Microwave magnetic control plasma thruster and working method thereof

Abstract

The invention belongs to the field of spaceflight plasma electric propulsion, and relates to a microwave magnetic control plasma thruster and a working method thereof. A permanent magnet is arranged on the outer side of a discharge chamber of the thruster, and the permanent magnet is arranged close to one side of a spray pipe; the permanent magnet is composed of a plurality of same strip-shaped magnet units, the strip-shaped magnet units are evenly distributed in the circumferential direction of the outer wall of the discharge chamber, and each strip-shaped magnet unit is formed by regularly arranging a plurality of permanent magnets; the permanent magnet forms a multiplexing magnetic field in the discharge chamber, and the multiplexing magnetic field is composed of an embedded magnetic mirror, an envelope magnetic mirror, a magnetic trap and a magnetic spray pipe; the plurality of embedded magnetic mirrors cling to the wall surface of the discharge chamber and are tightly arranged along the axial direction, and the outer sides of the embedded magnetic mirrors are surrounded and coated by the enveloping magnetic mirror to form a multi-magnetic mirror structure; the magnetic trap is arranged at the downstream of the multiple magnetic mirror structure; the magnetic nozzle is located downstream of the magnetic trap. A plurality of tightly arranged embedded magnetic mirrors exist in the magnetic field configuration, the exterior of the embedded magnetic mirrors is surrounded by the enveloping magnetic mirror, the axial and radial restraining capacity of the plasma is enhanced through magnetic field distribution, and the thrust performance is remarkably improved.

Description

Technical Field

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

[0002] The Electron Cyclotron Resonance Nozzle (ECRN) thruster consists primarily of a discharge chamber and a magnetic nozzle. A permanent magnet or electromagnetic coil is located at the front of the discharge chamber, generating a constant axial magnetic field. Microwaves are injected into the discharge chamber via a coaxial antenna. When the microwave frequency matches the electron cyclotron frequency, electrons are heated through electron cyclotron resonance. The resulting high-energy electrons further ionize the neutral gas, producing plasma. The plasma then enters the magnetic nozzle region, where the magnetic field gradually diverges. Due to their light mass and high velocity, electrons preferentially escape along the magnetic field lines, forming an axial electron flow. This induction of a bipolar electric field further accelerates the ions axially, generating thrust.

[0003] However, an analysis of existing ECRNs reveals that existing thruster structures are relatively simple, with diameters typically ranging from 2 to 3 cm. They generally employ a permanent magnet or electromagnetic coil at the front end of the discharge chamber to create an axially distributed static magnetic field. In such magnetic field structures, the electron cyclotron resonance region is typically small and nearly perpendicular to the magnetic field lines, making it difficult for electrons to continuously acquire energy as they move along the magnetic field lines. Furthermore, since the axially distributed magnetic field structure struggles to confine electrons, microwave coupling and energy accumulation efficiencies are low, resulting in poor plasma ionization efficiency, making it difficult to form high-density plasma and, consequently, unfavorable for achieving high thrust density.

[0004] In summary, the existing ECRN still has significant deficiencies in electron heating path design, ionization efficiency improvement and microwave energy utilization, and it is urgent to carry out in-depth optimization research in terms of magnetic field configuration, ECR zone position control and microwave magnetic field coordination mechanism. Summary of the Invention

[0005] The purpose of the present invention is to provide a microwave magnetron plasma thruster and an operating method thereof, aiming to solve the technical problems of insufficient microwave coupling, insufficient plasma confinement capability and limited thrust density in the operation process of existing microwave electromagnetic nozzle thrusters.

[0006] The present invention is achieved through the following technical solutions: The present invention discloses a microwave magnetron plasma thruster, comprising a housing with an air inlet and a nozzle connected to the end of the housing; a discharge chamber is provided inside the housing, a coaxial line is provided in the center of the discharge chamber, an antenna is connected to one side of the coaxial line, and the antenna is connected to a microwave connector, which is connected to a circular hole on the side of the housing upstream of the discharge chamber; A permanent magnet is provided outside the discharge chamber and is arranged close to one side of the nozzle; The permanent magnet is composed of a plurality of identical strip magnet units, which are evenly distributed along the circumference of the outer wall of the discharge chamber. Each strip magnet unit is composed of a plurality of permanent magnets arranged regularly. The permanent magnet forms a multiplexed magnetic field in the discharge chamber, and the multiplexed magnetic field is composed of an embedded magnetic mirror, an envelope magnetic mirror, a magnetic trap and a magnetic nozzle; Multiple embedded magnetic mirrors are closely attached to the wall of the discharge chamber and arranged closely along the axial direction. The outer side of the magnetic mirrors is surrounded by an envelope magnetic mirror to form a multiple magnetic mirror structure. The magnetic trap is arranged downstream of the multiple magnetic mirror structure; The magnetic nozzle is formed by the divergent magnetic field and is located downstream of the magnetic trap.

[0007] Furthermore, the discharge chamber adopts λ 0 / 4 coaxial line resonant cavity structure, λ 0 is the microwave wavelength.

[0008] Furthermore, microwave energy injection adopts a transverse feeding mode, and the microwave connector is far away from the discharge region and plasma.

[0009] Furthermore, the nozzle has a trumpet-like structure that expands outward.

[0010] Furthermore, the antenna extends in a radial direction and is short-circuited to the coaxial line; One end of the coaxial line is short-circuited to the housing.

[0011] Furthermore, three permanent magnets are tightly fitted together to form a magnetization period, and each strip magnet unit is composed of at least two or more magnetization periods arranged cyclically along the axial direction.

[0012] Furthermore, the axial direction from the discharge chamber to the nozzle is defined as the positive direction of the Z axis, and the radial direction from the inside of the discharge chamber to the outside is defined as the positive direction of the R axis; The magnetization direction of the first permanent magnet is the positive direction of the R axis, the magnetization direction of the second permanent magnet is the positive direction of the Z axis, and the magnetization direction of the third permanent magnet is the negative direction of the R axis.

[0013] Furthermore, the magnetic lines of force of the nozzle and the magnetic nozzle are aligned.

[0014] Furthermore, the permanent magnet is clamped and covered by the fixing member and the shell from top to bottom, and is fixed on the outer wall surface of the discharge chamber.

[0015] The present invention also discloses a working method of the microwave magnetron plasma thruster, which includes the following process: The working fluid gas enters the discharge chamber through the air inlet; after the microwave power is transmitted to the microwave connector, it is coupled to the coaxial line through the antenna and finally fed into the discharge chamber; the microwave excites a local strong electric field in the discharge chamber, triggering induced discharge or electric field breakdown discharge to generate initial electrons; Permanent magnets form a multiplexed magnetic field in the discharge chamber. Under the confinement of the multiplexed magnetic field, electrons move back and forth in the embedded magnetic mirror and envelope magnetic mirror structure, and continue to gain energy under the resonant condition of matching the microwave electric field with the electron cyclotron frequency, forming high-energy electrons. The high-energy electrons further ionize the working fluid gas, forming a plasma in the discharge chamber, which is effectively confined by the magnetic mirror. Driven by the magnetic field gradient, the plasma moves toward the axial magnetic trap area, and high-density plasma forms and expands, increasing its kinetic energy. Under the action of the magnetic nozzle, the radial kinetic energy of the plasma is converted into axial kinetic energy, forming a plasma flow, and ultimately generating thrust.

[0016] Compared with the prior art, the present invention has the following beneficial technical effects: The present invention discloses a microwave magnetron plasma thruster, which forms a multiplexed magnetic field configuration by designing special strip magnet units, wherein a plurality of strip magnet units are evenly distributed along the circumference of the outer wall of the discharge chamber. Compared with the prior art, the electron cyclotron resonance region formed by the magnet units in the present invention is larger than the electron cyclotron resonance region formed by the traditional Halbach array, which is more conducive to electron energy acquisition and the formation of a higher density plasma; at the same time, the magnet units in the present invention form an envelope magnetic mirror around the multiple embedded magnetic mirrors formed by the traditional Halbach array, which can further effectively confine the plasma while enhancing the magnetic field, thereby improving the working fluid ionization rate, plasma density, thrust, specific impulse and other performance. Compared with traditional microwave electromagnetic nozzle thrusters, they do not have a multiplexed magnetic field composed of four parts: embedded magnetic mirrors, envelope magnetic mirrors, magnetic traps and magnetic nozzles, while the above structure can effectively improve the ionization efficiency and plasma confinement capability. The magnetic field configuration and microwave feeding method used by the microwave magnetron plasma thruster of the present invention overcome the problems of low plasma density, low ionization efficiency, low thrust density and microwave joint corrosion, ensuring that it can operate at higher power, and will achieve higher propellant utilization efficiency and higher performance.

[0017] The multiple magnetic mirror array structure in the reused magnetic field configuration can realize axial multi-level magnetic mirror confinement and repeated acceleration of electrons in the discharge chamber, thereby overcoming the shortcomings of traditional microwave electromagnetic nozzle plasma thrusters such as low electron energy, insufficient ionization, and poor plasma confinement ability; the envelope magnetic mirror provides an overall magnetic confinement framework, and the embedded magnetic mirror enhances the local confinement effect, which can effectively improve the electron energy, working gas ionization rate and energy accumulation efficiency.

[0018] The magnetic field structure forms a magnetic trap at the thruster exit, utilizing the drift of the magnetic field gradient to concentrate high-density plasma. This also serves to block microwave propagation out of the nozzle, creating an effective microwave shield and improving microwave energy utilization, overcoming the low microwave coupling efficiency found in traditional structures. Furthermore, as the plasma moves toward areas of lower magnetic pressure, it expands rapidly, significantly enhancing its kinetic energy.

[0019] In the downstream area of the discharge chamber, the magnetic nozzle structure formed by the expanding magnetic lines of force will cause the plasma in the magnetic trap to move along the magnetic lines of force and convert radial kinetic energy into axial kinetic energy to form thrust.

[0020] Furthermore, the thruster adopts λ The 0 / 4 coaxial resonant cavity structure serves as a discharge chamber, which excites a standing wave electric field and cooperates with the electron cyclotron resonance region to efficiently ionize and generate plasma.

[0021] Furthermore, the microwave connector is away from the strong ionization area to avoid plasma erosion, thereby greatly improving the connector life. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 Schematic diagram of the structure of the microwave magnetron plasma thruster of the present invention; Figure 2 Schematic diagram of a single magnet structure of the microwave magnetron plasma thruster of the present invention; Figure 3 Schematic diagram of the magnetic field distribution of the microwave magnetron plasma thruster of the present invention; Figure 4 This is a working image of a microwave magnetron plasma thruster of one configuration.

[0023] Among them, 1. air inlet; 2. outer shell; 3. discharge chamber; 4. permanent magnet; 5. antenna; 6. coaxial line; 7. microwave connector; 8. nozzle; 9. fixing parts. DETAILED DESCRIPTION

[0024] 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.

[0025] 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.

[0026] It should be noted that the terms "comprises", "includes" or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, element, method, article or device comprising a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to the process, element, method, article or device. In addition, the terms "horizontal" and "vertical" are based on the orientation and positional relationship of the devices or components shown in the drawings, and are only for the purpose of better describing the present invention, rather than requiring the devices, components or devices shown to have such a specific orientation, and therefore should not be understood as limiting the present invention.

[0027] The features and performance of the present invention are further described in detail below with reference to the embodiments.

[0028] The present invention discloses a microwave magnetron plasma thruster, the cross-sectional structure, magnet structure and multiplexed magnetic field structure schematic diagram are shown in FIG. Figure 1 、 Figure 2 、 Figure 3 As shown, the device comprises a housing 2 with an air inlet 1 formed therein and a nozzle 8 connected to the end of the housing 2. The housing 2 contains a discharge chamber 3, which has a coaxial line 6 located in the center. An antenna 5 is connected to one side of the coaxial line 6, and the antenna 5 is connected to a microwave connector 7, which is mounted on the housing 2.

[0029] The discharge chamber 3 is mainly used to generate high-density plasma, and the nozzle 8 is located downstream of the discharge chamber. The working medium gas is injected into the discharge chamber 3 through the air inlet 1. The microwave operating frequency is 2.45GHz, and the microwave feeding device includes a microwave connector 7, an antenna 5, and a coaxial line 6. The microwave connector 7 is introduced through the side circular hole of the shell 2. One end of the coaxial line 6 is short-circuited to the cavity and the other end is open, forming a λ 0 / 4 coaxial line resonant cavity, microwave connector 7 and coaxial line 6 are connected through antenna 5.

[0030] λ The 0 / 4 coaxial resonant cavity is a structure designed using the principle of electromagnetic wave resonance to enhance the electromagnetic field of a specific frequency. λ0 / 4 means that the length of the coaxial line 6 is equal to an odd multiple of one quarter of the wavelength of the microwave used. This parameter condition enables the cavity to form a standing wave at the target frequency, thereby achieving efficient energy concentration and enhancement.

[0031] in, λ 0 is the microwave wavelength.

[0032] A permanent magnet 4 is provided outside the discharge chamber 3 and is embedded between the housing 2 and the fixing member 9 .

[0033] The permanent magnet 4 is composed of a plurality of identical strip magnet units, which are arranged in sequence along the axial direction of the housing 2. Each strip magnet unit surrounds the outer wall of the discharge chamber 3. The specific structure of a single strip magnet unit is as follows: Figure 2 As shown, each strip magnet unit is composed of multiple small permanent magnets arranged in a specific pattern. The axial direction from the discharge chamber 3 toward the nozzle 8 is defined as the positive Z-axis direction, and the radial direction from the inside of the discharge chamber 3 to the outside is defined as the positive R-axis direction. Thus, the magnetization direction of the first small permanent magnet is the positive R-axis direction, the magnetization direction of the second small permanent magnet is the positive Z-axis direction, and the magnetization direction of the third small permanent magnet is the negative R-axis direction.

[0034] The three small permanent magnets are tightly packed together to form a magnetization cycle, and each bar magnet unit consists of at least two or more magnetization cycles arranged axially. Specifically, the fourth small permanent magnet has the same magnetization direction as the first, which is the positive direction of the R axis; the fifth small permanent magnet has the same magnetization direction as the second, which is the positive direction of the Z axis; the sixth small permanent magnet has the same magnetization direction as the third, which is the negative direction of the R axis; and so on.

[0035] The magnetization direction of the small permanent magnets mentioned above is not constant. Figure 2 The arrangement and quantity are only given as a specific embodiment.

[0036] The permanent magnet 4 composed of multiple bar magnet units is used to form Figure 3 The multiplexed magnetic field shown in the figure consists of four parts: an embedded magnetic mirror, an envelope magnetic mirror, a magnetic trap, and a magnetic nozzle. Multiple embedded magnetic mirrors are closely attached to the wall of the discharge chamber 3 and arranged closely in the axial direction. The outer sides of the embedded magnetic mirrors are surrounded and covered by the envelope magnetic mirror, forming a multiple magnetic mirror structure. The synergistic effect of the internal and external magnetic mirrors can effectively constrain electron motion, improve electron energy accumulation and working fluid ionization efficiency. The magnetic trap is located downstream of the multiple magnetic mirror structure to further concentrate high-density plasma and prevent premature axial diffusion of the plasma. Downstream of the magnetic trap is a magnetic nozzle formed by a divergent magnetic field, which is used to accelerate the plasma flow and achieve effective extraction, thereby generating axial thrust.

[0037] The working process of a microwave magnetron plasma thruster of the present invention is as follows: The working fluid gas enters the discharge chamber 3 through the air inlet 1. After the microwave power is transmitted to the microwave connector 7, it is coupled to the coaxial line 6 through the antenna 5 and finally fed into the discharge chamber 3. The microwave excites a local strong electric field in the discharge chamber 3, triggering induced discharge or electric field breakdown discharge to produce initial electrons. Under the confinement of the magnetic field, the electrons reciprocate in the embedded magnetic mirror and the envelope magnetic mirror structure, and continue to gain energy under the resonance condition of matching the microwave electric field with the electron cyclotron frequency, forming high-energy electrons. The high-energy electrons further ionize the working fluid gas, forming a large amount of plasma in the discharge chamber 3, which is effectively confined by the magnetic mirror. Driven by the magnetic field gradient, the plasma moves toward the axial magnetic trap region, where high-density plasma is formed and rapidly expands, with a significant increase in kinetic energy. Under the action of the magnetic nozzle, the radial kinetic energy of the plasma is converted into axial kinetic energy, forming a high-density, high-energy, and highly concentrated plasma particle beam, ultimately generating thrust.

[0038] Furthermore, during the ignition phase, considering that there are no sharp points inside the discharge chamber 3 to cause electric field concentration, the microwave electric field is designed in conjunction with electron cyclotron resonance, using a local strong electric field to ionize the gas to form an initial plasma. At the same time, the microwave joint 7 is kept away from the electron cyclotron resonance discharge area, effectively reducing joint losses, thereby enabling the thruster to operate stably and continuously for a long time.

[0039] The electron cyclotron resonance region (ECR) is the spatial region where, under specific magnetic field and microwave frequency conditions, electrons resonate, absorb energy, are efficiently heated, and stimulate plasma discharge. This region is designed to be located within the embedded and envelope magnetic mirrors.

[0040] The present invention utilizes multiple magnetic units to construct a multiplexed magnetic field structure. The coordinated configuration of multiple built-in magnetic mirrors and envelope magnetic mirrors constrains the trajectory of electron motion and combines this with the spatial distribution of the microwave electric field to form high-energy electrons, thereby significantly improving the ionization efficiency of the working gas. The magnetic trap region helps to gather high-density plasma while utilizing its characteristics to shield electromagnetic waves, thereby improving microwave energy utilization. Furthermore, the resonant cavity structure used in the discharge chamber 3 can achieve a stable microwave standing wave distribution. The optimized coordination between the microwave electric and magnetic fields, as well as the placement of the microwave connector 7 away from the strong discharge zone, can effectively reduce plasma erosion of the microwave connector, thereby improving the system's tolerance to high-power microwaves and operational stability.

[0041] Figure 4 This image shows a microwave magnetron plasma thruster designed based on the present invention in operation. When the thruster is operating, argon gas is first introduced, followed by microwave power to achieve ignition. Figure 4The image shows a successful thruster discharge and beam extraction, taken from the nozzle toward the discharge chamber. The image shows the microwave discharge concentrated in the multiple magnetic mirrors, and the plasma ejected outward under the guidance of the magnetic nozzle.

[0042] In summary, the present invention discloses a microwave magnetic plasma thruster (MMPT). The thruster can use a set of magnetic field structures to simultaneously meet the microwave power ignition at 2.45GHz and the generation, confinement and acceleration of plasma. There are multiple closely arranged embedded magnetic mirrors in the magnetic field configuration, and the outside is surrounded by an envelope magnetic mirror. This magnetic field distribution is conducive to enhancing the axial and radial confinement capabilities of the plasma and significantly improving the thrust performance. The magnetic trap area downstream of the discharge chamber 3 can gather high-density plasma, thereby realizing self-shielding and efficient transmission of microwaves. The magnetic nozzle structure can further accelerate the extraction of plasma to generate thrust. The thruster adopts a transverse feeding mode and λ The 0 / 4 coaxial resonant cavity structure can further improve the efficiency of the microwave transmission system while reducing microwave joint losses, thereby increasing the working efficiency and life of the thruster.

[0043] Compared to traditional microwave magnetic nozzle thrusters, the microwave magnetron plasma thruster proposed in this paper offers significant advantages in plasma confinement, high-density plasma generation efficiency, propellant utilization, and microwave coupling efficiency, enabling greater thrust output. This invention achieves a combination of miniaturization, high efficiency, and high thrust output, making it suitable for high-performance micro-electric propulsion systems.

[0044] 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 microwave magnetron plasma thruster, characterized in that: The invention comprises a shell (2), an air inlet (1) is provided on the shell (2), and a nozzle (8) is connected to the end of the shell (2); the inside of the shell (2) is a discharge chamber (3), a coaxial line (6) is provided in the center of the discharge chamber (3), an antenna (5) is connected to one side of the coaxial line (6), and the antenna (5) is connected to a microwave connector (7), and the microwave connector (7) is connected to a circular hole on the side of the shell (2) upstream of the discharge chamber (3); A permanent magnet (4) is provided outside the discharge chamber (3), and the permanent magnet (4) is provided close to one side of the nozzle (8); The permanent magnet (4) is composed of a plurality of identical strip-shaped magnet units, the strip-shaped magnet units are evenly distributed along the circumference of the outer wall of the discharge chamber (3), and each strip-shaped magnet unit is composed of a plurality of permanent magnets arranged regularly; The permanent magnet (4) forms a multiplexed magnetic field in the discharge chamber (3), wherein the multiplexed magnetic field is composed of an embedded magnetic mirror, an envelope magnetic mirror, a magnetic trap, and a magnetic nozzle; A plurality of embedded magnetic mirrors are closely attached to the wall of the discharge chamber (3) and are closely arranged along the axial direction, and the outer sides of the embedded magnetic mirrors are surrounded and covered by the envelope magnetic mirror to form a multiple magnetic mirror structure; The magnetic trap is arranged downstream of the multiple magnetic mirror structure; The magnetic nozzle is formed by the divergent magnetic field and is located downstream of the magnetic trap.

2. The microwave magnetron plasma thruster according to claim 1, characterized in that: The discharge chamber (3) adopts λ 0 / 4 coaxial line resonant cavity structure, λ 0 is the microwave wavelength.

3. The microwave magnetron plasma thruster according to claim 1, characterized in that: The microwave energy injection adopts the transverse feeding mode, and the microwave connector (7) is far away from the discharge region and the plasma.

4. The microwave magnetron plasma thruster according to claim 1, characterized in that: The nozzle (8) has a trumpet-like structure that expands outward.

5. The microwave magnetron plasma thruster according to claim 1, characterized in that: The antenna (5) extends in a radial direction and is short-circuited to the coaxial line (6); One end of the coaxial line (6) is short-circuited to the housing (2).

6. The microwave magnetron plasma thruster according to claim 1, characterized in that: Three permanent magnets are tightly fitted together to form a magnetization period, and each strip magnet unit is composed of at least two or more magnetization periods arranged cyclically along the axial direction.

7. The microwave magnetron plasma thruster according to claim 6, characterized in that: The axial direction from the discharge chamber (3) to the nozzle (8) is defined as the positive direction of the Z axis, and the radial direction from the inside of the discharge chamber (3) to the outside is defined as the positive direction of the R axis; The magnetization direction of the first permanent magnet is the positive direction of the R axis, the magnetization direction of the second permanent magnet is the positive direction of the Z axis, and the magnetization direction of the third permanent magnet is the negative direction of the R axis.

8. The microwave magnetron plasma thruster according to claim 1, characterized in that: The nozzle (8) is aligned with the magnetic field lines of the magnetic nozzle.

9. The microwave magnetron plasma thruster according to claim 1, characterized in that: The permanent magnet (4) is clamped and covered by the fixing member (9) and the outer shell (2) from top to bottom, and is fixed on the outer wall surface of the discharge chamber (3).

10. The operating method of a microwave magnetron plasma thruster according to any one of claims 1 to 9, characterized in that: The following processes are included: The working medium gas enters the discharge chamber (3) through the air inlet (1); after the microwave power is transmitted to the microwave connector (7), it is coupled to the coaxial line (6) through the antenna (5) and finally fed into the discharge chamber (3); the microwave excites a local strong electric field in the discharge chamber (3), triggering induced discharge or electric field breakdown discharge to generate initial electrons; The permanent magnet (4) forms a reused magnetic field in the discharge chamber (3). Under the constraint of the reused magnetic field, the electrons reciprocate in the embedded magnetic mirror and the envelope magnetic mirror structure and continuously gain energy under the resonance condition of the microwave electric field matching the electron cyclotron frequency, thereby forming high-energy electrons. The high-energy electrons further ionize the working fluid gas, and a plasma is formed in the discharge chamber (3), which is effectively constrained by the magnetic mirror. Driven by the magnetic field gradient, the plasma moves toward the axial magnetic trap region, and a high-density plasma is formed and expands, thereby increasing the kinetic energy. Under the action of the magnetic nozzle, the radial kinetic energy of the plasma is converted into axial kinetic energy, thereby forming a plasma flow, and finally generating thrust.

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