Double-stage anode layer Hall thruster

Abstract

The present invention provides a dual-stage anode layer Hall thruster, comprising a dual anode, a magnetic circuit, and a discharge chamber. The dual anode comprises a primary anode and a secondary anode, wherein the top of the secondary anode is provided with a chamfer, and the chamfered surface is arc-shaped. When the primary anode is made of a ferromagnetic metal material and the secondary anode is made of a non-magnetic material, the primary anode and the magnetic circuit cooperate to form a thruster magnetic field. When the secondary anode is made of a ferromagnetic metal material and the primary anode is made of a non-magnetic material, the secondary anode and the magnetic circuit cooperate to form a thruster magnetic field. The present invention utilizes a primary anode or a secondary anode in conjunction with a magnetic circuit to form a high-performance magnetic field configuration, thereby significantly improving the basic performance of the dual-stage anode layer Hall thruster, such as specific impulse and efficiency. Improvements to the secondary anode structure can significantly reduce the energy and number of electrons reaching the anode, thereby lowering anode temperature and improving thruster operating stability and reliability.

Description

Technical Field

[0001] The present invention relates to the field of space electric propulsion, and in particular to a double-stage anode layer Hall thruster for space applications. Background Art

[0002] In the field of space electric propulsion, Hall propulsion offers advantages such as a high thrust-to-power ratio, simple structure, and high reliability. It is widely used in low- and high-orbit satellites, as well as deep-space probes, to perform space missions such as drag compensation, on-orbit position maintenance, and orbit enhancement, and serves as the main propulsion force for deep-space probes. The continuous expansion of Hall electric propulsion applications is driving the development and innovation of related technologies. Dual-stage anode layer propulsion technology is a key approach to increasing the specific impulse of Hall propulsion.

[0003] Patent document US6640535B2 Figure 4 、Document IEPC-2005-145 Figure 1 、Document IEPC-2007-128 Figure 2 、Document IEPC-2005-141 Figure 7 et al. disclosed the basic structure and magnetic field configuration of a conventional two-stage anode layer Hall thruster, which mainly includes a primary anode, a secondary anode, a magnetic circuit and a discharge chamber. Among them, the primary anode and the secondary anode are made of non-magnetic metal materials (typically molybdenum, stainless steel, etc.), and the axial gradient of the magnetic induction intensity in the discharge channel usually does not exceed 0.2-0.3 mT / mm. The thruster's comprehensive performance such as specific impulse and efficiency is significantly lower than the design indicators. In addition, it was found during the development of the thruster that the secondary anode is prone to overheating, local melting and other problems, resulting in unstable operation of the thruster or even flameout, especially for thrusters with a power level of 10kW and above.

[0004] Patent document CN106837722B discloses a Hall thruster using a lightweight integrated anode. The anode partially replaces part of the function of the magnetic circuit to achieve a compact structure, small size and lightweight design effect, but the thruster magnetic field configuration does not change significantly.

[0005] The inventors believe that the existing technology has problems such as overheating and local melting of the thruster anode, and low thruster specific impulse, efficiency and other performance problems, and it is necessary to propose a new dual-stage anode layer Hall thruster. Summary of the Invention

[0006] In view of the defects in the prior art, the object of the present invention is to provide a dual-stage anode layer Hall thruster.

[0007] According to the present invention, a dual-stage anode layer Hall thruster is provided, comprising: dual anodes, a magnetic circuit, and a discharge chamber; the dual anodes include a primary anode and a secondary anode, the secondary anode having a chamfered top, the chamfered plane being arc-shaped; the discharge chamber includes an inner ring and an outer ring, a discharge channel being formed between the inner ring and the outer ring; when the primary anode is made of a ferromagnetic metal material and the secondary anode is made of a non-magnetic material, the primary anode and the magnetic circuit cooperate to form a thruster magnetic field; when the secondary anode is made of a ferromagnetic metal material and the primary anode is made of a non-magnetic material, the secondary anode and the magnetic circuit cooperate to form a thruster magnetic field.

[0008] Preferably, the ferromagnetic metal material includes soft magnetic alloy 1J22.

[0009] Preferably, the chamfered plane at the top of the secondary anode is parallel to the direction of the magnetic lines of force, and the arc angle is no greater than the top chamfer.

[0010] Preferably, when the material of the primary anode is a ferromagnetic metal material, the maximum magnetic induction intensity is inside the discharge channel, and the axial gradient of the magnetic field from the top of the primary anode to the maximum magnetic induction intensity is greater than 0.5 mT / mm.

[0011] Preferably, when the material of the secondary anode is a ferromagnetic metal material, the maximum magnetic induction intensity is outside the discharge channel, and the axial gradient of the magnetic field from the top of the primary anode to the maximum magnetic induction intensity is greater than 0.5 mT / mm.

[0012] Compared with the prior art, the present invention has the following beneficial effects:

[0013] 1. The dual-stage anode layer Hall thruster provided by the present invention can significantly improve the basic performance of existing dual-stage anode layer Hall thrusters, with specific impulse and efficiency increased by at least 10% to 30%, and help reduce the anode temperature, thereby improving the stability and reliability of the thruster operation.

[0014] 2. The present invention forms a high-performance magnetic field configuration through an improved design in which the first-level anode is made of a ferromagnetic metal material and the second-level anode is made of a non-magnetic material, or the first-level anode is made of a non-magnetic material and the second-level anode is made of a ferromagnetic metal material, which helps to improve the thruster's specific impulse, efficiency and other performance.

[0015] 3. The present invention helps to reduce the energy and number of electrons reaching the anode, helps to lower the anode temperature, and helps to improve the working stability and reliability of the thruster through improved designs such as providing a chamfer on the top of the secondary anode, the chamfered plane is arc-shaped, and the chamfered plane on the top of the secondary anode is parallel to the direction of the magnetic lines of force. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0017] Figure 1 This is a three-dimensional diagram of a dual-stage anode layer Hall thruster mainly embodied in the present invention;

[0018] Figure 2 This is a cross-sectional view of the cross section AA of the dual-stage anode layer Hall thruster mainly embodied in the present invention;

[0019] Figure 3 This is a schematic circuit connection diagram of the cross section BB of a dual-stage anode layer Hall thruster mainly embodied in the present invention;

[0020] Figure 4 This is a three-dimensional cross-sectional view of a dual anode structure mainly embodied in the present invention;

[0021] Figure 5 This is a cross-sectional view of the secondary anode structure design mainly embodied in the present invention;

[0022] Figure 6 The present invention mainly embodies the axial distribution of magnetic induction intensity of the double-stage anode layer Hall thruster;

[0023] Figure 7 The present invention mainly embodies the magnetic field configuration formed by the primary anode as a supplementary magnetic circuit;

[0024] Figure 8 The present invention mainly embodies the magnetic field configuration formed by the secondary anode as a supplementary magnetic circuit.

[0025] As shown in the figure:

[0026] Primary anode 1 Secondary anode 2 Secondary insulation pad 3

[0027] Anode gas pipe insulation sleeve 4 Anode gas pipe 5 First-level insulation pad 6

[0028] Primary anode terminal 7 Primary anode terminal insulation sleeve 8 Discharge chamber inner ring 9

[0029] Discharge chamber outer ring 10 Inner magnetic pole 11 Inner excitation coil 12

[0030] Inner excitation cylinder 13 Outer magnetic pole plate 14 Outer magnetic pole 15

[0031] External excitation coil 16 External excitation cylinder 17 Magnetic base plate 18

[0032] Protective screen 19 Secondary anode terminal insulation sleeve 20 Secondary anode terminal 21

[0033] Discharge power supply 101 Acceleration power supply 102 Cathode 103

[0034] Discharge channel 201 Secondary distribution cavity 202 Primary distribution cavity 203 DETAILED DESCRIPTION

[0035] The present invention will be described in detail below with reference to specific embodiments. The following examples 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 skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0036] Example 1

[0037] like Figure 1-4 As shown, a dual-stage anode layer Hall thruster provided according to the present invention includes: a dual anode, a magnetic circuit and a discharge chamber; the dual anode includes a primary anode 1 and a secondary anode 2, the top of the secondary anode 2 is provided with a chamfer, and the chamfered plane is arc-shaped; the discharge chamber includes a discharge chamber inner ring 9 and a discharge chamber outer ring 10, and a discharge channel 201 is formed between the discharge chamber inner ring 9 and the discharge chamber outer ring 10.

[0038] The dual anode further includes: a primary insulating pad 6, a secondary insulating pad 3, an anode gas pipe 5, an anode gas pipe insulating sleeve 4, a primary anode terminal 7, a primary anode terminal insulating sleeve 8, a secondary anode terminal 21, and a secondary anode terminal insulating sleeve 20. The primary anode 1 is insulated from the secondary anode 2 by the primary insulating pad 6, the secondary anode 2 is insulated from the protective screen 19 by the secondary insulating pad 3, the anode gas pipe 5 is insulated from the secondary anode 2 and the protective screen 19 by the anode gas pipe insulating sleeve 4, the primary anode terminal 7 is insulated from the secondary anode 2 and the protective screen 19 by the primary anode terminal insulating sleeve 8, and the secondary anode terminal 21 is insulated from the protective screen 19 by the secondary anode terminal insulating sleeve 20.

[0039] The primary anode 1 also functions as a gas distributor. The working gas enters the primary anode 1 through the anode gas pipe 5 and is evenly distributed in the discharge channel 201 through the primary distribution cavity 203 and the secondary distribution cavity 202 inside the primary anode 1 .

[0040] The primary anode 1 is connected to the positive electrode of the discharge power supply 101 through the primary anode terminal 7, and the secondary anode 2 is connected to the negative electrode of the discharge power supply 101 and the positive electrode of the acceleration power supply 102 through the secondary anode terminal 21. The discharge power supply 101 and the acceleration power supply 102 are connected in series, and the negative electrode of the acceleration power supply 102 is connected to the cathode 103.

[0041] The magnetic circuit includes an inner magnetic pole 11, an inner excitation coil 12, an inner excitation tube 13, an outer magnetic pole 15, an outer excitation coil 16, an outer excitation tube 17, an outer magnetic pole plate 14, and a magnetic base plate 18. The inner excitation coil 12 and the outer excitation coil 16 are connected to a constant-current DC power supply to generate a magnetic field. There are no fewer than four outer magnetic poles 15, no fewer than four outer excitation coils 16, and no fewer than four outer excitation tubes 17. The inner magnetic pole 11, outer magnetic pole 15, outer magnetic pole plate 14, and magnetic base plate 18 are all made of ferromagnetic metal, typically the soft magnetic alloy 1J22.

[0042] The discharge chamber includes an inner ring 9 and an outer ring 10, with a discharge channel 201 formed therebetween. The inner ring 9 and the outer ring 10 are made of graphite or non-magnetic metal, such as molybdenum or stainless steel.

[0043] When the primary anode 1 is made of a ferromagnetic metal and the secondary anode 2 is made of a non-magnetic material, the primary anode 1 and the magnetic circuit work together to form the thruster's magnetic field. This complements the magnetic circuit to create a high-performance magnetic field configuration, significantly improving the thruster's basic performance, such as specific impulse and efficiency.

[0044] Strong magnetic metal materials include soft magnetic alloy 1J22.

[0045] Non-magnetic materials include graphite or non-magnetic metals, and non-magnetic metals include molybdenum and stainless steel.

[0046] like Figure 5 As shown, the top of the secondary anode 2 is chamfered, with the chamfered surface forming an arc. The chamfered surface is parallel to the magnetic field lines, with an arc angle α no greater than the top chamfer angle θ. The structural design of the secondary anode 2, combined with the high-performance magnetic field configuration, significantly reduces the energy and number of electrons reaching the anode, lowering the temperature at the top of the secondary anode 2 and significantly improving the operational stability and reliability of the thruster.

[0047] When the material of the primary anode 1 is a ferromagnetic metal material, the maximum magnetic induction intensity is inside the discharge channel 201, and the axial gradient of the magnetic field from the top of the primary anode 1 to the maximum magnetic induction intensity is greater than 0.5 mT / mm.

[0048] This application can effectively solve the problems of overheating and local melting of the thruster anode. By improving the design of the magnetic circuit to form a high-performance magnetic field configuration, the thruster's specific impulse, efficiency and other performance can be improved.

[0049] The specific impulse of the double-stage anode layer Hall thruster provided in this application can be increased by 20% to 30%, up to 6000 to 8000s, and the efficiency can be increased by 10% to 20%, up to 60% to 70%.

[0050] like Figure 6 and 7 As shown, the chamfered plane of the top of the secondary anode 2 is parallel to the direction of the magnetic field line, the top chamfer angle θ is 19 degrees, and the arc angle α is 19 degrees. The maximum magnetic induction intensity of the thruster is at 1.7L inside the discharge channel 201. b Position, the axial gradient of the magnetic field between the top of the first-stage anode 1 and the maximum magnetic induction intensity is greater than 0.72mT / mm. b is the length of the discharge channel, 2L b is the discharge channel outlet position, 0L b It is the top position of the first-level anode.

[0051] Compared with the existing technology, the present application forms a high-performance magnetic field configuration through the combined action of the first-stage anode 1 and the magnetic circuit, which can significantly improve the basic performance of the two-stage anode layer Hall thruster, such as specific impulse and efficiency; combined with the structural improvement of the secondary anode 2, it can significantly reduce the energy and number of electrons reaching the anode, reduce the anode temperature, and improve the working stability and reliability of the thruster.

[0052] Example 2

[0053] like Figure 1-4 As shown, a dual-stage anode layer Hall thruster provided according to the present invention includes: a dual anode, a magnetic circuit and a discharge chamber; the dual anode includes a primary anode 1 and a secondary anode 2, the top of the secondary anode 2 is provided with a chamfer, and the chamfered plane is arc-shaped; the discharge chamber includes a discharge chamber inner ring 9 and a discharge chamber outer ring 10, and a discharge channel 201 is formed between the discharge chamber inner ring 9 and the discharge chamber outer ring 10.

[0054] The dual anode further includes: a primary insulating pad 6, a secondary insulating pad 3, an anode gas pipe 5, an anode gas pipe insulating sleeve 4, a primary anode terminal 7, a primary anode terminal insulating sleeve 8, a secondary anode terminal 21, and a secondary anode terminal insulating sleeve 20. The primary anode 1 is insulated from the secondary anode 2 by the primary insulating pad 6, the secondary anode 2 is insulated from the protective screen 19 by the secondary insulating pad 3, the anode gas pipe 5 is insulated from the secondary anode 2 and the protective screen 19 by the anode gas pipe insulating sleeve 4, the primary anode terminal 7 is insulated from the secondary anode 2 and the protective screen 19 by the primary anode terminal insulating sleeve 8, and the secondary anode terminal 21 is insulated from the protective screen 19 by the secondary anode terminal insulating sleeve 20.

[0055] The primary anode 1 also functions as a gas distributor. The working gas enters the primary anode 1 through the anode gas pipe 5 and is evenly distributed in the discharge channel 201 through the primary distribution cavity 203 and the secondary distribution cavity 202 inside the primary anode 1 .

[0056] The primary anode 1 is connected to the positive electrode of the discharge power supply 101 through the primary anode terminal 7, and the secondary anode 2 is connected to the negative electrode of the discharge power supply 101 and the positive electrode of the acceleration power supply 102 through the secondary anode terminal 21. The discharge power supply 101 and the acceleration power supply 102 are connected in series, and the negative electrode of the acceleration power supply 102 is connected to the cathode 103.

[0057] The magnetic circuit includes an inner magnetic pole 11, an inner excitation coil 12, an inner excitation tube 13, an outer magnetic pole 15, an outer excitation coil 16, an outer excitation tube 17, an outer magnetic pole plate 14, and a magnetic base plate 18. The inner excitation coil 12 and the outer excitation coil 16 are connected to a constant-current DC power supply to generate a magnetic field. There are no fewer than four outer magnetic poles 15, no fewer than four outer excitation coils 16, and no fewer than four outer excitation tubes 17. The inner magnetic pole 11, outer magnetic pole 15, outer magnetic pole plate 14, and magnetic base plate 18 are all made of ferromagnetic metal, typically the soft magnetic alloy 1J22.

[0058] The discharge chamber includes an inner ring 9 and an outer ring 10, with a discharge channel 201 formed therebetween. The inner ring 9 and the outer ring 10 are made of graphite or non-magnetic metal, such as molybdenum or stainless steel.

[0059] When the secondary anode 2 is made of a ferromagnetic metal and the primary anode 1 is made of a non-magnetic material, the secondary anode 2 and the magnetic circuit work together to form the thruster's magnetic field. This complements the magnetic circuit to create a high-performance magnetic field configuration, significantly improving fundamental thruster performance, such as specific impulse and efficiency.

[0060] Strong magnetic metal materials include soft magnetic alloy 1J22.

[0061] Non-magnetic materials include graphite or non-magnetic metals, and non-magnetic metals include molybdenum and stainless steel.

[0062] like Figure 5 As shown, the top of the secondary anode 2 is chamfered, with the chamfered surface forming an arc. The chamfered surface is parallel to the magnetic field lines, with an arc angle α no greater than the top chamfer angle θ. The structural design of the secondary anode 2, combined with the high-performance magnetic field configuration, significantly reduces the energy and number of electrons reaching the anode, lowering the temperature at the top of the secondary anode and significantly improving the operational stability and reliability of the thruster.

[0063] When the secondary anode 2 is made of a ferromagnetic metal material, the maximum magnetic induction intensity is outside the discharge channel 201, and the axial gradient of the magnetic field from the top of the primary anode 1 to the maximum magnetic induction intensity is greater than 0.5 mT / mm.

[0064] This application can effectively solve the problems of overheating and local melting of the thruster anode. By improving the design of the magnetic circuit to form a high-performance magnetic field configuration, the thruster's specific impulse, efficiency and other performance can be improved.

[0065] The specific impulse of the double-stage anode layer Hall thruster provided in this application can be increased by 20% to 30%, up to 6000 to 8000s, and the efficiency can be increased by 10% to 20%, up to 60% to 70%.

[0066] like Figure 6-8 As shown, the chamfered plane of the top of the secondary anode 2 is parallel to the direction of the magnetic field line, the chamfer angle θ is 28 degrees, and the arc angle α is 28 degrees. The maximum magnetic induction intensity of the thruster is 2.3L outside the discharge channel 201. b Position, the axial gradient of the magnetic field between the top of the secondary anode 2 and the maximum magnetic induction intensity is greater than 0.61mT / mm. b is the length of the discharge channel, 2L b is the discharge channel outlet position, 0L b It is the top position of the first-level anode.

[0067] Compared with the existing technology, the present invention forms a high-performance magnetic field configuration through the interaction of the secondary anode 2 and the magnetic circuit, which can significantly improve the basic performance of the dual-stage anode layer Hall thruster, such as specific impulse and efficiency; combined with the structural improvement of the secondary anode 2, it can significantly reduce the energy and number of electrons reaching the anode, reduce the anode temperature, and improve the working stability and reliability of the thruster.

[0068] In the description of this application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application.

[0069] The above describes specific embodiments of the present invention. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. The embodiments of this application and the features in the embodiments may be combined with each other in any manner unless there is a conflict.

Claims

1. A dual-stage anode layer Hall thruster, characterized in that: include: Double anode, magnetic circuit and discharge chamber; The dual anode comprises a primary anode (1) and a secondary anode (2), wherein the top of the secondary anode (2) is provided with a chamfer, and the plane of the chamfer is arc-shaped; The discharge chamber comprises a discharge chamber inner ring (9) and a discharge chamber outer ring (10), and a discharge channel (201) is formed between the discharge chamber inner ring (9) and the discharge chamber outer ring (10); When the material of the primary anode (1) is a ferromagnetic metal material, the material of the secondary anode (2) is a non-magnetic material, and the primary anode (1) and the magnetic circuit work together to form a thruster magnetic field; When the material of the secondary anode (2) is a ferromagnetic metal material, the material of the primary anode (1) is a non-magnetic material, and the secondary anode (2) and the magnetic circuit work together to form a thruster magnetic field.

2. The dual-stage anode layer Hall thruster according to claim 1, characterized in that: The ferromagnetic metal material includes the soft magnetic alloy 1J22.

3. The dual-stage anode layer Hall thruster according to claim 1, characterized in that: The chamfered plane at the top of the secondary anode (2) is parallel to the direction of the magnetic lines of force, and the arc angle is no greater than the chamfered angle at the top.

4. The dual-stage anode layer Hall thruster according to claim 1, characterized in that: When the material of the primary anode (1) is a ferromagnetic metal material, the maximum magnetic induction intensity is inside the discharge channel (201), and the axial gradient of the magnetic field between the top of the primary anode (1) and the maximum magnetic induction intensity is greater than 0.5 mT / mm.

5. The dual-stage anode layer Hall thruster according to claim 1, characterized in that: When the material of the secondary anode (2) is a ferromagnetic metal material, the maximum magnetic induction intensity is outside the discharge channel (201), and the axial gradient of the magnetic field between the top of the primary anode (1) and the maximum magnetic induction intensity is greater than 0.5 mT / mm.

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