Integrated magnetic anode hall thruster and spacecraft

Abstract

The application 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 chamber and a cathode chamber, the anode chamber is divided into an anode buffer chamber and an anode channel through a throttle, the cathode chamber is divided into a cathode buffer chamber and a cathode channel through a throttle, the anode buffer chamber is communicated with a vent rod, and the anode buffer chamber and the cathode buffer chamber are communicated through a cathode vent hole. Part of working gas enters the anode channel through the throttle from the anode buffer chamber, and the other part enters the cathode channel through the throttle from the cathode buffer chamber through the cathode vent hole. The application integrates the anode channel, the cathode channel, the throttle element and the magnetic shielding structure in the anode, homogenizes the working gas in the anode channel and the cathode channel, reduces the axial speed of the working gas, fully ionizes the working gas, and improves the performance of the thruster.

Description

Technical Field

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

[0002] Hall thrusters are an advanced space propulsion technology that is currently widely used in missions such as spacecraft attitude and orbit control. Compared with other thrusters, they have advantages such as simple structure, high specific impulse, and long lifespan, and can meet the power requirements of large-scale satellite constellations, effectively reducing satellite mass and lowering constellation costs.

[0003] Hall thrusters can be divided into two basic configurations: stationary plasma thrusters (SPT) and thrusters with an anode layer (TAL). The latter uses a metallic discharge channel and has a shorter acceleration region. Both employ a hollow cathode as a seed electron source, which is confined by orthogonal electromagnetic fields to collide and ionize with the working gas, accelerating the ejected ions to generate thrust. The hollow cathode is typically installed as an independent component, mainly in external or central placement configurations. It requires specific assembly tools, insulation and heat protection measures, and independent electrical and gas circuits to ensure its normal operation.

[0004] The existing application (CN201910670105.0) describes a thruster structure that deeply integrates a hollow cathode into 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 plays the role of the original cathode contact electrode. Using this device to replace the original combination of Hall thruster and hollow cathode can significantly reduce the total mass of the electric propulsion system, thereby increasing the payload. Although the above solution can solve the problems of independent cathode circuit and gas path, it requires the setting of certain assembly tooling and insulation and heat insulation measures, and the overall structure is slightly bulky, increasing the system complexity.

[0005] Furthermore, the working gas diffuses directly in the discharge chamber channel, resulting in poor uniformity and high axial velocity. This leads to poor uniformity and quantity of electrons generated, affecting thruster performance. Additionally, charged particles, under the influence of the magnetic field, sputter and bombard the anode channel and thruster structure within the discharge channel, impacting the thruster's service life. Summary of the Invention

[0006] To address the above problems, the present invention provides an integrated magnetic anode Hall thruster.

[0007] The present invention adopts the following technical solution:

[0008] This invention discloses an integrated magnetic anode Hall thruster, comprising an anode, which is divided into an anode chamber and a cathode chamber. The anode chamber is further divided into an anode buffer chamber and an anode channel by a throttle device. The cathode chamber is also divided into a cathode buffer chamber and a cathode channel by a throttle device. The anode buffer chamber is connected to a venting rod, and the anode buffer chamber and the cathode buffer chamber are connected by a cathode vent. Part of the working gas enters the anode channel from the anode buffer chamber through the throttle device, and the other part enters the cathode buffer chamber through the cathode vent and then enters the cathode channel through the throttle device.

[0009] By adopting the above scheme, the throttling elements of the cathode and anode can also be integrated together, which can homogenize the working gas in the anode and cathode channels, reduce its axial velocity, and enable the working gas to be fully ionized, thereby improving the performance of the thruster. This simplified design cannot be achieved if the conventional hollow cathode is placed in the middle.

[0010] The present invention discloses an integrated magnetic anode Hall thruster, wherein the anode is made of soft magnetic material and a discharge channel is formed above the anode channel.

[0011] By adopting the above scheme, there are no magnetic induction lines in the anode channel, and the strongest magnetic field is pushed outward relative to the thruster outlet. This effectively alleviates the sputtering corrosion of the anode channel by ions, avoids the phenomenon of metal excess in the anode layer Hall thruster, and thus effectively extends the thruster life and improves operational reliability.

[0012] This invention discloses an integrated magnetic anode Hall thruster. Further, the throttling device includes a primary throttling device, a secondary throttling device, and a tertiary throttling device. The primary throttling device has an anode inlet and a cathode inlet on one side, and an annular slot corresponding to the anode inlet and cathode inlet on the other side. The secondary throttling device has an anode inlet and a cathode inlet on one side corresponding to both ends of the annular slot, and an annular slot corresponding to both the anode inlet and cathode inlet on the other side. The tertiary throttling device has an anode outlet and a cathode outlet corresponding to both ends of the annular slot.

[0013] By adopting the above scheme, the working gas enters the anode buffer chamber from the venting rod and diffuses within the anode buffer chamber. A portion flows into the anode inlet of the first-stage throttling device, diffuses through the annular slot, passes through the second-stage throttling device, and diffuses from the anode outlet of the third-stage throttling device to the anode channel. The other portion of the working gas enters the cathode buffer chamber from the cathode inlet, then flows into the cathode inlet of the first-stage throttling device, diffuses through the annular slot, passes through the second-stage throttling device, and diffuses from the cathode outlet of the third-stage throttling device to the cathode channel. By setting up throttling devices, the working gas in the anode and cathode channels is homogenized, and the axial velocity of the gas molecules is reduced, allowing for sufficient ionization of the working gas, improving the propeller performance. Furthermore, the flow resistance effectively throttles the gas flow, thus ensuring that the uniformity and flow rate of the working gas entering the cathode and anode channels meet the technical requirements.

[0014] The present invention discloses an integrated magnetic anode Hall thruster. Further, the first-stage throttle is provided with four anode air inlets and four cathode air inlets on one side and four annular slots on the other side; the second-stage throttle is provided with eight anode air inlets and eight cathode air inlets on one side and eight annular slots on the other side; the third-stage throttle is provided with sixteen anode air outlets and sixteen cathode air outlets.

[0015] The present invention provides an integrated magnetic anode Hall thruster, which further includes:

[0016] Support frame;

[0017] An insulating ceramic is mounted on a support frame, and the insulating ceramic has an installation chamber. The anode is located in the installation chamber. The vent rod passes through the support frame, the insulating ceramic, and communicates with the anode buffer chamber.

[0018] The external magnet is located on the outer periphery of the insulating ceramic.

[0019] An internal magnet is located on the inner circumference of an insulating ceramic.

[0020] The cathode assembly is mounted on insulating ceramic and located at the upper center of the anode.

[0021] By adopting the above scheme, the insulating ceramic isolates the discharge channel from the external magnet, internal magnet, heater, etc.

[0022] The present invention discloses an integrated magnetic anode Hall thruster. Further, the cathode assembly includes an emitter, a heater, and a heat shield. The heater, the heat shield, and the 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.

[0023] This invention discloses an integrated magnetic anode Hall thruster, further comprising an inner retaining ring and an outer retaining ring. Mounting steps are formed on both sides of the inner peripheral wall of the insulating ceramic. The inner retaining ring is mounted on the inner periphery of the insulating ceramic, and the outer retaining ring is mounted on the outer periphery of the insulating ceramic. An mounting groove for mounting an emitter is formed between the inner retaining ring and the mounting steps on the inner side of the inner peripheral wall of the insulating ceramic, and an mounting groove for mounting a heater and a heat shield is formed between the inner retaining ring and the mounting steps on the outer side of the inner peripheral wall of the insulating ceramic. An mounting groove for mounting an external magnet is formed between the outer retaining ring and the support frame.

[0024] The present invention discloses an integrated magnetic anode Hall thruster. Further, a portion of the emitter corresponds to the outer wall of the anode channel, and another portion is located in the discharge channel region. The inner protective ring is provided with an inner protective edge, which wraps around the emitter located in the discharge channel region. The outer protective ring is provided with an outer protective edge, which wraps around the insulating ceramic located in the discharge channel region.

[0025] By adopting the above scheme, a protective structure for the thruster is formed, preventing the structure from being bombarded by ions and extending its service life.

[0026] The present invention provides an integrated magnetic anode Hall thruster, which further includes a housing mounted on a support frame, the housing enclosing the outer side of the outer magnet and fixing the outer protective ring.

[0027] The present invention also provides a spacecraft including the aforementioned integrated magnetic anode Hall thruster, wherein the spacecraft is a satellite or a space station.

[0028] The above-mentioned solution provides support and protection.

[0029] Compared with the prior art, the present invention has the following beneficial effects:

[0030] 1. This application integrates the anode channel, cathode channel, throttling element, and magnetic shielding structure into the anode. On one hand, this homogenizes the working gas within the anode and cathode channels, reducing its axial velocity and ensuring full ionization of the working gas, thus improving thruster performance. On the other hand, it eliminates magnetic induction lines within the anode channel and shifts the strongest magnetic field point outwards relative to the thruster outlet, effectively mitigating ion sputtering corrosion of the anode channel and preventing the accumulation of excess metal in the anode layer Hall thruster. This effectively extends thruster life and improves operational reliability. Furthermore, it significantly simplifies the system structure, reduces structural dimensions, and optimizes thruster performance. In addition, this integration allows for the integration of the throttling elements of the cathode and anode. This simplified design cannot be achieved using a hollow cathode with a centrally located cathode.

[0031] 2. By setting inner and outer protective rings, the thruster structure is further protected from ion bombardment, thus extending the thruster's service life;

[0032] 3. Traditional Hall thrusters typically use a hollow cathode as a separate component, either externally placed around the thruster or located at the center. This invention integrates the cathode assembly into the center of the thruster, sharing a buffer cavity with the anode, significantly reducing the structural size. Furthermore, the emitted electrons are ring-shaped, providing a uniform electron source for the peripheral anode discharge channel. Simultaneously, using the anode to provide the high potential required for ionization reduces the number of power supply channels in the power processing unit, simplifying system design.

[0033] 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 a soft magnetic material, thus enabling the anode channel to also have a magnetic shielding effect, eliminating the need for additional magnetic shielding structures on both sides and greatly simplifying the structural design.

[0034] 5. Traditional Hall thrusters integrate the throttling element into the flow regulation module. This invention, by integrating the throttling element into the anode, effectively simplifies the overall system design. This invention replaces the traditional anode gas distributor with a throttling device, which can both homogenize the working gas and provide different flow rates of working gas to the cathode and anode.

[0035] 6. Reduced system complexity. This invention integrates the throttling element of the flow regulation module in a traditional Hall thruster into the anode. By modifying the gas distributor, it enables it to have a throttling function, which can both homogenize the chemical gas and ensure that the flow rate in the cathode and anode channels meets the technical requirements.

[0036] 7. Optimized cathode electron source. This invention integrates the cathode assembly into the center of the thruster, utilizing the inner wall of the anode to provide a high ignition potential, thereby forming a ring-shaped electron source. Compared to the beam-like electron source of traditional cathode assemblies, this ring-shaped electron source offers significant improvements in uniformity and quantity. Therefore, it can effectively improve thruster performance;

[0037] 8. Reduced system size and weight. This invention optimizes the structural design, reduces modular components, and significantly shrinks the system size by integrating the magnetic shielding structure and throttling element into the anode and integrating the cathode assembly into the center of the thruster, effectively reducing the overall weight.

[0038] The invention will now be further described with reference to the accompanying drawings. Attached Figure Description

[0039] Figure 1 This is a schematic diagram of the structure of the present invention;

[0040] Figure 2 This is a schematic diagram illustrating the operation of the present invention;

[0041] Figure 3 This is a schematic diagram of the throttle structure of the present invention;

[0042] Figure 4 This is a schematic diagram illustrating the anodic magnetic shielding effect of the present invention.

[0043] Figure label:

[0044] 1. Outer shell; 2. Outer magnet; 3. Insulating ceramic; 4. Outer retaining ring; 5. Anode; 6. Emitter; 7. Heater; 8. Heat shield; 9. Inner magnet; 10. Inner retaining ring; 11. Support frame; 12. Vent rod; 13. Installation chamber; 14. Discharge channel; 15. Anode buffer chamber; 16. Anode channel; 17. Cathode buffer chamber; 18. Cathode channel; 19. Cathode vent; 20. Inner edge; 21. Outer edge; 51. Throttling device; 511. First-stage throttling device; 512. Second-stage throttling device; 513. Third-stage throttling device; 514. Anode inlet; 515. Cathode inlet; 516. Annular slot; 517. Anode outlet; 518. Cathode outlet. Detailed Implementation

[0045] like Figures 1-4 As shown, this invention discloses an integrated magnetic anode Hall thruster, comprising a shell 1, an outer magnet 2, an insulating ceramic 3, an outer protective ring 4, an anode 5, an emitter 6, a heater 7, a heat shield 8, an inner magnet 9, an inner protective ring 10, a support frame 11, and a ventilation rod 12. The support frame 11 has an overall T-shaped structure. The insulating ceramic 3 has an annular cylindrical structure and is mounted on the support frame 11. The insulating ceramic 3 has an installation chamber 13, in which the anode 5 is located. The outer magnet 2 is located on the outer periphery of the insulating ceramic 3, and the inner magnet 9 is located on the inner periphery of the insulating ceramic 3. The outer magnet 2 and the inner magnet 9 form a radial magnetic field to trap electrons and ionize the working gas. The emitter 6, heater 7, and heat shield 8 constitute a cathode assembly for generating an electron source, mounted on the insulating ceramic 3 and located at the upper center of the anode 5. A discharge channel 14 is formed between the inner retaining ring 10 and the outer retaining ring 4 to protect the thruster structure from ion bombardment; the insulating ceramic 3 insulates and separates the discharge channel 14 from the outer magnet 2, the inner magnet 9, the heater 7, etc.

[0046] The anode 5 is divided into an anode chamber and a cathode chamber, which are integrated into one structure. 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 vent 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 a cathode vent hole 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 hole 19 and enters the cathode channel 18 through the throttle 51. The anode 5 is made of soft magnetic material, allowing the inner and outer walls of the anode channel 16 to serve as diffusion channels for the working gas, as well as to provide high potential ionization for the working gas within the anode 5 and cathode channel 18. It also forms a magnetic shielding structure, eliminating magnetic induction lines within the anode channel 16 and pushing the strongest magnetic field outwards from the thruster outlet. A discharge channel 14 is formed above the anode channel 16, effectively mitigating sputter corrosion of the anode channel 16 by ions and preventing the accumulation of excess metal in the Hall thruster layer of the anode 5. This effectively extends the thruster's lifespan and improves operational reliability. The anode 5 serves the following functions: the working gas flows from the vent rod 12 into the throttle 51, creating different flow rates and homogenizing them within the cathode channel 18 and anode channel 16; it generates a high potential in the anode 5, producing a cathode ignition potential; and it also forms a magnetic shielding effect.

[0047] The working principle of this application is as follows: the working gas flows from the venting 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 homogenize them in the anode channel 16 and the cathode channel 18; the heater 7 heats the emitter 6, and when it reaches the working 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, in which electrons are drawn out under the high potential; the outer magnet 2 and the inner magnet 9 form a radial magnetic field, which forms an orthogonal electromagnetic field with the anode 5, and is used to bind the emitted electrons of the cathode assembly to ionize the working gas in the discharge channel 14 to generate plasma, in which ions are accelerated and ejected under the action of the electric field, generating thrust.

[0048] The throttle device 51 includes a primary throttle device 511, a secondary throttle device 512, and a tertiary throttle device 513. The primary throttle device 511 has four anode inlet holes 514 and four cathode inlet holes 515 on one side, and four annular slots 516 corresponding to the anode inlet holes 514 and cathode inlet holes 515 on the other side. The secondary throttle device 512 has eight anode inlet holes 514 and eight cathode inlet holes 515 on one side, respectively, corresponding to the two ends of the annular slots 516. The tertiary throttle device 513 has sixteen anode outlet holes 517 and sixteen cathode outlet holes 518 corresponding to the two ends of the annular slots 516.

[0049] The working process is as follows: the working gas enters the anode buffer chamber 15 from the vent rod 12 and diffuses within the anode buffer chamber 15. A portion of the working gas flows into the anode inlet 514 of the first-stage throttle 511 in the throttle 51, diffuses through the annular slot 516, passes through the second-stage throttle 512, and diffuses from the anode outlet 517 in the third-stage throttle 513 to the anode channel 16. Another portion of the working gas enters the cathode buffer chamber 17 from the cathode vent 19, and then flows into the cathode inlet 515 of the first-stage throttle 511 in the throttle 51, diffuses through the annular slot 516, passes through the second-stage throttle 512, and diffuses from the cathode outlet 518 in the third-stage throttle 513 to the cathode channel 18. By setting the throttle 51, the working gas in the anode channel 16 and cathode channel 18 is homogenized, and the axial velocity of the gas molecules is reduced, so that the working gas is fully ionized, improving the performance of the thruster. In addition, its flow resistance can effectively throttle the gas, thereby ensuring that the uniformity and flow rate of the working gas entering the cathode and anode channels 16 meet the technical requirements.

[0050] 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. The heat shield 8 separates the heater 7 from the inner magnet 9.

[0051] The inner circumferential wall of the insulating ceramic 3 has mounting steps formed on both sides. The inner protective ring 10 is installed on the inner circumference of the insulating ceramic 3, and the outer protective ring 4 is installed on the outer circumference of the insulating ceramic 3. The inner protective ring 10 and the mounting steps on the inner side of the inner circumferential wall of the insulating ceramic 3 form a mounting groove for installing the emitter 6, and the inner protective ring 10 and the mounting steps on the outer side of the inner circumferential wall of the insulating ceramic 3 form a mounting groove for installing the heater 7 and the heat insulation screen 8. The outer protective ring 4 and the support frame 11 form a mounting groove for installing the outer magnet 2.

[0052] One part of the emitter 6 corresponds to the outer wall of the anode channel 16, and the other part is located in the discharge channel 14 region. The inner guard ring 10 is provided with an inner guard edge 20, which wraps around the emitter 6 located in the discharge channel 14 region. The outer guard ring 4 is provided with an outer guard edge 21, which wraps around the insulating ceramic 3 located in the discharge channel 14 region. The outer shell 1 encloses the outer magnet 2 and fixes the outer guard ring 4.

[0053] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Various modifications and improvements made by those skilled in the art to the technical solutions of the present invention without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.

Claims

1. An integrated magnetic anode Hall thruster comprising an anode, characterized in that, Also comprising: a support frame; an insulating ceramic provided on the support frame, the insulating ceramic having a mounting cavity on it, and an anode provided in the mounting cavity; a vent rod passing through the support frame and the insulating ceramic and communicating with an anode buffer cavity of the anode; an outer magnet provided on the outer periphery of the insulating ceramic; an inner magnet provided on the inner periphery of the insulating ceramic; a cathode assembly mounted on the insulating ceramic and located at the upper center of the 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 passage by a restrictor, the cathode cavity is divided into a cathode buffer cavity and a cathode passage by a restrictor, the anode buffer cavity communicates with the vent rod, and the anode buffer cavity and the cathode buffer cavity communicate with each other through a cathode vent hole; a part of the working medium gas enters the anode passage from the anode buffer cavity through the restrictor, and another part enters the cathode buffer cavity through the cathode vent hole and enters the cathode passage through the restrictor; the upper part of the anode passage forms a discharge passage; the restrictor comprises a primary restrictor, a secondary restrictor and a tertiary restrictor, one side of the primary restrictor is provided with anode gas inlet holes and cathode gas inlet holes, and the other side is provided with annular groove holes corresponding to the anode gas inlet holes and the cathode gas inlet holes respectively; one side of the secondary restrictor is provided with anode gas inlet holes and cathode gas inlet holes corresponding to the two ends of the annular groove holes, and the other side is provided with annular groove holes corresponding to the anode gas inlet holes and the cathode gas inlet holes respectively; the tertiary restrictor is provided with anode gas outlet holes and cathode gas outlet holes corresponding to the two ends of the annular groove holes; one side of the primary restrictor is provided with four anode gas inlet holes and four cathode gas inlet holes respectively, and the other side is provided with four annular groove holes respectively; one side of the secondary restrictor is provided with eight anode gas inlet holes and eight cathode gas inlet holes respectively, and the other side is provided with eight annular groove holes respectively; the tertiary restrictor is provided with sixteen anode gas outlet holes and sixteen cathode gas outlet holes respectively; the cathode assembly comprises an emitter, a heater and a heat shield, the heater, the heat shield and the emitter are located on both sides of the inner periphery wall of the insulating ceramic, and the heat shield separates the heater from the inner magnet; one part of the emitter corresponds to the outer wall of the anode passage, and the other part is located in the discharge passage region.

2. The integrated magnetic anode Hall thruster of claim 1, wherein, The anode is made of soft magnetic material.

3. The integrated magnetic anode Hall thruster of claim 1, wherein, It also comprises an inner retaining ring and an outer retaining ring, the inner periphery wall of the insulating ceramic is formed with mounting steps on both sides, the inner retaining ring is mounted on the inner periphery of the insulating ceramic, the outer retaining ring is mounted on the outer periphery of the insulating ceramic, the inner retaining ring and the mounting steps on the inner side of the inner periphery wall of the insulating ceramic form a mounting groove for mounting the emitter, and the mounting steps on the outer side of the inner periphery wall of the insulating ceramic form a mounting groove for mounting the heater and the heat shield; the outer retaining ring and the support frame form a mounting groove for mounting the outer magnet.

4. The integrated magnetic anode Hall thruster of claim 3, wherein, The inner retaining ring is provided with an inner retaining edge, and the inner retaining edge wraps the emitter located in the discharge passage region; the outer retaining ring is provided with an outer retaining edge, and the outer retaining edge wraps the insulating ceramic located in the discharge passage region.

5. An integrated magnetic anode Hall thruster according to claim 4, characterized in that It also comprises a shell mounted on the support frame, the shell is wrapped outside the outer magnet and fixes the outer retaining ring.

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