Buffer cavity structure of hall thruster and hall thruster

Abstract

The application discloses a buffer cavity structure of a Hall thruster and the Hall thruster, and relates to the technical field of Hall thrusters. The buffer cavity structure comprises: at least two air inlet components, each having an air inlet, and the other end of each air inlet component being connected to a first buffer cavity; the first buffer cavity is used for connecting the air inlet components, and the side wall of the first buffer cavity is provided with a first air hole, so that the first air hole is communicated with a second buffer cavity; the second buffer cavity is provided with a second air hole, and the second buffer cavity is sealed based on the first buffer cavity except the second air hole; and the position of the second air hole does not correspond to the position of the first air hole. The buffer cavity structure optimizes the structure of the air supply buffer cavity of the Hall thruster, so that the air outlet speed of the buffer cavity is more uniform, and the uniformity of ion distribution is improved.

Description

Technical Field

[0001] This application relates to the field of satellite equipment technology, and in particular to a buffer cavity structure for a Hall thruster and a Hall thruster. Background Technology

[0002] Hall thrusters are a type of plasma discharge device widely used in space propulsion. They utilize electrical energy to ionize propellant into plasma, which is then accelerated within a channel to generate thrust. Hall thrusters offer advantages such as high specific impulse, high efficiency, and long lifespan. Using Hall electric propulsion systems can reduce the mass of propellant carried by satellites, increase the satellite's payload ratio, and lower launch costs. They are widely used in satellite orbit maintenance, orbit transfer, and main propulsion for deep space exploration.

[0003] The existing Hall thruster has poor uniformity of gas flow out of the buffer chamber outlet, and the flow rate of multiple outlets is inconsistent, which affects the uniformity of plasma distribution and thrust skew and other technical indicators. Summary of the Invention

[0004] This application provides a buffer chamber structure and a Hall thruster to optimize the structure of the air supply buffer chamber of the Hall thruster, making the air outlet velocity of the buffer chamber more uniform, thereby improving the uniformity of ion distribution and improving technical indicators such as thrust deflection.

[0005] This application provides a buffer cavity structure for a Hall thruster, including:

[0006] At least two air intake components are provided, each having an air intake port and the other end of the air intake port being connected to a first buffer chamber. The at least two air intake components are distributed and arranged based on the first buffer chamber.

[0007] The first buffer chamber is used to connect to the air intake assembly. The side opposite to the air intake assembly is sealed, and a first air hole is provided on its side wall to communicate with the second buffer chamber based on the first air hole.

[0008] The second buffer chamber is provided with a second air hole, and except for the second air hole, it is sealed based on the first buffer chamber. The position of the second air hole does not correspond to the position of the first air hole.

[0009] Optionally, the buffer cavity structure is generally ring-shaped, and at least two of the air intake components are arranged circumferentially based on the buffer cavity structure.

[0010] Optionally, the first buffer cavity is also annular in shape, with the first air hole provided on its radial sidewall, and the first buffer cavity is sealed circumferentially by a cover plate except for the first air hole.

[0011] Optionally, the second buffer cavity has an annular structure, and the second air hole is provided in its circumferential direction.

[0012] Optionally, the radial relative positions of the second pore and the radial relative positions of the first pore are intersected.

[0013] Optionally, the number of the air intake components is 2, and they are symmetrically distributed based on the first buffer cavity.

[0014] This application also proposes a Hall thruster, including the buffer cavity structure of the Hall thruster as described above.

[0015] The embodiments of this application optimize the structure of the Hall thruster air supply buffer chamber by distributing at least two air intake components based on the first buffer chamber, and by cooperating with other structures, thereby making the air outlet velocity of the buffer chamber more uniform and thus improving the uniformity of ion distribution.

[0016] The above description is only an overview of the technical solution of this application. In order to better understand the technical means of this application and to implement it in accordance with the contents of the specification, and to make the above and other objects, features and advantages of this application more obvious and understandable, the following are specific embodiments of this application. Attached Figure Description

[0017] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of this application. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings:

[0018] Figure 1 This is a cross-sectional schematic diagram of the buffer cavity structure according to an embodiment of this application;

[0019] Figure 2 This is an example of the first buffer cavity structure in an embodiment of this application;

[0020] Figure 3 This is an example of the external structure of the first buffer cavity in an embodiment of this application;

[0021] Figure 4 This is a partial structural example of the connection between the air intake assembly and the first buffer cavity in an embodiment of this application.

[0022] Figure 5 This is an example diagram of an explosion of the buffer cavity structure according to an embodiment of this application. Detailed Implementation

[0023] Exemplary embodiments of the present disclosure will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.

[0024] This application provides a buffer cavity structure for a Hall thruster, such as... Figure 1 , Figure 5 As shown, it includes:

[0025] The air intake assembly 4, at least two in number, has an air intake port 41, and the other end opposite to the air intake port 41 is connected to the first buffer cavity 2, and the at least two air intake assemblies are distributed based on the first buffer cavity 2.

[0026] The first buffer chamber 2 is used to connect to the air intake assembly 4. Its side facing the air intake assembly 4 is sealed, and its sidewall is provided with a first air hole 22 for communication with the second buffer chamber 1. Specifically, as follows... Figure 1 As shown, the first buffer cavity 2 can be implemented based on the corresponding first component 21. For example, the first component 21 is closed based on the cover plate 3 to form the first buffer cavity 2.

[0027] The second buffer chamber 1 is provided with a second vent 12, and except for the second vent 12, it is sealed based on the first buffer chamber 2. The position of the second vent 12 does not correspond to the position of the first vent 21. Specifically, the second buffer chamber 1 can be sealed based on the first component 21 of the second buffer chamber 1. For example, the first component 21 can be placed inside the second buffer chamber 1, thereby realizing the air passage connection between the first buffer chamber 2 and the second buffer chamber 1 based on the first vent 21. Similarly, the second flushing chamber 1 can also be implemented based on the second component 11.

[0028] The embodiments of this application optimize the structure of the Hall thruster air supply buffer chamber by distributing at least two air intake components 4 based on the first buffer chamber 2, and by cooperating with other structures, thereby making the air outlet speed of the buffer chamber more uniform and thus improving the uniformity of ion distribution.

[0029] In existing technologies, after gas enters the primary buffer chamber, uniform gas distribution is desired. However, the flow rate at the outlet of the buffer chamber, which is farther from the inlet, is relatively low, resulting in uneven gas distribution and large flow rate deviations at the outlet, thus failing to achieve the desired effect. In some embodiments, such as Figure 2As shown, the buffer chamber structure is generally ring-shaped, and at least two of the air intake components are circumferentially distributed based on the buffer chamber structure. Specifically, two, three, or even more sets of air intake components can be provided, thereby improving the uniformity of gas distribution based on multiple sets of air intake components and the first buffer chamber 2. In some embodiments, the number of air intake components is two, and they are symmetrically distributed based on the first buffer chamber. By designing two sets of air intake components and symmetrically distributing them, the desired uniform gas distribution can be achieved while facilitating welding.

[0030] In some embodiments, such as Figure 2 As shown, the first buffer cavity 2 also has an annular structure, and the first air hole 22 is provided on its radial sidewall. In addition to the first air hole 22, the first buffer cavity 2 is sealed in the circumferential direction based on the cover plate 3.

[0031] In some embodiments, such as Figure 3 As shown, the second buffer cavity 1 has an annular structure, and the second air hole 12 is provided in its circumferential direction.

[0032] In some embodiments, the radial relative positions of the second vent 12 and the first vent 22 are intersected. In some specific examples, the first vents 22 are evenly distributed along the circumferential direction and symmetrically distributed on both sides of the line connecting the centers of the two air inlets. The air outlets (first vents 22) of the first buffer chamber 2 are provided on the inner and outer sidewalls of the buffer chamber, and the number of first vents 22 can be 12 to 32. Figure 3 As shown, the second air holes 12 of the second buffer chamber 1 are evenly distributed along the circumferential direction, and the center of the two holes on the left and right is located on the line connecting the centers of the air inlet 1 and the air inlet 2 or its extension line; the number of air outlets of the secondary buffer chamber is 6 to 16, for example, it can be half of the number of the first air holes 22, and they are distributed intersectingly with the first air holes 22.

[0033] like Figure 4 As shown, in this embodiment of the application, a first seal 23 is provided between the air intake assembly 4 and the first buffer chamber 2, and between the first buffer chamber 2 and the cover plate 3. This seal can be, for example, a welded seal. A second seal 13 is provided between the first buffer chamber 2 and the second buffer chamber 1, which can also be a welded seal. Specifically, a circular continuous welding method can be used to complete the welded seal.

[0034] This application embodiment designs at least two sets of air intake components, improving the uniformity of gas distribution within the first buffer chamber. A second buffer chamber structure is designed so that the uniformity of gas distribution is further improved after gas enters from the first buffer chamber. Simultaneously, a sealed welding method is employed to prevent various malfunctions caused by leakage.

[0035] This application also proposes a Hall thruster, including the buffer cavity structure of the Hall thruster as described above.

[0036] It should be noted that, in this document, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Unless otherwise specified, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes that element.

[0037] The sequence numbers of the embodiments in this application are for descriptive purposes only and do not represent the superiority or inferiority of the embodiments.

[0038] The embodiments of this application have been described above with reference to the accompanying drawings. However, this application is not limited to the specific embodiments described above. The specific embodiments described above are merely illustrative and not restrictive. Those skilled in the art can make many other forms under the guidance of this application without departing from the spirit and scope of the claims. All of these forms are within the protection scope of this application.

Claims

1. A buffer chamber structure for a Hall thruster, characterized in that, include: At least two air intake components are provided, each having an air intake port and the other end of the air intake port being connected to a first buffer chamber. The at least two air intake components are distributed and arranged based on the first buffer chamber. The first buffer chamber is used to connect to the air intake assembly. The side opposite to the air intake assembly is sealed, and a first air hole is provided on its side wall to communicate with the second buffer chamber based on the first air hole. The second buffer chamber is provided with a second air hole, and except for the second air hole, it is sealed based on the first buffer chamber. The position of the second air hole does not correspond to the position of the first air hole. The first buffer cavity is also annular in shape, with the first air hole provided on its radial sidewall, and the first buffer cavity is sealed circumferentially by the cover plate except for the first air hole. The second buffer cavity has an annular structure, and the second air hole is provided on its circumference; The radial relative positions of the second pore and the first pore are intersected. The buffer cavity structure is generally ring-shaped, and at least two of the air intake components are arranged circumferentially based on the buffer cavity structure.

2. The buffer chamber structure of the Hall thruster as described in claim 1, characterized in that, The number of air intake components is 2, and they are symmetrically distributed based on the first buffer cavity.

3. A Hall thruster, characterized in that, Includes the buffer cavity structure of the Hall thruster as described in claim 1 or 2.

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