Vacuum arc pulse plasma thruster

Abstract

The application relates to the technical field of aerospace propulsion, and particularly discloses a vacuum arc pulse plasma thruster. The vacuum arc pulse plasma thruster comprises a vacuum arc ignition system and a pulse plasma acceleration system. The vacuum arc ignition system forms an arc to generate plasma based on high-voltage pulse discharge ablation of metal, and injects the plasma into the pulse plasma acceleration system; the pulse plasma acceleration system axially accelerates the plasma based on the Lorentz force generated by the internal formed orthogonal electromagnetic field, and the high-speed ejection of the plasma from the discharge channel forms a recoil force. The introduction of the pulse plasma propulsion acceleration mechanism promotes the efficient conversion of the capacitor energy storage into axial directional kinetic energy, and improves the thrust, specific impulse and energy conversion efficiency of the thruster.

Description

Technical Field

[0001] This invention relates to the field of aerospace propulsion technology, and in particular to a vacuum arc pulse plasma thruster. Background Technology

[0002] In recent years, microsatellite technology, especially CubeSat platforms, has experienced exponential growth in space science exploration and commercial space applications. Traditional chemical propulsion systems have significant technical limitations: specific impulse is generally limited to the 200-300s range, and complex fuel storage and supply systems are required. For modern CubeSat platforms with a volume of less than 12U (20×20×30cm³) and a dry weight of no more than 20kg, these systems are insufficient to meet mission requirements in terms of mass-to-volume ratio and thrust control accuracy (typically only at the millinewton level).

[0003] Vacuum arc thrusters (VAT) and microcathode arc thrusters (μ-CAT) represent the next generation of micro-propulsion systems. Their engineering progress is still constrained by two main issues: low pulse count (short lifespan) and low thrust. The short lifespan is primarily due to uneven cathode ablation and degradation of the insulating properties between the cathode and anode. Experimental studies show that concentrated ablation of cathode spots during arc discharge can reduce the effective working life of the thruster by more than 30%, and cause reliability risks such as thrust fluctuations. The low thrust is because the kinetic energy of metal atomic gases or ions mainly comes from the electric or aerodynamic forces experienced when escaping the solid; the electric field voltage on the metal surface is low, and the average axial velocity of the plasma is also low.

[0004] The above content is only used to help understand the technical solution of the present invention and does not represent an admission that the above content is prior art. Summary of the Invention

[0005] The main objective of this invention is to provide a vacuum arc pulse plasma thruster, which aims to solve the problems of low thrust, total impulse and energy efficiency of pulsed space thrusters in the prior art.

[0006] To achieve the above objectives, the present invention provides a vacuum arc pulsed plasma thruster, which includes: a vacuum arc ignition system and a pulsed plasma acceleration system; The vacuum arc ignition system includes components such as a first anode and cathode discharge channel, a pulse generation and control circuit, and a first support structure. The first anode and cathode discharge channel of the vacuum arc ignition system extends into or is adjacent to the second anode and cathode discharge channel of the pulsed plasma acceleration system, but the two are electrically isolated. The vacuum arc ignition system uses a pulse generation and control circuit to generate a high-voltage pulse discharge that ablates the cathode working medium to form an arc-generated plasma, which is then injected into the anode and cathode discharge channels of the pulse plasma acceleration system. The pulsed plasma acceleration system includes components such as a second anode and cathode discharge channel, an energy storage capacitor, a charging circuit, and a second support structure. It is used to axially accelerate the plasma based on the Lorentz force generated by the orthogonal electromagnetic field formed inside, and then eject it to generate thrust.

[0007] In one embodiment, the first anode and cathode discharge channel of the vacuum arc ignition system includes: a cathode working medium, an anode structure, and an insulating layer; The anode structure is located near the entrance of the second anode-cathode discharge channel of the pulsed plasma acceleration system, and the insulating layer is located between the anode structure and the cathode working medium and is in close contact. The anode structure is provided with a porous mesh shape, and the holes in the porous mesh shape can be circular, elliptical or polygonal, etc. The insulating layer is provided with the same shape as the anode structure, and the inner wall surface of its porous mesh is coated or plated with a thin film layer that can be broken down by a high voltage pulse. The vacuum arc ignition system is used to form an arc between the cathode working medium and the anode structure within a certain grid range of the anode structure and within a preset distance range around the grid range when a high-voltage pulse that breaks down the thin film layer of the porous grid inner wall of the insulating layer is received. The cathode working fluid can be cylindrical, and the anode structure and the insulating layer are matched with the cathode working fluid in a corresponding cross-sectional shape.

[0008] In one embodiment, the support structure of the vacuum arc ignition system includes: a spring, a limiter, and a fixed housing; One end of the spring is connected to the end of the cathode working medium away from the anode structure, and the other end of the spring is connected to the fixed housing. The limiter is located at the end of the anode structure away from the cathode working medium. The spring and the limiter are used to constrain the contact area of ​​the cathode working medium, the anode structure and the insulating layer at a preset discharge position. The spring is also used for advancing and supplying the cathode working medium.

[0009] In one embodiment, the vacuum arc ignition system further includes: a magnetic coil; The magnetic coil is disposed on the outer surface of the limiter and the fixed housing near the insulating layer; The magnetic coil is used to generate a preset magnetic field, which is used to control the trajectory of the electric arc.

[0010] In one embodiment, both the cathode working fluid and the anode structure are made of metallic materials with a melting point exceeding a preset value; The porous mesh shape of the anode structure is set as a porous structure that is uniformly distributed within the circumference.

[0011] In one embodiment, the second anode and cathode discharge channel includes a cathode plate, an anode plate, an isolation wall, and a support member; The energy storage capacitor is charged by the charging circuit; The cathode plate and the anode plate are respectively connected to the two poles of the energy storage capacitor, and the cathode plate and the anode plate are respectively disposed on both sides of the axis of the discharge channel of the vacuum arc ignition system. In one embodiment, the electric field formed by the cathode plate and the anode plate, and the self-induced magnetic field formed by the discharge current, form an orthogonal electromagnetic field.

[0012] The pulsed plasma acceleration system may also be equipped with: a permanent magnet component; The magnetic field generated by the permanent magnet assembly is perpendicular to the electric field direction between the cathode plate and the anode plate, as well as the axial direction of the discharge channel of the vacuum arc ignition system, and is the same as the direction of the initial self-induced magnetic field between the plates.

[0013] In one embodiment, the cathode plate, the anode plate, and the permanent magnet assembly form an orthogonal electromagnetic field.

[0014] In one embodiment, the pulsed plasma acceleration system further includes: an isolation wall; The pulsed plasma acceleration system confines the plasma through the isolation wall, preventing the plasma from flying laterally out of the discharge channel through the isolation wall.

[0015] In one embodiment, the pulsed plasma acceleration system further includes: a support member; The support member is used to fix the cathode plate, anode plate, and isolation wall; In one embodiment, the pulsed plasma acceleration system further includes: a connector; The pulsed plasma acceleration system is connected to the vacuum arc ignition system via the connector.

[0016] This invention proposes a vacuum arc pulsed plasma thruster. The vacuum arc pulsed plasma thruster includes a vacuum arc ignition system and a pulsed plasma acceleration system; the discharge channel of the vacuum arc ignition system is electrically isolated from the discharge channel of the pulsed plasma acceleration system; the vacuum arc ignition system is used to generate plasma by forming an arc discharge with a high-voltage pulse, and then injects the plasma into the pulsed plasma acceleration system; the pulsed plasma acceleration system is used to axially accelerate the plasma based on an internally formed orthogonal electromagnetic field, and then directionally eject it to generate thrust. The introduction of a pulsed plasma propulsion acceleration mode, by constructing a composite electromagnetic acceleration field, promotes the efficient transfer of plasma kinetic energy to axially directional kinetic energy, thereby improving the thrust specific impulse of the thruster. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the structure of the first embodiment of the vacuum arc pulse plasma thruster proposed in this invention; Figure 2 This is a schematic diagram of the anode structure and insulating layer of the vacuum arc ignition system in the second embodiment of the vacuum arc pulse plasma thruster proposed in this invention. Figure 3 This is a schematic diagram of the main structure of the second embodiment of the vacuum arc pulse plasma thruster proposed in this invention; Figure 4 This is a schematic diagram of the pulsed plasma acceleration system in the third embodiment of the vacuum arc pulsed plasma thruster proposed in this invention; Figure 5 This is a schematic diagram of the fixed connection structure in the third embodiment of the vacuum arc pulse plasma thruster proposed in this invention.

[0018] Explanation of reference numerals in the attached drawings: 1. Cathode working medium; 2. Anode structure; 3. Insulating layer; 4. Magnetic coil; 5. Spring; 6. Limiter; 7. Fixed housing; 8. Connector; 9. Cathode plate; 10. Anode plate; 11. Support; 12. Permanent magnet assembly; 13. Isolation wall; 14. Screw hole.

[0019] The realization of the objective, functional features and advantages of the present invention will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0020] It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

[0021] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0022] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indication will also change accordingly.

[0023] Furthermore, the use of terms such as "first" and "second" in this invention is for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of that feature. Additionally, the technical solutions of the various embodiments can be combined with each other, but only on the basis of being achievable by those skilled in the art. When the combination of technical solutions is contradictory or impossible to implement, such a combination of technical solutions should be considered non-existent and not within the scope of protection claimed by this invention.

[0024] Reference Figure 1 , Figure 1 This is a schematic diagram of the first embodiment of the vacuum arc pulse plasma thruster proposed in this invention. Based on Figure 1 The first embodiment of the vacuum arc pulse plasma thruster of the present invention is presented.

[0025] In this embodiment, the vacuum arc pulsed plasma thruster includes: a vacuum arc ignition system and a pulsed plasma acceleration system; the discharge channel of the vacuum arc ignition system is electrically isolated from the discharge channel of the pulsed plasma acceleration system; the vacuum arc ignition system and the pulsed plasma acceleration system are mechanically connected.

[0026] It should be noted that the vacuum arc ignition system generates plasma by forming an arc discharge from a high-voltage pulse generated by a pulse generation and control circuit, and injects the plasma into the pulsed plasma acceleration system; the pulsed plasma acceleration system can axially accelerate the plasma based on an internally formed orthogonal electromagnetic field and then eject it in a directional manner to generate thrust.

[0027] It should be understood that vacuum arc thrusters (VAT) and microcathode arc thrusters (μ-CAT) are based on the principle of vacuum arc discharge of metal electrodes in a vacuum environment, generating high-speed plasma jets by ablating the cathode material. Compared with traditional chemical propulsion systems, VAT or μ-CAT have significantly improved specific impulse, completely avoiding the need for gas storage by using a solid metal cathode, and the system dry weight can be controlled to several hundred grams with a volume not exceeding 1U. At the same time, μ-CAT can maintain efficient operation under low power conditions (1-100W), and its unique pulse operating mode can accurately output microNewton-level thrust (nanoNewton-second to microNewton-second range), adapting to the fine maneuvering requirements of CubeSats such as attitude control, orbit correction, and formation flying.

[0028] To further enhance the axial velocity of the metallic gas and plasma generated by VAT arc ablation, this embodiment introduces an electromagnetic acceleration mode using a pulsed plasma thruster (PPT). By constructing a composite electromagnetic acceleration field, the efficient conversion of plasma kinetic energy into axially oriented kinetic energy is facilitated, thereby improving the thruster's thrust, specific impulse, and energy efficiency. This embodiment employs a two-stage operating mode of VAT and PPT. The initial plasma is generated by the VAT discharge channel; the plasma then enters the acceleration channel of the PPT stage, where it is further ionized and accelerated under the influence of electric and magnetic fields.

[0029] In this embodiment, the vacuum arc ignition system includes components such as a first anode and cathode discharge channel, a pulse generation and control circuit, and a first support structure. Specifically, the first anode and cathode discharge channel of the vacuum arc ignition system may include: a cathode working medium 1, an anode structure 2, and an insulating layer 3; the anode structure 2 is disposed at the end of the insulating layer 3 away from the cathode working medium, and the insulating layer 3 is disposed between the anode structure and the cathode working medium 1.

[0030] It should be noted that the anode structure 2 has a porous mesh shape, and the insulating layer 3 has the same shape as the anode structure 2. A pulsed voltage is applied between the cathode working medium 1 and the anode structure 2 to generate an electric arc. Specifically, an electric arc is formed between the cathode working medium 1 and the anode structure 2 within a certain mesh range of the anode structure 2 and within a preset distance around the mesh range. The electric arc acts on the cathode working medium 1, causing it to ablate based on the porous mesh shape of the anode structure 2, generating plasma; the plasma then discharges through the discharge channel.

[0031] The vacuum arc ignition system first outputs a high-voltage pulse through the pulse generation and control circuit, which breaks down the conductive film in the insulating mesh between the cathode working medium and the mesh anode, forming an initial arc discharge between the electrodes. The extremely high temperature generated by the arc discharge acts on the cathode surface, causing local ablation of the cathode metal working medium, which is ionized into metal vapor and charged plasma by the arc energy.

[0032] It should be understood that the cathode working medium 1 serves as both the propellant and the discharge electrode, requiring continuous generation of metal vapor under the action of an electric arc (temperatures typically reaching thousands of degrees Celsius). Therefore, high-melting-point metal materials (such as Ti, Mo, W, etc.) can be selected, as their high thermal stability can effectively improve the system's service life. The anode uses a uniform mesh structure made of high-melting-point metal materials, and its pore distribution can be optimized to ensure uniform ablation of the cathode surface under vacuum conditions. The pores are uniformly distributed (e.g., circular, elliptical, polygonal, etc., with the pore diameter and spacing matching the discharge gap). Solid anodes tend to cause arc spots to concentrate in a certain area, while the pore spacing of the mesh structure allows each mesh hole to correspond to a potential discharge point on the cathode surface. Combined with the magnetic coil driving the arc rotation, the arc spots on the cathode surface can uniformly cover the entire discharge area, reducing localized concentrated ablation at the source and extending the cathode's lifespan.

[0033] Furthermore, the insulating layer adopts a geometric layout isomorphic to the anode and selects insulating materials with both high melting point and high hardness (such as boron nitride, alumina, zirconium oxide, silicon carbide, etc.). The inner wall surface of its porous grid is coated or plated with a thin film layer (such as metal thin film, carbon thin film or semiconductor ceramic layer) that can be broken down by high voltage pulse, so as to achieve reliable electrical isolation and breakdown between electrodes.

[0034] In practice, the high-voltage pulse first breaks down the thin film on the inner wall of the porous grid insulation layer between the cathode and the anode, forming an electric arc discharge. The high temperature of the electric arc causes local ablation and ionization of the high-melting-point metal working medium on the cathode surface, generating metal vapor and plasma.

[0035] In this embodiment, the anode structure is disposed at the end of the insulating layer away from the cathode working medium, and the insulating layer is disposed between the anode structure and the cathode working medium. The anode structure has a porous mesh shape, and the insulating layer has the same shape as the anode structure. The insulating layer is used to form an electric arc between the cathode working medium and the anode structure when a breakdown high-voltage pulse is received. The cathode working medium is used to undergo uniform ablation based on the porous mesh shape of the anode structure under the action of the electric arc, and discharge through the discharge channel. By adopting a planar porous anode structure, each channel can independently establish a discharge channel. These channels work alternately in an intermittent mode to ablate the cathode to suppress working medium accumulation and improve the thruster's service life. At the same time, it can avoid long-term scouring and sputtering of ceramics by metal atoms and ions in the electric arc environment. The introduction of a pulsed plasma propulsion acceleration mode promotes the efficient conversion of plasma kinetic energy into axially oriented kinetic energy by constructing a composite electromagnetic acceleration field, thereby improving the thrust specific impulse of the thruster.

[0036] Reference Figure 2 , Figure 2 This is a schematic diagram of the anode structure and insulating layer of the vacuum arc ignition system in the second embodiment of the vacuum arc pulse plasma thruster proposed in this invention. Based on the first embodiment of the vacuum arc pulse plasma thruster described above, a second embodiment of the vacuum arc pulse plasma thruster of this invention is proposed.

[0037] In this embodiment, the porous mesh shape of the anode structure is set as a fan-shaped structure uniformly distributed within the circumference. The mesh structure of the anode is completely consistent with the geometry of the insulating layer (for example, the insulating layer is also mesh-shaped, only the material is changed to insulating materials such as boron nitride or aluminum oxide). Specifically, a multi-layer fan-shaped structure with rotational symmetry distributed around the center of the circular anode structure can be adopted. Figure 2 As shown, the anode employs a double-layer fan-shaped grid structure. Specifically, the inner layer has six evenly distributed fan-shaped grids, while the outer layer has twelve correspondingly distributed fan-shaped grids, with a through-hole at its center. This structural design aims to ensure the uniformity of discharge on the cathode surface and promote efficient plasma generation.

[0038] Furthermore, the vacuum arc ignition system also includes: a spring 5, a limiter 6, and a fixed housing 7; one end of the spring 5 is connected to the end of the cathode working medium 1 away from the anode structure 2, the other end of the spring 5 is connected to the fixed housing 7, and the limiter 6 is disposed at one end of the anode structure 2.

[0039] It should be noted that the spring and the limiter can be used to constrain the contact area of ​​the cathode working fluid, the anode structure and the insulating layer at a preset discharge position.

[0040] It should be understood that the spring, limiter, and fixed housing work together to form a mechanical limiting system: through its own elastic tension, it tightly and precisely constrains the core components of the vacuum arc ignition system, such as the cathode working fluid, anode (mesh structure), and insulating layer (isomorphic with the anode), at the preset discharge position, preventing component displacement due to factors such as micro-vibrations in spacecraft orbit and arc impacts during thruster operation, thus ensuring the relative stability of each component. Simultaneously, the cathode working fluid, as a propellant, is continuously consumed by high-temperature ablation during arc discharge, causing its length to gradually decrease. The spring, with its elastic deformation capability, can continuously apply axial thrust to the cathode through its own contraction / extension after the cathode working fluid ablates, pushing the cathode working fluid slowly towards the anode, thereby dynamically compensating for the ablation loss and maintaining the preset discharge gap between the cathode and anode (this gap can be used to form a stable arc). Without the compensating effect of the spring, the gap would gradually increase with cathode ablation, eventually leading to failure of the discharge, premature thruster failure, and directly affecting service life. The limiter and fixed housing can both be made of high-strength plastics (such as PEEK) or ceramic insulating materials. By constraining the mechanical displacement of the components, the system simultaneously achieves integrated connection with the pulsed plasma acceleration system and self-supply of working fluid.

[0041] Reference Figure 3 , Figure 3 This is a front view schematic diagram of the second embodiment of the vacuum arc pulse plasma thruster proposed in this invention. The vacuum arc ignition system further includes a magnetic coil 4; the magnetic coil 4 is disposed on the outer surface of the limiter 6 and the fixed housing 7.

[0042] It should be noted that the preset magnetic field generated by the magnetic coil 4 is used to control the trajectory of the electric arc, thereby guiding the cathode working medium 1 to achieve uniform ablation.

[0043] It should be understood that the magnetic coils are closely arranged on the outer surface of the limiter and the fixed housing, which can generate a magnetic field when current is applied, causing the discharge arc to rotate and further improving the uniformity of the working fluid ablation.

[0044] Specifically, the working process of the vacuum arc ignition system is as follows: First, the high-voltage pulse breaks down the thin film of the insulating layer between the cathode and the anode, forming an arc discharge; the high temperature of the arc causes local ablation and ionization of the high-melting-point metal working medium on the cathode surface, generating metal vapor and plasma; at the same time, the magnetic field generated by the magnetic coil regulates the arc trajectory through the Lorentz force, realizing sweeping ablation of the cathode surface and significantly improving the uniformity of working medium ablation; the plasma forms a quasi-neutral beam under the confinement of the electromagnetic field, and after directional expansion, it is injected into the pulsed plasma acceleration system cavity to complete the arc discharge-plasma generation task.

[0045] In addition, the vacuum arc ignition system also includes a connector 8; the vacuum arc ignition system is connected to the pulsed plasma acceleration system through the connector 8.

[0046] In this embodiment, the thruster internally includes a spring, a limiter, and a fixed housing. The spring and the limiter constrain the contact area of ​​the cathode working fluid, the anode structure, and the insulating layer at a preset discharge position. By constraining the mechanical displacement of the components, the integrated connection with the pulsed plasma acceleration system and the self-supply function of the working fluid are simultaneously achieved. The vacuum arc ignition system also includes a magnetic coil, which is disposed on the outer surface of the limiter and the fixed housing. The magnetic coil can be used to generate a preset magnetic field, which is used to control the trajectory of the arc. The ablation process of the cathode working fluid 1 is controlled by the trajectory of the arc: the arc movement is regulated by the Lorentz force, so that it achieves sweeping ablation on the cathode surface, improving the ablation uniformity of the working fluid.

[0047] Reference Figure 4 , Figure 4 This is a schematic diagram of the pulsed plasma acceleration system in the third embodiment of the vacuum arc pulsed plasma thruster proposed in this invention. Based on the above embodiments, a third embodiment of the vacuum arc pulsed plasma thruster of this invention is proposed.

[0048] In this embodiment, the pulsed plasma acceleration system is mechanically connected to the vacuum arc ignition system described above. The pulsed plasma acceleration system includes components such as a second anode and cathode discharge channel, an energy storage capacitor, a charging circuit, and a second support structure. The second anode and cathode discharge channel of the pulsed plasma acceleration system includes a cathode plate 9, an anode plate 10, an isolation wall 13, and a support member 11. The cathode plate 9 and the anode plate 10 are respectively connected to the two poles of the energy storage capacitor (not shown in the figure). The cathode plate 9 and the anode plate 10 are respectively disposed on both sides of the axis of the discharge channel of the vacuum arc ignition system. The magnetic field generated by the permanent magnet 12 is perpendicular to the electric field direction between the cathode plate 9 and the anode plate 10, and is the same as the direction of the initial induced magnetic field between the plates.

[0049] VAT and μ-CAT also have relatively low specific impulse and thrust because the kinetic energy of metal atomic gases or ions mainly comes from the electric or aerodynamic forces they experience when escaping from the solid. The electric field voltage on the metal surface is not high, and the average axial velocity of the plasma is not high.

[0050] It should be noted that the pulsed plasma acceleration system employs a staged energy loading strategy, generating metal vapor and plasma through pulsed discharge, and then using an electromagnetic field to accelerate the plasma to generate thrust. The cathode and anode plates are made of high-melting-point metal materials (titanium, tungsten, copper, etc.); the permanent magnet assembly uses powerful permanent magnets capable of generating a transverse magnetic field of 0.1-1T.

[0051] It should be understood that during system operation, cathode plate 9 and anode plate 10 are connected to the energy storage capacitor. The energy storage capacitor is first fully charged (to 100V~2000V), creating an electric field between the electrodes, orthogonal to the transverse magnetic field generated by the permanent magnet. When the plasma and metal vapor generated by the aforementioned vacuum arc ignition system enter the electrode space, they trigger capacitor discharge, generating an arc and forming a self-induced magnetic field. Initially, the self-induced magnetic field is aligned with the permanent magnetic field. Electrons and ions undergo gyratory and directional acceleration within the electric and magnetic fields. The metal vapor and plasma entering the discharge channel are further ionized and accelerated. During this process, the electric field maintained by the capacitor, the magnetic field generated by the permanent magnet, and the superimposed self-induced magnetic field produce a combined acceleration effect on the plasma through the E×B drift mechanism, efficiently converting plasma kinetic energy into axial kinetic energy, ultimately increasing the particle beam velocity.

[0052] Furthermore, the pulsed plasma acceleration system also includes a support member 11. (Refer to...) Figure 5 , Figure 5 This is a schematic diagram of the fixed connection structure in the third embodiment of the vacuum arc pulse plasma thruster proposed in this invention.

[0053] The pulsed plasma acceleration system is connected to the vacuum arc ignition system via the connector 8. Specifically, the support member 11 is provided with at least four screw holes 14, through which the support member 11 securely connects the pulsed plasma acceleration system and the vacuum arc ignition system.

[0054] The fixed housing 7 is made of polyetheretherketone (PEEK) or other insulating materials such as plastics and ceramics, and the components are precisely assembled with the vacuum arc ignition system through the fixing screw holes.

[0055] In this embodiment, the pulsed plasma acceleration system includes components such as a second anode and cathode discharge channel, an energy storage capacitor, a charging circuit, and a second support structure. The second anode and cathode discharge channel of the pulsed plasma acceleration system includes a cathode plate, an anode plate, an isolation wall, a support component, and a permanent magnet assembly. The cathode plate and the anode plate are respectively connected to the two poles of the energy storage capacitor, and are respectively disposed on both sides of the axis of the discharge channel of the vacuum arc ignition system. The magnetic field generated by the permanent magnet is perpendicular to both the electric field direction between the cathode plate and the anode plate and the axial direction of the discharge channel of the vacuum arc ignition system, and is the same as the direction of the initial induced magnetic field between the plates. A pulsed plasma propulsion (PPT) acceleration mode is introduced into the VAT to further increase the plasma ionization rate. A composite electromagnetic acceleration field is constructed through an E×B drift mechanism, promoting the efficient migration of plasma kinetic energy towards axially oriented kinetic energy, achieving synergistic optimization of plasma density and velocity parameters. The PPT electromagnetic field is used to further ionize the metal vapor, increasing the ionization rate and the number of charged particles. At the same time, the plasma density was increased, and a powerful orthogonal electromagnetic field was used to accelerate ions and electrons, which improved both thrust specific impulse and energy efficiency.

[0056] It should be noted that, in this document, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or system that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or system. Unless otherwise specified, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or system that includes that element.

[0057] The above are merely preferred embodiments of the present invention and do not limit the scope of the patent. Any equivalent structural or procedural transformations made based on the description and drawings of the present invention, or direct or indirect applications in other related technical fields, are similarly included within the scope of patent protection of the present invention.

Claims

1. A vacuum arc pulse plasma thruster, characterized in that, The vacuum arc pulsed plasma thruster includes: a vacuum arc ignition system and a pulsed plasma acceleration system; The vacuum arc ignition system includes a first anode and cathode discharge channel, a pulse generation and control circuit, and a first support structure. The first anode and cathode discharge channel of the vacuum arc ignition system extends into or is adjacent to the second anode and cathode discharge channel of the pulsed plasma acceleration system, but the two are electrically isolated. The vacuum arc ignition system uses a pulse generation and control circuit to generate a high-voltage pulse discharge that ablates the cathode working medium to form an arc-generated plasma, which is then injected into the anode and cathode discharge channels of the pulse plasma acceleration system. The pulsed plasma acceleration system includes a second anode and cathode discharge channel, a charging circuit, an energy storage capacitor, and a second support structure. It is used to axially accelerate the plasma based on the Lorentz force generated by the orthogonal electromagnetic field formed inside, and then eject it to generate thrust.

2. The vacuum arc pulse plasma thruster as described in claim 1, characterized in that, The first cathode and anode discharge channel of the vacuum arc ignition system includes: a cathode working medium, an anode structure, and an insulating layer; The anode structure is located near the entrance of the second anode-cathode discharge channel of the pulsed plasma acceleration system, and the insulating layer is located between the anode structure and the cathode working medium and is in close contact. The anode structure is provided with a porous mesh shape, and the holes in the porous mesh shape are circular, elliptical or polygonal. The insulating layer is provided with the same shape as the anode structure, and the inner wall surface of its porous mesh is coated or plated with a thin film layer that can be broken down by a high voltage pulse. The vacuum arc ignition system is used to form an arc between the cathode working medium and the anode structure within a certain grid range of the anode structure and within a preset distance range around the grid range when a high-voltage pulse that breaks down the thin film layer of the porous grid inner wall of the insulating layer is received. The cathode working fluid is configured as a cylinder or prism, and the anode structure and the insulating layer are matched with the cathode working fluid in a corresponding cross-sectional shape.

3. The vacuum arc pulse plasma thruster as described in claim 2, characterized in that, The support structure of the vacuum arc ignition system includes: a spring, a limiter, and a fixed housing; One end of the spring is connected to the end of the cathode working medium away from the anode structure, and the other end of the spring is connected to the fixed housing. The limiter is disposed at one end of the anode structure. The spring and the limiter are used to constrain the contact area of ​​the cathode working medium, the anode structure and the insulating layer at a preset discharge position. The spring is also used for advancing and supplying the cathode working medium.

4. The vacuum arc pulse plasma thruster as described in claim 3, characterized in that, The vacuum arc ignition system also includes: a magnetic coil; The magnetic coil is disposed on the outer surface of the limiter and the fixed housing near the insulating layer; The magnetic coil is used to generate a preset magnetic field, which is used to control the trajectory of the electric arc.

5. The vacuum arc pulse plasma thruster as described in claim 2, characterized in that, Both the cathode working fluid and the anode structure are made of metallic materials with a melting point exceeding the preset value.

6. The vacuum arc pulse plasma thruster as described in claim 1, characterized in that, The second cathode-cathode discharge channel includes a cathode plate, an anode plate, an isolation wall, and a support component; The energy storage capacitor is charged by the charging circuit; The cathode plate and the anode plate are respectively connected to the two poles of the energy storage capacitor, and the cathode plate and the anode plate are respectively disposed on both sides of the discharge channel of the vacuum arc ignition system.

7. The vacuum arc pulse plasma thruster as described in claim 6, characterized in that, The electric field formed by the cathode plate and the anode plate, and the self-induced magnetic field formed by the discharge current, form an orthogonal electromagnetic field.

8. The vacuum arc pulse plasma thruster as described in claim 7, characterized in that, The pulsed plasma acceleration system also includes: a permanent magnet assembly; The magnetic field generated by the permanent magnet assembly is perpendicular to the electric field direction between the cathode plate and the anode plate, as well as the axial direction of the discharge channel of the vacuum arc ignition system, and is the same as the direction of the initial self-induced magnetic field between the plates.

9. The vacuum arc pulse plasma thruster as described in claim 8, characterized in that, The pulsed plasma acceleration system confines the plasma through the isolation wall, preventing the plasma from flying laterally out of the discharge channel through the isolation wall.

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