CN111306024B - Microwave ion propulsion unit based on lateral wall cusped magnetic field - Google Patents
Microwave ion propulsion unit based on lateral wall cusped magnetic field Download PDFInfo
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- CN111306024B CN111306024B CN202010093562.0A CN202010093562A CN111306024B CN 111306024 B CN111306024 B CN 111306024B CN 202010093562 A CN202010093562 A CN 202010093562A CN 111306024 B CN111306024 B CN 111306024B
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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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- 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
- F03H1/0006—Details applicable to different types of plasma thrusters
- F03H1/0018—Arrangements or adaptations of power supply systems
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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
- F03H1/0031—Thermal management, heating or cooling parts of the thruster
Abstract
The invention provides a microwave ion propulsion device based on a side wall cusped magnetic field, which comprises a discharge chamber and a side wall cusped magnetic field unit, microwave input unit and gas supply unit, the discharge chamber includes the discharge cavity, diapire and grid accelerating unit, arrange gas supply unit and microwave input unit on the diapire, lateral wall cusped magnetic field unit includes two lateral wall magnet rings at least, all lateral wall magnet rings all arrange with the discharge cavity is coaxial, all lateral wall magnet rings adopt homopolar relative mode to arrange on the internal face of discharge cavity, the internal face of discharge cavity is covered with to a plurality of lateral wall magnet rings, lateral wall cusped magnetic field unit forms the electron cyclotron resonance face in the discharge chamber, the microwave input unit stretches into the diapire central authorities of discharge chamber and is fretwork taper cage type antenna input microwave, fretwork taper cage type antenna is located the strong magnetic field area of electron cyclotron resonance face upper reaches, gas supply unit lets in working medium gas to the discharge cavity. The invention can maintain lower plasma density and lower thrust lower limit.
Description
Technical Field
The invention belongs to the field of plasma micro-propulsion, and particularly relates to a microwave ion propulsion device based on a side wall cusped magnetic field.
Background
With the requirement of a space-based gravitational wave detection task in recent years, the precision requirement of the satellite spacing of the satellite formation reaches 10-21, the drag-free control of the space-based gravitational wave detection task puts thrust requirements of low thrust lower limit (1 mu N), wide thrust adjusting range (50-100 times), high precision, high stability and high resolution (0.1 mu N) on the propelling device, and further the propelling device is required to be miniaturized.
An Electron Cyclotron Resonance Ion Thruster (ECRIT) is a thruster which utilizes the resonance of microwave frequency and electron around the cyclotron frequency of magnetic lines of force to further heat electrons to generate working medium ionization, and then utilizes ion beams ejected by a grid electric field at high speed to generate reaction force. The ionization type ion source has the characteristics of high ionization rate, high specific impulse, simple structure and the like. Falcon No. 2 falcon detectors in japan both use this type of thruster as their main thruster for deep space exploration tasks. Meanwhile, the grid current of the ion thruster has a direct numerical relationship with the thrust, which provides great convenience for thrust measurement and drag-free feedback control. More importantly, the mode of ECR resonance heating determines the basic conditions of wide range of the working air pressure, low thrust and wide range adjustment of the thrust.
Currently, the microminiature ECRIT takes a Japanese mu-1 thruster as the highest level of development. The mu-1 microminiature ECR ion thruster adopts a bottom wall cusped magnetic field configuration, the diameter of the thruster is typically 20mm, and the typical thrust value is 300 mu N. Aiming at the above-mentioned wide-range requirement of low thrust for the thruster for the space-based gravitational wave detection, the current ECRIT structure has the following two problems: (1) under the restriction of a magnetic field condition, the diameter of a tangential magnetic ring at the bottom wall of a channel of an ionization chamber cannot be too small, so that the diameter of a thruster is 20mm high, and the thrust is positively correlated with the section of the channel of the thruster, so that the lower limit of the thrust which can be reached by the thruster can not meet the requirement of the lower limit of the thrust; (2) the magnetic field configuration strategy can only form a magnetic mirror effect on the bottom wall of the thruster channel, and the side wall is basically not limited, so that the ionization loss of the side wall surface in the whole discharge chamber is severe, the working can not be maintained in the extremely thin state of the plasma, and the lower limit of the thrust is further limited. In addition, there are two other disadvantages to be improved: (1) the bottom wall double magnetic rings only can construct two magnetic mirror regions, so that the movement path of electrons between the magnetic mirror regions is single, the movement distance of the electrons is limited, and the ionization sufficiency and the efficiency improvement of a thruster are limited; (2) the resonance surface can only be designed into one layer in the ionization chamber at the outer side of the magnetic ring, the design configuration is single, and the adjustable margin is small.
Disclosure of Invention
In view of the above, the present invention provides a microwave ion propulsion device based on a side wall cusped magnetic field, which changes the original bottom wall magnet arrangement method, removes the bottom wall outer layer magnetic ring (or removes both the inner and outer magnetic rings), and reduces the restriction that the size of the bottom wall magnetic ring cannot reduce the inner diameter of the thruster; meanwhile, the side wall is formed by butting a plurality of magnetic rings, the side wall magnets are arranged in a mode of homopolar opposition, and magnetic tips of a side wall multistage cusped magnetic field are formed between the magnetic rings to form a magnetic mirror field inside the ionization chamber. The side wall cusped magnetic field restrains the loss of plasma on the wall surface, and can maintain lower plasma density and lower thrust limit. Meanwhile, the number of stages of the magnetic rings can be adjusted, the design dimension of the resonance surface is increased, the electronic path is changed from the original radial direction to the axial direction, the movement distance is increased, and the efficiency and the ionization degree of the thruster can be improved.
In order to achieve the purpose, the technical scheme of the invention is realized as follows:
the utility model provides a microwave ion advancing device based on lateral wall cusp magnetic field, includes discharge chamber, lateral wall cusp magnetic field unit, microwave input unit and gas supply unit, the discharge chamber includes discharge cavity, rigid coupling in the diapire of discharge cavity front end and the grid accelerating unit of rigid coupling in the discharge cavity rear end, the discharge cavity be the tubular construction, the diapire on arrange gas supply unit and microwave input unit, lateral wall cusp magnetic field unit include two lateral wall magnet rings at least, all lateral wall magnet rings all arrange with discharge cavity coaxial, all lateral wall magnet rings adopt homopolar relative mode to arrange on discharge cavity's internal face, a plurality of lateral wall magnet rings are covered with discharge cavity's internal face, lateral wall cusp magnetic field unit forms strong magnetic field area and weak magnetic field area in the discharge chamber, and forms the electron resonance face between strong magnetic field area and the weak magnetic field area, the microwave input unit stretches into the center of the bottom wall of the discharge chamber and inputs microwaves for the hollow conical cage type antenna arranged in the discharge chamber, the hollow conical cage type antenna is positioned in a strong magnetic field region at the upper stream of the electron cyclotron resonance surface, and the gas supply unit introduces working medium gas into the discharge chamber.
Furthermore, the height of the side wall magnet ring close to the bottom wall of the discharge chamber is greater than that of the rest side wall magnet rings.
Furthermore, the side wall cusped magnetic field unit comprises three side wall magnet rings, the magnetizing directions are axial, and the side wall cusped magnetic field unit is installed in an NS-SN-NS or SN-NS-SN arrangement mode according to the polarity direction.
Furthermore, the grid accelerating unit comprises a screen and an accelerating grid, the screen is arranged between the discharging cavity and the accelerating grid, the screen is in a positive potential, the accelerating grid is in a negative potential, and the grid accelerating unit further comprises an annular ceramic gasket coaxially arranged between the screen and the accelerating grid.
Furthermore, the radius of a plurality of first lead-out holes formed in the screen grating is larger than the radius of a plurality of second lead-out holes formed in the accelerating grating.
Further, a bottom wall magnet ring is arranged in the middle of the bottom wall, and the bottom wall magnet ring is sleeved on the part, extending into the bottom wall of the discharge chamber, of the microwave input unit.
Further, the gas supply unit comprises an external gas pipe and a homogenizing cavity, the homogenizing cavity is arranged in the middle of the bottom wall and communicated with the external gas pipe through a gas passage arranged on the bottom wall, and a plurality of small holes communicated with the homogenizing cavity and the discharge cavity are uniformly formed in the bottom wall.
Furthermore, the material of the discharge cavity is stainless steel or aluminum alloy.
Compared with the prior art, the microwave ion propulsion device based on the side wall cusped magnetic field has the advantages that microwaves input by the microwave input unit enter the discharge chamber through the hollow conical cage-shaped microwave antenna, the side wall cusped magnetic field generates uniform and wavy magnetic lines, the magnetic lines reaching a certain strength are matched with microwaves with a specific frequency to form a microwave electromagnetic field with specific distribution, deaf rare gas is fed into the microwave electromagnetic field, residual seed electrons perform cyclotron motion in the magnetic field generated by the permanent magnet at a certain frequency to generate a resonance phenomenon, when the microwave frequency and the electron cyclotron frequency are equal, the electrons can absorb microwave energy to a large extent to generate high-energy electrons, ionized gas forms high-density plasma, the ions are led out under the combined action of the screen grid and the accelerating grid, and the electrons are prevented from being accelerated out through a beam path.
The microwave ion propulsion device based on the side wall cusped magnetic field has the following advantages:
1. the performance index of the microwave ion thruster has an important relation with the constraint capacity of the magnetic mirror effect of the microwave ion thruster on electrons, the constraint capacity of the microwave ion thruster is maximized by adopting a side wall cusp type magnetic field, a wave-shaped uniform magnetic line configuration is formed in a discharge area, electrons are constrained at each magnetic line peak, when the electrons in the center of the magnetic mirror move towards two sides, the electrons are constrained by the magnetic mirror force and reflected back to the center, a movement area is limited, and energy transfer is realized. The side wall cusped magnetic field has the advantages that firstly, the magnetic tips generated by the multistage magnetic rings form a stronger magnetic mirror effect, electrons can be better restrained in the discharge chamber, and the electrons are not easy to collide with the metal wall surface to cause loss; secondly, magnetic lines of force develop along the axial direction of the discharge chamber, the magnetic lines of force wrap the inner wall surface of the whole discharge chamber, and the motion path of electrons is longer under the guidance of the magnetic lines of force of the electrons constrained by the magnetic field, so that the detention time of the electrons is prolonged more effectively; finally, the resonance surface formed by the side wall magnetic ring is larger, so that electrons can obtain energy more probably, and the energy absorption efficiency is higher. Under the common influence of the factors, the constraint capacity of the magnetic field on electrons is greatly improved, the collision between the electrons and the wall surface is reduced, and the loss is further reduced.
2. The microwave input of this patent adopts a fretwork awl cage type antenna to stretch into the arrester region, directly expose in the resonant cavity, the awl bottom annular of this fretwork awl cage type antenna is parallel with arrester region middle part magnetic line of force, around this antenna, microwave and electromagnetic field mutually support with higher speed to the electron, save space more, the actual discharge area is bigger under the same volume, carry out many times acceleration process to the arrester region exit along the antenna, gaseous ionization repeatedly, by the electron of restriction more and more, ionization efficiency is higher, it is more sensitive to the small change of working medium flow, thrust response is faster, can realize the thrust regulatory function under the low-pressure micro flow operating mode. Meanwhile, the cone cage type antenna is arranged on the upper stream of the resonant magnetic field intensity, namely the hollowed cone cage type antenna is located in a strong magnetic field area on the upper stream of the electron cyclotron resonance surface, the space magnetic field intensity where the hollow cone cage type antenna is located is stronger, the protection effect on the antenna is better, the collision loss between charged particles and the wall surface of the antenna can be effectively reduced, and the working medium utilization rate is higher.
3. This patent takes the design mode in lateral wall cusped magnetic field, and discharge area bottom cross-section need not to consider the permanent magnet to put, and the cross sectional area multiple reduces, adjustment discharge chamber length, and whole discharge chamber volume multiple reduces, and its electron cyclotron resonance face is bigger, and the electron capacitation is more abundant, and is more abundant with gas collision, and the yardstick that discharges obviously increases, effectively improves working medium utilization ratio.
4. The grid combination adopted by the patent comprises a screen grid and an accelerating grid which is responsible for extracting ion beam current, and ions are led out under the combined action of the screen grid and the accelerating grid to prevent electrons from being accelerated out through a beam current path. The diameter of the discharge cavity is smaller, the hole positions of the grid are more concentrated, the extracted beam is more concentrated, and the ions are easier to collect.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate an embodiment of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
fig. 1 is a schematic structural diagram of a microwave ion propulsion device based on a side wall cusped magnetic field according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of the hollow conical cage antenna according to the present invention.
Description of reference numerals:
the antenna comprises a hollow conical cage type antenna 1, an electron cyclotron resonance surface 2, a grid accelerating unit 3, a side wall magnet ring 4, a bottom wall 5, a bottom wall 6, a bottom wall magnet ring 7, a microwave input unit 8, an external air pipe 9, a discharge cavity 10, a homogenizing cavity 10, an air passage 11 and a small hole 12.
Detailed Description
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.
The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
As shown in fig. 1-2, a microwave ion propulsion device based on a side wall cusped magnetic field comprises a discharge chamber, a side wall cusped magnetic field unit, a microwave input unit 7 and a gas supply unit, wherein the discharge chamber comprises a discharge cavity 9, a bottom wall 5 fixedly connected to the front end of the discharge cavity and a grid accelerating unit 3 fixedly connected to the rear end of the discharge cavity, the discharge cavity 9 is of a cylindrical structure, the gas supply unit and the microwave input unit 7 are arranged on the bottom wall 5, the side wall cusped magnetic field unit at least comprises two side wall magnet rings 4, all the side wall magnet rings 4 are coaxially arranged with the discharge cavity 9, all the side wall magnet rings 4 are arranged on the inner wall surface of the discharge cavity 9 in a homopolar opposite manner, the side wall magnet rings 4 are fully distributed on the inner wall surface of the discharge cavity 9, and the side wall cusped magnetic field unit forms a strong magnetic field region and a weak magnetic field region in the discharge chamber, an electron cyclotron resonance surface 2 is formed between the strong magnetic field region and the weak magnetic field region, the microwave input unit 7 extends into the center of the bottom wall 5 of the discharge chamber and inputs microwaves for the hollow conical cage type antenna 1 arranged in the discharge cavity 9, the hollow conical cage type antenna 1 is located in the strong magnetic field region on the upper stream of the electron cyclotron resonance surface 2, and the gas supply unit introduces working medium gas into the discharge cavity 9.
The height of the side wall magnet ring close to the bottom wall 5 of the discharge chamber is greater than the height of the remaining side wall magnet rings. The side wall cusped magnetic field unit comprises three side wall magnet rings 4 to form a three-stage magnetic ring, the magnetizing directions are axial, and the side wall cusped magnetic field unit is installed in an NS-SN-NS or SN-NS-SN arrangement mode according to the polarity direction.
The grid accelerating unit 3 comprises a screen and an accelerating grid, the screen is arranged between the discharging cavity 9 and the accelerating grid, the screen is in a positive potential, the accelerating grid is in a negative potential, and the grid accelerating unit 3 further comprises an annular ceramic gasket coaxially arranged between the screen and the accelerating grid. An annular ceramic spacer is used for insulation.
The radiuses of the first lead-out holes formed in the screen grating are larger than the radiuses of the second lead-out holes formed in the accelerating grating.
A bottom wall magnet ring 6 is arranged in the middle of the bottom wall 5, and the bottom wall magnet ring 6 is sleeved on the part of the bottom wall 5 of the microwave input unit 7 extending into the discharge chamber.
The gas supply unit comprises an external gas pipe 8 and a homogenizing cavity 10, the homogenizing cavity 10 is arranged in the middle of the bottom wall 5, the homogenizing cavity 10 is communicated with the external gas pipe 8 through a gas passage 11 arranged on the bottom wall 5, a plurality of small holes 12 for communicating the homogenizing cavity 10 with the discharge cavity 9 are uniformly formed in the bottom wall 5, and gas is uniformly input into a discharge area of the discharge cavity 9 through the eight small holes 12 after being input into the homogenizing cavity 10 through the external gas pipe 8.
The discharging cavity 9 is made of stainless steel or aluminum alloy, an opening at the upper part of the discharging cavity is butted with an opening of the grid accelerating unit, so that ion beams can be conveniently led out, the diameter of the discharging cavity 9 is 16mm, and the height of the discharging cavity is not more than 30 mm.
The invention generates a constant magnetic field by the side wall magnetic ring 4 and the bottom wall magnetic ring 6 through the ionization chamber which is composed of the side wall magnetic ring 4 with different heights and the nonmagnetic stainless steel discharge cavity 9. The microwave input unit 7 feeds in the microwave with a certain frequency, the microwave frequency can be selected between 2 GHz and 5GHz, 2.45GHz is selected as an example, the microwave input unit 7 extends into the center of the discharge chamber to input the microwave, the hollow conical cage type antenna 1 is placed in the discharge area, and the magnetic induction intensity when the hollow conical cage type antenna and the input microwave frequency achieve the same action stably surrounds the periphery of the antenna to form a regular annular area; the 2.45GHz microwave and 875G intensity surface of the static magnetic field act together to form electron cyclotron resonance, at the moment, deaf enters rare gas, the microwave frequency is equal to the electron cyclotron frequency, heating electrons absorb energy, and the screen grid-accelerating grid unit 3 acts together to lead out ions, so that the electrons are prevented from being accelerated out through a beam path.
The working principle is as follows:
the microwave input unit 7 transmits microwave power to the discharge area through a hollow conical cage antenna 1, three side wall magnet rings 4 which are different in size and adjacent at the same level and surround the cylinder wall of the discharge area (the three side wall magnet rings 4 are arranged in an NS-SN-NS or SN-NS-SN arrangement mode according to the polarity direction) generate waveform uniform magnetic force line distribution in the discharge area, charged seed electrons in motion are subjected to Lorentz force to form electron convolution, the side wall can cut a magnetic field to form a magnetic mirror effect, electrons are bound in the discharge area, and repeated alternate acceleration is carried out between the wave crests and the wave troughs of the magnetic force lines. The microwave antenna is parallel to the magnetic lines of force in the middle of the discharge area, a resonance surface is formed around the whole antenna immersed in the discharge area, electrons are accelerated into high-energy electrons, and the electron energy gain is greatly improved by the multiple increase of the size of the resonance surface. The gas supply unit fills a small flow of working medium gas into the discharge region, electrons transfer energy to the gas, the electrons collide with the neutral gas, ionization is carried out to generate a large amount of ions and electrons, the electrons and the ionized gas are accelerated repeatedly from the bottom end to the top end region of the discharge region, the small-volume discharge region is recycled, the electrons and the gas collide fully, and the working medium utilization rate is improved. And finally, ions are led out from the grid hole under the combined action of the screen grid and the accelerating grid unit, electrons are remained in the discharge region to continue working, and ion beam current led out by the grid system with the small diameter is more concentrated.
The invention solves the problems of lower thrust lower limit which can not be realized by a single magnetic field position type, insensitive thrust response under the working condition of micro-flow low air pressure and particle loss in a small-volume discharge area. Utilize the constraint effect of lateral wall cusped magnetic field to plasma, with electron restraint in the discharge chamber, along with magnetic line of force is worked repeatedly, to the shape optimization of discharge chamber simultaneously, discharge chamber volume multiple reduces, and both are under the simultaneous action, and the regional bigger that discharges, electron capacitation is regional bigger, and ionization efficiency is higher, utilizes working medium more effectively, and the wall loss is still less, and the thruster discharges more stably, can satisfy higher thruster performance requirement.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (8)
1. A microwave ion propulsion unit based on lateral wall cusped magnetic field which characterized in that: including discharge chamber, lateral wall cusped magnetic field unit, microwave input unit (7) and gas supply unit, the discharge chamber includes discharge cavity (9), rigid coupling in diapire (5) of discharge cavity front end and rigid coupling grid accelerating unit (3) at the discharge cavity rear end, discharge cavity (9) be the tubular construction, diapire (5) on arrange gas supply unit and microwave input unit (7), lateral wall cusped magnetic field unit include two lateral wall magnet rings (4) at least, all lateral wall magnet rings (4) all with discharge cavity (9) coaxial arrangement, all lateral wall magnet rings (4) adopt homopolar relative mode to arrange on the internal face of discharge cavity (9), the internal face of discharge cavity (9) is covered with to a plurality of lateral wall magnet rings (4), lateral wall cusped magnetic field unit forms strong magnetic field area and weak magnetic field area in the discharge chamber, and an electron cyclotron resonance surface (2) is formed between the strong magnetic field area and the weak magnetic field area, the microwave input unit (7) stretches into the center of the bottom wall (5) of the discharge chamber and inputs microwaves for the hollow conical cage type antenna (1) arranged in the discharge cavity (9), the hollow conical cage type antenna (1) is positioned in the strong magnetic field area at the upper stream of the electron cyclotron resonance surface (2), and the gas supply unit introduces working medium gas into the discharge cavity (9).
2. A microwave ion propulsion device based on a side wall cusped magnetic field according to claim 1, characterized in that: the height of the side wall magnet ring close to the bottom wall (5) of the discharge chamber is greater than the height of the rest side wall magnet rings.
3. A microwave ion propulsion device based on a side wall cusped magnetic field according to claim 2, characterized in that: the side wall cusped magnetic field unit comprises three side wall magnet rings (4), the magnetizing directions are axial, and the side wall cusped magnetic field unit is installed in an NS-SN-NS or SN-NS-SN arrangement mode according to the polarity direction.
4. A microwave ion propulsion device based on side wall cusped magnetic fields according to any one of claims 1 to 3, characterized in that: the grid accelerating unit (3) comprises a screen and an accelerating grid, the screen is arranged between the discharge cavity (9) and the accelerating grid, the screen is in a positive potential, the accelerating grid is in a negative potential, and the grid accelerating unit (3) further comprises an annular ceramic gasket coaxially arranged between the screen and the accelerating grid.
5. A microwave ion propulsion device based on a side wall cusped magnetic field according to claim 4, characterized in that: the radiuses of the first lead-out holes formed in the screen grating are larger than the radiuses of the second lead-out holes formed in the accelerating grating.
6. A microwave ion propulsion device based on a side wall cusped magnetic field according to claim 1, characterized in that: the middle part of the bottom wall (5) is provided with a bottom wall magnet ring (6), and the bottom wall magnet ring (6) is sleeved on the part of the microwave input unit (7) extending into the bottom wall (5) of the discharge chamber.
7. A microwave ion propulsion device based on a side wall cusped magnetic field according to claim 6, characterized in that: the gas supply unit comprises an external gas pipe (8) and a homogenizing cavity (10), the homogenizing cavity (10) is arranged in the middle of the bottom wall (5), the homogenizing cavity (10) is communicated with the external gas pipe (8) through a gas passage (11) arranged on the bottom wall (5), and a plurality of small holes (12) communicated with the homogenizing cavity (10) and the discharge cavity (9) are uniformly formed in the bottom wall (5).
8. A microwave ion propulsion device based on side wall cusped magnetic fields according to claims 1, 2, 3, 6 or 7, characterized in that: the discharging cavity (9) is made of stainless steel or aluminum alloy.
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