A small-caliber micro microwave ion thruster and its working method

Abstract

The present invention belongs to the field of aerospace electric propulsion and relates to a small-caliber miniature microwave ion thruster, comprising a discharge chamber, an antenna, and a magnetic array structure. The diameter of the discharge chamber is less than 2.5 cm. The antenna is installed within the discharge chamber and located on the discharge chamber axis, and the antenna size matches the electron cyclotron resonance region. The magnetic array structure is installed outside the discharge chamber and is composed of multiple Halbach-type permanent magnets. After ignition, a large amount of plasma is generated within the discharge chamber. Under the action of the magnetic array structure, a magnetic field gradient directed toward the grid system is generated, inducing the plasma to migrate upstream of the grid system along the magnetic field gradient direction. At this time, a voltage is applied to the grid system to form a high-voltage sheath that accelerates and extracts ions, generating thrust. The small-caliber miniature microwave ion thruster of the present invention can operate at higher microwave power, ensuring the power supply of the thruster, and will achieve higher propellant utilization efficiency and greater thrust.

Description

Technical Field

[0001] The present invention belongs to the field of aerospace electric propulsion, and in particular relates to a small-caliber miniature microwave ion thruster and a working method thereof. Background Art

[0002] In a microwave ion thruster, microwaves are fed into the discharge chamber through an antenna, permanent magnets form magnetic mirrors to confine electrons, electrons are heated through the electron cyclotron resonance mechanism, high-energy electrons ionize neutral gases to produce plasma, and the grid system accelerates the ions to eject them to generate thrust.

[0003] There are three common microwave ion thrusters available at home and abroad: 10cm, 5cm, and 2cm apertures. The aperture is defined as the diameter inside the discharge chamber. Examples include Japan's μ10 and μ2 microwave ion thrusters, Northwestern Polytechnical University's 10cm and 2cm ECR ion thrusters, Dalian University of Technology's 5cm microwave ion thruster, and Shanghai Institute 803's M2 and M5 microwave ion thrusters.

[0004] An analysis of the thrust performance of the aforementioned microwave ion thrusters reveals that, during the process of miniaturization, the power of microwave ion thrusters decreases as the aperture decreases, leading to a decrease in thrust density and propellant utilization. To increase the thrust of a micro-microwave ion thruster, the microwave power must first be increased. However, existing 2cm-aperture microwave ion thrusters utilize a built-in permanent magnet design. As microwave power increases, the temperature within the discharge chamber in a vacuum environment rapidly rises. Once the temperature exceeds the tolerance of the magnetic material, the magnet demagnetizes. This phenomenon severely limits the input power of the micro-microwave ion thruster, and thus its performance. Summary of the Invention

[0005] The purpose of the present invention is to provide a small-aperture micro-microwave ion thruster and a working method thereof, which solves the problem that the microwave power of existing small-aperture micro-microwave ion thrusters is difficult to increase, resulting in low extraction current density.

[0006] The present invention is achieved through the following technical solutions:

[0007] The present invention discloses a small-caliber micro-microwave ion thruster, which comprises a discharge chamber, an antenna and a magnetic array structure;

[0008] The diameter of the discharge chamber is less than 2.5 cm;

[0009] The antenna is installed in the discharge chamber and is located on the axis of the discharge chamber, and the size of the antenna matches the electron cyclotron resonance region;

[0010] The magnetic array structure is installed outside the discharge chamber and consists of multiple Halbach-type permanent magnets.

[0011] Furthermore, the micro microwave ion thruster further comprises a shielding cover, and a base, a front cover, a rear cover, a microwave connector and a grid system arranged in the shielding cover;

[0012] The base and front cover are located on one side of the discharge chamber, and the grid system is located on the other side of the discharge chamber;

[0013] The air storage chamber is a cavity formed by the base and the front cover. The base is connected to an air intake pipe, one end of which is connected to the air storage chamber.

[0014] The microwave connector is installed on the base, which connects the gas circuit and the microwave circuit;

[0015] The permanent magnet surrounds the outside of the discharge chamber and is arranged between the front cover and the rear cover;

[0016] The antenna is installed on the microwave connector and is used to transmit microwaves into the discharge chamber.

[0017] Furthermore, a plurality of inclined through holes are prefabricated on the front end cover, and the gas storage chamber and the discharge chamber are connected through the inclined through holes.

[0018] Furthermore, the antenna is threadedly connected to the inner conductor of the microwave connector to emit microwaves into the discharge chamber.

[0019] Furthermore, the discharge chamber is cylindrical.

[0020] Furthermore, the distance between the outermost edge of the antenna and the electron cyclotron resonance region is controlled at 0.5 mm.

[0021] Furthermore, the antenna shape is round or T-shaped.

[0022] Furthermore, the magnetic array structure is composed of 6 Halbach permanent magnets arranged in a circular shape outside the discharge chamber, and the magnetic field enhancement of each Halbach magnetic strip points to the center of the distribution circle where the circular ring is located.

[0023] Furthermore, six Halbach permanent magnets are evenly distributed on the circumference at intervals of 60 degrees, and are respectively named Halbach magnetic stripe No. 1, Halbach magnetic stripe No. 2, Halbach magnetic stripe No. 3, Halbach magnetic stripe No. 4, Halbach magnetic stripe No. 5, and Halbach magnetic stripe No. 6;

[0024] Among them, the magnetic field enhancement direction of Halbach stripe No. 1 points to the center of the distribution circle; Halbach stripe No. 2 rotates 60°, and the magnetic field enhancement direction points to the center of the distribution circle; Halbach stripe No. 3 rotates 120°, and the magnetic field enhancement direction points to the center of the distribution circle; Halbach stripe No. 4 rotates 180°, and the magnetic field enhancement direction points to the center of the distribution circle; Halbach stripe No. 5 rotates 240°, and the magnetic field enhancement direction points to the center of the distribution circle; Halbach stripe No. 6 rotates 300°, and the magnetic field enhancement direction points to the center of the distribution circle.

[0025] The present invention also discloses a working method of the micro microwave ion thruster, which includes the following steps:

[0026] The working fluid gas flows into the discharge chamber; microwaves are fed into the discharge chamber from the antenna, generating initial electrons through microwave-induced discharge or microwave local electric field breakdown discharge. The electrons are confined by the magnetic field and move back and forth in the magnetic mirror. By virtue of the resonance between the microwave electric field and the electron cyclotron frequency, the electrons continuously gain energy and become high-energy electrons, further ionizing the gas to generate and maintain plasma.

[0027] After ignition, a large amount of plasma is generated inside the discharge chamber. Under the action of the magnetic array structure, a magnetic field gradient pointing to the gate system is generated, inducing the plasma to migrate to the upstream of the gate system along the direction of the magnetic field gradient; at this time, voltage is applied to the gate system to form a high-voltage sheath to accelerate and extract ions, generating thrust.

[0028] Compared with the prior art, the present invention has the following beneficial technical effects:

[0029] The present invention discloses a small-aperture miniature microwave ion thruster. By installing a specially designed magnetic array structure outside the discharge chamber, it not only circumvents power limitations but also ensures that the internal magnetic field meets ionization requirements. Compared with the existing technology, this prevents the magnetic material from being demagnetized by high temperature or plasma erosion, and the microwave power can be further increased, effectively improving the thrust density and thrust upper limit of the thruster. The present invention plays the role of constructing a magnetic field structure from the outside, so that only the antenna structure exists in the discharge chamber. While ensuring the confinement of electrons and maintaining efficient discharge, it plays the role of preventing the magnet from being demagnetized by high temperature or erosion. Compared with miniature microwave ion thrusters with built-in permanent magnets, the small-aperture miniature microwave ion thruster of the present invention can operate at higher microwave power. After ensuring the power supply of the thruster, it will achieve higher propellant utilization efficiency and greater thrust.

[0030] Furthermore, the magnetic array structure consists of six specially designed Halbach magnetic strips, which can enhance the magnetic field in a specified direction, increase the height of the electron cyclotron resonance zone, and assist electrons in the microwave ion thruster to better obtain microwave energy.

[0031] Furthermore, the magnetic field structure in the discharge chamber forms a magnetic field gradient pointing to the gate, which promotes the plasma to drift toward the gate and can increase the thruster-induced current density.

[0032] Furthermore, by adjusting the antenna diameter and length to within 0.5 mm of the electron cyclotron resonance region, the coupling between the magnetic field and microwaves on the electrons can be enhanced, improving the efficiency of electron energy harvesting and enabling instant ignition upon reaching the rated discharge power. In contrast, existing technologies require a period of time after reaching the rated discharge power before ignition can occur, and this duration is relatively random and difficult to control.

[0033] Furthermore, the internal components of the discharge chamber are all made of metal, which is heat-resistant and resistant to plasma erosion and can withstand higher microwave power. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 This is an assembly diagram of a small-caliber micro-microwave ion thruster according to the present invention;

[0035] Figure 2 is a cross-sectional view of a prototype of a micro microwave ion thruster applicable to the present invention in an embodiment;

[0036] Among them, 1. Shielding cover; 2. Base; 3. Microwave connector; 4. Gas storage chamber; 5. Front cover; 6. Rear cover; 7. Magnetic array structure; 8. Antenna; 9. Discharge chamber; 10. Grid system; 11. Inlet pipe;

[0037] Figure 3 Schematic diagram of the Halbach magnetic strip structure used in the examples, where the white arrow indicates the magnetization direction of the magnet;

[0038] Figure 4 Magnetic field distribution formed by the Halbach magnetic strip used in the embodiment, wherein the white solid line is the 0.15T isovalue line, i.e., the so-called electron cyclotron resonance region;

[0039] Figure 5 The three-view diagram and isometric view of the magnetic array structure in the embodiment, wherein the direction pointed by the black arrow is the direction of magnetic field enhancement; Figure 5 a is the left view of the magnetic array structure, Figure 5 b is the front view of the magnetic array structure, Figure 5 c is a top view of the magnetic array structure, Figure 5 d is an elevation view of the magnetic array structure;

[0040] Figure 6 : The magnetic field distribution formed by the magnetic array structure in the embodiment, wherein the white solid line is the electron cyclotron resonance region, and the white arrow is the magnetic field gradient direction;

[0041] Figure 7 This is an ignition image of a small-caliber miniature microwave ion thruster in an embodiment;

[0042] Figure 8 This is an image of the plume of a small-caliber micro-microwave ion thruster in an embodiment when it is working normally. DETAILED DESCRIPTION

[0043] In order to make the purpose, technical solutions and advantages of the present invention more clear, the following is a further detailed description with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention. That is, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments.

[0044] The components described and illustrated in the drawings and embodiments of the present invention may be arranged and designed in a variety of different configurations. Therefore, the detailed description of the embodiments of the present invention provided in the following drawings is not intended to limit the scope of the claimed invention, but merely represents a selected embodiment of the present invention. All other embodiments derived by those skilled in the art based on the drawings and embodiments of the present invention without inventive effort shall fall within the scope of protection of the present invention.

[0045] It should be noted that the terms "comprise," "include," or any other variations thereof are intended to encompass non-exclusive inclusion, such that a process, element, method, article, or apparatus comprising a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to the process, element, method, article, or apparatus. To address the technical challenges faced in miniaturizing existing micro-microwave ion thrusters, the present invention provides a small-aperture micro-microwave ion thruster employing an external permanent magnet design and containing only an antenna 8 within a discharge chamber 9.

[0046] The present invention discloses a small-caliber micro-microwave ion thruster, the structure of which is as follows: Figure 1 and Figure 2 As shown, the discharge chamber 9 is the core component. The discharge chamber 9 is a cavity formed by the front cover 5, the rear cover 6 and the grid system 10. The discharge chamber 9 is cylindrical and serves as the main place for the micro microwave ion thruster to generate plasma. It adopts a small-caliber design with a diameter of no more than 2.5 cm to ensure that the magnetic array structure 7 can achieve the best effect.

[0047] In front of the discharge chamber 9 are the gas storage chamber 4, base 2, microwave connector 3, and air inlet pipe 11. The gas storage chamber 4 is a cavity formed by the base 2 and the front cover 5. It is connected to the discharge chamber 9 through six inclined holes punched in the front cover 5. The holes are tilted to facilitate gas concentration in the middle of the discharge chamber 9.

[0048] Behind the discharge chamber 9 is a grid system 10, which is fixed to the rear end cover 6. The grid system 10 is composed of two metal grids, a screen grid and an acceleration grid. A large number of concentric circular holes are opened on the grid. A specific electric field is formed by applying a DC voltage to accelerate ions.

[0049] Outside the discharge chamber 9 are the magnetic array structure 7 and the shielding cover 1. The magnetic array structure 7 is clamped by the front cover 5 and the rear cover 6. The shielding cover 1 serves as the outer shell of the micro microwave ion thruster, enclosing all other structures and isolating high voltage.

[0050] In the center of the discharge chamber 9 is the antenna 8 , which is connected to the inner conductor of the microwave connector 3 by threads and is used to emit microwaves into the discharge chamber 9 .

[0051] Antenna 8, a crucial component for ignition in a micro-microwave ion thruster, has been specially designed to fit within the electron cyclotron resonance region. This ultimately allows the distance between the outermost edge of antenna 8 and the electron cyclotron resonance region to be controlled to within 0.5 mm, maximizing the success rate of ignition in the micro-microwave ion thruster. With this controllable distance, the shape of antenna 8 is no longer limited; both round and T-shaped designs offer excellent results.

[0052] The magnetic array structure 7 used in the small-caliber micro-microwave ion thruster is composed of six Halbach magnetic strips. Figure 3 As shown, it is divided into three stages: front stage, middle stage and rear stage. In terms of size, the length and width of the front, middle and rear stage magnets are the same, but the height is different, showing a sequentially increasing relationship. In terms of coercive force distribution, the coercive force of the front stage magnet is greater than the coercive force of the middle stage magnet and the coercive force of the rear stage magnet. The coercive force range is between 500 and 600 kA / m. In the direction of the magnetic pole, as shown in the figure, the length and width of the front, middle and rear stage magnets are the same, but the height is different, showing a sequentially increasing relationship. In terms of coercive force distribution, the coercive force of the front stage magnet is greater than the coercive force of the middle stage magnet and the coercive force range is between 500 and 600 kA / m. Figure 3 As shown, the front N-stage magnets are magnetized along the positive direction of the Z axis, the middle N-stage magnets are magnetized along the positive direction of the X axis, and the rear N-stage magnets are magnetized along the negative direction of the Z axis.

[0053] The magnetic field distribution formed by a single Halbach strip is as follows: Figure 4 As shown in the figure, the electron cyclotron resonance region is higher in the middle than the ordinary strip magnetic strip, which can help the electrons in the microwave ion thruster to better obtain microwave energy. Among them, the electron cyclotron resonance region in the present invention refers to the isoline of the magnetic induction intensity of 0.15T, that is, Figure 4 The single Halbach magnetic stripe not only raises the electron cyclotron resonance region, but also maintains the complete magnetic mirror structure and maintains its complete function. The magnetic mirror refers to the densely distributed arched magnetic field lines, such as Figure 4The dense black lines below the center magnetic stripe indicate that in an ion thruster, electrons are confined by magnetic mirrors, moving back and forth along the mirror's trajectory and absorbing energy when passing through the electron cyclotron resonance region.

[0054] The magnetic array structure 7 is composed of six Halbach magnetic strips, and the specific arrangement is as follows: Figure 5 As shown. Six Halbach magnets are evenly distributed on the circumference at intervals of 60 degrees. Among them, the magnetic field enhancement direction of Halbach stripe No. 1 points to the center of the distribution circle; Halbach stripe No. 2 rotates 60°, and the magnetic field enhancement direction points to the center of the distribution circle; Halbach stripe No. 3 rotates 120°, and the magnetic field enhancement direction points to the center of the distribution circle; Halbach stripe No. 4 rotates 180°, and the magnetic field enhancement direction points to the center of the distribution circle; Halbach stripe No. 5 rotates 240°, and the magnetic field enhancement direction points to the center of the distribution circle; Halbach stripe No. 6 rotates 300°, and the magnetic field enhancement direction points to the center of the distribution circle, that is, Figure 5 The black arrow in the figure indicates the direction of the magnetic field. The magnetic field distribution of the magnetic array composed of six Halbach magnetic strips is as follows: Figure 6 As shown, the magnetic field distribution of the 0-180° section is as follows Figure 6 As shown in (a), the magnetic field distribution of the 30-210° section is as follows Figure 6 As shown in (b), a magnetic field gradient with a specific direction is formed. This magnetic field gradient with a specific direction can induce plasma to migrate upstream of the grid system 10 along the direction of the magnetic field gradient, thereby increasing the thrust density and thruster electrical efficiency.

[0055] The working process of the small-caliber micro-microwave ion thruster of the present invention is as follows:

[0056] The working fluid gas enters the gas storage chamber 4 from the inlet pipe 11, where it is pressure-equalized and then flows into the discharge chamber 9. Microwaves are transmitted via the coaxial line to the microwave connector 3 and fed into the discharge chamber 9 from the antenna 8. Microwave-induced discharge or microwave local electric field breakdown discharge generates initial electrons, which are confined by the magnetic field and reciprocate in the magnetic mirror. By resonating the microwave electric field with the electron cyclotron frequency, the electrons continuously gain energy and become high-energy electrons, further ionizing the gas to generate and maintain plasma. After ignition, a large amount of plasma is generated inside the discharge chamber 9. Under the influence of the magnetic field gradient, the plasma migrates toward the gate system 10. At this time, a voltage is applied to the gate system 10, with the screen grid carrying a positive voltage and the acceleration grid carrying a negative voltage, forming a high-voltage sheath that accelerates and extracts ions, generating thrust.

[0057] As a supplemental note, during the ignition phase, the tip of antenna 8 is aligned with the electron cyclotron resonance region, ensuring a distance of less than 0.5 mm. This allows the thruster to be directly started at a higher power level by utilizing the strong local electric field at the tip of antenna 8. Compared to existing technologies, the discharge chamber 9 of the present invention does not require a sharp point to cause electric field concentration in order to discharge, thus extending its applicability.

[0058] The present invention creates an external magnetic field structure, ensuring only the antenna 8 exists within the discharge chamber 9. This prevents demagnetization of the magnet due to high temperatures or corrosion, while ensuring electron confinement and maintaining efficient discharge. The thrust of an electric thruster is directly related to input power. The internal components of the discharge chamber 9 of the small-aperture micro-microwave ion thruster of the present invention are all made of metal, which is heat-resistant and resistant to plasma erosion, and can withstand higher microwave powers. Compared to micro-microwave ion thrusters with internal permanent magnets, the small-aperture micro-microwave ion thruster of the present invention can operate at higher microwave powers. By ensuring the thruster's power supply, the microwave ion thruster of the present invention achieves higher propellant utilization efficiency and greater thrust.

[0059] Figure 7 and Figure 8 This is a real-life image of the present invention in operation. The normal operation of the microwave ion thruster of the present invention is a two-step process: thruster ignition in the first step and beam extraction in the second. During the first step, 0.3 sccm of xenon gas is introduced into the thruster, followed by microwave power, which immediately ignites successfully. Figure 7 The image shows a successful ignition in this step, taken from the side and rear of the grid system 10, facing the grid system 10. During the second beam extraction step, a DC voltage is applied to the grid system 10, which then extracts a large number of positive ions from the grid system 10, forming a visible ion beam. Figure 8 The image shows the successful beam extraction in this step, taken from the side of the thruster. Figure 2 Same angle.

[0060] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit it. Although the present invention has been described in detail with reference to the above embodiments, ordinary technicians in the field should understand that the specific implementation methods of the present invention can still be modified or replaced by equivalents. Any modification or equivalent replacement that does not depart from the spirit and scope of the present invention should be covered by the scope of protection of the claims of the present invention.

Claims

1. A small-caliber micro-microwave ion thruster, characterized in that: The micro microwave ion thruster comprises a discharge chamber (9), an antenna (8) and a magnetic array structure (7); The diameter of the discharge chamber (9) is less than 2.5 cm; The antenna (8) is installed in the discharge chamber (9) and is located on the axis of the discharge chamber (9), and the size of the antenna (8) matches the electron cyclotron resonance region; The magnetic array structure (7) is installed outside the discharge chamber (9) and consists of a plurality of Halbach type permanent magnets; The magnetic stripe structure of a single Halbach permanent magnet is divided into three stages: front, middle, and back. In terms of size, the length and width of the front, middle, and back magnets are the same, but the heights are different, showing a sequentially increasing relationship. In terms of coercive force distribution, the coercive force of the front magnet is greater than that of the middle magnet and greater than that of the back magnet, and the coercive force range is 500-600 kA / m. In the direction of magnetic poles, the front N-stage magnets are magnetized along the positive direction of the Z axis, the middle N-stage magnets are magnetized along the positive direction of the X axis, and the rear N-stage magnets are magnetized along the negative direction of the Z axis. The magnetic array structure (7) is arranged in a circular ring outside the discharge chamber (9), and the magnetic field enhancement of each Halbach magnetic strip points to the center of the distribution circle where the circular ring is located.

2. A small-caliber micro microwave ion thruster according to claim 1, characterized in that: The micro microwave ion thruster further comprises a shielding cover (1), a base (2), a front end cover (5), a rear end cover (6), a microwave connector (3), and a grid system (10) arranged in the shielding cover (1); The base (2) and the front cover (5) are located on one side of the discharge chamber (9), and the grid system (10) is located on the other side of the discharge chamber (9); The air storage chamber (4) is a cavity formed by the base (2) and the front cover (5). An air intake pipe (11) is connected to the base (2), and one end of the air intake pipe (11) is connected to the air storage chamber (4). The microwave connector (3) is mounted on the base (2), and the base (2) connects the gas circuit and the microwave circuit; The permanent magnet surrounds the outside of the discharge chamber (9) and is arranged between the front cover (5) and the rear cover (6); The antenna (8) is mounted on the microwave connector (3) and is used to transmit microwaves into the discharge chamber (9).

3. A small-caliber micro microwave ion thruster according to claim 2, characterized in that: A plurality of inclined through holes are prefabricated on the front end cover (5), and the gas storage chamber (4) and the discharge chamber (9) are connected via the inclined through holes.

4. A small-caliber micro microwave ion thruster according to claim 2, characterized in that: The antenna (8) is threadably connected to the inner conductor of the microwave connector (3) and is used to transmit microwaves into the discharge chamber (9).

5. The small-caliber micro microwave ion thruster according to claim 1, characterized in that: The discharge chamber (9) is cylindrical.

6. The small-caliber micro microwave ion thruster according to claim 1, characterized in that: The distance between the outermost edge of the antenna (8) and the electron cyclotron resonance region is controlled to be 0.5 mm.

7. The small-caliber micro microwave ion thruster according to claim 1, characterized in that: The shape of the antenna (8) is round or T-shaped.

8. A small-caliber micro microwave ion thruster according to any one of claims 1 to 7, characterized in that: The magnetic array structure (7) is composed of 6 Halbach-type permanent magnets arranged in an array.

9. The small-caliber micro microwave ion thruster according to claim 8, characterized in that: Six Halbach permanent magnets are evenly distributed on the circumference at intervals of 60 degrees, and are named Halbach magnetic stripe No. 1, Halbach magnetic stripe No. 2, Halbach magnetic stripe No. 3, Halbach magnetic stripe No. 4, Halbach magnetic stripe No. 5, and Halbach magnetic stripe No. 6; Among them, the magnetic field enhancement direction of Halbach stripe No. 1 points to the center of the distribution circle; Halbach stripe No. 2 rotates 60°, and the magnetic field enhancement direction points to the center of the distribution circle; Halbach stripe No. 3 rotates 120°, and the magnetic field enhancement direction points to the center of the distribution circle; Halbach stripe No. 4 rotates 180°, and the magnetic field enhancement direction points to the center of the distribution circle; Halbach stripe No. 5 rotates 240°, and the magnetic field enhancement direction points to the center of the distribution circle; Halbach stripe No. 6 rotates 300°, and the magnetic field enhancement direction points to the center of the distribution circle.

10. The operating method of the micro microwave ion thruster according to any one of claims 1 to 9, characterized in that: The following processes are included: The working fluid gas flows into the discharge chamber (9); microwaves are fed into the discharge chamber (9) from the antenna (8), and initial electrons are generated through microwave-induced discharge or microwave local electric field breakdown discharge. The electrons are confined by the magnetic field and move back and forth in the magnetic mirror; relying on the resonance between the microwave electric field and the electron cyclotron frequency, the electrons continuously gain energy and become high-energy electrons, further ionizing the gas to generate and maintain plasma; After ignition, a large amount of plasma is generated inside the discharge chamber (9). Under the action of the magnetic array structure (7), a magnetic field gradient pointing to the grid system (10) is generated, inducing the plasma to migrate to the upstream of the grid system (10) along the direction of the magnetic field gradient; at this time, a voltage is applied to the grid system (10) to form a high-voltage sheath to accelerate and extract ions, thereby generating thrust.

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