Hall thruster thrust vector adjusting structure and adjusting method thereof
By dividing the magnetic circuit structure of the Hall thrust into multiple independent sector-shaped areas, and independently adjusting the working fluid supply, excitation current and discharge voltage in each area, the problems of complex structure and reduced discharge efficiency of the existing Hall thrust are solved, and continuous adjustment of the thrust vector and improved maneuverability of the spacecraft are achieved.
Patent Information
- Application Number
- CN202510003395.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-01-02
- Publication Date
- 2025-05-06
AI Technical Summary
The existing Hall thrust devices have complex structures, increased weight and reduced discharge efficiency when adjusting the thrust vector, which is difficult to meet the demand for thrust vectors in aerospace missions.
By designing the magnetic circuit structure of the Hall thrust into multiple independent sectors, and independently supplying working fluid in each area, adjusting the excitation current and applying discharge voltage, multiple independent discharge areas are formed to achieve continuous adjustment of the thrust vector.
The continuous adjustment of thrust vector is achieved, which improves the maneuverability and weight control capabilities of the spacecraft, and optimizes the discharge state and improves the overall performance of the thrust.
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Figure CN119933968A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the technical field of Hall thrusters, and in particular to a thrust vector adjustment structure of a Hall thruster and an adjustment 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 Hall thruster has the ability to adjust thrust vectors, which can improve the maneuverability of spacecraft, adjust the attitude of spacecraft, and eliminate the impact of the thrust vector eccentricity inherent in the propulsion device and the impact of the change in the center of mass of the spacecraft caused by the consumption of working fluid. At the same time, the Hall thruster has the ability to adjust thrust vectors, which can solve the problems of structural complexity, weight increase, failure of thrust vector adjustment due to mechanical failure, and application limitations of small spacecraft caused by the use of thrust vector adjustment mechanisms and thruster cluster solutions in engineering applications.
[0004] The existing thrust vectoring Hall thrusters have the problems of complex structure and reduced discharge stability. At present, there are two main solutions for Hall thrusters to achieve thrust vectoring adjustment: 1. Local air supply; 2. Additional magnetic circuit adjustment structure. Both increase the complexity and weight of the thruster. At the same time, under the condition of mismatched discharge parameters, non-uniform discharge will cause a serious decrease in discharge efficiency.
[0005] In summary, since the traditional Hall thruster structure does not have the ability to adjust the thrust vector, it can only be adjusted by using a mechanical arm or a universal joint, a thruster cluster, etc., which will cause problems such as increased mass, complex structure, and reduced reliability. At the same time, the existing thrust vector type Hall thrusters have problems such as high structural complexity and low discharge efficiency caused by the incompatibility of local discharge parameters. Therefore, a new Hall thruster thrust vector adjustment structure is needed to meet the needs of aerospace missions for the Hall thruster thrust vector and overcome the problem of reduced discharge performance caused by the thrust vector adjustment of the existing Hall thruster. Summary of the invention
[0006] In view of the defects in the prior art, an object of the present invention is to provide a Hall thruster thrust vector adjustment structure and an adjustment method thereof.
[0007] A Hall thruster thrust vector adjustment structure provided by the present invention comprises an inner magnetic pole, an inner magnetic column, an inner excitation coil group, an outer magnetic pole, an outer magnetic column group, an outer excitation coil group, a magnetic pole bottom plate, a discharge channel, and a gas distributor;
[0008] An inner magnetic column, a discharge channel, and an outer magnetic column group are sequentially arranged on the upper surface of the magnetic pole bottom plate in a radially outward direction, the upper end and the lower end of the inner magnetic column are respectively connected to the inner magnetic pole and the magnetic pole bottom plate, and the upper end and the lower end of the outer magnetic column group are respectively connected to the outer magnetic pole and the magnetic pole bottom plate;
[0009] The inner excitation coil group and the outer excitation coil group are respectively arranged on the inner magnetic conductive column member and the outer magnetic conductive column group;
[0010] The gas distributor is disposed at the bottom of the discharge channel.
[0011] Preferably, the inner magnetic conductive column member includes a plurality of inner magnetic conductive columns, and the plurality of inner magnetic conductive columns are arranged at the center of the upper surface of the magnetic pole bottom plate and are arranged in a centrally symmetrical manner;
[0012] The internal excitation coil group includes a plurality of internal excitation coils, one internal excitation coil is wound around an internal magnetic conductive column, and the internal excitation coils are independently powered.
[0013] Preferably, the inner magnetic pole plate adopts any of the following structures:
[0014] It is an annular integrated structure, and the inner magnetic pole plate is connected to the top of the inner magnetic conductive pillars of the plurality of inner magnetic conductive pillars;
[0015] It comprises a plurality of inner magnetic pole segments, each of which is connected to the top of the inner magnetic conductive column of one or more inner magnetic conductive column members.
[0016] Preferably, the outer magnetic conductive column group includes a plurality of outer magnetic conductive columns, and the plurality of outer magnetic conductive columns are evenly arranged along the circumference of the outer magnetic shield;
[0017] The external excitation coil group includes a plurality of external excitation coils, one external excitation coil is wound around one of the external magnetic conductive columns, and the external excitation coils are independently powered.
[0018] Preferably, the outer magnetic pole plate adopts any of the following structures:
[0019] It is an annular integrated structure, and the outer magnetic pole plate is connected to the tops of the plurality of outer magnetic conductive columns;
[0020] It comprises a plurality of outer magnetic pole segments, each of which is connected to the top of one or more outer magnetic conductive columns.
[0021] Preferably, the gas distributor is coaxially arranged with the discharge channel;
[0022] The gas distributor is a circular metal structure, comprising a hollow chamber, wherein the hollow chamber (91) adopts a continuous circular chamber structure or the hollow chamber is divided into a plurality of circular arc chambers by a partition, and each circular arc chamber is independently supplied with gas.
[0023] Preferably, it also includes an inner magnetic shield and an outer magnetic shield; an inner magnetic column, an inner magnetic shield, a discharge channel, an outer magnetic shield, and an outer magnetic column group are arranged in sequence on the upper surface of the magnetic pole bottom plate in the radial outward direction, and the inner magnetic shield and the outer magnetic shield are fixed on the upper surface of the magnetic pole bottom plate and are coaxial with the magnetic pole bottom plate.
[0024] Preferably, it also includes an anode, which is a ring-shaped structure and made of metal. The anode is fixed at the bottom of the discharge channel and is coaxial with the discharge channel.
[0025] Preferably, the anode is an integral structure or is divided into a plurality of circular arc anode segments insulated from each other, and each circular arc anode segment is independently powered.
[0026] According to a method for adjusting the thrust vector of a Hall thruster provided by the present invention, the thrust vector adjustment structure of the Hall thruster is adopted, and the overall magnetic circuit of the thruster is divided into a plurality of sector-shaped independent adjustment areas. The adjustment method adopts any of the following methods:
[0027] During the discharge process of the Hall thruster, the excitation current of the inner excitation coil and / or the excitation current of the outer excitation coil in one or more local sector-shaped independent adjustment areas in the circumferential direction is adjusted, so that the thrust generated by the local sector-shaped independent adjustment areas in the circumferential direction is different, and the direction and magnitude of the thrust vector are continuously changed, so as to realize the thrust vector adjustment capability of the Hall thruster; at the same time, the discharge state of the local sector-shaped independent adjustment area can be optimized by matching the excitation current of the inner excitation coil and the excitation current of the outer excitation coil;
[0028] During the discharge process of the Hall thruster, by adjusting at least one physical quantity among the excitation current of the inner excitation coil, the excitation current of the outer excitation coil, and the working fluid flow rate of the arc segment chamber on the gas distributor in one or more local sectors in the circumferential direction of the independent adjustment area, the thrust generated in the local areas in the circumferential direction can be different, the direction and magnitude of the thrust vector can be continuously changed, and the thrust vector adjustment capability of the Hall thruster can be realized; at the same time, by matching the excitation current of the inner excitation coil, the excitation current of the outer excitation coil, and the working fluid flow rate of the arc segment chamber on the gas distributor, the discharge state of the local sector-shaped independent adjustment area can be optimized;
[0029] During the discharge process of the Hall thruster, at least one physical quantity among the excitation current of the inner excitation coil, the excitation current of the outer excitation coil, the working fluid flow rate of the arc segment chamber on the gas distributor circle, and the anode voltage on the anode in one or more local sectors in the circumferential direction and the independent adjustment area is adjusted, so that the thrust generated in the local area in the circumferential direction has differences, the direction and size of the thrust vector are continuously changed, and the thrust vector adjustment capability of the Hall thruster is realized; at the same time, the discharge state of the local sector-shaped independent adjustment area is optimized by matching the excitation current of the inner excitation coil, the excitation current of the outer excitation coil, the working fluid flow rate of the arc segment chamber on the gas distributor, and the anode voltage on the anode.
[0030] Compared with the prior art, the present invention has the following beneficial effects:
[0031] 1. The magnetic circuit structure of the Hall thruster in the present invention constructs multiple independent fan-shaped areas. In different fan-shaped areas, working fluid is independently supplied, excitation current is adjusted, and discharge voltage is applied to form multiple independent discharge areas. Different discharges in different fan-shaped areas can be achieved by adjusting the non-consistency of the current of the excitation coil, the working fluid flow rate, and the discharge voltage value in the circumferential direction alone or in combination, thereby achieving continuous adjustment of the thrust vector.
[0032] 2. The present invention ensures the matching of working fluid, magnetic field and electric potential in the local area by adjusting the air supply flow, magnetic field strength and position, and anode voltage value in the independent sector area, realizes the stability of thruster discharge, and expands the thrust vector adjustment capability. BRIEF DESCRIPTION OF THE DRAWINGS
[0033] 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:
[0034] Figure 1 is a schematic diagram of the thrust vector adjustment structure of the Hall thruster of the present invention;
[0035] Figure 2 is a cross-sectional view of the thrust vector adjustment structure of the Hall thruster of the present invention;
[0036] Figure 3 It is a schematic diagram of a local sector area of the thrust vector adjustment structure of the Hall thruster according to the present invention.
[0037] The figure shows:
[0038] Inner pole 1
[0039] Inner magnetic pole segment 11
[0040] Internal magnetic column 2
[0041] Inner magnetic column 21
[0042] Internal excitation coil group 3
[0043] Internal excitation coil 31
[0044] Outer magnetic pole 4
[0045] Outer magnetic pole segment 41
[0046] External magnetic column group 5
[0047] External magnetic column 51
[0048] External excitation coil group 6
[0049] External excitation coil 61
[0050] Pole bottom plate 7
[0051] Discharge channel 8
[0052] Gas distributor 9
[0053] Hollow chamber 91
[0054] Arc segment chamber 92
[0055] Anode 12
[0056] Arc anode segment 121
[0057] External magnetic shield 20 DETAILED DESCRIPTION
[0058] 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.
[0059] Embodiment 1:
[0060] In order to solve the problem of reduced discharge performance during thrust vector adjustment of a single Hall thruster, realize thrust vector adjustment, increase spacecraft maneuverability, and optimize spacecraft weight control, the present invention provides a Hall thruster thrust vector adjustment structure, comprising an inner magnetic pole 1, an inner magnetic column member 2, an inner excitation coil group 3, an outer magnetic pole 4, an outer magnetic column group 5, an outer excitation coil group 6, a magnetic pole bottom plate 7, a discharge channel 8, and a gas distributor 9; the inner magnetic column member 2, the discharge channel 8, and the outer magnetic column group 5 are sequentially arranged on the upper surface of the magnetic pole bottom plate 7 in a radially outward direction, and the inner magnetic pole plate group 1, the outer magnetic pole plate group 4, the inner magnetic column member 2, and the outer magnetic column group 5 are uniformly arranged along the circumferential direction of the upper surface of the magnetic bottom plate 7, with the axes coinciding.
[0061] Specifically, the upper end and the lower end of the inner magnetic conductive column member 2 are connected to the inner magnetic pole 1 and the magnetic pole bottom plate 7 respectively, and the upper end and the lower end of the outer magnetic conductive column group 5 are connected to the outer magnetic pole 4 and the magnetic pole bottom plate 7 respectively.
[0062] The inner magnetic conductive column member 2 includes a plurality of inner magnetic conductive columns 21, which are arranged at the center of the upper surface of the pole bottom plate 7 and are arranged in a centrally symmetrical manner. For example, the number of the inner magnetic conductive columns 21 is 3, and the three inner magnetic conductive columns 21 are arranged in a ring shape when viewed from above.
[0063] The inner excitation coil group 3 includes a plurality of inner excitation coils 31, and one inner excitation coil 31 is wound around one inner magnetic column 21. The outer magnetic column group 5 includes a plurality of outer magnetic columns 51, and the outer excitation coil group 6 includes a plurality of outer excitation coils 61, and one outer magnetic column 51 is wound around one outer excitation coil 61, wherein the inner excitation coil 31 and the outer excitation coil 61 are independently powered.
[0064] like Figure 1 , Figure 2 , Figure 3 As shown, the gas distributor 9 is fixed at the bottom of the discharge channel 8 and is coaxially arranged with the discharge channel 8. The gas distributor 9 is a circular metal structure, including a hollow chamber 91. The hollow chamber (91) can adopt a continuous circular chamber structure or the internal circular hollow chamber 91 of the gas distributor 9 is divided into a plurality of circular arc segment chambers 92 by a partition, preferably 3 circular arc segment chambers 92, each circular arc segment chamber 92 is independently supplied with gas, and the gas distributor 9 can supply working fluid gas to the discharge channel 8 through the hollow chamber 91, and can also provide anode high potential. The discharge channel 8 is fixed on the upper surface of the magnetic pole bottom plate 7 and is coaxially arranged with the magnetic pole bottom plate 7.
[0065] In the circumferential direction, the overall magnetic circuit of the thruster is divided into a plurality of sector-shaped independent adjustment areas, preferably three sector-shaped independent adjustment areas, each sector-shaped independent adjustment area includes i inner magnetic conductive columns 21 and inner excitation coils 31, j outer magnetic conductive columns 51, and an outer excitation coil 61, the values of i and j are both positive integers, and the specific values are set according to design requirements. In this embodiment, i=j=1.
[0066] During the discharge process of the Hall thruster, by adjusting the excitation current of the inner excitation coil 31 and / or the excitation current of the outer excitation coil 61 in one or more local sector-shaped independent adjustment areas in the circumferential direction, the thrust magnitudes generated by the local sector-shaped independent adjustment areas in the circumferential direction can be different, the direction and magnitude of the thrust vector can be continuously changed, and the thrust vector adjustment capability of the Hall thruster can be realized. At the same time, the discharge state of the local sector-shaped independent adjustment area can be optimized by matching the excitation current of the inner excitation coil 31 and the excitation current of the outer excitation coil 61.
[0067] The inner magnetic pole plate 1 can be an annular integrated structure, and the inner magnetic pole plate 1 is connected to the top of the inner magnetic conductive column 21 of the multiple inner magnetic conductive column members 2. The inner magnetic pole plate 1 can also be divided into multiple inner magnetic pole segments 11, and correspondingly, each inner magnetic pole segment 11 can be connected to one or more inner magnetic conductive columns 21. The outer magnetic pole plate 4 can be an annular integrated structure, and the outer magnetic pole plate 4 is connected to the top of multiple outer magnetic conductive columns 51; or the outer magnetic pole plate 4 is divided into multiple outer magnetic pole segments 41, and correspondingly, each outer magnetic pole segment 41 can be connected to multiple outer magnetic conductive columns 51.
[0068] Embodiment 2:
[0069] The present embodiment is different from the first embodiment in that the thrust vector adjustment structure of the Hall thruster further includes an inner magnetic shield 10 and an outer magnetic shield 20; an inner magnetic column 2, an inner magnetic shield 10, a discharge channel 8, an outer magnetic shield 20, and an outer magnetic column group 5 are sequentially arranged on the upper surface of the magnetic pole bottom plate 7 in the radial outward direction, and the inner magnetic shield 10 and the outer magnetic shield 20 are fixed on the upper surface of the magnetic pole bottom plate 7 and are coaxial with the magnetic pole bottom plate 7. A plurality of outer magnetic columns 51 are evenly arranged along the circumference of the outer magnetic shield 20.
[0070] Embodiment 3:
[0071] This embodiment is a preferred example of embodiment 1. In this embodiment, in the circumferential direction, the thruster overall magnetic circuit is divided into a plurality of sector-shaped independent adjustment areas, each sector-shaped independent adjustment area includes i inner magnetic conductive columns 21 and inner excitation coils 31, j outer magnetic conductive columns 51 and outer excitation coils 61, and k arc segment chambers 92, wherein the values of i, j, and k are all positive integers, and the specific values are set according to design requirements. In this embodiment, i=j=k=1.
[0072] During the discharge process of the Hall thruster, by adjusting at least one physical quantity among the excitation current of the inner excitation coil 31, the excitation current of the outer excitation coil 61, and the working fluid flow rate of the arc segment chamber 92 on the gas distributor 9 in one or more local sectors in the circumferential direction of the independent adjustment area, it is possible to achieve differences in the thrust magnitudes generated in the local areas in the circumferential direction, achieve continuous changes in the direction and magnitude of the thrust vector, and achieve the thrust vector adjustment capability of the Hall thruster. At the same time, the discharge state of the local sector-shaped independent adjustment area can be optimized by matching the excitation current of the inner excitation coil 31, the excitation current of the outer excitation coil 61, and the working fluid flow rate of the arc segment chamber 92 on the gas distributor 9.
[0073] Embodiment 4:
[0074] This embodiment is another preferred example of embodiment 1, and further includes an anode 12. The anode 12 is a ring-shaped structure made of metal. The anode 12 is fixed at the bottom of the discharge channel 8 and is coaxial with the discharge channel 8. The anode 12 can be an integral structure, or divided into a plurality of mutually insulated circular arc anode segments 121. In this embodiment, the anode 12 is equally divided into three circular arc anode segments 121, and each circular arc anode segment 121 is independently powered.
[0075] In this embodiment, the material of the gas distributor 9 is not limited to metal. In the circumferential direction, the thruster's overall magnetic circuit is divided into a plurality of sector-shaped independent adjustment areas, each of which includes i inner magnetic columns 21 and inner excitation coils 31, j outer magnetic columns 51 and outer excitation coils 61, k circular arc chambers 92, and m anode segments 121. The values of i, j, k, and m are all positive integers, and the specific values are set according to design requirements. In this embodiment, i=j=k=m=1.
[0076] Correspondingly, during the discharge process of the Hall thruster, by adjusting at least one of the excitation current of the inner excitation coil 31, the excitation current of the outer excitation coil 61, the working fluid flow rate of the arc segment chamber 92 on the gas distributor 9, and the anode voltage on the anode 121 in one or more local sectors in the circumferential direction and in the independent adjustment area, it is possible to achieve differences in the thrust magnitudes generated in the local areas in the circumferential direction, achieve continuous changes in the direction and magnitude of the thrust vector, and achieve the thrust vector adjustment capability of the Hall thruster. At the same time, the discharge state of the local sector-shaped independent adjustment area is optimized by matching the excitation current of the inner excitation coil 31, the excitation current of the outer excitation coil 61, the working fluid flow rate of the arc segment chamber 92 on the gas distributor 9, and the anode voltage on the anode 121.
[0077] The structure of the present invention mainly carries out the following designs:
[0078] 1. The excitation structure of the thruster is equally divided into a plurality of sector-shaped areas. The inner excitation coil 31 and the outer excitation coil 61 in each sector-shaped area can be powered and the excitation current can be adjusted separately. Targeted magnetic field construction can be performed in each area to achieve circumferential inconsistency of the magnetic field.
[0079] 2. The anode ring is equally divided into a plurality of arc anode segments 121. Each arc anode segment 121 can be independently applied with an anode voltage and independently regulated to achieve circumferential non-uniformity of the anode voltage.
[0080] 3. The annular chamber of the gas distributor 9 is equally divided into a plurality of arc-section chambers 92, and each section chamber performs independent gas supply and gas supply flow rate regulation to achieve circumferential inconsistency of gas supply flow rate.
[0081] 4. In the circumferential direction, the overall magnetic circuit of the thruster is divided into a plurality of independent sector-shaped adjustment areas. The excitation current of the inner excitation coil 31, the excitation current of the outer excitation coil 61, the working fluid flow rate of the arc segment chamber 92 on the gas distributor 9, and the anode voltage on the anode segment 121 in one or more local sector-shaped areas in the circumferential direction are adjusted to achieve continuous changes in the direction and size of the thrust vector. By matching the above-mentioned adjustment parameters, the discharge state of the local sector-shaped area can be optimized, thereby achieving an improvement in the overall performance.
[0082] 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.
[0083] 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 thrust vector adjustment structure, characterized in that: It comprises an inner magnetic pole (1), an inner magnetic column (2), an inner excitation coil group (3), an outer magnetic pole (4), an outer magnetic column group (5), an outer excitation coil group (6), a magnetic pole bottom plate (7), a discharge channel (8), and a gas distributor (9); An inner magnetic column member (2), a discharge channel (8), and an outer magnetic column group (5) are sequentially arranged on the upper surface of the magnetic pole bottom plate (7) in a radially outward direction, the upper end and the lower end of the inner magnetic column member (2) are respectively connected to the inner magnetic pole (1) and the magnetic pole bottom plate (7), and the upper end and the lower end of the outer magnetic column group (5) are respectively connected to the outer magnetic pole (4) and the magnetic pole bottom plate (7); The inner excitation coil group (3) and the outer excitation coil group (6) are respectively arranged on the inner magnetic conductive column member (2) and the outer magnetic conductive column group (5); The gas distributor (9) is arranged at the bottom of the discharge channel (8).
2. The Hall thruster thrust vector adjustment structure according to claim 1, characterized in that: The inner magnetic conductive column member (2) comprises a plurality of inner magnetic conductive columns (21), and the plurality of inner magnetic conductive columns (21) are arranged at the center of the upper surface of the magnetic pole bottom plate (7) and are arranged in a centrally symmetrical manner; The internal excitation coil group (3) comprises a plurality of internal excitation coils (31), one internal excitation coil (31) is wound around an internal magnetic conductive column (21), and the internal excitation coil (31) is independently powered.
3. The Hall thruster thrust vector adjustment structure according to claim 1 or 2, characterized in that: The inner magnetic pole plate (1) adopts any of the following structures: It is an annular integrated structure, wherein the inner magnetic pole plate (1) is connected to the tops of the inner magnetic conductive columns (21) of the plurality of inner magnetic conductive column members (2); It comprises a plurality of inner magnetic pole segments (11), each of the inner magnetic pole segments (11) being connected to the top of an inner magnetic conductive column (21) possessed by one or more inner magnetic conductive column members (2).
4. The Hall thruster thrust vector adjustment structure according to claim 1, characterized in that: The outer magnetic conductive column group (5) comprises a plurality of outer magnetic conductive columns (51), and the plurality of outer magnetic conductive columns (51) are evenly arranged along the circumference of the outer magnetic shield (20); The external excitation coil group (6) comprises a plurality of external excitation coils (61), one external excitation coil (61) is wound around one of the external magnetic conductive columns (51), and the external excitation coils (61) are independently powered.
5. The Hall thruster thrust vector adjustment structure according to claim 4, characterized in that: The outer magnetic pole plate (4) adopts any of the following structures: It is an annular integrated structure, and the outer magnetic pole plate (4) is connected to the tops of a plurality of the outer magnetic conductive columns (51); It comprises a plurality of outer magnetic pole segments (41), each of the outer magnetic pole segments (41) being connected to the top of one or more outer magnetic conductive columns (51).
6. The Hall thruster thrust vector adjustment structure according to claim 1, characterized in that: The gas distributor (9) is coaxially arranged with the discharge channel (8); The gas distributor (9) is a circular metal structure, comprising a hollow chamber (91), wherein the hollow chamber (91) adopts a continuous circular chamber structure or the hollow chamber (91) is divided into a plurality of circular arc segment chambers (92) by a partition, and each circular arc segment chamber (92) is independently supplied with gas.
7. The Hall thruster thrust vector adjustment structure according to claim 1, characterized in that: It also includes an inner magnetic shield (10) and an outer magnetic shield (20); an inner magnetic column member (2), an inner magnetic shield (10), a discharge channel (8), an outer magnetic shield (20), and an outer magnetic column group (5) are arranged in sequence on the upper surface of the magnetic pole bottom plate (7) in a radially outward direction; the inner magnetic shield (10) and the outer magnetic shield (20) are fixed on the upper surface of the magnetic pole bottom plate (7) and are coaxial with the magnetic pole bottom plate (7).
8. The Hall thruster thrust vector adjustment structure according to claim 1, characterized in that: It also comprises an anode (12), which is an annular structure and made of metal. The anode (12) is fixed at the bottom of the discharge channel (8) and is coaxial with the discharge channel (8).
9. The Hall thruster thrust vector adjustment structure according to claim 8, characterized in that: The anode (12) is an integral structure or is divided into a plurality of circular arc anode segments (121) that are insulated from each other, and each circular arc anode segment (121) is independently powered.
10. A method for adjusting the thrust vector of a Hall thruster, characterized in that: By adopting the thrust vector adjustment structure of the Hall thruster according to any one of claims 1 to 9, the overall magnetic circuit of the thruster is divided into a plurality of sector-shaped independent adjustment areas, and the adjustment method adopts any of the following methods: During the discharge process of the Hall thruster, the excitation current of the inner excitation coil (31) and / or the excitation current of the outer excitation coil (61) in one or more local sector-shaped independent adjustment areas in the circumferential direction is adjusted, so that the thrust magnitudes generated by the local sector-shaped independent adjustment areas in the circumferential direction are different, and the direction and magnitude of the thrust vector are continuously changed, thereby realizing the thrust vector adjustment capability of the Hall thruster; at the same time, the discharge state of the local sector-shaped independent adjustment area can be optimized by matching the excitation current of the inner excitation coil (31) and the excitation current of the outer excitation coil (61); During the discharge process of the Hall thruster, at least one physical quantity among the excitation current of the inner excitation coil (31), the excitation current of the outer excitation coil (61), and the working fluid flow rate of the arc segment chamber (92) on the gas distributor (9) in one or more local sector-shaped independent adjustment areas in the circumferential direction is adjusted, so that the thrust magnitudes generated in the local areas in the circumferential direction are different, the direction and magnitude of the thrust vector are continuously changed, and the thrust vector adjustment capability of the Hall thruster is realized; at the same time, the discharge state of the local sector-shaped independent adjustment area can be optimized by matching the excitation current of the inner excitation coil (31), the excitation current of the outer excitation coil (61), and the working fluid flow rate of the arc segment chamber (92) on the gas distributor (9); During the discharge process of the Hall thruster, at least one physical quantity among the excitation current of an inner excitation coil (31), the excitation current of an outer excitation coil (61), the flow rate of a working fluid in an arc segment chamber (92) on a gas distributor circle (9), and the anode voltage on an anode (121) in a certain or multiple local sector-shaped independent adjustment area in the circumferential direction is adjusted, so that the thrust generated in the local area in the circumferential direction has differences, the direction and magnitude of the thrust vector are continuously changed, and the thrust vector adjustment capability of the Hall thruster is realized; at the same time, the discharge state of the local sector-shaped independent adjustment area is optimized by matching the excitation current of the inner excitation coil (31), the excitation current of the outer excitation coil (61), the flow rate of a working fluid in an arc segment chamber (92) on a gas distributor (9), and the anode voltage on an anode (121).