Integrated magnetic anode Hall thruster and spacecraft

Abstract

The invention relates to an integrated magnetic anode Hall thruster and a spacecraft, and belongs to the field of space propulsion. The Hall thruster comprises an anode, the anode is divided into an anode cavity and a cathode cavity, the anode cavity is divided into an anode buffer cavity and an anode channel through a throttler, the cathode cavity is divided into a cathode buffer cavity and a cathode channel through the throttler, the anode buffer cavity is communicated with a ventilation rod, and the cathode buffer cavity is communicated with the ventilation rod. The anode buffer cavity is communicated with the cathode buffer cavity through a cathode vent hole; one part of the working medium gas enters the anode channel from the anode buffer cavity through the throttler, and the other part of the working medium gas enters the cathode buffer cavity through the cathode vent hole and enters the cathode channel through the throttler. The anode channel, the cathode channel, the throttling element and the magnetic shielding structure are jointly integrated in the anode, working medium gas in the anode channel and the cathode channel is homogenized, the axial speed of the anode channel and the cathode channel is reduced, the working medium gas is fully ionized, and the performance of the propeller is improved.

Description

Technical Field

[0001] The present invention relates to the field of space propulsion, and in particular to an integrated magnetic anode Hall thruster and a spacecraft. Background Art

[0002] Hall thrusters are an advanced space propulsion technology currently used extensively in spacecraft attitude and orbit control missions. Compared to other thrusters, they offer advantages such as simple structure, high specific impulse, and long life. They can meet the power requirements of large-scale satellite networks, effectively reducing satellite mass and lowering network costs.

[0003] Hall thrusters can be divided into two basic configurations: the Stationary Plasma Thruster (SPT) and the Thruster with Anode Layer (TAL). The latter uses a metal discharge channel and a shorter acceleration region. Both utilize a hollow cathode as a seed electron source. This electron source is confined by orthogonal electromagnetic fields, causing collision ionization with the working gas, accelerating the ejected ions and generating thrust. The hollow cathode is typically installed as a separate component, primarily in external and central configurations. This requires specialized assembly tooling, insulation and thermal insulation, and independent electrical and gas circuits to ensure proper operation.

[0004] The existing application number is CN201910670105.0, a thruster structure in which a hollow cathode is deeply integrated into the interior of the anode layer Hall thruster. In this structure, the core components of the cathode are merged into the inner ring wall of the anode layer Hall thruster, and the anode will play the role of the original cathode contact pole. Using this device to replace the original combination of Hall thruster and hollow cathode can greatly reduce the total mass of the electric propulsion system, thereby increasing the payload. Although the above solution can solve the problem of independent cathode circuit and gas path, it requires the setting of certain assembly tooling and insulation and thermal insulation measures. The overall structure is slightly bloated, which increases the complexity of the system.

[0005] In addition, the working fluid gas diffuses directly in the discharge chamber channel, with poor uniformity and high axial velocity, resulting in poor uniformity and quantity of electrons generated, which affects the performance of the thruster. Moreover, under the action of the magnetic field, charged particles sputter and bombard the anode channel and thruster structure in the discharge channel, affecting the service life of the thruster. Summary of the Invention

[0006] In order to solve the above problems, the present invention provides an integrated magnetic anode Hall thruster.

[0007] The present invention adopts the following technical solutions: The present invention provides an integrated magnetic anode Hall thruster, comprising an anode, wherein the anode is divided into an anode chamber and a cathode chamber, the anode chamber is divided into an anode buffer chamber and an anode channel by a throttle, the cathode chamber is divided into a cathode buffer chamber and a cathode channel by a throttle, the anode buffer chamber is connected to a ventilation rod, and the anode buffer chamber and the cathode buffer chamber are connected via a cathode vent; a portion of the working fluid gas enters the anode channel from the anode buffer chamber through the throttle, and the other portion enters the cathode buffer chamber through the cathode vent and enters the cathode channel through the throttle.

[0008] By adopting the above scheme, the throttling elements of the cathode and anode can also be integrated together in this integrated manner, thereby homogenizing the working gas in the anode channel and the cathode channel, reducing its axial velocity, fully ionizing the working gas, and improving the performance of the thruster; if the conventional hollow cathode center placement method is adopted, this simplified design cannot be achieved.

[0009] The present invention provides an integrated magnetic anode Hall thruster. Furthermore, the anode is made of soft magnetic material, and a discharge channel is formed above the anode channel.

[0010] By adopting the above solution, there are no magnetic induction lines in the anode channel, and the strongest magnetic field is extrapolated compared to the thruster outlet, thereby effectively alleviating the sputtering corrosion of ions on the anode channel and avoiding the phenomenon of overlapping of excess metal in the anode layer Hall thruster, thereby effectively extending the thruster life and improving working reliability.

[0011] The present invention provides an integrated magnetic anode Hall thruster. Further, the throttle includes a first-stage throttle, a second-stage throttle and a third-stage throttle. The first-stage throttle is provided with an anode air inlet hole and a cathode air inlet hole on one side, and an annular slot corresponding to the anode air inlet hole and the cathode air inlet hole on the other side; the second-stage throttle is provided with an anode air inlet hole and a cathode air inlet hole corresponding to the two ends of the annular slot on one side, and an annular slot corresponding to the anode air inlet hole and the cathode air inlet hole on the other side; the third-stage throttle is provided with an anode air outlet hole and a cathode air outlet hole corresponding to the two ends of the annular slot.

[0012] By adopting the above scheme, the working gas enters the anode buffer chamber from the vent rod and diffuses in the anode buffer chamber. A portion of the working gas flows into the anode inlet hole of the first-stage throttle in the throttle, diffuses through the annular slot, passes through the second-stage throttle, and diffuses from the anode outlet hole in the third-stage throttle to the anode channel; the other portion of the working gas enters the cathode buffer chamber from the cathode inlet hole, then flows into the cathode inlet hole of the first-stage throttle in the throttle, diffuses through the annular slot, passes through the second-stage throttle, and diffuses from the cathode outlet hole in the third-stage throttle to the cathode channel. By setting the throttle, the working gas in the anode channel and the cathode channel is homogenized, and the axial motion speed of the gas molecules is reduced, so that the working gas is fully ionized, improving the performance of the thruster, and its flow resistance can effectively throttle the gas, thereby jointly ensuring that the uniformity and flow rate of the working gas entering the cathode and anode channels meet the technical requirements.

[0013] The present invention provides an integrated magnetic anode Hall thruster. Further, the first-stage throttle is respectively provided with four anode air inlet holes and cathode air inlet holes on one side, and four annular slots on the other side; the second-stage throttle is respectively provided with eight anode air inlet holes and cathode air inlet holes on one side, and eight annular slots on the other side; the third-stage throttle is respectively provided with sixteen anode air outlet holes and cathode air outlet holes.

[0014] The present invention provides an integrated magnetic anode Hall thruster, further comprising: Support frame; Insulating ceramic is mounted on a support frame, the insulating ceramic has a mounting chamber, and the anode is mounted in the mounting chamber; the ventilation rod passes through the support frame, the insulating ceramic and is in communication with the anode buffer chamber; An external magnet is arranged on the outer periphery of the insulating ceramic; An inner magnet is arranged on the inner periphery of the insulating ceramic; The cathode assembly is mounted on the insulating ceramic and located in the center of the upper part of the anode.

[0015] By adopting the above solution, the insulating ceramic insulates and separates the discharge channel from the external magnet, the internal magnet, the heater, etc.

[0016] The present invention provides an integrated magnetic anode Hall thruster. Furthermore, the cathode assembly includes an emitter, a heater and a heat shield. The heater, heat shield and emitter are located on both sides of the inner peripheral wall of the insulating ceramic. The heat shield separates the heater from the inner magnet.

[0017] The present invention provides an integrated magnetic anode Hall thruster, which further includes an inner guard ring and an outer guard ring. Mounting steps are respectively formed on both sides of the inner peripheral wall of the insulating ceramic. The inner guard ring is mounted on the inner periphery of the insulating ceramic, and the outer guard ring is mounted on the outer periphery of the insulating ceramic. A mounting groove for mounting an emitter is formed between the inner guard ring and the mounting steps on the inner side of the inner peripheral wall of the insulating ceramic, and a mounting groove for mounting a heater and a heat shield is formed between the inner guard ring and the mounting steps on the outer side of the inner peripheral wall of the insulating ceramic; and a mounting groove for mounting an external magnet is formed between the outer guard ring and the support frame.

[0018] The present invention provides an integrated magnetic anode Hall thruster. Furthermore, a portion of the emitter corresponds to the outer wall of the anode channel, and the other portion is located in the discharge channel area. The inner guard ring is provided with an inner guard, and the inner guard wraps the emitter located in the discharge channel area; the outer guard ring is provided with an outer guard, and the outer guard wraps the insulating ceramic located in the discharge channel area.

[0019] By adopting the above solution, the thruster structure is protected to avoid ion bombardment and extend its service life.

[0020] The integrated magnetic anode Hall thruster of the present invention further includes a shell installed on the support frame, wherein the shell encloses the outer side of the outer magnet and fixes the outer guard ring.

[0021] The present invention also provides a spacecraft, comprising the above-mentioned integrated magnetic anode Hall thruster, wherein the spacecraft is a satellite or a space station.

[0022] By adopting the above scheme, a supporting and protective effect is achieved.

[0023] Compared with the prior art, the present invention has the following beneficial effects: 1. This application integrates the anode channel, cathode channel, throttling element, and magnetic shielding structure into the anode. On the one hand, it homogenizes the working gas in the anode channel and cathode channel, reduces its axial velocity, fully ionizes the working gas, and improves the performance of the thruster. On the other hand, it eliminates magnetic induction lines in the anode channel, and makes the strongest magnetic field extrapolated compared to the thruster outlet, thereby effectively alleviating the sputtering corrosion of ions on the anode channel and avoiding the phenomenon of metal overlap in the anode layer Hall thruster, thereby effectively extending the life of the thruster and improving the working reliability. It also greatly simplifies the system structure, reduces the structural size, and optimizes the thruster performance. In addition, through this integration method, the throttling elements of the cathode and anode can also be integrated together. If a hollow cathode is placed in the middle, this simplified design cannot be achieved. 2. By providing inner and outer guard rings, the thruster structure is further protected from ion bombardment, thus extending the service life of the thruster; 3. Traditional Hall thrusters typically use a hollow cathode as a separate component, either externally located around the thruster or placed in the center. The present invention integrates the cathode assembly into the center of the thruster, sharing a buffer cavity with the anode, significantly reducing the structural size. The generated electrons are annular, providing a uniform electron source for the peripheral anode discharge channel. Furthermore, the anode is used to provide the high potential required for ionization, eliminating one power supply circuit from the power processing unit and simplifying the system design. 4. Traditional Hall thrusters have independent magnetic shielding structures. This invention integrates the magnetic shielding structure into the anode, effectively reducing the thruster's structural size. The anode of this invention uses soft magnetic material, which allows the anode channel to also have a magnetic shielding effect, eliminating the need for additional magnetic shielding structures on both sides, greatly simplifying the structural design. 5. Traditional Hall thrusters integrate the throttling element into the flow control module. This invention integrates the throttling element into the anode, effectively simplifying the overall system design. This invention replaces the traditional anode gas distributor with a throttling device, which not only serves to uniformly distribute the working gas, but also provides different flow rates of working gas to the cathode and anode. 6. Reduced system complexity. This invention integrates the throttling element of the flow regulation module in the traditional Hall thruster into the anode. By modifying the gas distributor, it has a throttling function, which can not only evenly distribute the chemical gas, but also ensure that the flow in the cathode and anode channels meets the technical requirements; 7. Optimized cathode electron source. This invention integrates the cathode assembly into the center of the thruster and utilizes the inner wall of the anode to provide it with a high ignition potential, thus forming a ring-shaped electron emission source. Compared with the beam-shaped electron source of the traditional cathode assembly, this ring-shaped electron source has significantly improved in uniformity and quantity. Therefore, it can effectively improve thruster performance; 8. Reduced system size and weight. By integrating the magnetic shielding structure and throttling elements into the anode and the cathode assembly into the center of the thruster, this invention optimizes the structural design, reduces modular components, significantly reduces the system size, and effectively reduces the overall weight.

[0024] The present invention will be further described below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a structural schematic diagram of the present invention; Figure 2 It is a working schematic diagram of the present invention; Figure 3 Schematic diagram of the throttle structure of the present invention; Figure 4 Schematic diagram of the anode magnetic shielding effect of the present invention.

[0026] Reference numerals: 1. Outer shell; 2. Outer magnet; 3. Insulating ceramic; 4. Outer guard ring; 5. Anode; 6. Emitter; 7. Heater; 8. Heat shield; 9. Inner magnet; 10. Inner guard ring; 11. Support frame; 12. Vent rod; 13. Mounting chamber; 14. Discharge channel; 15. Anode buffer chamber; 16. Anode channel; 17. Cathode buffer chamber; 18. Cathode channel; 19. Cathode vent; 20. Inner guard; 21. Outer guard; 51. Throttle; 511. First-stage throttle; 512. Second-stage throttle; 513. Third-stage throttle; 514. Anode air inlet; 515. Cathode air inlet; 516. Annular slot; 517. Anode air outlet; 518. Cathode air outlet. DETAILED DESCRIPTION

[0027] like Figure 1-Figure 4 As shown, the present invention discloses an integrated magnetic anode Hall thruster, including a shell 1, an outer magnet 2, an insulating ceramic 3, an outer guard ring 4, an anode 5, an emitter 6, a heater 7, a heat shield 8, an inner magnet 9, an inner guard ring 10, a support frame 11 and a ventilation rod 12. The support frame 11 is a T-shaped structure as a whole. The insulating ceramic 3 is an annular cylindrical structure and is arranged on the support frame 11. The insulating ceramic 3 has a mounting chamber 13, and the anode 5 is arranged in the mounting chamber 13. The outer magnet 2 is arranged on the outer periphery of the insulating ceramic 3, and the inner magnet 9 is arranged on the inner periphery of the insulating ceramic 3. The outer magnet 2 and the inner magnet 9 form a radial magnetic field for confining electrons to ionize the working fluid gas; the emitter 6, the heater 7, and the heat shield 8 constitute a cathode assembly for generating an electron source, which is installed on the insulating ceramic 3 and located at the upper center of the anode 5. A discharge channel 14 is formed between the inner guard ring 10 and the outer guard ring 4 to protect the thruster structure from ion bombardment; the insulating ceramic 3 insulates the discharge channel 14 from the outer magnet 2, the inner magnet 9, the heater 7, etc.

[0028] The anode 5 is divided into an anode chamber and a cathode chamber. The anode chamber and the cathode chamber are an integrated structure. The anode chamber is divided into an anode buffer chamber 15 and an anode channel 16 by a throttle 51. The cathode chamber is divided into a cathode buffer chamber 17 and a cathode channel 18 by a throttle 51. The ventilation rod 12 passes through the support frame 11 and the insulating ceramic 3 and is connected to the anode buffer chamber 15. The anode buffer chamber 15 and the cathode buffer chamber 17 are connected by the cathode vent 19. Part of the working gas enters the anode channel 16 from the anode buffer chamber 15 through the throttle 51, and the other part enters the cathode buffer chamber 17 through the cathode vent 19 and enters the cathode channel 18 through the throttle 51. The anode 5 is made of a soft magnetic material, allowing the inner and outer walls of the anode channel 16 to serve as diffusion channels for the working gas and provide a high potential to ionize the working gas within the anode 5 and cathode channel 18. This also creates a magnetic shielding structure, eliminating magnetic induction lines within the anode channel 16 and pushing the strongest magnetic field outward from the thruster outlet. This creates a discharge channel 14 above the anode channel 16, effectively mitigating ion sputtering corrosion on the anode channel 16 and preventing metal overlap within the anode 5 layer Hall thruster. This effectively extends the thruster's life and improves operational reliability. The anode 5 performs the following functions: The working gas flows from the vent rod 12 into the throttle 51, forming different flow rates and evenly distributing them to the cathode channel 18 and anode channel 16; generates a high potential within the anode 5, generating a cathode ignition potential; and also creates a magnetic shielding effect.

[0029] The working principle of the present application is as follows: the working gas flows from the ventilation rod 12 into the anode buffer chamber 15 and the cathode buffer chamber 17, and then passes through the throttle 51 to form different flow rates and is uniformly distributed in the anode channel 16 and the cathode channel 18; the heater 7 heats the emitter 6, and when it reaches the operating temperature, the working gas flowing through the cathode channel 18 will be ionized by the high potential of the inner wall of the anode channel 16 of the anode 5 to generate plasma, wherein the electrons are drawn out at the high potential; the outer magnet 2 and the inner magnet 9 form a radial magnetic field, and form an orthogonal electromagnetic field with the anode 5, which is used to confine the emitted electrons of the cathode assembly to ionize the working gas in the discharge channel 14 to generate plasma, wherein the ions are accelerated and ejected under the action of the electric field to generate thrust.

[0030] The throttle 51 includes a first-stage throttle 511, a second-stage throttle 512 and a third-stage throttle 513. The first-stage throttle 511 has four anode air inlet holes 514 and four cathode air inlet holes 515 on one side, and four annular slots 516 corresponding to the anode air inlet holes 514 and the cathode air inlet holes 515 on the other side; the second-stage throttle 512 has eight anode air inlet holes 514 and cathode air inlet holes 515 corresponding to the two ends of the annular slots 516 on one side; and eight annular slots 516 corresponding to the other side; the third-stage throttle 513 has sixteen anode air outlet holes 517 and cathode air outlet holes 518 corresponding to the two ends of the annular slots 516.

[0031] The working process is as follows: the working gas enters the anode buffer chamber 15 from the vent rod 12, diffuses in the anode buffer chamber 15, and a part of it flows into the anode inlet hole 514 of the first-level throttle 511 in the throttle 51, diffuses through the annular slot 516, passes through the second-level throttle 512, and diffuses from the anode outlet hole 517 in the third-level throttle 513 to the anode channel 16; the other part of the working gas enters the cathode buffer chamber 17 from the cathode vent 19, and then flows into the cathode inlet hole 515 of the first-level throttle 511 in the throttle 51, diffuses through the annular slot 516, passes through the second-level throttle 512, and diffuses from the cathode outlet hole 518 in the third-level throttle 513 to the cathode channel 18. By setting the throttle 51, the working gas in the anode channel 16 and the cathode channel 18 is homogenized, and the axial movement speed of the gas molecules is reduced, so that the working gas is fully ionized and the performance of the thruster is improved. In addition, its flow resistance can effectively throttle the gas, thereby jointly ensuring that the uniformity and flow rate of the working gas entering the cathode and anode channels 16 meet the technical requirements.

[0032] The heater 7 , the heat shield 8 and the emitter 6 are located on both sides of the inner peripheral wall of the insulating ceramic 3 , and the heat shield 8 separates the heater 7 from the inner magnet 9 .

[0033] Installation steps are formed on both sides of the inner wall of the insulating ceramic 3. The inner guard ring 10 is installed on the inner periphery of the insulating ceramic 3, and the outer guard ring 4 is installed on the outer periphery of the insulating ceramic 3. A mounting groove for installing the emitter 6 is formed between the inner guard ring 10 and the mounting steps on the inner side of the inner periphery of the insulating ceramic 3, and a mounting groove for installing the heater 7 and the heat insulation screen 8 is formed between the inner guard ring 10 and the mounting steps on the outer side of the inner periphery of the insulating ceramic 3; a mounting groove for installing the external magnet 2 is formed between the outer guard ring 4 and the support frame 11.

[0034] A portion of emitter 6 corresponds to the outer wall of anode channel 16, while the other portion is located in the discharge channel 14 region. Inner guard ring 10 is provided with inner edge protection 20, which surrounds emitter 6 in the discharge channel 14 region. Outer guard ring 4 is provided with outer edge protection 21, which surrounds insulating ceramic 3 in the discharge channel 14 region. Housing 1 encloses outer magnet 2 and secures outer guard ring 4.

[0035] The embodiments described above are merely descriptions of preferred implementations of the present invention and are not intended to limit the scope of the present invention. Without departing from the spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by ordinary technicians in this field should fall within the scope of protection determined by the claims of the present invention.

Claims

1. An integrated magnetic anode Hall thruster, comprising an anode (5), characterized in that: The anode (5) is divided into an anode chamber and a cathode chamber. The anode chamber is divided into an anode buffer chamber (15) and an anode channel (16) through a throttle (51). The cathode chamber is divided into a cathode buffer chamber (17) and a cathode channel (18) through a throttle (51). The anode buffer chamber (15) is connected to the ventilation rod (12). The anode buffer chamber (15) and the cathode buffer chamber (17) are connected via the cathode vent (19). A portion of the working gas enters the anode channel (16) from the anode buffer chamber (15) through the throttle (51), and the other portion enters the cathode buffer chamber (17) through the cathode vent (19) and enters the cathode channel (18) through the throttle (51).

2. The integrated magnetic anode Hall thruster according to claim 1, characterized in that: The anode (5) is made of soft magnetic material, and a discharge channel (14) is formed above the anode channel (16).

3. The integrated magnetic anode Hall thruster according to claim 1, characterized in that: The throttle (51) comprises a first-stage throttle (511), a second-stage throttle (512) and a third-stage throttle (513); the first-stage throttle (511) is provided with an anode air inlet (514) and a cathode air inlet (515) on one side, and an annular slot (516) corresponding to the anode air inlet (514) and the cathode air inlet (515) on the other side; the second-stage throttle (512) is provided with an anode air inlet (514) and a cathode air inlet (515) corresponding to both ends of the annular slot (516) on one side, and an annular slot (516) corresponding to both ends of the anode air inlet (514) and the cathode air inlet (515) on the other side; and the third-stage throttle (513) is provided with an anode air outlet (517) and a cathode air outlet (518) corresponding to both ends of the annular slot (516).

4. The integrated magnetic anode Hall thruster according to claim 3, characterized in that: One side of the first-stage throttle (511) is provided with four anode air inlet holes (514) and cathode air inlet holes (515), and the other side is provided with four annular slots (516); one side of the second-stage throttle (512) is provided with eight anode air inlet holes (514) and cathode air inlet holes (515), and the other side is provided with eight annular slots (516); and the third-stage throttle (513) is provided with sixteen anode air outlet holes (517) and cathode air outlet holes (518).

5. The integrated magnetic anode Hall thruster according to claim 1, characterized in that: Also includes: Support frame (11); The insulating ceramic (3) is arranged on the support frame (11), the insulating ceramic (3) has a mounting chamber (13), and the anode (5) is arranged in the mounting chamber (13); the ventilation rod (12) passes through the support frame (11), the insulating ceramic (3) and is in communication with the anode buffer chamber (15); An external magnet (2) is arranged on the outer periphery of the insulating ceramic (3); An inner magnet (9) is arranged on the inner periphery of the insulating ceramic (3); The cathode assembly is mounted on the insulating ceramic (3) and is located at the upper center of the anode (5).

6. The integrated magnetic anode Hall thruster according to claim 5, characterized in that: The cathode assembly comprises an emitter (6), a heater (7) and a heat shield (8), wherein the heater (7), the heat shield (8) and the emitter (6) are located on both sides of the inner peripheral wall of the insulating ceramic (3), and the heat shield (8) separates the heater (7) from the inner magnet (9).

7. The integrated magnetic anode Hall thruster according to claim 6, characterized in that: The insulating ceramic (3) further comprises an inner protective ring (10) and an outer protective ring (4), wherein mounting steps are respectively formed on both sides of the inner peripheral wall of the insulating ceramic (3), the inner protective ring (10) is mounted on the inner periphery of the insulating ceramic (3), and the outer protective ring (4) is mounted on the outer periphery of the insulating ceramic (3), a mounting groove for mounting the emitter (6) is formed between the inner protective ring (10) and the mounting steps on the inner side of the inner peripheral wall of the insulating ceramic (3), and a mounting groove for mounting the heater (7) and the heat shield (8) is formed between the inner protective ring (10) and the mounting steps on the outer side of the inner peripheral wall of the insulating ceramic (3); and a mounting groove for mounting the outer magnet (2) is formed between the outer protective ring (4) and the support frame (11).

8. The integrated magnetic anode Hall thruster according to claim 7, characterized in that: A portion of the emitter (6) corresponds to the outer wall of the anode channel (16), and another portion is located in the discharge channel (14) region. The inner guard ring (10) is provided with an inner guard edge (20), and the inner guard edge (20) wraps the emitter (6) located in the discharge channel (14) region. The outer guard ring (4) is provided with an outer guard edge (21), and the outer guard edge (21) wraps the insulating ceramic (3) located in the discharge channel (14) region.

9. The integrated magnetic anode Hall thruster according to claim 8, characterized in that: It also includes a housing (1) mounted on the support frame (11), wherein the housing (1) encloses the outside of the outer magnet (2) and fixes the outer protective ring (4).

10. A spacecraft, characterized in that It comprises an integrated magnetic anode Hall thruster according to any one of claims 1-8, wherein the spacecraft is a satellite or a space station.

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