Coaxial pulse plasma thruster

Abstract

The invention provides a coaxial pulse plasma thruster, and relates to the technical field of spacecraft propulsion, and the thruster comprises an insulating housing, the front end face of the insulating housing is provided with a discharge port communicated with a cavity of the insulating housing, and the rear end face is provided with an anode mounting hole; the cathode is fixedly arranged on the insulating shell; a spark plug connected to the cathode; the working medium is arranged in the cavity of the insulating shell and clamped between the inner wall of the cavity of the insulating shell and the cathode, and an insertion hole extending in the axial direction of the insulating shell is formed in the working medium; the anode penetrates through the anode mounting hole of the insulating shell and is inserted into the jack of the working medium; the displacement mechanism comprises a mounting seat and an axial push-pull assembly, the axial push-pull assembly is mounted on the mounting seat, the anode is mounted on the axial push-pull assembly, and the axial push-pull assembly is used for driving the anode to advance or retreat relative to the insulating shell in the axial direction of the insulating shell when the insulating shell is fixed. According to the coaxial pulse plasma thruster, the element impulse can be adjusted in a wide range, and the working stability and reliability of the power supply processing unit are kept.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft propulsion technology, in particular to a coaxial pulsed plasma thruster. Background Art

[0002] With the continuous advancement of space technology, the application of microsatellites and their constellations is becoming increasingly widespread, particularly in fields such as communications, remote sensing, and space science missions. Microsatellites are favored for their light weight and compact size, but this also places higher demands on their propulsion systems. An efficient propulsion system is crucial for orbit adjustment, attitude control, and mission execution.

[0003] Electric propulsion systems, due to their high specific impulse, are ideal for microsatellite propulsion. In particular, coaxial pulsed plasma thrusters, as an application of electric propulsion technology, offer a compact structure and a high thrust-to-power ratio, making them particularly suitable for efficient operation under low-power conditions. A coaxial pulsed plasma thruster primarily consists of an anode, a working fluid, a cathode, an insulating housing, and a spark plug. Its operating principle is as follows: a high-voltage power supply is connected between the cathode and anode leads, along with a parallel energy storage capacitor. Subsequently, an external circuit controls the discharge between the inner and outer electrodes of the spark plug, generating sparks. These sparks cause an arc discharge between the cathode and anode, instantly releasing the energy stored in the energy storage capacitor, typically lasting from a few microseconds to tens of microseconds. During this process, the arc ablates the inner wall of the working fluid, vaporizing and ionizing it. Through the electrothermal effect, the working fluid is heated within the cavity and ejected at high speed along the thruster's axis, generating impulse.

[0004] Despite the numerous advantages of coaxial pulsed plasma thrusters, current coaxial pulsed plasma technology relies on a solid working fluid, making it impossible to control the generated impulse during operation by adjusting the working fluid flow rate. Therefore, given a fixed discharge configuration, the thruster's output impulse can only be controlled by adjusting the discharge voltage. However, coaxial pulsed plasma thrusters operate at a high voltage, and achieving wide-range voltage regulation would increase the size of the thruster's power processing unit, thereby reducing the thruster's reliability during orbital operation. Therefore, achieving wide-range regulation of the impulse in coaxial pulsed plasma thrusters is difficult.

[0005] How to achieve wide range meta-impulse regulation of the thruster without increasing the complexity of the power processing unit has become an urgent problem to be solved. Summary of the Invention

[0006] The object of the present invention is to provide a coaxial pulsed plasma thruster, which can adjust the impulse within a wide range and maintain the stability and reliability of the power processing unit during operation.

[0007] To achieve the above objectives, the embodiments of the present invention adopt the following technical solutions: An embodiment of the present invention provides a coaxial pulsed plasma thruster, comprising: An insulating shell having a cavity, wherein an axial front end face thereof is provided with a discharge port communicating with the cavity, and an axial rear end face thereof is provided with an anode mounting hole; a cathode fixedly mounted on the axial front end surface of the insulating shell; a spark plug, the outer electrode of which is connected to the cathode; A working medium is provided in the cavity of the insulating shell and is clamped between the inner wall of the cavity of the insulating shell and the cathode, and a socket extending along the axial direction of the insulating shell is provided inside the working medium; an anode, passing through the anode mounting hole of the insulating shell and inserted into the working medium socket; And a displacement mechanism, including a mounting seat and an axial push-pull assembly, the axial push-pull assembly is mounted on the mounting seat, the anode is mounted on the axial push-pull assembly, and the axial push-pull assembly is used to drive the anode forward or backward along the axial direction of the insulating shell relative to the insulating shell when the insulating shell is fixed.

[0008] In an optional embodiment, the displacement mechanism is provided axially rearward of the insulating housing and includes: a first fixing seat and a second fixing seat, wherein the first fixing seat is located between the second fixing seat and the insulating shell; a slide rail, one end of which is fixedly connected to the first fixing base and the other end of which is fixedly connected to the second fixing base; a rotating motor, mounted on the second fixing seat with its output end facing the first fixing seat; A lead screw, one end of which is transmission-connected to the output end of the rotating motor and the other end of which is rotatably mounted on the first fixing seat, wherein the lead screw is externally transmission-connected to a lead screw nut; A translation stage, fixedly connected to the lead screw nut and axially slidably connected to the slide rail; a connecting rod, one end of which is fixedly connected to the translation stage and the other end of which is fixedly connected to the anode; The rotary motor can drive the lead screw to rotate, so that the translation platform can slide axially along the slide rail with the connecting rod, thereby axially pushing and pulling the anode.

[0009] In an optional embodiment, the slide rail includes a first slide rail and a second slide rail distributed on both sides of the lead screw.

[0010] In an optional embodiment, the connecting rod includes a first connecting rod and a second connecting rod distributed on both sides of the lead screw.

[0011] In an optional embodiment, the connecting rod is a ceramic stud, one end of which is screwed to the translation stage and the other end is screwed to the anode.

[0012] In an optional embodiment, the part of the anode inserted into the working substance is provided with a sharp cone structure for changing the direction of the electric arc.

[0013] In an optional embodiment, the insertion hole of the working substance penetrates the working substance along the axial direction of the insulating shell.

[0014] In an optional embodiment, the anode is in the shape of a cylinder.

[0015] In an optional embodiment, the cathode is a straight jet pipe or an expanding jet pipe.

[0016] In an optional embodiment, a cathode lead is fixedly connected to the cathode, an anode lead is fixedly connected to the anode, and an inner electrode lead of the spark plug is fixedly connected to the spark plug. The anode lead and the cathode lead are connected to the positive and negative poles of a high-voltage power supply respectively and are connected in parallel with an energy storage capacitor. The inner electrode lead of the spark plug and the cathode lead are connected to the output positive and negative poles of an ignition circuit respectively.

[0017] The embodiments of the present application can achieve the following beneficial effects: The coaxial pulse plasma thruster provided by the embodiments of the present application comprises an insulating shell, a cathode, a spark plug, a working substance, an anode and a displacement mechanism, wherein the cathode is fixed to the insulating shell, and the working substance is clamped between the insulating shell and the cathode. Compared with the working substance of the prior art thruster which is fixed between the anode and the cathode, in the use process of the present embodiment, the insulating shell is fixed, while the anode can be freely moved along the axial direction of the insulating shell through the displacement mechanism, so as to accurately adjust the length of the discharge channel and achieve the effect of wide-range adjustment of the specific impulse.

[0018] In the working process of the coaxial pulse plasma thruster, the discharge of the spark plug initiates the electric arc between the cathode and the anode, the electric arc propagates along the path between the cathode, the surface of the working substance and the anode, and this path is the discharge channel. The position of the anode determines the length of the discharge channel. In the present embodiment, the insulating shell is fixed, and when the anode is moved backward along the axial direction of the insulating shell through the displacement mechanism, the length of the discharge channel is increased, which is suitable for outputting large specific impulse and low specific impulse; when the anode is moved forward along the axial direction through the displacement mechanism, the length of the discharge channel is decreased, which is suitable for outputting small specific impulse and high specific impulse.

[0019] The structural design of the embodiment of the present invention can achieve a wide range of adjustment of the thruster impulse, thereby adjusting the thruster discharge mode according to different mission requirements (such as the need to save propellant or the need for a large impulse), and the structural design does not increase the complexity of the power processing unit. Its structure is compact and efficient, and maintains good stability. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0021] Figure 1 A schematic diagram of the overall structure of a coaxial pulsed plasma thruster provided in an embodiment of the present invention.

[0022] Icon: 1- cathode; 2- working fluid; 3- insulating shell; 4- anode; 5- first connecting rod; 6- first fixed seat; 7- first slide rail; 8- translation stage; 9- second fixed seat; 10- motor lead; 11- second slide rail; 12- lead screw; 13- second connecting rod; 14- anode lead; 15- spark plug; 16- spark plug inner electrode lead; 17- cathode lead. DETAILED DESCRIPTION

[0023] To make the objectives, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings herein can be arranged and designed in various different configurations.

[0024] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention as claimed, but rather merely represents selected embodiments of the present invention. All other embodiments derived by persons of ordinary skill in the art based on the embodiments of the present invention without creative effort shall fall within the scope of protection of the present invention.

[0025] It should be noted that like reference numerals and letters denote similar items in the drawings, and therefore, once an item is defined in one drawing, it does not require further definition or explanation in subsequent drawings.

[0026] In the description of the present invention, it should be noted that: Unless otherwise clearly indicated or implied to the contrary by context, the terms "set", "install", "connect" are to be construed broadly, for example, can be fixed connection, can also be detachable connection, or integrally connected; can be mechanical connection, can also be electrical connection; can be directly connected, can also be indirectly connected through an intermediate medium, can be internal communication of two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0027] The terms "front", "back", "axial", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship when the product of the application is usually placed, which is only for the convenience of describing the application and simplifying the description, and does not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the application.

[0028] The terms "first", "second", and the like are only used to distinguish the description, and do not indicate the total number, or the relative position in time and / or space, and cannot be understood as indicating or implying relative importance.

[0029] Some embodiments of the application will be described in detail below with reference to the accompanying drawings. The features of the following embodiments and the optional embodiments in the embodiments can be combined with each other without conflict.

[0030] The present embodiment provides a coaxial pulse plasma thruster, referring to Figure 1 The coaxial pulse plasma thruster includes an insulating shell 3, a cathode 1, a spark plug 15, a working medium 2, an anode 4 and a displacement mechanism. Specifically: the insulating shell 3 has a cavity, an exhaust port communicating with the cavity is arranged on the axial front end face thereof, and an anode mounting hole is arranged on the axial rear end face thereof. The cathode 1 is fixedly installed on the axial front end face of the insulating shell 3; the outer electrode of the spark plug 15 is connected to the cathode 1; the working medium 2 is arranged in the cavity of the insulating shell 3 and is clamped between the inner wall of the cavity of the insulating shell 3 and the cathode 1, and the working medium 2 has a insertion hole extending along the axial direction of the insulating shell 3. The anode 4 is inserted into the insertion hole of the working medium 2 through the anode mounting hole of the insulating shell 3. The displacement mechanism includes a mounting seat and an axial push-pull assembly, the axial push-pull assembly is installed on the mounting seat, the anode 4 is installed on the axial push-pull assembly, and the axial push-pull assembly is used to drive the anode 4 to advance or retreat along the axial direction of the insulating shell 3 relative to the insulating shell 3 when the insulating shell 3 is fixed.

[0031] In use, the fixing seat is fixedly connected to a fixing mechanism such as a satellite mounting plate by bolts or other means, such as Figure 1As shown, in this coaxial pulsed plasma thruster, a cathode lead 17 is fixedly connected to the cathode 1, an anode lead 14 is fixedly connected to the anode 4, and a spark plug inner electrode lead 16 is fixedly connected to the spark plug 15. Connection methods for each lead to the corresponding component include, but are not limited to, bolting or welding. Anode lead 14 and cathode lead 17 are respectively connected to the positive and negative poles of a high-voltage power supply and connected in parallel with an energy storage capacitor. Spark plug inner electrode lead 16 and cathode lead 17 are respectively connected to the positive and negative output poles of the ignition circuit. Under control of an external circuit, discharge between the inner and outer electrodes of spark plug 15 generates sparks. These sparks cause an arc discharge to form between cathode 1 and anode 4, instantly releasing the electrical energy in the energy storage capacitor, typically lasting from a few microseconds to tens of microseconds. During this process, the arc ablates the inner wall of the working medium 2, causing the working medium 2 to evaporate and ionize. Through the electrothermal effect, the working medium 2 is heated in the cavity of the insulating shell 3 and ejected at high speed from the discharge port on the axial front end face of the insulating shell 3 along the axial direction, generating impulse.

[0032] This embodiment can achieve at least the following beneficial effects: The coaxial pulsed plasma thruster provided in this embodiment includes an insulating shell 3, a cathode 1, a spark plug 15, a working fluid 2, an anode 4 and a displacement mechanism, wherein the cathode 1 is fixed on the insulating shell 3, and the working fluid 2 is clamped between the insulating shell 3 and the cathode 1. Compared with the thruster of the prior art in which the working fluid 2 is fixed between the anode 4 and the cathode 1, during use of this embodiment, the insulating shell 3 is fixed, and the anode 4 can be freely moved along the axial direction of the insulating shell 3 through the displacement mechanism to accurately adjust the length of the discharge channel, thereby achieving the effect of adjusting the elementary impulse over a wide range.

[0033] When the coaxial pulsed plasma thruster is operating, the spark plug 15 discharges and triggers an arc between the cathode 1 and the anode 4. The arc propagates along the path between the cathode 1, the surface of the working fluid 2, and the anode 4. This path is the "discharge channel", and the position of the anode 4 determines the length of the discharge channel. In this embodiment, the insulating shell 3 is fixed. When the displacement mechanism is used to adjust the anode 4 to move axially backward relative to the insulating shell, the discharge channel becomes longer, which is suitable for outputting large elementary impulse and low specific impulse. When the displacement mechanism is used to adjust the anode 4 to move axially forward, the discharge channel becomes shorter, which is suitable for outputting small elementary impulse and high specific impulse.

[0034] The structural design of this embodiment can achieve a wide range of adjustment of the thruster impulse, thereby adjusting the thruster discharge mode according to different mission requirements (such as the need to save propellant or the need for a large impulse), and this structural design does not increase the complexity of the power processing unit. Its structure is compact and efficient, and maintains good stability.

[0035] In this embodiment, the displacement mechanism has a variety of optional structures for selection. For example, in an optional embodiment, the displacement mechanism is arranged at the axial rear of the insulating shell 3, and specifically includes a first fixed seat 6, a second fixed seat 9, a rotating motor, a screw 12, a screw nut, a translation stage 8, at least one slide rail and at least one connecting rod; the first fixed seat 6 is located between the second fixed seat 9 and the insulating shell 3; one end of the slide rail is fixedly connected to the first fixed seat 6, and the other end is fixedly connected to the second fixed seat 9, and the fixing method includes but is not limited to threaded connection or clamping or other optional fixed connection methods; the rotating motor is installed The anode 4 is mounted on the second fixed seat 9 and its output end faces the first fixed seat 6; one end of the lead screw 12 is transmission-connected to the output end of the rotating motor, and the other end is rotationally mounted on the first fixed seat 6 (the rotation connection can be, but is not limited to, corresponding bearings to ensure smooth rotation), and the external transmission connection of the lead screw 12 is connected to the lead screw nut; the translation stage 8 is fixedly connected to the lead screw nut and axially slidably connected to the aforementioned slide rail; one end of the connecting rod is fixedly connected to the translation stage 8, and the other end is fixedly connected to the anode 4; the rotating motor can drive the lead screw 12 to rotate, so that the translation stage 8 slides axially along the slide rail with the connecting rod, thereby axially pushing and pulling the anode 4. The structure of this optional embodiment achieves precise control of the position of the anode 4 through the transmission of the rotating motor and the lead screw 12, improving the adjustment accuracy and reliability. The design of the slide rail ensures the stability of the anode 4 during movement and avoids discharge abnormalities caused by vibration or offset. The entire displacement mechanism has a simple structure, is easy to implement, and occupies a small space, making it more suitable for application scenarios of micro-satellites.

[0036] In this optional embodiment, a motor lead 10 is provided on the rotating motor for connecting to a controller or a computer to accurately control the displacement. The motor lead 10 can be connected to the second fixed seat 9 through an aviation plug connector. The rotating motor is preferably, but not limited to, a stepper motor that is easy to program and control. In addition, in this optional embodiment, in order to further increase the stability during translation, the above-mentioned slide rails optionally include a first slide rail 7 and a second slide rail 11 distributed on both sides of the screw 12, further ensuring the linearity of the anode 4 during movement, avoiding the tilting or jamming problems that may be caused by the single-rail design, and improving the working reliability of the entire displacement mechanism, especially in the case of long-term operation or high-frequency adjustment. Similarly, the connecting rods include a first connecting rod 5 and a second connecting rod 13 distributed on both sides of the screw 12. The symmetrically arranged connecting rods can evenly transmit force, reduce the problem of uneven stress that may occur during the movement of the anode 4, improve the smoothness and consistency of the anode movement, and further optimize the accuracy of the discharge channel length adjustment. In addition, optionally, the above-mentioned connecting rod is a ceramic stud, one end of which is threadedly connected to the translation stage 8 and the other end is threadedly connected to the anode 4. The ceramic material has good insulation properties and high temperature resistance, which can effectively prevent the risk of leakage or breakdown during high-voltage discharge. The threaded connection method is convenient for disassembly and maintenance, and provides reliable mechanical connection strength.

[0037] Those skilled in the art should be aware that the above only provides a specific structural arrangement of an optional implementation of the displacement mechanism. In the actual design process, the displacement mechanism can also be designed into other optional structures, including but not limited to using a fixed cylinder or an electric hydraulic cylinder on a fixed seat, the cylinder structure cooperates with the piston rod, and the anode 4 is fixedly connected to the free end of the piston rod to control the translation of the anode 4. The fixed seat is not necessarily provided on the axial rear side of the insulating shell 3, but can also be provided at the bottom, and a slide rail and a translation platform are provided on its upper surface, which is then connected to the anode 4 through a longitudinal rod, or other optional displacement mechanisms, as long as the above-mentioned function of pushing and pulling the anode 4 using the displacement mechanism can be achieved.

[0038] In addition, in this embodiment, in an optional implementation, the portion of the anode 4 inserted into the working medium 2 is provided with a pointed cone structure for changing the direction of the arc. In this optional implementation, when in use, the pointed cone structure can change the direction of the arc, which helps to improve the specific impulse and optimize the plasma injection efficiency.

[0039] In an optional implementation manner of this embodiment, the insertion hole of the working medium 2 passes through the working medium 2 along the axial direction of the insulating shell 3 to extend the length of the discharge channel as much as possible and increase the adjustment range.

[0040] In an optional implementation of this embodiment, the anode 4 is cylindrical, and the cylindrical anode 4 matches well with the socket of the working medium 2, which can achieve a stable coaxial structure and reduce energy loss during arc discharge. In addition, the cylindrical design is easy to process and install, and has high mechanical strength.

[0041] In an optional implementation manner of this embodiment, the cathode 1 is a straight nozzle or an expanded nozzle. The straight nozzle design is suitable for tasks requiring high specific impulse and can utilize propellant more efficiently; the expanded nozzle design is suitable for tasks requiring large impulse and can provide greater thrust output. The appropriate cathode structure can be selected according to different mission requirements to improve the applicability and flexibility of the thruster.

[0042] Finally, it should be noted that: this application does not impose any specific restrictions on the materials selected for the above-mentioned components in this embodiment, and only provides the following materials for reference and selection. Other materials can also be used for design during specific implementation: for the insulating shell 3, it can be optionally but not limited to being made of polyimide or polyetheretherketone; for the working fluid 2, it can be optionally but not limited to being made of polytetrafluoroethylene or other various non-conductive solid non-metallic materials; for the anode 4 and the cathode 1, it can be optionally but not limited to being made of brass or other various solid conductive metal materials.

[0043] The above embodiments and optional implementation methods in this specification are only used to illustrate the technical solutions of the present invention, rather than to limit them. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the above optional implementation methods, or replace some or all of the technical features therein by equivalents. These modifications or replacements do not deviate the essence of the corresponding technical solutions from the scope of the technical solutions of the embodiments of the present invention. In addition, it is emphasized again that the features of the embodiments and optional implementation methods in the embodiments in this specification can be combined with each other unless there is a conflict.

Claims

1. A coaxial pulsed plasma thruster, characterized in that: include: An insulating housing (3) having a cavity, wherein the axial front end surface thereof is provided with a discharge port communicating with the cavity, and the axial rear end surface thereof is provided with an anode mounting hole; A cathode (1) fixedly mounted on the axial front end surface of the insulating housing (3); a spark plug (15), the outer electrode of which is connected to the cathode (1); A working medium (2) is provided in the cavity of the insulating shell (3) and is clamped between the inner wall of the cavity of the insulating shell (3) and the cathode (1); a socket extending along the axial direction of the insulating shell (3) is provided inside the working medium (2); An anode (4) is inserted into the socket of the working medium (2) through the anode mounting hole of the insulating housing (3); And a displacement mechanism, comprising a mounting seat and an axial push-pull assembly, wherein the axial push-pull assembly is mounted on the mounting seat, and the anode (4) is mounted on the axial push-pull assembly, and the axial push-pull assembly is used to drive the anode (4) to advance or retreat relative to the insulating shell (3) along the axial direction of the insulating shell (3) when the insulating shell (3) is fixed.

2. The coaxial pulsed plasma thruster according to claim 1, characterized in that: The displacement mechanism is arranged axially rearward of the insulating housing (3) and comprises: a first fixing seat (6) and a second fixing seat (9), wherein the first fixing seat (6) is located between the second fixing seat (9) and the insulating housing (3); A slide rail, one end of which is fixedly connected to the first fixing seat (6) and the other end of which is fixedly connected to the second fixing seat (9); a rotating motor, mounted on the second fixing seat (9) with its output end facing the first fixing seat (6); A lead screw (12), one end of which is transmission-connected to the output end of the rotating motor and the other end of which is rotationally mounted on the first fixed seat (6); the lead screw (12) is externally transmission-connected to a lead screw nut; A translation stage (8) is fixedly connected to the lead screw nut and axially slidably connected to the slide rail; A connecting rod, one end of which is fixedly connected to the translation platform (8) and the other end of which is fixedly connected to the anode (4); The rotary motor can drive the lead screw (12) to rotate, so that the translation platform (8) slides axially along the slide rail with the connecting rod, thereby axially pushing and pulling the anode (4).

3. The coaxial pulsed plasma thruster according to claim 2, characterized in that: The slide rail comprises a first slide rail (7) and a second slide rail (11) distributed on both sides of the lead screw (12).

4. The coaxial pulsed plasma thruster according to claim 2, characterized in that: The connecting rod comprises a first connecting rod (5) and a second connecting rod (13) distributed on both sides of the lead screw (12).

5. The coaxial pulsed plasma thruster according to claim 2, characterized in that: The connecting rod is a ceramic stud, one end of which is threadedly connected to the translation stage (8) and the other end of which is threadedly connected to the anode (4).

6. The coaxial pulsed plasma thruster according to claim 1, characterized in that: The portion of the anode (4) inserted into the working medium (2) is provided with a pointed cone structure for changing the direction of the arc.

7. The coaxial pulsed plasma thruster according to claim 1, characterized in that: The insertion hole of the working medium (2) penetrates the working medium (2) along the axial direction of the insulating shell (3).

8. The coaxial pulsed plasma thruster according to claim 1, characterized in that: The anode (4) is cylindrical.

9. The coaxial pulsed plasma thruster according to claim 1, characterized in that: The cathode (1) is a straight nozzle or an expansion nozzle.

10. The coaxial pulsed plasma thruster according to claim 1, characterized in that: A cathode lead (17) is fixedly connected to the cathode (1), an anode lead (14) is fixedly connected to the anode (4), and a spark plug inner electrode lead (16) is fixedly connected to the inner electrode of the spark plug (15); The anode lead (14) and the cathode lead (17) are respectively connected to the positive and negative electrodes of the high-voltage power supply and are connected in parallel with the energy storage capacitor; The spark plug inner electrode lead (16) and the cathode lead (17) are respectively connected to the output positive and negative electrodes of the ignition circuit.

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