阅读说明：本技术 一种磁场力/力矩作用投送系统及其地面测试装置 (Magnetic field force/moment action delivery system and ground testing device thereof ) 是由 张元文 赵宏亮 杨乐平 朱彦伟 黄涣 朱昊逵 陈鹏霖 于 2021-08-27 设计创作，主要内容包括：本发明涉及一种磁场力/力矩作用投送系统,包含等离子体收集装置和脉冲等离子体环发射装置,所述脉冲等离子体环发射装置用于产生和发射脉冲等离子体环,包括内轴、外轴、内轴电磁铁、外轴电磁铁、高能电容器、等离子注入口,所述内轴与所述外轴为同轴两套筒,所述内轴电磁铁安装于内轴内壁、外轴电磁铁安装于外轴外壁。该系统可较好解决电磁力/力矩作用距离受限问题,实现对空间目标超远距快速投送电磁姿轨操控。(The invention relates to a magnetic field force/moment action delivery system, which comprises a plasma collecting device and a pulse plasma torus transmitting device, wherein the pulse plasma torus transmitting device is used for generating and transmitting a pulse plasma torus and comprises an inner shaft, an outer shaft, an inner shaft electromagnet, an outer shaft electromagnet, a high-energy capacitor and a plasma injection port, the inner shaft and the outer shaft are two coaxial sleeves, the inner shaft electromagnet is arranged on the inner wall of the inner shaft, and the outer shaft electromagnet is arranged on the outer wall of the outer shaft. The system can better solve the problem that the acting distance of electromagnetic force/torque is limited, and realize the ultra-long-distance rapid delivery of electromagnetic attitude and orbit control on the space target.)

1. The utility model provides a magnetic field force/moment effect system of delivering, its characterized in that, the system contains plasma collection device and pulse plasma ring emitter, pulse plasma ring emitter is used for producing and emitting pulse plasma ring, including interior axle, outer axle, interior axle electro-magnet, outer axle electro-magnet, high-energy capacitor, plasma injection port, interior axle with the outer axle is two coaxial sleeves, interior axle electro-magnet is installed in interior axle inner wall, outer axle electro-magnet and is installed in outer axle outer wall, the step that pulse plasma ring emitter produced pulse plasma ring is:

electrifying the electromagnets of the inner shaft and the outer shaft to obtain a radial magnetic field pointing to the outer shaft from the inner shaft, wherein the magnetic field of the outer ring is stronger than that of the inner ring;

injecting plasma with certain mass into an annular inner cavity formed between the inner shaft and the outer shaft to form a plasma group, wherein the plasma group is frozen in a radial magnetic field;

the inner shaft is connected with the outer shaft through a plasmoid, and current flows through the inner shaft in the axial direction and flows out of the outer shaft after flowing through the plasmoid; the current passing through the inner shaft generates a toroidal magnetic field, the current flowing through the plasma group interacts with the toroidal magnetic field to drive the plasma group to flow upwards and cut the radial magnetic field;

the radial magnetic lines frozen in the plasma cluster are connected into closed magnetic lines, and the plasma cluster reaches a stable ring state with minimum energy after microsecond-order time diffusion, so that a pulse plasma ring in a stable state is obtained.

2. The system of claim 1, wherein the pulsed plasma loop launcher accelerates the launching plasma loop by:

high-energy capacitors are used for discharging quickly to generate high voltage in the annular inner cavity, and the pulse plasma torus cuts the radial magnetic field to generate axial electromagnetic thrust to drive the pulse plasma torus to move at high speed and accelerate emission.

3. The system of claim 2, wherein the accelerated emission model of the pulsed plasma loop is:

wherein L is loop capacitance, i is loop current, R is loop resistance, and R is_{Inner part}Is the inner shaft radius, r_{Outer cover}Inner shaft radius, μ₀For vacuum permeability, γ ═ μ₀ln(r_{Inner part}/r_{Outer cover}) L is the distance between the center of the emitting end face and the center of the plasma ring,Resistance, C of plasma loop emitter per unit length₀The capacitance of the high-energy capacitor and the ring mass of the plasma are m.

4. The system of claim 1, wherein the pulsed plasma torus equivalent magnetic moment is:q is the charge of the charged particles in the pulse plasma ring, omega is the rotation frequency of the charged particles along the ring in the pulse plasma ring, r_{Inner part}≤r≤r_{Outer cover}Is the plasma torus radius; the equivalent magnetic moment of the pulsed plasma torus can be improved by increasing the radius of the plasma torus, the speed of charged particles along the torus and the charge of the charged particles.

5. The system of claim 4, wherein the exit spread angle of the pulsed plasma loop transmitted by the pulsed plasma loop transmitting device is constrained by the length of the outer shaft and the charging voltage of the high energy capacitor.

6. The system of claim 1, wherein the attitude and orbit control based on the pulsed plasma loop is performed by changing the current magnitude and direction of the high energy capacitor discharge to change the density and direction of rotation of the charged particles in the plasma loop, thereby controlling the magnitude and direction of the frozen magnetic field, which interacts with the magnetic field charged by the spatial object to achieve a desired manipulation of attraction or repulsion of the spatial object.

7. The system of claim 1, wherein the plasma collection device is extendable in an outwardly nested loop for collecting plasma in situ in a space environment.

8. The ground testing device is characterized by being used for ground testing of the pulsed plasma torus emission device as claimed in claim 1, and comprising an external support frame, the pulsed plasma torus emission device and a pulsed plasma torus emission device support frame, wherein the pulsed plasma torus emission device is used for generating and emitting pulsed plasma torus and comprises an inner shaft, an outer shaft, an inner shaft electromagnet, an outer shaft electromagnet, a high-energy capacitor and a plasma injection port, the inner shaft and the outer shaft are coaxial two sleeves, the inner shaft electromagnet is arranged on the inner wall of the inner shaft, and the outer shaft electromagnet is arranged on the outer wall of the outer shaft.

9. The device of claim 8, wherein the external support frame is composed of a square acrylic vacuum cover and a slide rail, and a partition plate is arranged inside the external support frame and used for supporting the pulse plasma ring emission device; pulse plasma ring emitter support frame comprises electro-magnet mount, copper ring support frame and copper ring draw-in groove, the copper ring support frame is used for fixed outer axle, the copper ring draw-in groove is fixed with interior axle electro-magnet mount and interior axle and outer axle, and it has the round hole to open its bottom can be used to point discharge with ionization neutral gas.

Technical Field

The invention belongs to the technical field of electromagnetic control of spacecrafts, and relates to a delivery system under the action of magnetic field force/moment and a ground testing device thereof.

Background

The electromagnetic control technology of the spacecraft (covering the application of electromagnetic butt joint, formation flight, vortex racemization and the like) has the advantages of no propellant consumption, no plume pollution, continuous reversible control capability and the like, and has great application potential; at present, relevant scientific research institutions at home and abroad develop systematic ground test research and are intended to develop on-orbit technical verification. However, the electromagnetic force/moment action has the inherent disadvantage that the force/moment value is inversely proportional to the 3-4 th power of the relative distance, and the control space is limited. For this reason, in recent decades, researchers have explored and researched various auxiliary means, such as superconductor application, tether-electromagnetic coordination, etc., but the manipulation space can only be expanded to tens of meters, and the space target attitude and orbit manipulation requirements can not be met.

The system and the method for the ultra-long-distance rapid delivery of the magnetic field force/moment action aiming at the attitude and orbit control of the space target have not been disclosed and published. In the field of nuclear fusion, the tokamak feeding system (such as an axial gun, a compact ring and the like) relates to some common technologies, such as plasma sheet generation and accelerated emission; however, because the input end constraint and the output end requirement of the system and the method are different greatly, the specific electromagnetic field design and the control method are different greatly:

first, the charging voltage, volume, and mass of the capacitor at the input of the existing device are large, and are not suitable for on-rail control applications.

Due to the huge energy and feeding speed/precision requirements of the nuclear fusion reactor, the charging voltage, the volume and the mass of the capacitor are huge; a single spacecraft or space station cannot meet the requirements of energy and the like required by the design of the existing device.

Second, the existing devices do not focus on transport performance after plasma loop emission.

The prior device is mainly required for feeding of a nuclear fusion reactor, a plasma sheet is emitted and then transferred to the reactor to control relay, and the emission device does not pay attention to the transport performance of the subsequent plasma sheet.

Third, existing devices do not consider on-demand control of plasma loop direction and size.

The existing device aims at feeding the nuclear reactor, and does not consider the running direction of charged particles in a plasma ring, the size of a freezing magnetic field and the like; based on the attitude and orbit control requirements of the space target, the controllability of the direction and the size of the freezing magnetic field needs to be considered.

Fourth, existing devices do not have plasma in-situ collection capability.

Disclosure of Invention

Based on the above technical problem, the present invention provides a system for serving attitude and orbit control of a space target and delivering magnetic field force/torque at an ultra-long distance (km, sub-second order) and a ground testing device thereof.

The utility model provides a system of delivering of magnetic field force/moment effect, contains plasma collection device and pulse plasma ring emitter, pulse plasma ring emitter is used for producing and transmitting pulse plasma ring, including interior axle, outer axle, interior axle electro-magnet, outer axle electro-magnet, high-energy capacitor, plasma injection port, interior axle with the outer axle is two coaxial sleeves, interior axle electro-magnet is installed in interior axle inner wall, and outer axle electro-magnet is installed in outer axle outer wall.

The pulse plasma loop emission device generates a pulse plasma loop by the following steps:

electrifying the electromagnets of the inner shaft and the outer shaft to obtain a radial magnetic field pointing to the outer shaft from the inner shaft, wherein the magnetic field of the outer ring is stronger than that of the inner ring;

a certain mass of plasma is filled in an annular inner cavity formed between the inner shaft and the outer shaft to form a plasma group, and the plasma group is frozen in a radial magnetic field;

the inner shaft is connected with the outer shaft through a plasmoid, and current flows through the inner shaft in the axial direction and flows out of the outer shaft after flowing through the plasmoid; the current passing through the inner shaft generates a toroidal magnetic field, the current flowing through the plasma group interacts with the toroidal magnetic field to drive the plasma group to flow upwards and cut the radial magnetic field;

the radial magnetic lines frozen in the plasma cluster are connected into closed magnetic lines, and the plasma cluster reaches a stable ring state with minimum energy after microsecond-order time diffusion, so that a pulse plasma ring in a stable state is obtained.

The pulse plasma loop emission device for accelerating emission of the plasma loop comprises the following steps:

high-energy capacitors are used for fast discharging to generate high voltage in the annular inner cavity, the pulse plasma torus cuts the radial magnetic field to generate axial electromagnetic thrust, and the pulse plasma torus is driven to move at high speed and is emitted and sprayed out.

The accelerated emission model of the pulse plasma loop is as follows:

wherein L is loop capacitance, i is loop current, R is loop resistance, and R is_{Inner part}Is the inner shaft radius, r_{Outer cover}Inner shaft radius, μ₀For vacuum permeability, γ ═ μ₀ln(r_{Inner part}/r_{Outer cover}) L is the distance between the center of the emitting end face and the center of the plasma ring,Resistance, C of plasma loop emitter per unit length₀The capacitance of the high-energy capacitor and the ring mass of the plasma are m.

The equivalent magnetic moment of the pulsed plasma loop is:q is the charge of the charged particles in the pulse plasma ring, omega is the circumferential rotation frequency of the charged particles in the pulse plasma ring, r_{Inner part}≤r≤r_{Outer cover}The plasma loop radius is increased, the plasma loop radius, the charged particle speed along the loop and the charged particle charge can improve the equivalent magnetic moment of the pulsed plasma loop.

The exit spread angle of the pulsed plasma loop transmitted by the pulsed plasma loop transmitting device can be constrained by the length of the outer shaft and the charging voltage of the high-energy capacitor.

The attitude and orbit control of the pulse plasma loop changes the density and the rotating direction of charged particles in the plasma loop by changing the discharge current and the discharge current direction of the high-energy capacitor, further controls the size and the direction of a frozen magnetic field, and the magnetic field interacts with the magnetic field carried by a space target to achieve the expected control of the attraction or the repulsion of the space target.

The plasma collecting device can extend towards the outer sleeve type ring shape and is used for collecting plasma in situ in space environment.

The invention also provides a ground testing device for better testing the pulse plasma torus launching device and simulating the influence of the space physical environment to a certain extent, the ground testing device is used for ground testing of the pulse plasma torus launching device and comprises an external support frame, the pulse plasma torus launching device and a pulse plasma torus launching device support frame, the pulse plasma torus launching device is used for generating and launching pulse plasma toricles and comprises an inner shaft, an outer shaft, an inner shaft electromagnet, an outer shaft electromagnet, a high-energy capacitor and a plasma injection port, the inner shaft and the outer shaft are coaxial two sleeves, the inner shaft electromagnet is arranged on the inner wall of the inner shaft, and the outer shaft electromagnet is arranged on the outer wall of the outer shaft.

The external support frame is composed of a square acrylic vacuum cover and a slide rail, and a partition plate is arranged in the external support frame and used for supporting the pulse plasma ring emission device; pulse plasma ring emitter support frame comprises electro-magnet mount, copper ring support frame and copper ring draw-in groove, the copper ring support frame is used for fixed outer axle, the copper ring draw-in groove is fixed with interior axle electro-magnet mount and interior axle and outer axle, and it has the round hole to open its bottom can be used to point discharge with ionization neutral gas.

The pulse plasma loop emitter of the ultra-long-distance rapid delivery system with magnetic field force/moment action and the ground test device thereof can generate and accelerate the emission of the pulse plasma loop, the pulse plasma loop freezes a radial magnetic field and a circumferential magnetic field with certain strength, the pulse plasma loop can stably fly for a period of time in a vacuum environment, the pulse plasma loop flies to the vicinity of a space target and acts with the magnetic field carried by the pulse plasma loop to generate magnetic field force/moment control on the pulse plasma loop, and further the attitude and orbit motion state of the pulse plasma loop is changed, so that the problem of limited action distance of electromagnetic force/moment can be better solved, and the ultra-long-distance rapid electromagnetic orbit control on the space target can be realized.

Drawings

Fig. 1 is an overall structure of a magnetic field force/moment action super-long-distance rapid delivery system carried by a control spacecraft;

FIG. 2 is a structural diagram of a pulsed plasma toroidal launcher;

FIG. 3 is a graph of loop current over time for a pulsed plasma loop;

FIG. 4 is a graph of speed as a function of time;

FIG. 5 is a graph of overall kinetic energy as a function of time;

FIG. 6 is a graph of acceleration position versus time;

FIG. 7 is a spatial target attitude and orbit manipulation under the influence of a pulsed magnetic field;

FIG. 8 is a calculation of the force/moment equivalence of the pulsed magnetic field and the target magnetic field;

FIG. 9 is a pulsed magnetic field eddy current force/torque equivalent calculation;

FIG. 10 is a nested annular extension of the plasma collection device;

fig. 11 shows a ground test apparatus.

Detailed Description

In order to make the objects, technical solutions and advantages of the present application more apparent, the present application is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present application and are not intended to limit the present application.

The general structure of the magnetic field force/moment action ultra-remote rapid delivery system carried by a control spacecraft comprises a plasma collecting device 1 and a pulse plasma ring emission device 2 as shown in figure 1, wherein the pulse plasma ring emission device 2 is used for generating and emitting a pulse plasma ring, the structure of the pulse plasma ring emission device 2 is shown in figure 2, the pulse plasma ring emission device 2 comprises an inner shaft 2-1, an outer shaft 2-2, an inner shaft electromagnet, an outer shaft electromagnet, a high-energy capacitor and a plasma injection port, the inner shaft and the outer shaft are coaxial two sleeves, the inner shaft electromagnet is arranged on the inner wall of the inner shaft, the outer shaft electromagnet is arranged on the outer wall of the outer shaft, and the high-energy capacitor is positioned in a high-energy capacitor discharge and cable module 2-3 of figure 2.

In one embodiment, the step of generating the pulsed plasma loop by the pulsed plasma loop transmitting apparatus 2 is:

electrifying electromagnets of an inner shaft and an outer shaft of the pulse plasma ring emission device 2 to obtain a radial magnetic field pointing from the inner shaft to the outer shaft, wherein the magnetic field of the outer ring is stronger than that of the inner ring;

a certain mass of plasma is filled in an annular inner cavity formed between the inner shaft and the outer shaft to form a plasma group, and the plasma group is frozen in a radial magnetic field;

the inner shaft is connected with the outer shaft through a plasmoid, and current flows through the inner shaft in the axial direction and flows out of the outer shaft after flowing through the plasmoid; the current passing through the inner shaft generates a toroidal magnetic field, the current flowing through the plasma group interacts with the toroidal magnetic field to drive the plasma group to flow upwards and cut the radial magnetic field;

the radial magnetic lines frozen in the plasma cluster are connected into closed magnetic lines, and the plasma cluster reaches a stable ring state with minimum energy after microsecond-order time diffusion, so that a pulse plasma ring in a stable state is obtained.

Pulsed plasma toroidal stable generation and acceleration involves superimposed motion of charged particles in an electromagnetic field: under the action of an electromagnetic field, the motion of the injected plasma is changed from a disordered state to an ordered state, namely a stable ring shape; the plasma toroidal acceleration process relates to magnetohydrodynamics, radiation hydrodynamics and the like, the current design neglects the influence of collision, aerodynamics and the like, and only considers the on-demand action of an electromagnetic field on charged particle clusters; the generation and accelerated emission processes of the plasma loop are the superposition of three motions, namely the circular motion of the plasma around the annular magnetic field, the axial circular motion of the plasma around the device under the action of the radial magnetic field, and the integral accelerated motion of the plasma loop.

The step of accelerating the emission of the plasma loop by the pulse plasma loop emission device 2 is as follows:

high-energy capacitors are used for fast discharging to generate high voltage in the annular inner cavity, the pulse plasma torus cuts the radial magnetic field to generate axial electromagnetic thrust, and the pulse plasma torus is driven to move at high speed and is emitted and sprayed out.

The accelerated emission model of the pulse plasma loop is as follows:

wherein L is loop capacitance, i is loop current, R is loop resistance, and R is_{Inner part}Is the inner shaft radius, r_{Outer cover}Inner shaft radius, μ₀For vacuum permeability, γ ═ μ₀ln(r_{Inner part}/r_{Outer cover}) L is the distance between the center of the emitting end face and the center of the plasma ring,Resistance, C of plasma loop emitter per unit length₀The capacitance of the high-energy capacitor and the ring mass of the plasma are m.

By the above formula, in order to increase the emission speed of the outlet of the pulsed plasma loop, the loop current i is equivalently increased, and the method can be realized by expanding the acceleration time, adjusting the quality of the plasma loop, enhancing the energy storage and instantaneous discharge capacity of the capacitor and the like. By writing a Matlab simulation program, the change relationship of the loop current of the numerical simulation pulse plasma loop with time is shown in FIG. 3, the change relationship of the speed with time is shown in FIG. 4, the change relationship of the overall kinetic energy with time is shown in FIG. 5, and the change relationship of the acceleration position with time is shown in FIG. 6, and the change rule accords with the design expectation. Where the 'mg' legend indicates three different plasma loop masses.

In one embodiment, the pulsed plasma ring is frozen with an axial ring magnetic field and a poloidal ring magnetic field, wherein only the latter exerts a magnetic field force on the outside. The axial ring magnetic field is generated by a current loop, the current value depends on the discharge capacity of the high-energy capacitor, and is calculated as:

wherein i is the discharge current of the high-energy capacitor, r₁Is the radial distance from the center of the axial ring.

The polar ring magnetic field generates a magnetic field force action outwards, the magnetic field force action is the dominant magnetic field of the pulse plasma loop, and the equivalent magnetic moment is calculated as follows:

wherein q is the charge of charged particles in the pulsed plasma loop, ω is the rotation frequency of the particles along the polar ring in the pulsed plasma loop, and r is the radius of the polar ring of the plasma. Therefore, the equivalent magnetic moment of the pulsed plasma loop can be improved by increasing the radius of the polar ring, the speed of the charged particles along the loop and the charge of the charged particles.

In another embodiment, the exit spread angle of the pulsed plasma loop transmitted by the pulsed plasma loop transmitting device can be constrained by the length of the outer shaft and the charging voltage of the high energy capacitor.

After the plasma loop is ejected from the apparatus, the configuration factors include: ionization of neutral gas by kinetic energy, lack of magnetic confinement, influence of external plasma environment and the like. For the vacuum environment, because the density of neutral atmosphere is ultralow, the ionization of the kinetic energy of the plasma ring motion on the neutral gas can cause that the influence of the kinetic energy converted into heat energy and electromagnetic energy can be ignored; after the geometrical constraint of the electromagnetic field of the transmitting device is removed, the ejected plasma ring can be rapidly diffused due to density gradient and thermal expansion, so that the energy density is rapidly reduced in the transportation process; the larger the divergence angle of the plasma loop, the shorter the propagation distance.

The attitude and orbit control of the pulse plasma loop changes the density and the rotating direction of charged particles in the plasma loop by changing the current magnitude and the flow direction of high-energy capacitor discharge, further controls the magnitude and the direction of a frozen magnetic field, and the magnetic field interacts with a magnetic field carried by a space target to achieve expected control on attraction or repulsion of the space target.

After the pulsed magnetic field is emitted at a high speed, magnetic field interaction can be generated between the pulsed magnetic field and a spacecraft with an electromagnetic device (called a magnetic control spacecraft) and magnetic field eddy current interaction can be generated between the pulsed magnetic field and a spacecraft without an electromagnetic device (called a non-magnetic spacecraft), so that acting force/torque required by attitude and orbit control can be generated on a target spacecraft, as shown in fig. 7.

The interaction between the magnetic field and the magnetic field can be calculated based on the equivalent electromagnetic force and the equivalent torque shown in fig. 8, and the calculation model is as follows:

wherein, the T and C magnetic dipoles are equivalent magnetic dipoles and o of the target spacecraft and the control spacecraft magnetic field respectively_CMIs the center of the line of two magnetic dipoles, o_CMx_EMAlong the connecting line from T to C, o_CMy_EMAnd o_CMz_EMDefinition with certain degree of freedom (set according to specific control task), (mu)_T,μ_C) Magnetic moments of T and C, respectively, (alpha, beta) T, C and o, respectively_CMx_EMThe angle (X, delta) is respectively T and C magnetic dipole is o_CMy_EMz_EMProjection of a surface and_CMy_EMangle of (d) r_TCIs the two magnetic dipole spacing.

The magnetic field eddy current interaction can be calculated based on the equivalent electromagnetic force and moment shown in fig. 9, and the calculation model is as follows:

wherein, B_zThe pulse magnetic field intensity, h, the outer surface wall thickness, sigma, the outer surface material electric conductivity and the magnetic field intensity are respectively measured, and_r,E_t) Radial and tangential eddy electric field intensity, v is translational motion velocity vector, (J, J)_t) Respectively the total and tangential eddy current densities, omega is the rotating motion velocity vector of the target spacecraft, r is the equivalent radius of the target spacecraft,And the spherical coordinate integral variable of the equivalent spherical surface of the target spacecraft is obtained.

The space target attitude and orbit control strategy under the action of the pulsed magnetic field is designed as follows:

1) because the pulse plasma magnetic field is stripped to control the spacecraft, the electromagnetic field force/moment can be considered to only act on the attitude and orbit motion of the target spacecraft, and the attitude and orbit motion of the controlled spacecraft is not interfered; therefore, the steering design process may assume that the steered spacecraft moves along the initial orbit, which may be used as a relative motion analysis basis.

2) Due to the instantaneous action and the collimation characteristic of the pulsed magnetic field after the pulsed magnetic field reaches the vicinity of the target spacecraft, the action of the pulsed magnetic field can be equivalent to the action of a constant magnetic field (with constant strength, position and direction) on the target spacecraft, and the control effect analysis can be carried out on the basis.

3) The transient force generated by the action of the pulse magnetic field on the target spacecraft can be equivalent to a speed increment effect, and the relative attitude control/absolute orbit maneuvering control design of the target spacecraft can be developed on the basis.

In one embodiment, the plasma collection device may extend annularly outwardly of the sheath, as shown in fig. 10, and is used to collect plasma in situ in a space environment.

In order to better test the pulse plasma torus emission device and simulate the physical environment influence of the space to a certain extent, the invention also provides a ground test device, as shown in fig. 11, the ground test device is used for ground test of generation and emission of a pulse plasma torus and comprises an external support frame 4, a pulse plasma torus emission device 2 and a pulse plasma torus emission device support frame, wherein the pulse plasma torus emission device 2 is used for generating and emitting the pulse plasma torus and comprises an inner shaft, an outer shaft, an inner shaft electromagnet, an outer shaft electromagnet, a high-energy capacitor and a plasma injection port, the inner shaft and the outer shaft are coaxial two sleeves, the inner shaft electromagnet is arranged on the inner wall of the inner shaft, and the outer shaft electromagnet is arranged on the outer wall of the outer shaft.

The external support frame 4 consists of a square acrylic vacuum cover and a slide rail, and a partition plate is arranged inside the external support frame and used for supporting the pulse plasma ring emission device; pulse plasma ring emitter support frame comprises electro-magnet mount, copper ring support frame 3 and copper ring draw-in groove 5, the copper ring support frame is used for fixed outer axle, the copper ring draw-in groove is fixed interior axle electro-magnet mount and interior axle and outer axle, and it has the round hole to open its bottom can be used to point discharge with ionization neutral gas.

The technical features of the above embodiments can be arbitrarily combined, and for the sake of brevity, all possible combinations of the technical features in the above embodiments are not described, but should be considered as the scope of the present specification as long as there is no contradiction between the combinations of the technical features.

The above-mentioned embodiments only express several embodiments of the present application, and the description thereof is more specific and detailed, but not construed as limiting the scope of the invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the concept of the present application, which falls within the scope of protection of the present application. Therefore, the protection scope of the present patent shall be subject to the appended claims.