Composite discharge cavity of high-power Hall thruster

Abstract

The invention relates to the technical field of spaceflight space electric propulsion, in particular to a high-power Hall thruster composite discharge cavity which comprises a ceramic outer ring, a ceramic inner ring, an integrated module, a ceramic base and an air supply pipe. The ceramic inner ring is arranged at the top end of the integrated module inner ring structure; the ceramic outer ring is arranged at the top end of the integrated module outer ring structure; an inner air supply chamber is arranged on the outer wall of the inner ring structure of the integrated module, and an outer air supply chamber is arranged on the inner wall of the outer ring structure; a lower air supply chamber is arranged between the bottom end of the integrated module and the ceramic base; and one end of the air supply pipe penetrates through the ceramic base and is communicated with the lower air supply chamber. The gas supply structures of the inner and outer side walls are added, gas can be directly supplied to the ionization area in the radial direction, the neutral gas density of the ionization area is greatly improved, accordingly, working medium ionization can be enhanced, the working medium utilization rate is increased, and the high-efficiency purpose of the thruster is achieved.

Description

Technical Field

[0001] This application relates to the field of aerospace electric propulsion technology, and more specifically, to a high-power Hall thruster composite discharge cavity. Background Technology

[0002] With the planning and implementation of large-scale space missions such as large-scale orbital transfers, deep space exploration, and large space tugs, efficient and advanced space propulsion is required to support them. These large-scale space missions are characterized by high speed increments and large payloads. Traditional chemical propulsion has low energy density and low specific impulse, which would lead to a significant increase in the launch weight of the spacecraft to low Earth orbit, exceeding the launch capacity and failing to meet application requirements. High-power Hall thrusters (typically with power exceeding 10kW) have outstanding advantages such as high specific impulse, high thrust-to-power ratio, and high technological maturity, making them particularly suitable for use as space propulsion for the aforementioned large-scale missions.

[0003] The Hall thruster discharge chamber mainly consists of an anode, a gas distributor, and an integrated ceramic chamber (an axisymmetric, one-end-opening, annular hollow structure). The ceramic chamber is the main body of the discharge chamber, carrying the anode and gas distributor. The anode is usually placed at the bottom of the discharge chamber, collecting electrons in the discharge chamber to form a discharge circuit and maintain the continuous and stable discharge of the thruster. The working fluid enters the discharge chamber through the gas distributor at the bottom of the ceramic chamber, where it couples and matches with the externally applied electric and magnetic fields, ionizing to form plasma and accelerating to generate thrust.

[0004] The discharge chamber is the most crucial component of a Hall thruster. As power increases, the discharge chamber diameter also increases, reaching over 1 meter. This makes the one-piece molding of the integrated ceramic discharge chamber more difficult and hinders its performance in aerospace mechanical testing. Furthermore, traditional bottom-supply methods for ceramic chambers make it difficult to achieve high working fluid density in the ionization region of a wide-diameter discharge chamber, limiting the efficient utilization of the working fluid. Therefore, a discharge chamber suitable for high-power Hall thrusters needs to be designed that is easy to engineer, enables efficient working fluid feeding, and achieves efficient coupling with electric and magnetic fields to achieve the high efficiency of high-power Hall thrusters. Additionally, it is worth noting that high-power Hall thrusters currently employ magnetic shielding technology to reduce the impact of plasma on the discharge chamber walls, particularly in the middle and bottom of the chamber. This also provides support for the design of novel discharge chambers. Summary of the Invention

[0005] This application provides a high-power Hall thruster composite discharge cavity, which realizes a composite ceramic cavity with a mixed structure of metal and ceramic, thereby improving the utilization rate of the working fluid.

[0006] To achieve the above objectives, this application provides a high-power Hall thruster composite discharge cavity, comprising a ceramic outer ring, a ceramic inner ring, an integrated module, a ceramic base, and a gas supply pipe, wherein: the integrated module integrates the anode and the gas distributor together, forming a ring structure; the integrated module is fixed above the ceramic base; the ceramic inner ring is located at the top of the inner ring structure of the integrated module; the ceramic outer ring is located at the top of the outer ring structure of the integrated module; a discharge cavity is formed between the inner ring structure, the outer ring structure, and the ceramic base; an inner gas supply chamber is provided on the outer wall of the inner ring structure, and an outer gas supply chamber is provided on the inner wall of the outer ring structure; a lower gas supply chamber is provided between the bottom of the integrated module and the ceramic base; the lower gas supply chamber is connected to both the inner and outer gas supply chambers; one end of the gas supply pipe passes through the ceramic base and is connected to the lower gas supply chamber.

[0007] Furthermore, both the inner and outer ring structures of the integrated module are made of metal materials.

[0008] Furthermore, the internal air supply chamber includes a first internal air supply chamber and a second internal air supply chamber, wherein: the first internal air supply chamber is located above the second internal air supply chamber; multiple ventilation holes are provided between the first internal air supply chamber and the second internal air supply chamber; and multiple ventilation holes are provided on the outside of the first internal air supply chamber.

[0009] Furthermore, the external air supply chamber includes a first external air supply chamber and a second external air supply chamber, wherein: the first external air supply chamber is located above the second external air supply chamber; multiple vents are provided between the first external air supply chamber and the second external air supply chamber; and multiple vents are provided on the inner side of the first external air supply chamber.

[0010] Furthermore, the lower air supply chamber includes a first lower air supply chamber and a second lower air supply chamber, wherein: the first lower air supply chamber is located above the second lower air supply chamber; multiple vents are provided between the first lower air supply chamber and the second lower air supply chamber; and multiple vents are provided above the first lower air supply chamber.

[0011] Furthermore, multiple ventilation holes are provided between the second lower air supply chamber, the second inner air supply chamber, and the second outer air supply chamber.

[0012] Furthermore, an air outlet baffle is installed above the first lower air supply chamber.

[0013] Furthermore, the contact surfaces of the ceramic outer ring, ceramic inner ring, ceramic base, and integrated module are all covered with copper sheets.

[0014] The high-power Hall thruster composite discharge cavity provided in this application has the following beneficial effects: 1. This application adds a gas supply structure to the inner and outer walls, which can directly supply gas radially to the ionization zone. Under the same flow rate (compared to simple bottom gas supply), the density of neutral gas in the ionization zone can be greatly increased, thereby enhancing the ionization of the working fluid, improving the utilization rate of the working fluid, and achieving the purpose of high thruster efficiency.

[0015] 2. This application uses a composite discharge cavity formed of metal and ceramic to replace the traditional integrated ceramic cavity of low- and medium-power Hall thrusters, which avoids the difficulties in forming ceramic cavities under large diameter and can significantly improve the mechanical adaptability of the discharge cavity.

[0016] 3. This application integrates the anode and gas distributor into a modular design, with the inner and outer ceramic rings and ceramic bases fixed by screws on both the upper and lower parts. The structure is simple, easy to modular design, and improves the versatility of engineering applications. At the same time, a dual-chamber gas supply structure is adopted to fully homogenize the working fluid, which can improve the uniformity of the circumferential gas in the discharge chamber, thereby improving the discharge stability of the thruster. Attached Figure Description

[0017] The accompanying drawings, which form part of this application, are used to provide a further understanding of the application and to make other features, objects, and advantages of the application more apparent. The illustrative embodiments and descriptions of this application are used to explain the application and do not constitute an undue limitation of the application.

[0018] In the attached diagram: Figure 1 This is a planar sectional view of the high-power Hall thruster composite discharge cavity provided according to an embodiment of this application; Figure 2 This is a three-dimensional sectional view of the high-power Hall thruster composite discharge cavity provided according to an embodiment of this application; In the diagram: 1-Ceramic outer ring, 2-Ceramic inner ring, 3-Integrated module, 31-Inner ring structure, 32-Outer ring structure, 33-Discharge chamber, 34-Ion acceleration zone, 35-Gas ionization zone, 4-Ceramic base, 5-Gas supply pipe, 61-First inner gas supply chamber, 62-Second inner gas supply chamber, 71-First outer gas supply chamber, 72-Second outer gas supply chamber, 81-First lower gas supply chamber, 82-Second lower gas supply chamber, 83-Outlet baffle, 9-Ventilation hole. Detailed Implementation

[0019] To enable those skilled in the art to better understand the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present application, and not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative effort should fall within the scope of protection of the present application.

[0020] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this application are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate for the embodiments of this application described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0021] In this application, the terms "upper," "lower," "left," "right," "front," "rear," "top," "bottom," "inner," "outer," "middle," "vertical," "horizontal," "lateral," and "longitudinal" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. These terms are primarily for the purpose of better describing this application and its embodiments, and are not intended to limit the indicated device, element, or component to having a specific orientation, or to be constructed and operated in a specific orientation.

[0022] Furthermore, in addition to indicating location or positional relationship, some of the aforementioned terms may also have other meanings. For example, the term "above" may also be used in some cases to indicate a certain dependency or connection relationship. Those skilled in the art can understand the specific meaning of these terms in this application based on the specific circumstances.

[0023] In addition, the term "multiple" should mean two or more.

[0024] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. This application will now be described in detail with reference to the accompanying drawings and embodiments.

[0025] like Figure 1-2As shown, this application provides a high-power Hall thruster composite discharge cavity, including a ceramic outer ring 1, a ceramic inner ring 2, an integrated module 3, a ceramic base 4, and a gas supply pipe 5, wherein: the integrated module 3 integrates the anode and the gas distributor together, forming a ring structure; the integrated module 3 is fixed above the ceramic base 4; the ceramic inner ring 2 is located at the top of the integrated module's inner ring structure 31; the ceramic outer ring 1 is located at the top of the integrated module's outer ring structure 32; a discharge cavity 33 is formed between the integrated module's inner ring structure 31, the integrated module's outer ring structure 32, and the ceramic base 4; the outer wall of the integrated module's inner ring structure 31 is provided with an inner gas supply chamber, and the inner wall of the outer ring structure 32 is provided with an outer gas supply chamber; a lower gas supply chamber is provided between the bottom end of the integrated module 3 and the ceramic base 4; the lower gas supply chamber is connected to both the inner and outer gas supply chambers; one end of the gas supply pipe 5 passes through the ceramic base 4 and is connected to the lower gas supply chamber.

[0026] Specifically, the high-power Hall thruster composite discharge cavity provided in this application realizes a composite ceramic cavity composed of a metal and ceramic hybrid structure, and is equipped with inner and outer wall gas supply structures, which can directly supply the working fluid radially to the ionization region, improving the working fluid utilization rate and enhancing the thruster efficiency and mechanical adaptability. Among them, the integrated module 3 integrates the anode and gas distributor together, which is processed by 3D printing technology, and includes an outer wall dual-stage gas supply cavity, an inner wall dual-stage cavity, and a bottom dual-stage gas supply cavity, directly injecting gas from both sides and the bottom into the discharge cavity 33, significantly increasing the neutral gas density in the ionization region and enhancing the ionization rate; the ceramic inner ring 2 is fixed to the top of the integrated module inner ring structure 31 by circumferentially evenly distributed screws, and the ceramic outer ring 1 is fixed to the top of the integrated module outer ring structure 32 by circumferentially evenly distributed screws. The space between the ceramic inner ring 2 and the ceramic outer ring 1 forms an ion acceleration region 34, and the ceramic inner ring 2 and the ceramic outer ring 1 are flanged to cover part of the inner and outer metal sidewalls to protect the sidewalls from plasma erosion.

[0027] Furthermore, both the inner ring structure 31 and the outer ring structure 32 of the integrated module are made of metal. The integrated module has a ceramic ring at the top, enabling the separate processing of the large-diameter discharge cavity 33 and avoiding the difficulties of integrated molding of a large-diameter all-ceramic cavity.

[0028] Furthermore, the internal air supply chamber includes a first internal air supply chamber 61 and a second internal air supply chamber 62, wherein: the first internal air supply chamber 61 is located above the second internal air supply chamber 62; a plurality of vent holes 9 are provided between the first internal air supply chamber 61 and the second internal air supply chamber 62; and a plurality of vent holes 9 are provided on the outside of the first internal air supply chamber 61.

[0029] Specifically, 24 vent holes 9 are evenly distributed circumferentially between the second inner gas supply chamber 62 and the second lower gas supply chamber 82 to guide gas from the lower gas supply chamber into the second inner gas supply chamber 62. 24 vent holes 9 are also evenly distributed circumferentially between the second inner gas supply chamber 62 and the first inner gas supply chamber 61 to guide gas from the second inner gas supply chamber 62 into the first inner gas supply chamber 61. 24 vent holes 9 are evenly distributed circumferentially on the outer side of the first inner gas supply chamber 61 to allow gas to enter the discharge chamber 33. The vent holes 9 on the outer side of the first inner gas supply chamber 61 are provided with sidewall protrusions and ceramic flanges to prevent upward gas flow, thus allowing the gas to flow more efficiently into the neutral gas ionization region 35. Depending on the actual situation, the orifice diameter gradually decreases according to the gas flow direction, achieving the purpose of homogenizing the pressurized gas in each chamber.

[0030] Furthermore, the external air supply chamber includes a first external air supply chamber 71 and a second external air supply chamber 72, wherein: the first external air supply chamber 71 is located above the second external air supply chamber 72; a plurality of vent holes 9 are provided between the first external air supply chamber 71 and the second external air supply chamber 72; a plurality of vent holes 9 are provided on the inner side of the first external air supply chamber 71.

[0031] Specifically, 24 vent holes 9 are evenly distributed circumferentially between the second external gas supply chamber 72 and the second lower gas supply chamber 82 to guide gas from the lower gas supply chamber into the second external gas supply chamber 72. 24 vent holes 9 are also evenly distributed circumferentially between the second external gas supply chamber 72 and the first external gas supply chamber 71 to guide gas from the second external gas supply chamber 72 into the first external gas supply chamber 71. 24 vent holes 9 are evenly distributed circumferentially on the inner side of the first external gas supply chamber 71 to allow gas to enter the discharge chamber 33. The vent holes 9 on the outer side of the first external gas supply chamber 71 are provided with sidewall protrusions and ceramic flanges to prevent upward gas flow, allowing the gas to flow more efficiently into the neutral gas ionization region 35. Depending on the actual situation, the orifice diameter gradually decreases according to the gas flow direction, achieving the purpose of homogenizing the pressurized gas in each chamber.

[0032] Furthermore, the lower air supply chamber includes a first lower air supply chamber 81 and a second lower air supply chamber 82, wherein: the first lower air supply chamber 81 is located above the second lower air supply chamber 82; a plurality of vent holes 9 are provided between the first lower air supply chamber 81 and the second lower air supply chamber 82; and a plurality of vent holes 9 are provided above the first lower air supply chamber 81.

[0033] Furthermore, multiple ventilation holes 9 are provided between the second lower air supply chamber 82, the second inner air supply chamber 62, and the second outer air supply chamber 72.

[0034] Specifically, one end of the gas supply pipe 5 passes through the ceramic base 4 and enters the second lower gas supply chamber 82. After the gas enters the second lower gas supply chamber 82, it enters the second inner gas supply chamber 62 and the second outer gas supply chamber 72 through the vent holes 9 on both sides, and enters the first lower gas supply chamber 81 through 24 vent holes 9 evenly arranged around the top. The first lower gas supply chamber 81 also has 24 vent holes 9 evenly arranged around the top. In this way, the gas in the first lower gas supply chamber 81 enters the discharge chamber above through the vent holes 9.

[0035] Furthermore, an exhaust baffle 83 is provided above the first lower gas supply chamber 81. The exhaust baffle 83 is used to suppress the axial velocity of the gas ejected from the vent hole 9 of the lower gas supply chamber. Reducing the velocity helps to prolong the residence time of the gas in the discharge chamber 33 and enhance the ionization rate of the gas.

[0036] Furthermore, the contact surfaces of the ceramic outer ring 1, the inner ceramic ring 2, and the ceramic base 4 with the integrated module 3 are all covered with copper sheets. Thin copper sheets are provided at the contact surfaces between the ceramic outer ring 1 and the inner ceramic ring 2 and the integrated module 3, as well as between the integrated module 3 and the ceramic base 4. This fully utilizes the good ductility of copper to ensure good contact at the contact surfaces, reduces contact thermal resistance, enhances the heat transfer capacity of the discharge cavity 33, and achieves good heat conduction and discharge within the discharge cavity 33.

[0037] The above description is merely a preferred embodiment of this application and is not intended to limit this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A high-power Hall thruster composite discharge cavity, characterized in that, It includes a ceramic outer ring, a ceramic inner ring, an integrated module, a ceramic base, and an air supply pipe, among which: The integrated module combines the anode and gas distributor together in a ring-shaped structure. The integrated module is fixed above the ceramic base; The ceramic inner ring is disposed at the top of the integrated module inner ring structure; The ceramic outer ring is disposed at the top of the integrated module outer ring structure; A discharge cavity is formed between the inner ring structure of the integrated module, the outer ring structure of the integrated module, and the ceramic base; The inner ring structure of the integrated module has an inner air supply chamber on its outer wall, and the outer ring structure has an outer air supply chamber on its inner wall. A lower air supply chamber is provided between the bottom of the integrated module and the ceramic base; The lower air supply chamber is connected to the inner air supply chamber and the outer air supply chamber, respectively; One end of the air supply pipe passes through the ceramic base and communicates with the lower air supply chamber.

2. The high-power Hall thruster composite discharge cavity according to claim 1, characterized in that, Both the inner and outer ring structures of the integrated module are made of metal materials.

3. The high-power Hall thruster composite discharge cavity according to claim 2, characterized in that, The internal air supply chamber includes a first internal air supply chamber and a second internal air supply chamber, wherein: The first internal air supply chamber is located above the second internal air supply chamber; Multiple ventilation holes are provided between the first internal air supply chamber and the second internal air supply chamber; Multiple ventilation holes are provided on the outside of the first internal air supply chamber.

4. The high-power Hall thruster composite discharge cavity according to claim 3, characterized in that, The external air supply chamber includes a first external air supply chamber and a second external air supply chamber, wherein: The first external air supply chamber is located above the second external air supply chamber; Multiple ventilation holes are provided between the first external air supply chamber and the second external air supply chamber; The inner side of the first external air supply chamber is provided with multiple air vents.

5. The high-power Hall thruster composite discharge cavity according to claim 4, characterized in that, The lower air supply chamber includes a first lower air supply chamber and a second lower air supply chamber, wherein: The first lower air supply chamber is located above the second lower air supply chamber; Multiple ventilation holes are provided between the first lower air supply chamber and the second lower air supply chamber; Multiple ventilation holes are provided above the first lower air supply chamber.

6. The high-power Hall thruster composite discharge cavity according to claim 5, characterized in that, Multiple ventilation holes are provided between the second lower air supply chamber and the second inner air supply chamber and the second outer air supply chamber.

7. The high-power Hall thruster composite discharge cavity according to claim 6, characterized in that, An air outlet baffle is provided above the first lower air supply chamber.

8. The high-power Hall thruster composite discharge cavity according to claim 7, characterized in that, The contact surfaces of the ceramic outer ring, the ceramic inner ring, the ceramic base, and the integrated module are all covered with copper sheets.

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