Miniature radio frequency ion thruster feed system

Abstract

This invention discloses a gas supply system for a miniature radio frequency ion thruster, belonging to the field of electric propulsion technology, and relating to rarefied gas flow in plasma propulsion. By placing a gas distribution structure at the working fluid inlet in the ionization chamber and arranging the disc of the gas distribution structure coaxially with the ionization chamber, the propellant entering the ionization chamber is uniformly distributed after passing through the gas distribution structure, increasing the average density of the propellant in the ionization chamber. This results in higher absorption efficiency of radio frequency energy by the miniature radio frequency ion thruster, more uniform plasma distribution, and higher ion density in the plume, significantly improving the performance and operational stability of the miniature radio frequency ion thruster. Furthermore, the gas distribution structure is simple, with both the disc and cylinder being cylindrical, reducing manufacturing difficulty and increasing economic efficiency compared to existing technologies. The gas supply system for the miniature radio frequency ion thruster of this invention solves the problems of complex structure and low propellant density in existing gas supply structures.

Description

Technical Field

[0001] This invention belongs to the field of electric propulsion technology, and relates to rarefied gas flow in plasma propulsion, particularly to a gas supply system for a miniature radio frequency ion thruster. Background Technology

[0002] Electric propulsion technology plays a significant role in a wide variety of space missions. Among them, the micro radio frequency ion thruster system, with its high specific impulse, high precision, long lifespan and high efficiency, can significantly improve the payload rate of space platforms and is widely used in space missions with high total impulse requirements, such as orbit transfer and deep space exploration.

[0003] The main working process of the gas supply system for the miniature radio frequency ion thruster is as follows: (1) Gas flows from the high-pressure storage bottle of the propulsion device through the gas supply pipeline into the ionization chamber and diffuses in the ionization chamber; (2) The radio frequency antenna receives the electrical signal from the radio frequency power supply and excites an alternating electromagnetic field in the ionization chamber; (3) The alternating electromagnetic field excites plasma in the ionization chamber; (4) Ions are accelerated and ejected through the optical system to generate thrust. Under the premise of ensuring the uniformity of gas in the ionization chamber, the higher the overall density of gas in the ionization chamber, the better the ionization effect and the greater the thrust generated. However, the existing gas supply system for the miniature radio frequency ion thruster is not only complex in structure and has high manufacturing and operating costs, but also has a low gas density in the ionization chamber, which affects the overall performance of the miniature radio frequency ion thruster and cannot meet the increasingly demanding space mission requirements. Summary of the Invention

[0004] The purpose of this invention is to provide a novel gas supply system for a miniature radio frequency ion thruster, in order to solve the problems of existing miniature radio frequency ion thruster gas supply systems, which are not only complex in structure and have high manufacturing and operating costs, but also have low gas density in the ionization chamber, thus affecting the overall performance of the miniature radio frequency ion thruster and making it unable to meet the increasingly demanding space mission requirements.

[0005] To achieve the above objectives, the present invention provides the following solution:

[0006] This invention provides a gas supply system for a miniature radio frequency ion thruster, comprising:

[0007] A miniature radio frequency ion thruster includes an ionization chamber and a radio frequency antenna. The ionization chamber is provided with a working fluid inlet for the propellant to flow in. The radio frequency antenna is wound around the outer wall of the ionization chamber to generate an alternating electromagnetic field, so as to ionize the propellant to form ions and electrons and form plasma in the ionization chamber. The plasma is ejected from the ejection end of the ionization chamber to form a plume.

[0008] The gas distribution structure includes a disk and a plurality of cylinders disposed on one side of the disk. The axis of any one of the cylinders is parallel to the axis of the disk, and all the cylinders are evenly distributed on the disk. The gas distribution structure is disposed in the ionization chamber and at the working fluid inlet. The disk is coaxial with the ionization chamber, and any one of the cylinders faces the working fluid inlet. The gas distribution structure is used to uniformly distribute the propellant flowing into the ionization chamber so as to make the particle number density of the propellant uniform.

[0009] Optionally, the working fluid inlet is located at the center of the first end face of the ionization chamber, and the working fluid inlet is coaxial with the ionization chamber; all the cylinders of the gas distribution structure are connected to the first end face.

[0010] Optionally, all the cylinders are arranged in a circle around the center of the disk.

[0011] Optionally, 3 to 6 cylinders are arranged on the disk; the diameter of the disk is 34 to 38 mm and the axial length is 2 to 4 mm; the diameter of any one of the cylinders is 2 to 8 mm and the axial length is 2 to 5 mm; the center distance between any one of the cylinders and the disk is 6 to 15 mm.

[0012] Optionally, three cylinders are provided on the disk. The diameter of the disk is 34 mm and the axial length is 2 mm. The diameter of any one of the cylinders is 2 to 8 mm and the axial length is 3 mm. The center distance between any one of the cylinders and the center of the disk is 10 mm.

[0013] Optionally, four cylinders are provided on the disk.

[0014] Optionally, the gas distribution structure is integrally formed with the ionization chamber.

[0015] Optionally, a neutralizer is also included, disposed on the ionization chamber, for emitting electrons into the plume to neutralize the ions in the plume.

[0016] Optionally, it also includes an optical system disposed at the ejection end of the miniature radio frequency ion thruster, the optical system being capable of generating an electric field to accelerate the ejection velocity of the plasma.

[0017] Optionally, the optical system includes a screen grid and an acceleration grid, which are arranged sequentially along the jet direction of the plasma, and both the screen grid and the acceleration grid are connected to a gate circuit.

[0018] Optionally, it also includes a propellant supply source, the propellant supply source including a high-pressure storage bottle for storing the propellant, the high-pressure storage bottle for supplying the propellant to the propellant inlet.

[0019] The present invention achieves the following technical effects compared to the prior art:

[0020] The gas supply system for a miniature radio frequency ion thruster proposed in this invention, by placing a gas distribution structure at the working fluid inlet within the ionization chamber and arranging the disc of the gas distribution structure coaxially with the ionization chamber, ensures that the propellant entering the ionization chamber is uniformly distributed after passing through the gas distribution structure. This increases the average density of the propellant within the ionization chamber, thereby improving the absorption efficiency of radio frequency energy by the miniature radio frequency ion thruster, resulting in a more uniform plasma distribution and a higher ion density in the plume. This significantly enhances the performance and operational stability of the miniature radio frequency ion thruster. Furthermore, the gas distribution structure is simple, with both the disc and cylinder being cylindrical, reducing manufacturing difficulty and increasing economic efficiency compared to existing technologies. The gas supply system for a miniature radio frequency ion thruster proposed in this invention solves the problems of complex structures and low propellant density within the ionization chamber in existing gas supply systems. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 This is a schematic diagram of the overall structure of the gas supply system for the miniature radio frequency ion thruster disclosed in the embodiments of the present invention.

[0023] Figure 2 This is a schematic diagram of the gas distribution structure in the gas supply system of the miniature radio frequency ion thruster disclosed in the embodiments of the present invention.

[0024] Figure 3 for Figure 2 Top view of the central air distribution structure;

[0025] Figure 4 for Figure 2 Front view of the central air distribution structure;

[0026] Figure 5 This is a schematic diagram of the gas distribution structure two in the gas supply system of the miniature radio frequency ion thruster disclosed in the embodiment of the present invention;

[0027] Figure 6 for Figure 5 Top view of the second air distribution structure;

[0028] Figure 7 for Figure 5 Front view of the second air distribution structure;

[0029] Figure 8 This is a simulation cloud map of the number density of propellant particles in the gas supply system of the miniature radio frequency ion thruster disclosed in the embodiments of the present invention.

[0030] Figure 9 A schematic diagram of the gas flow path for the gas supply structure of an existing miniature radio frequency ion thruster.

[0031] Figure 10 for Figure 9 Axial schematic diagram of the gas supply structure of an existing micro radio frequency ion thruster in China;

[0032] Figure 11 for Figure 9 Simulation cloud map of the number density of propellant particles in the gas supply structure of an existing micro radio frequency ion thruster.

[0033] The attached figures are labeled as follows:

[0034] 100. Miniature radio frequency ion thruster gas supply system;

[0035] 1. High-pressure storage bottle; 2. Gas path control valve unit; 3. Miniature radio frequency ion thruster; 4. Ionization chamber; 41. Working fluid inlet; 5. Propellant; 6. Gas distribution structure; 61. Disk; 62. Cylinder; 7. Radio frequency antenna; 8. Propellant ions; 9. Electron; 10. Neutralizer; 11. Plume; 12. Optical system; 13. Existing miniature radio frequency ion thruster gas supply structure. Detailed Implementation

[0036] 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 some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0037] One of the objectives of this invention is to provide a novel gas supply system for a miniature radio frequency ion thruster, in order to solve the problem that existing gas supply systems for miniature radio frequency ion thrusters are not only complex in structure and have high manufacturing and operating costs, but also have low gas density in the ionization chamber, which affects the overall performance of the miniature radio frequency ion thruster and makes it unable to meet the increasingly demanding space mission requirements.

[0038] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0039] Example 1

[0040] like Figures 1 to 8 As shown, this embodiment provides a micro radio frequency ion thruster gas supply system 100, including a micro radio frequency ion thruster 3 and a gas distribution structure 6. The micro radio frequency ion thruster 3 includes an ionization chamber 4 and a radio frequency antenna 7. The ionization chamber 4 has a working fluid inlet 41 for the propellant 5 to flow into it. The radio frequency antenna 7 is wound around the outer wall of the ionization chamber 4 to form a coil, used to pass alternating current and generate an alternating electromagnetic field, so that the propellant 5 is ionized to form propellant ions 8 and electrons 9, and plasma is formed in the ionization chamber 4. The plasma is ejected from the nozzle of the ionization chamber 4. The ejected material forms a plume 11. The gas distribution structure 6 includes a disk 61 and multiple cylinders 62 disposed on one side of the disk 61. The axis of any cylinder 62 is parallel to the axis of the disk 61, and all cylinders 62 are evenly distributed on the disk 61. The gas distribution structure 6 is disposed inside the ionization chamber 4 and at the working fluid inlet 41. The disk 61 is coaxial with the ionization chamber 4, and any cylinder 62 faces the working fluid inlet 41. The gas distribution structure 6 is used to uniformly distribute the propellant 5 flowing into the ionization chamber 4, so as to make the particle number density of the propellant 5 in the ionization chamber 4 uniform. When the propellant 5 flows through each cylinder 62 of the gas distribution structure 6, the gas density distribution of the propellant 5 does not change abruptly because the curvature of each point on the side of the cylinder is the same, which helps to ensure the uniformity of the working fluid distribution. Setting both the disk 61 and the cylinder 62 as cylindrical structures not only makes the structure simple and easy to process and manufacture, but also ensures high reliability and good uniform distribution of working fluid.

[0041] In the above scheme, by setting the gas distribution structure 6 at the working fluid inlet 41 inside the ionization chamber 4 and arranging the disk 61 of the gas distribution structure 6 coaxially with the ionization chamber 4, the propellant 5 entering the ionization chamber 4 is evenly distributed after passing through the gas distribution structure 6, increasing the average density of the propellant in the ionization chamber 4. This results in higher absorption efficiency of radio frequency energy by the micro radio frequency ion thruster 3, more uniform plasma distribution, and higher ion density in the plume, significantly improving the performance and operational stability of the micro radio frequency ion thruster 3. Furthermore, the gas distribution structure 6 has a simple structure, is easy to manufacture, has high processing reliability, and is low in processing cost and economical. Therefore, the above-mentioned micro radio frequency ion thruster gas supply system 100 reduces the processing difficulty of the gas distribution structure 6, increases economic efficiency, and increases the average density of the propellant 5 in the ionization chamber 4, thereby improving the overall performance of the micro radio frequency ion thruster 3. This micro radio frequency ion thruster gas supply system 100 can solve the problems of complex structure and low propellant density in existing gas supply structures.

[0042] In this embodiment, the propellant 5 is generally a gas, such as xenon or krypton.

[0043] In this embodiment, the working fluid inlet 41 is preferably located at the center of the first end face of the ionization chamber 4, and the working fluid inlet 41 is coaxial with the ionization chamber 4. All cylinders 62 of the gas distribution structure 6 are connected to the first end face, that is, in the gas distribution structure 6, one end of all cylinders 62 is connected to one side of the disk 61, and the other end of all cylinders 62 is connected to the first end face of the ionization chamber 4. Based on this structure, after the propellant 5 flows into the ionization chamber 4, the gas distribution structure 6 redistributes the density of the propellant 5, which can ensure that the particle number density of the propellant 5 in the ionization chamber 4 is uniform, making the average density of the propellant 5 in the ionization chamber 4 higher, thereby helping the micro radio frequency ion thruster 3 to obtain better performance. The ejection end of the ionization chamber 4 is located at the second end of the ionization chamber 4, which, along with the aforementioned first end, are the two axial ends of the ionization chamber 4.

[0044] In this embodiment, all cylinders 62 are arranged in a circular pattern around the center of the disk 61, typically forming a single circular ring. Generally, 3 to 6 cylinders 62 can be arranged on the disk 61. The diameter of the disk 61 is 34 to 38 mm, and its axial length is 2 to 4 mm. The diameter of any cylinder 62 is 2 to 8 mm, and its axial length is 2 to 5 mm. The center-to-center distance between any cylinder 62 and the disk 61 (i.e., the distance between the center of the circular projection of the cylinder 62 onto the disk 61 and the center of the disk 61) is 6 to 15 mm. As one feasible solution, 3 cylinders 62 can be arranged on the disk 61, with a diameter of 34 mm and an axial length of 2 mm. The diameter of any cylinder 62 is 2 to 8 mm, and its axial length is 3 mm. The center-to-center distance between any cylinder 62 and the disk 61 is 10 mm. In addition, four, five, or six cylinders 62 can be set on the disk 61. Specifically, in each feasible scheme, the diameter and axial length of the disk 61, the diameter and axial length of any cylinder 62, and the center-axis distance between any cylinder 62 and the disk 61 can be adaptively adjusted and randomly combined according to different design requirements. To determine the specific structure and dimensions of the gas distribution structure 6, an initial design of the structure and dimensions of the gas distribution structure 6 was carried out based on the dimensions of the ionization chamber 4, and rarefied gas flow simulations were performed. In the experiment, the gas path control valve unit 2 controlled the outflow rate of the propellant 5 in the high-pressure storage bottle 1 to 0.7 sccm. sccm (Standard Cubic Centimeter per Minute) represents standard milliliters per minute. Therefore, the supply flow rate of the propellant 5 was set to 0.7 sccm in the simulation, and all simulation flow rates below are set to this value. The initial design of the structure and dimensions of the gas distribution structure 6 is shown in Table 1. Table 1 shows a gas distribution structure with three narrow, long cylinders, as exemplified by number 1. Figures 5-7 As shown, the air distribution structure with 4 narrow, elongated cylinders, taking number 9 as an example, is as follows: Figures 2-4As shown.

[0045] Table 1. Specific Structure and Dimensions of the Air Distribution Structure

[0046]

[0047]

[0048] Appendix: A refers to cylinder 62, and B refers to disk 61. Compared with disk 61, cylinder 62 is a long and narrow cylinder, while disk 61 is a relatively wide and flat cylinder. Due to space limitations, the codes have been replaced.

[0049] The rarefied gas flow simulations were performed on items 1 to 16 in Table 1. The density distribution of the rarefied gas at different locations within ionization chamber 4 was obtained after the simulations. The average density per cubic meter of the propellant 5 within ionization chamber 4, calculated by the simulation, is shown in Table 2.

[0050] Table 2 shows the average rarefied gas density obtained from rarefied gas flow simulation based on gas distribution structure 6 in Table 1.

[0051]

[0052] The simulation results of the average density of the propellant 5 inside the ionization chamber 4, obtained from Table 2, show that the maximum average density is found in gas distribution structures numbered 11, 9, and 1, respectively, while the minimum average density is found in gas distribution structure numbered 2. The difference between the maximum and minimum average density is 4.32E17 / m³. 3 The average density is 0.89%, which is the minimum. Although the average density of number 11 is the highest, the bottom of the gas distribution structure of numbers 10 and 11 (i.e., the side of disk 61 facing away from the working fluid inlet 41) is closer to the optical system 12 than the other numbers, occupying more space in the ionization chamber 4, which is not conducive to gas diffusion. Therefore, numbers 10 and 11 are not selected. After excluding number 11, the gas distribution structure with the second highest average density, number 9, can be selected as the optimal gas distribution structure.

[0053] Figure 8 The density cloud diagram of the rarefied gas in the four longitudinal sections of the ionization chamber is shown in the simulation results. Figure 8 As shown, Figure 8 The density distribution of rarefied gas at different locations within ionization chamber 4 is shown.

[0054] Figure 9 and Figure 10 For the gas supply structure 13 of the existing micro radio frequency ion thruster, a rarefied gas flow simulation was performed on the existing gas supply structure 13 of the micro radio frequency ion thruster, and the results were obtained. Figure 11 The longitudinal section of the rarefied gas particle number density cloud map is shown, as follows: Figure 9 and 10As shown, the gas supply structure 13 of the existing micro radio frequency ion thruster is a radial gas supply model. In the simulation experiment, except for the gas supply structure which is different from the gas distribution structure 6 of this scheme, all other parameters are the same as the gas distribution structure 6 of this scheme.

[0055] As shown in Table 1 above, after the gas distribution structure 6 is installed in the ionization chamber 4 of the micro radio frequency ion thruster 3, the average density of the propellant 5 in the ionization chamber 4 is approximately 4.8968 × 10⁻⁶. 19 / m 3 After installing the existing micro radio frequency ion thruster gas supply structure 13 in the ionization chamber 4 of the micro radio frequency ion thruster 3, the average particle number density is 4.3746 × 10⁻⁶. 19 / m 3 The gas distribution structure 6 in this scheme has an average particle number density that is approximately 5.222 × 10⁶ higher than that of the existing micro radio frequency ion thruster gas supply structure 13. 18 / m 3 That is, 11.9%. Through Figure 8 and Figure 11 The comparison shows that at the same location in ionization chamber 4, Figure 8 density ratio in Figure 11 The large number of particles in the propellant 5 within the ionization chamber 4 indicates that the gas distribution structure 6, while ensuring uniformity of the propellant 5, compensates for the low particle number density of the propellant 5 within the ionization chamber 4. Under the same radio frequency power, the plasma density is greater, resulting in a larger ion beam generated by the electric field acceleration of the optical system 12. Therefore, the gas distribution structure 6 in this design can effectively increase the gas particle number density within the ionization chamber 4.

[0056] In this embodiment, the gas distribution structure 6 and the ionization chamber 4 are made of the same material and are preferably integrally formed, serving as components of the micro radio frequency ion thruster 3. In the micro radio frequency ion thruster 3, the gas distribution structure 6 and the ionization chamber 4 are used to distribute the propellant 5 and ionize the propellant 5 to form plasma, respectively. The integral formation of the gas distribution structure 6 and the ionization chamber 4 not only ensures high processing reliability and economy but also provides high structural strength and good mechanical and thermodynamic properties. During operation of the micro radio frequency ion thruster 3, it can resist certain mechanical impacts and thermal stresses, ensuring stable operation. As a feasible option, the gas distribution structure 6 and the ionization chamber 4 can specifically be made of alumina.

[0057] In this embodiment, a neutralizer 10 is also included. The neutralizer 10 is disposed on the ionization chamber 4, and preferably disposed on the side wall of the ionization chamber 4 near the jet end. The neutralizer 10 is used to emit electrons into the plume 11 to neutralize the ions in the plume 11.

[0058] In this embodiment, an optical system 12 is also included. The optical system 12 is disposed at the ejection end of the miniature radio frequency ion thruster 3. The optical system 12 can generate an electric field to accelerate the ejection velocity of the plasma. As a preferred embodiment, the optical system 12 includes a screen grid and an acceleration grid, which are arranged sequentially along the ejection direction of the plasma. Both the screen grid and the acceleration grid are connected to a gate circuit, which is also connected to a DC power supply. The DC power supply supplies a DC voltage to the gate circuit, which can form an electric field between the screen grid and the acceleration grid. The plasma diffused to the vicinity of the screen grid of the optical system 12 is accelerated and ejected to form a beam (i.e., plume 11) and generate thrust. At the same time, the neutralizer 10 emits electrons to the plume 11 to neutralize the positive ions in the plume 11, making the plume 11 electrically neutral. This method can effectively improve the energy coupling efficiency of the radio frequency electromagnetic field and enhance the ionization intensity of the propellant in the ionization chamber.

[0059] In this embodiment, a propellant supply source is also included, comprising a high-pressure storage bottle 1 for storing the propellant 5. The high-pressure storage bottle 1 is used to supply the propellant 5 to the propellant inlet 41. Generally, the outlet end of the high-pressure storage bottle 1 is connected to the propellant inlet 41 via a gas path control valve unit 2. The gas path control valve unit 2 can specifically be a solenoid valve, which can control the supply and disconnection of the propellant 5 in a timely manner, and can also adjust the supply rate of the propellant 5 as needed to meet the working requirements within the ionization chamber 4.

[0060] The working principle and working process of the micro radio frequency ion thruster gas supply system 100 described in this embodiment will be explained in detail below.

[0061] The gas path control valve unit 2 is opened, and the propellant 5 in the high-pressure storage bottle 1 is introduced into the ionization chamber 4. After the propellant 5 enters the ionization chamber 4 through the propellant inlet 41, it immediately flows through the side walls of each cylinder 62 of the gas distribution structure 6. After the propellant 5 is diffused and distributed by the gas distribution structure 6, an alternating current is introduced into the radio frequency antenna 7 wrapped tightly against the ionization chamber 4. The alternating current generates an alternating electromagnetic field, which is used to bind electrons in the ionization chamber 4 and accelerate these electrons to reach the ionization energy of the propellant 5, so as to ionize the propellant 5 into propellant ions 8 and electrons 9, and further form plasma in the ionization chamber 4.

[0062] The ionization chamber 4 is connected to the optical system 12 at the jet end. After plasma is formed in the ionization chamber 4, the large electric field generated by the optical system 12 accelerates the ions and ejects them backward to form a plume 11.

[0063] The neutralizer 10 on the miniature radio frequency ion thruster 3 can emit electrons into the plume 11 to neutralize the plume 11, so that the ions and electrons in the plume 11 are neutralized and become the propellant again to prevent charged particles from escaping.

[0064] Therefore, it can be seen that the gas supply system 100 for the micro radio frequency ion thruster proposed in this technical solution has a simple and reasonable gas distribution structure. It is not only easy to manufacture, with high processing reliability, low processing cost and good economy, but also the propellant is more evenly distributed and its density is significantly improved compared with the existing gas supply structure under the action of the gas distribution structure. This results in a higher average density and more uniform distribution of the propellant in the ionization chamber, enabling the micro radio frequency ion thruster to obtain better performance. It solves the problems of complex structure and low density of propellant in the ionization chamber of the existing gas supply structure.

[0065] The above description is merely a preferred embodiment of this application and is not intended to limit this application. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A gas supply system for a miniature radio frequency ion thruster, characterized in that, include: A miniature radio frequency ion thruster (3) includes an ionization chamber (4) and a radio frequency antenna (7). The ionization chamber (4) is provided with a working fluid inlet (41) for the propellant (5) to flow into. The radio frequency antenna (7) is wound around the outer wall of the ionization chamber (4) to generate an alternating electromagnetic field so that the propellant (5) is ionized to form ions and electrons and plasma is formed in the ionization chamber (4). The plasma is ejected from the ejector end of the ionization chamber (4) to form a plume (11). The working fluid inlet (41) is opened at the center of the first end face of the ionization chamber (4) and the working fluid inlet (41) is coaxial with the ionization chamber (4). The gas distribution structure (6) includes a disk (61) and a plurality of cylinders (62) disposed on one side of the disk (61). The axis of any one of the cylinders (62) is parallel to the axis of the disk (61), and all the cylinders (62) are evenly distributed on the disk (61). The gas distribution structure (6) is disposed in the ionization chamber (4) and at the working fluid inlet (41). The disk (61) is coaxial with the ionization chamber (4), and any one of the cylinders (62) is parallel to the axis of the disk (61). The cylinders (62) are all facing the working fluid inlet (41). All the cylinders (62) of the gas distribution structure (6) are connected to the first end face. All the cylinders (62) are distributed in a circle on the disk (61) with the center of the disk (61) as the center. The gas distribution structure (6) is used to uniformly distribute the propellant (5) flowing into the ionization chamber (4) so ​​that the particle number density of the propellant (5) is uniform.

2. The gas supply system for the miniature radio frequency ion thruster according to claim 1, characterized in that, The disk (61) is provided with 3 to 6 cylinders (62); the diameter of the disk (61) is 34 to 38 mm and the axial length is 2 to 4 mm; the diameter of any one of the cylinders (62) is 2 to 8 mm and the axial length is 2 to 5 mm; the center distance between any one of the cylinders (62) and the disk (61) is 6 to 15 mm.

3. The gas supply system for the miniature radio frequency ion thruster according to claim 2, characterized in that, Three cylinders (62) are arranged on the disk (61). The diameter of the disk (61) is 34 mm and the axial length is 2 mm. The diameter of any one of the cylinders (62) is 2~8 mm and the axial length is 3 mm. The center distance between any one of the cylinders (62) and the disk (61) is 10 mm.

4. The gas supply system for the miniature radio frequency ion thruster according to claim 3, characterized in that, Four cylinders (62) are arranged on the disk (61).

5. The gas supply system for the miniature radio frequency ion thruster according to claim 1, characterized in that, The gas distribution structure (6) is integrally formed with the ionization chamber (4).

6. The gas supply system for the miniature radio frequency ion thruster according to any one of claims 1 to 5, characterized in that, It also includes a neutralizer (10) disposed on the ionization chamber (4) for emitting electrons into the plume (11) to neutralize the ions in the plume (11).

7. The gas supply system for the miniature radio frequency ion thruster according to any one of claims 1 to 5, characterized in that, It also includes an optical system (12) disposed at the ejection end of the micro radio frequency ion thruster (3), the optical system (12) being capable of generating an electric field to accelerate the ejection speed of the plasma.

8. The gas supply system for the miniature radio frequency ion thruster according to any one of claims 1 to 5, characterized in that, It also includes a propellant supply source, which includes a high-pressure storage bottle (1) for storing the propellant (5) and the high-pressure storage bottle (1) for supplying the propellant (5) to the propellant inlet (41).

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