Hall thruster gas-magnetic integrated structure and 3D printing manufacturing method thereof

Abstract

The invention relates to the technical field of Hall thrusters, and provides a Hall thruster gas-magnetic integrated structure and a 3D printing manufacturing method thereof.The Hall thruster gas-magnetic integrated structure comprises a gas inlet pipe, a sinking groove cover plate, a magnetic pole bottom plate and a discharging channel; a magnetic pole bottom plate sinking groove is formed in the lower surface of the magnetic pole bottom plate, the sinking groove cover plate covers the magnetic pole bottom plate sinking groove in a sealed mode to form a cavity, and the air inlet pipe penetrates through the middle of the sinking groove cover plate and is communicated with the cavity; the first air outlet through holes formed in the edge of the upper bottom of the magnetic pole bottom plate sinking groove are in one-to-one correspondence with the second air outlet through holes formed in the lower bottom of the discharging channel, and the corresponding first air outlet through holes are communicated with the corresponding second air outlet through holes. According to the Hall thruster, the air path is constructed in the magnetic circuit, the air inlet pipe is arranged in the middle, the axial symmetry inner cavity design and the axial symmetry air path formed by the air holes evenly distributed in the circumferential direction are beneficial to air supply homogenization, the air supply uniformity and the thruster performance are improved, universality is good, and the Hall thruster can be applied to Hall thrusters of different power levels.

Description

Technical Field

[0001] The present invention relates to the technical field of Hall thrusters, and in particular to a gas-magnetic integrated structure of a Hall thruster and a 3D printing manufacturing method thereof. Background Art

[0002] The Hall thruster is an electric thruster that uses orthogonal electromagnetic fields to ionize and accelerate atomic fluids and convert electrical energy into ion kinetic energy. It has the advantages of simple structure, high specific impulse, high efficiency, and high reliability. It is suitable for attitude control, position maintenance, deep space exploration and other tasks of various spacecraft. It is one of the most mature electric propulsion devices currently used in the world.

[0003] The existing gas supply structure reduces the effective space utilization. In the current design, the Hall thruster gas supply structure is usually implemented by a gas distributor component with small hole holding and circumferential buffering; a multi-layer homogenization chamber / gas path is constructed inside the structure, and the downstream gas outlet holes are used to increase the flow resistance to promote the circumferential flow of gas, thereby achieving gas homogenization and supply. In order to save the number of parts and simplify the thruster structure, an anode / gas distributor structure with an integrated gas path and circuit design is adopted, and a high anode potential is applied to the gas distributor, eliminating the traditional anode structure. However, the anode / gas distributor structure occupies a certain axial dimension in the discharge channel due to the presence of a certain height of the buffer chamber, and the increase in the number of buffer chambers due to the gas homogenization requirements will cause the problem of reduced effective space utilization of the discharge channel structure.

[0004] The existing structure has inherent non-uniform air intake defects and causes non-uniform air supply. The traditional annular anode / gas distributor can only use circumferential single-point air intake, and this air intake layout causes inherent air intake non-uniformity. Although the multi-stage buffer chamber can only reduce but not eliminate the circumferential non-uniformity of the gas. Therefore, a new structure is needed to achieve a uniform air supply path.

[0005] The existing gas supply structure has the problem of difficulty in improving its own structure. The existing gas distributor is a small hole air holding-circumferential buffer structure. In order to achieve homogenization, it is necessary to adopt a multi-level buffer cavity structure or reduce the aperture of the small hole. The former will cause the size to increase and further reduce the effective space utilization rate, and the latter will increase the difficulty of processing and cause the processing cost to rise. This has caused certain difficulties in improving the gas distributor itself.

[0006] The existing gas supply structure limits the structural design optimization of the Hall thruster. The Hall thruster has a compact structure, especially the low-power Hall thruster, which cannot provide enough space for the optimization of the anode / gas distributor structure under the demand for performance improvement. At the same time, the processing and assembly of a large number of small-sized structural components have the problem of mutual interference. At the same time, the existence of the gas distributor also contributes to part of the weight of the thruster. The increase in the size of the gas distributor caused by structural optimization is not conducive to the miniaturization of the thruster.

[0007] In summary, the traditional gas distributor has inherent defects of non-uniform gas supply, low effective space utilization, and structural improvements that restrict and limit the optimization of thruster structural design. In order to solve the above problems, a new Hall thruster structure is needed. On the basis of maintaining the basic functions of the thruster, the traditional gas distributor structure is eliminated, the gas supply structure components are simplified, and the constraints on the improvement of the gas supply structure and the optimization of the overall thruster structure design are eliminated. Summary of the invention

[0008] In view of the defects in the prior art, the purpose of the present invention is to provide a Hall thruster gas-magnetic integrated structure and a 3D printing production method thereof.

[0009] According to the present invention, a Hall thruster gas-magnetic integrated structure includes an air inlet pipe, a sink cover plate, a magnetic pole bottom plate and a discharge channel;

[0010] A magnetic pole bottom plate sink groove is provided on the lower surface of the magnetic pole bottom plate, the outer edge contour of the sink groove cover plate matches the magnetic pole bottom plate sink groove and is sealed and covered on the magnetic pole bottom plate sink groove to form a cavity between the magnetic pole bottom plate sink groove, and the air inlet pipe passes through the middle of the sink groove cover plate and is connected to the cavity;

[0011] The lower bottom surface of the discharge channel is connected to the upper bottom surface of the magnetic pole bottom plate, the upper bottom edge of the magnetic pole bottom plate groove is provided with a plurality of circumferentially evenly distributed first gas outlet holes, and the lower bottom of the discharge channel is provided with a plurality of circumferentially evenly distributed second gas outlet holes, the first gas outlet holes correspond to the second gas outlet holes one by one, and the corresponding first gas outlet holes are connected to the second gas outlet holes.

[0012] Preferably, a transition surface sealing structure is adopted between the first air outlet through hole and the second air outlet through hole, and the transition surface sealing structure adopts any of the following methods:

[0013] The structure of large and small circles connected;

[0014] Concave-convex connection structure;

[0015] Pinhole connection structure;

[0016] Blade plate connection structure.

[0017] Preferably, a sealing ring is provided between the first air outlet through hole and the second air outlet through hole.

[0018] Preferably, it further comprises a gas outlet regulating structure, wherein the gas outlet regulating structure covers the bottom inside the discharge channel, and the bottom surface of the gas outlet regulating structure is in contact with the bottom plane of the discharge channel.

[0019] Preferably, the air outlet regulating structure is a circular ring structure, including a bottom plate and a plurality of ribs arranged on the bottom plate in sequence along the radial direction of the bottom plate, wherein the plurality of ribs are respectively recorded as level 1 ribs, level 2 ribs, ..., level n ribs, wherein a level 1 chamber is formed between the inner side of the level 1 rib and the bottom plate, a level 2 sink groove is formed between the level 1 rib and the level 2 rib, ..., an level n sink groove is formed between the n-1 level rib and the level n rib, wherein a notch is provided on the level 1 rib, the level 1 chamber is opposite to the second air outlet hole, and air outlet holes are provided on the level n ribs and / or the level n sink grooves.

[0020] Preferably, the notches on two adjacent ribs are staggered.

[0021] Preferably, the outlet direction of the air outlet hole is any one of radial outlet, axial outlet, and rotation outlet, or any combination of multiple thereof;

[0022] The number of the air outlet holes can be set.

[0023] Preferably, the gas outlet regulating structure is bonded to the discharge channel.

[0024] Preferably, the trough cover plate is bonded or welded to the magnetic pole bottom plate.

[0025] Preferably, the lower bottom surface of the trough cover plate is coplanar with the lower bottom surface of the magnetic pole bottom plate.

[0026] According to a method for manufacturing the gas-magnetic integrated structure of the Hall thruster by 3D printing provided by the present invention, the three components of the air inlet pipe, the sink cover plate and the magnetic pole bottom plate are processed into an integrally formed structure.

[0027] Compared with the prior art, the present invention has the following beneficial effects:

[0028] 1. The present invention constructs a gas circuit in the magnetic circuit, eliminates the gas distributor in the traditional structure of the Hall thruster, releases the space occupied by the gas distributor, increases the effective space utilization rate of the discharge channel, and eliminates the space limitation of the gas distributor structure on the structural design. The gas circuit is built into the magnetic circuit. The axially symmetrical gas circuit formed by the central placement of the air inlet pipe, the axially symmetrical inner chamber design and the circumferentially uniformly distributed air holes is conducive to the homogenization of the air supply, improves the uniformity of the air supply and the thruster performance, has a wide range of applicability, and can be applied to Hall thrusters of different power levels.

[0029] 2. The present invention eliminates the physical structure of the gas distributor and constructs a cavity inside the magnetic circuit, which can effectively reduce the weight of the thruster and is conducive to the lightweight design of the Hall thruster.

[0030] 3. The present invention sets a gas outlet adjustment structure at the bottom of the discharge channel cavity as an anti-breakdown structure, which can reduce gas path breakdown by extending the gas path length from the anode to the magnetic pole bottom plate, and can also change the gas outlet mode and direction of the working gas, which is convenient for the flow field design in the discharge channel.

[0031] 4. The gas-magnetic integrated structure of the Hall thruster in the present invention can use 3D printing technology to print some components into an integrated shape, which can not only improve the precision of the product, but also improve the processing efficiency. At the same time, it also provides a new idea for the precision and miniaturization processing of the Hall thruster air supply structure, which needs to be further promoted. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0033] Figure 1 It is a structural schematic diagram of the present invention;

[0034] Figure 2 It is a schematic cross-sectional view of the structure of the large and small circles connected structure;

[0035] Figure 3 It is a schematic cross-sectional view of the structure of the concave-convex connection structure;

[0036] Figure 4 It is a schematic cross-sectional view of the pinhole connection structure;

[0037] Figure 5 It is a schematic cross-sectional view of the structure of the blade plate connection structure;

[0038] Figure 6 It is a schematic cross-sectional view of the structure when a sealing ring is provided between the first air outlet through hole and the second air outlet through hole;

[0039] Figure 7 It is a structural schematic diagram of the gas outlet adjustment structure.

[0040] The figure shows:

[0041] Intake pipe 1

[0042] Sink cover 2

[0043] Pole bottom plate 3

[0044] Magnetic pole bottom plate sink 31

[0045] Cavity 311

[0046] First air outlet hole 32

[0047] Discharge channel 4

[0048] Second air outlet hole 41

[0049] Large and small circle connected structure 51

[0050] Concave-convex connection structure 52

[0051] Discharge channel boss 521

[0052] Magnetic pole bottom plate groove 522

[0053] Pinhole connection structure 53

[0054] Pin Header 531

[0055] Blade plate connection structure 54

[0056] First annular blade 541

[0057] Second annular blade 542

[0058] The first annular sealing ring 551

[0059] Second annular sealing ring 552

[0060] Air outlet adjustment structure 6

[0061] Vent 601

[0062] Bottom plate 61

[0063] Level 1 Chamber 611

[0064] Level 1 Rib 612

[0065] Gap 613

[0066] 2nd level sink 621 DETAILED DESCRIPTION

[0067] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0068] Embodiment 1:

[0069] In order to solve the problem that the improvement of the air supply structure is limited by space, the present invention provides a Hall thruster gas-magnetic integrated structure, such as Figure 1As shown, it includes an air inlet pipe 1, a groove cover plate 2, a pole bottom plate 3 and a discharge channel 4. A pole bottom plate groove 31 is opened on the lower surface of the pole bottom plate 3. The outer edge contour of the pole bottom plate groove 31 is an axisymmetric structure. For example, the pole bottom plate groove 31 is a cylindrical structure. The outer edge contour of the groove cover plate 2 matches the pole bottom plate groove 31 and is sealed and covered on the pole bottom plate groove 31. The groove cover plate 2 is a thin plate. The thickness of the groove cover plate 2 is less than the depth of the pole bottom plate groove 31. After the groove cover plate 2 is embedded in the pole bottom plate groove 31, the lower bottom surface of the groove cover plate 2 is coplanar with the lower bottom surface of the pole bottom plate 3, and the two surfaces are flush, and a cavity 311 is formed between the groove cover plate 2 and the pole bottom plate groove 31. The groove cover plate 2 is preferably bonded or welded to the pole bottom plate 3 to ensure the airtightness of the cavity 311.

[0070] like Figure 1 As shown, a circular hole is opened in the middle of the trough cover plate 2, which is fixedly connected to the air inlet pipe 1. The air inlet pipe 1 passes through the middle of the trough cover plate 2 and is connected to the cavity 311. The external working medium gas can enter the cavity 311 through the air inlet pipe 1.

[0071] Furthermore, the lower bottom surface of the discharge channel 4 is connected to the upper bottom surface of the pole bottom plate 3, and the lower surface of the discharge channel 4 is tightly fitted with the upper surface of the pole bottom plate 3, and is pressed or bonded by external force, preferably by pressing. The upper bottom edge of the pole bottom plate trough 31 is provided with a plurality of circumferentially uniformly distributed first gas outlet holes 32, and the lower bottom of the discharge channel 4 is provided with a plurality of circumferentially uniformly distributed second gas outlet holes 41, and the first gas outlet holes 32 correspond to the second gas outlet holes 41 one by one, and the corresponding first gas outlet holes 32 are connected to the second gas outlet holes 41. The working gas enters the axisymmetric cavity 311 constructed by the trough cover plate 2 and the pole bottom plate trough 31 from the air inlet pipe 1, and flows and diffuses evenly toward the edge, and then passes through the first gas outlet holes 32 and the second gas outlet holes 41 in sequence into the discharge channel 4 to participate in the discharge. The present invention can ensure that the Hall thruster can simplify the gas supply structural components, reduce the overall weight of the thruster, and eliminate the space limitations of the traditional gas distributor and its improvement on the basis of realizing the basic functions of gas supply and homogenization.

[0072] In order to prevent air leakage, a transition surface sealing structure is used between the first air outlet hole 32 and the second air outlet hole 41. The transition surface sealing structure can adopt a large and small circle connecting structure 51, a concave and convex connecting structure 52, a pinhole connecting structure 53, a blade plate connecting structure 54, a sealing ring, etc. Specifically:

[0073] like Figure 2 As shown, the large-small circle connecting structure 51 adopts a connecting method in which the diameter of the first air outlet hole 32 is smaller than the diameter of the second air outlet hole 41 .

[0074] like Figure 3As shown, the concave-convex connection structure 52 is a magnetic pole bottom plate groove 522 on the upper surface of the magnetic pole bottom plate 3 and a discharge channel boss 521 on the lower surface of the discharge channel 4 that fits together; or the magnetic pole bottom plate boss on the upper surface of the magnetic pole bottom plate 3 and the discharge channel groove on the lower surface of the discharge channel 4 fit together.

[0075] like Figure 4 As shown, the pinhole connection structure 53 is to construct a pin-type protrusion 531 at each outlet of the first air outlet hole 32, and the pin-type protrusion is inserted into or pressed against the second air outlet hole 41;

[0076] like Figure 5 As shown, the blade plate connection structure 54 constructs a first annular blade 541 and a second annular blade 542 inside and outside the limiting circle of the first gas outlet hole 32 to abut against the lower surface of the discharge channel 4.

[0077] like Figure 6 As shown, a sealing ring is provided between the first gas outlet hole 32 and the second gas outlet hole 41. A first annular sealing ring 551 and a second annular sealing ring 552 are respectively placed on the inner and outer sides of the limiting circle where the first gas outlet hole 32 and the second gas outlet hole 41 are located, and the upper and lower surfaces of the two sealing rings are respectively attached to the lower surface of the discharge channel 4 and the upper surface of the magnetic pole bottom plate 3 to increase the sealing performance of the connection surface between the discharge channel 4 and the magnetic pole bottom plate 3.

[0078] It should be noted that, in order to enhance the sealing effect, sealing rings may be further added to the large and small circle connecting structure 51, the concave and convex connecting structure 52, the pinhole connecting structure 53, and the blade plate connecting structure 54 to improve the sealing performance.

[0079] The gas-magnetic integrated structure of the Hall thruster in the present invention also includes an air outlet regulating structure 6, which covers the bottom of the discharge channel 4. The air outlet regulating structure 6 is preferably bonded to the discharge channel 4, and the bottom surface of the air outlet regulating structure 6 is in contact with the bottom plane of the discharge channel 4.

[0080] Specifically, the air outlet regulating structure 6 is a circular ring structure, including a bottom plate 61 and a plurality of ribs and ridges arranged in sequence along the radial direction of the bottom plate 61, wherein the plurality of ribs and ridges are respectively recorded as level 1 rib 612, level 2 rib 622, ..., level n rib 6n2, wherein a level 1 chamber 611 is formed between the inner side of the level 1 rib 612 and the bottom plate 61, a level 2 sink 621 is formed between the level 1 rib 612 and the level 2 rib 622, ..., and a level n sink 6n1 is formed between the level n-1 rib 6n-12 and the level n rib 6n2, wherein each rib is provided with a plurality of notches 613, and the plurality of notches 613 are arranged at intervals on the ribs, and the notches 613 on two adjacent ribs are staggered to ensure that the stroke of the front and rear two levels of notches 613 is maximized, and the number and distribution position of the notches 613 on each level of the ribs are determined according to the design. The number n is also determined according to the design requirements. Figure 1 In the embodiment shown, n=1 is selected; inside the gas outlet regulating structure 6, the working medium gas flows out from the second gas outlet hole 41 at the bottom of the discharge channel 4, enters the first-level chamber 611, and enters the discharge channel 4 through the gas outlet hole 601 to participate in the discharge.

[0081] Furthermore, the first-level chamber 611 is opposite to the second air outlet hole 41, and the n-level ribs 6n2 and / or the n-level grooves 6n1 are provided with air outlet holes 601, and the air outlet directions of the air outlet holes 601 are any one or any combination of radial air outlet, axial air outlet, and rotary air outlet, and the number of air outlet holes 601 can be set.

[0082] Inside the gas outlet regulating structure 6, the working medium gas flows out from the second gas outlet hole 41 at the bottom of the discharge channel 4, enters the first-level chamber 611, and then passes through the notch 613 on the first-level rib 612 to enter the second-level trough 621, and then passes through the notch 613 on the second-level rib 622 to enter the third-level trough 631, until it reaches the last-level trough and enters the discharge channel 4 through the gas outlet hole 601 to participate in the discharge.

[0083] The present invention eliminates the gas distributor in the traditional structure of the Hall thruster, constructs a cavity 311 on the pole bottom plate 3, and constructs through holes at the bottom of the pole bottom plate 3 and the discharge channel 4, connects the inner chamber of the pole bottom plate 3 with the discharge channel 4, supplies working fluid into the discharge channel 4, and realizes the integrated design of the gas circuit and magnetic circuit. The working fluid gas enters the axisymmetric cavity 311 constructed by the trough cover plate 2 and the pole bottom plate trough 31 through the air inlet pipe 1, flows and diffuses evenly toward the edge, and then enters the discharge channel 4 from the first gas outlet through hole 32 and the second gas outlet through hole 41 to participate in the discharge. At the same time, on the one hand, the air inlet pipe 1 is centrally placed, the cavity 311 in the magnetic pole bottom plate 3 is an axisymmetric structure, and the air outlet holes at the bottom of the magnetic pole bottom plate 3 and the discharge channel 4 are evenly distributed circumferentially to form a complete circumferentially uniform air supply path; on the other hand, a transition surface sealing structure is constructed at the interface between the upper surface of the magnetic pole bottom plate 3 and the lower surface of the discharge channel 4 to ensure the sealing of the transition interface area; an anti-breakdown structure is added at the bottom of the discharge channel 4 cavity to extend the air path length from the anode to the magnetic pole bottom plate 3, and at the same time, the way and direction of the air outlet can be changed.

[0084] The present invention also provides a method for manufacturing a gas-magnetic integrated structure of a Hall thruster by using 3D printing. The three components of the air intake pipe 1, the sink groove cover plate 2, and the magnetic pole bottom plate 3 are processed into an integrated structure by 3D printing technology, so that the overall structure is more precise and the processing efficiency can also be improved.

[0085] Embodiment 2:

[0086] This embodiment is a preferred example of Embodiment 1, and in this embodiment, n=2.

[0087] In this embodiment, the air outlet holes 601 are a combination of radial air outlet and axial air outlet.

[0088] In this embodiment, the gas outlet regulating structure 6 covers the bottom of the discharge channel 4, and the bottom surface of the gas outlet regulating structure 6 is in contact with the bottom plane of the discharge channel 4, and they are connected by an adhesive material.

[0089] The working principle of the present invention is as follows:

[0090] The working medium gas enters the axisymmetric cavity 311 formed by the sink cover plate 2 and the magnetic pole bottom plate sink 31 from the air inlet pipe 1, and flows and diffuses evenly toward the edge, and then flows out from the first gas outlet hole 32 and the second gas outlet hole 41, enters the first-level chamber 611, and then enters the second-level sink 621 through the notch 613 on the first-level rib 612, and then enters the third-level sink 631 through the notch 613 on the second-level rib 622 until the last-level sink, and enters the discharge channel 4 through the gas outlet 601 to participate in the discharge. The present invention can ensure that the Hall thruster can simplify the gas supply structural components, reduce the overall weight of the thruster, and eliminate the space limitation of the traditional gas distributor and its improvement on the basis of realizing the basic functions of gas supply and homogenization.

[0091] In the description of the present application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0092] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A Hall thruster gas-magnetic integrated structure, characterized in that: It comprises an air intake pipe (1), a sink cover plate (2), a magnetic pole bottom plate (3) and a discharge channel (4); The lower surface of the magnetic pole bottom plate (3) is provided with a magnetic pole bottom plate sink groove (31); the outer edge profile of the sink groove cover plate (2) matches the magnetic pole bottom plate sink groove (31) and is sealed and covered on the magnetic pole bottom plate sink groove (31) to form a cavity (311) between the magnetic pole bottom plate sink groove (31); the air intake pipe (1) passes through the middle of the sink groove cover plate (2) and is in communication with the cavity (311); The lower bottom surface of the discharge channel (4) is connected to the upper bottom surface of the magnetic pole bottom plate (3); the upper bottom edge of the magnetic pole bottom plate sink groove (31) is provided with a plurality of first gas outlet holes (32) evenly distributed in the circumferential direction; the lower bottom of the discharge channel (4) is provided with a plurality of second gas outlet holes (41) evenly distributed in the circumferential direction; the first gas outlet holes (32) correspond to the second gas outlet holes (41) one by one, and the corresponding first gas outlet holes (32) are connected to the second gas outlet holes (41).

2. The gas-magnetic integrated structure of the Hall thruster according to claim 1, characterized in that: A transition surface sealing structure is adopted between the first air outlet through hole (32) and the second air outlet through hole (41), and the transition surface sealing structure adopts any one of the following methods: Large and small circle connected structure (51); Concave-convex connection structure (52); Pinhole connection structure (53); Blade plate connection structure (54).

3. The gas-magnetic integrated structure of the Hall thruster according to claim 1 or 2, characterized in that: A sealing ring is provided between the first air outlet through hole (32) and the second air outlet through hole (41).

4. The gas-magnetic integrated structure of the Hall thruster according to claim 1, characterized in that: It also comprises a gas outlet regulating structure (6), wherein the gas outlet regulating structure (6) covers the bottom of the discharge channel (4), and the bottom surface of the gas outlet regulating structure (6) is in contact with the bottom plane of the discharge channel (4).

5. The gas-magnetic integrated structure of the Hall thruster according to claim 4, characterized in that: The air outlet regulating structure (6) is a circular ring structure, comprising a bottom plate (61) and a plurality of ribs and ridges arranged on the bottom plate (61) in sequence and at intervals along the radial direction of the bottom plate (61), wherein the plurality of ribs and ridges are respectively recorded as first-level ribs (612), second-level ribs (622), ..., and n-level ribs (6n2), wherein a first-level chamber (611) is formed between the inner side of the first-level ribs (612) and the bottom plate (61), and the first-level ribs (612) and the second-level ribs (622) are spaced apart from each other. A second level of sink grooves (621) are formed between the first level ribs (622), ..., an n level of sink grooves (6n1) are formed between the n-1 level ribs (6(n-1)2) and the n level ribs (6n2), wherein a notch (613) is provided on the first level rib (612), the first level chamber (611) faces the second air outlet hole (41), and an air outlet hole (601) is provided on the n-level ribs (6n2) and / or the n-level sink grooves (6n1).

6. The gas-magnetic integrated structure of the Hall thruster according to claim 5, characterized in that: The notches (613) on two adjacent ribs are arranged in a staggered manner.

7. The gas-magnetic integrated structure of the Hall thruster according to claim 5, characterized in that: The outlet direction of the outlet hole (601) is radial outlet, axial outlet, rotation outlet, or any combination thereof; The number of the air outlet holes (601) can be set.

8. The gas-magnetic integrated structure of the Hall thruster according to claim 4, characterized in that: The gas outlet regulating structure (6) is bonded to the discharge channel (4).

9. The gas-magnetic integrated structure of the Hall thruster according to claim 1, characterized in that: The trough cover plate (2) is bonded or welded to the magnetic pole bottom plate (3); The lower bottom surface of the trough cover plate (2) is coplanar with the lower bottom surface of the magnetic pole bottom plate (3).

10. A method for manufacturing the gas-magnetic integrated structure of a Hall thruster according to any one of claims 1 to 9 by 3D printing, characterized in that: The three components of the air intake pipe (1), the sink cover plate (2) and the magnetic pole bottom plate (3) are processed into an integrally formed structure.

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