetic circuit unit is located at the front end of a discharge area to guide electron cyclotron motion and is matched with microwaves generated by a microwave input unit 4 to form electron cyclotron resonance, a ring-shaped microwave antenna 41 on the microwave input unit 4 is directly exposed in an electron cyclotron resonance area 7, the problem that the microwaves are difficult to transmit is solved, energy is directly absorbed by electrons to achieve high microwave plasma absorption rate, and the electron cyclotron resonance area 7 is located in a discharge chamber 1.
An electric excitation adjusting unit switch positioned outside the discharge chamber 1 is connected in parallel with a microwave power supply, pulse microwaves with certain frequency are obtained from the microwave power supply and enter the discharge chamber 1 through a microwave input unit 4, a ring-shaped microwave antenna 41 arranged at the center of the discharge chamber 1 emits corresponding microwave frequency, a strong magnetic field area is formed in the cylindrical discharge chamber 1, the time-varying magnetic field change frequency is set to be consistent with the microwave change frequency, rare gas is introduced between an inner sleeve and an outer sleeve through an air supply unit 5 after the magnetic field intensity is adjusted to a certain value, the microwave frequency is equal to the electron cyclotron frequency, the microwaves generated by the ring-shaped microwave antenna 41 extending into the area and the magnetic field act together to generate a large amount of plasma, the grid accelerating unit 13 acts together to lead out the plasma, and electrons are prevented from being accelerated out through a beam path.
One side of the inner sleeve and the outer sleeve positioned in the discharge chamber 1 generates magnetic lines of force 8, the microwave input unit 4 extends into the center of the discharge chamber 1 to input microwaves, the microwaves generate resonance when the frequency of the microwaves is the same as the frequency of the electron gyration angle, an electron cyclotron resonance area 7 is formed, the electrons are heated to absorb energy, the electrons collide with working medium gas sent by the gas supply unit 5, and generated plasma is led out by the grid accelerating unit 13, the grid accelerating unit 13 comprises a screen 13-1 and an accelerating grid 13-2 which are coaxially arranged, the radius of a plurality of first lead-out holes 13-11 formed in the screen 13-1 is larger than the radius of a plurality of second lead-out holes 13-21 formed in the accelerating grid 13-2, the potential of the screen 13-1 is a positive potential close to kilovolt, the potential of the accelerating grid 13-2 is a negative potential, and a ceramic gasket can be adopted between the two grids for insulation treatment.
The coil 6 wound on the inner sleeve 2 is an inner coil, the coil 6 wound on the outer sleeve 3 is an outer coil, the current of the inner coil and the current of the outer coil are changed, the size and the position of the formed resonance surface 9 are changed, and the size and the position are particularly obvious in a miniaturized cavity. For example, when the inner coil is provided with 200 turns and the outer coil is provided with 90 turns, the position of the resonance surface 9 formed when the inner coil current is 10A is shown in fig. 3, and the position of the resonance surface 9 formed when the inner coil current is 4A is shown in fig. 4.
The working principle is as follows:
under the action of the magnetic circuit unit, the small amount of charged electrons in motion state are subject to the centripetal force of lorentz force to form electron cyclotron motion, and the electrons are bound in the discharge chamber 1 due to the magnetic mirror effect. The microwave input unit 4 is formed by directly exposing an annular microwave antenna 41 in an electron cyclotron resonant cavity, microwaves are transmitted into the discharge chamber 1 without reservation, an electromagnetic field presents a sine oscillation wave state of in-situ vibration, the electromagnetic waves are not transmitted forwards and are in a cut-off state, once the frequency of the electromagnetic waves reaches the gyration angle frequency, electrons obtain energy from the electric field through a collision-free heating mechanism continuously in the direction perpendicular to the magnetic field, power is supplied to a coil 6 wound on an inner sleeve and an outer sleeve, the working medium utilization rate is influenced by changing the intensity and the position of the magnetic field through regulating current, the extraction of particle beams is influenced by different resonance surface 9 positions, and under the combined action of the two, gas ionization is greatly improved. After the electrons are accelerated by microwaves, if the energy of the electrons is higher than the first ionization energy of neutral ions, the electrons collide with neutral gas to ionize the neutral gas to form plasma, and the plasma is led out under the combined action of the screen grid 13-1 and the acceleration grid 13-2 unit to prevent the electrons from being accelerated out through a beam path. Different numbers of ion beam current are guided out by different magnetic field strengths and bit types, and the adjusting mode of variable thrust is realized. However, because the radius of the discharge chamber 1 is small, the maximum cutoff wavelength (namely, the cutoff wavelength of the fundamental mode) in each transmission mode calculated according to the radius is smaller than the working wavelength of the microwave thruster, at the moment, the electromagnetic field is in a sine oscillation wave state of in-situ vibration, the electromagnetic waves are not transmitted forwards any more and are in the cutoff state, and by utilizing the characteristic, the discharge volume is adjusted, so that the beneficial effect can be generated on the ion source beam.
Once the frequency of the electromagnetic wave reaches the frequency of the gyration angle, the electrons can absorb the microwave energy to the maximum extent and collide with neutral gas, and the neutral gas is ionized to generate plasma. In the process, the electron cyclotron resonance thruster can realize stable discharge under the condition of low air pressure and small flow, and a discharge mechanism is based on microwave and electron cyclotron coupling, so that the requirement of quick response in the satellite drag-free control is met. Making it possible.
The invention has small discharge cavity and low air pressure, realizes lower thrust lower limit than the existing thruster, and realizes a low-power electric propulsion product in the field of microsatellites. The ionization adjusting means is not single any more, stable discharge under the condition of low pressure and small flow is realized, and the efficient and stable work of large-range adjustment is realized. The problem of microwave transmission difficulty has been solved through the microwave unit design of this application.
The grid microwave unit comprises an ultra-kilovolt screen 13-1 and an accelerating grid 13-2 (the height of the voltage value carried by the screen 13-1 is adjustable) for extracting ion beams, the accelerating grid 13-2 is loaded with negative potential to lead out the ion beams and generate reverse thrust, and tens of small holes are formed in each grid. The screen grid 13-1 and the accelerating grid 13-2 act together to lead out the plasma and prevent electrons from being accelerated out through a beam path.
The grid accelerating unit 13 comprises a screen 13-1 and an accelerating grid 13-2, wherein the screen 13-1 is arranged close to the microwave input unit 4, the potential of the screen 13-1 is a positive potential, and the potential of the accelerating grid 13-2 is a negative potential. The accelerating grid 13-2 is loaded with negative potential to lead out ion beam current and generate reverse thrust, and tens of small holes are formed in each grid. The screen grid 13-1 and the accelerating grid 13-2 act together to lead out the plasma and prevent electrons from being accelerated out through a beam path.
The diameter of a plurality of second lead-out holes 13-21 arranged on the accelerating grid 13-2 is smaller than that of a plurality of first lead-out holes 13-11 arranged on the screen grid 13-1.
The current of the coils 6 wound on the inner sleeve 2 is less than that of the coils 6 wound on the outer sleeve 3, and the current directions of the two groups of coils 6 are opposite.
A plurality of air supply holes 12-1 are provided on the outer side of the outer sleeve 3.
The number of a plurality of air supply holes is 20, and the equipartition is on the base. Ensuring that the gas uniformly enters the discharge chamber.
The discharge chamber body 11 is a stainless steel cylinder with a length less than or equal to 20mm, the base 12 is a steel base 12, and the inner sleeve 2 and the outer sleeve 3 both adopt DT 4C.
Claims (6)
1. The utility model provides a little ox advancing device of pulse electricity excitation which characterized in that: the microwave discharge chamber comprises a discharge chamber (1), an inner sleeve (2), an outer sleeve (3), a microwave input unit (4) and a plurality of gas supply units (5), wherein the discharge chamber (1) comprises a discharge chamber main body (11), a base (12) fixedly connected to one end of the discharge chamber main body (11) and a grid accelerating unit (13) fixedly connected to the other end of the discharge chamber main body (11), the discharge chamber main body (11) is of a cylindrical structure, a through hole, a first annular channel and a second annular channel are coaxially formed in the base (12), the inner sleeve (2) is inserted in the first annular channel and fixedly connected with the base (12), the outer sleeve (3) is inserted in the second annular channel and fixedly connected with the base (12), a coil (6) is wound on the outer wall of the outer part of the discharge chamber (1) on each sleeve, and the microwave input unit (4) is inserted in the through hole and fixedly connected with the base (12), and the one end that lies in discharge chamber (1) on microwave input unit (4) is coaxial to be set firmly annular microwave antenna (41), still set up a plurality of air feed holes (12-1) that quantity and a plurality of air feed unit (5) are the same on base (12), and a plurality of air feed unit (5) correspond through a plurality of air feed holes (12-1) intercommunication with discharge chamber (1), grid acceleration unit (13) are including screen bars (13-1) and acceleration grid (13-2), wherein screen bars (13-1) are close to microwave input unit (4) and set up, and screen bars (13-1) electric potential is positive potential, and acceleration grid (13-2) electric potential is negative potential.
2. A pulsed electrically excited micro-cow propulsion device according to claim 1, wherein: the diameter of a plurality of second lead-out holes (13-21) formed in the accelerating grid (13-2) is smaller than that of a plurality of first lead-out holes (13-11) formed in the screen grid (13-1).
3. A pulsed electrically excited micro-cow propulsion device according to any one of claims 1 or 2, wherein: the current of the winding coil (6) on the inner sleeve (2) is less than that of the winding coil (6) on the outer sleeve (3), and the current directions of the two groups of coils (6) are opposite.
4. A pulsed electrically excited micro-cow propulsion device according to claim 3, wherein: the air supply holes (12-1) are all arranged on the outer side of the outer sleeve (3).
5. A pulsed electrically excited micro-cow propulsion device according to claim 4, wherein: the number of the air supply holes (12-1) is 20, and the air supply holes are uniformly distributed on the base (12).
6. A pulsed electrically excited micro-cow propulsion device according to any one of claims 1, 2, 4 or 5, wherein: the discharge chamber main body (11) is a stainless steel cylinder body, the length of the discharge chamber main body is less than or equal to 20mm, the base (12) is a steel base, and the inner sleeve (2) and the outer sleeve (3) are made of DT4C type soft iron materials.
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| CN110985323B (en) * | 2019-12-17 | 2021-01-19 | 大连理工大学 | Circular plate antenna crossed magnetic field microwave electron cyclotron resonance ion thruster |
| CN111287922A (en) * | 2020-02-13 | 2020-06-16 | 哈尔滨工业大学 | Dual-frequency dual-antenna small wave ionized ion propulsion device |
| CN111706482A (en) * | 2020-06-28 | 2020-09-25 | 哈尔滨工业大学 | Ion wind thrust device cooperated with microwave |
| CN113279930B (en) * | 2021-06-30 | 2022-07-12 | 哈尔滨工业大学 | Grid component assembly structure and assembly method of micro ion thruster |
| CN116390320A (en) * | 2023-05-30 | 2023-07-04 | 安徽农业大学 | Electron cyclotron resonance discharge device and application |
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