CN116163905A

CN116163905A - Buffer cavity structure of Hall thruster and Hall thruster

Info

Publication number: CN116163905A
Application number: CN202310047598.9A
Authority: CN
Inventors: 王红霞; 李建; 谢侃
Original assignee: Aotian Technology Beijing Co ltd
Current assignee: Aotian Technology Beijing Co ltd
Priority date: 2023-01-31
Filing date: 2023-01-31
Publication date: 2023-05-26

Abstract

The application discloses buffer chamber structure and hall thruster of hall thruster includes: the air inlet assemblies are provided with air inlets, the other ends of the air inlets, which are opposite to the air inlets, are connected into the first buffer cavities, and the at least two air inlet assemblies are distributed and arranged based on the first buffer cavities; the first buffer cavity is used for being connected with the air inlet assembly, one surface of the first buffer cavity, which is opposite to the air inlet assembly, is sealed, and the side wall of the first buffer cavity is provided with a first air hole so as to be communicated with the second buffer cavity based on the first air hole; and the second buffer cavity is provided with a second air hole, and except for the second air hole, the second buffer cavity is sealed based on the first buffer cavity, and the position of the second air hole is not corresponding 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

Buffer cavity structure of Hall thruster and Hall thruster

Technical Field

The application relates to the technical field of satellite equipment, in particular to a buffer cavity structure of a Hall thruster and the Hall thruster.

Background

Hall thrusters are a type of plasma discharge device widely used for space propulsion, which ionize a propellant into plasma using electric energy and accelerate ions in a channel to generate thrust. The Hall thruster has the advantages of high specific impulse, high efficiency, long service life and the like. The Hall electric propulsion system can reduce the mass of the propellant carried by the satellite, improve the effective load ratio of the satellite, reduce the emission cost, and is widely applied to the fields of satellite orbit maintenance, orbit transfer, deep space exploration main propulsion and the like.

The uniformity of the gas flowing out of the buffer cavity of the existing Hall thruster is poor, the flow of a plurality of gas outlets is inconsistent, and the uniformity of plasma distribution, thrust deflection and other technical indexes are affected.

Disclosure of Invention

The embodiment of the application provides a buffer cavity structure of a Hall thruster and the Hall thruster for optimize the structure of the air supply buffer cavity of the Hall thruster, make the speed of giving vent to anger of the buffer cavity more even, thereby improve the homogeneity of ion distribution, improve technical indexes such as thrust deflection.

The embodiment of the application provides a buffer cavity structure of hall thruster, include:

the air inlet assemblies are provided with air inlets, the other ends of the air inlets, which are opposite to the air inlets, are connected into the first buffer cavities, and the at least two air inlet assemblies are distributed and arranged based on the first buffer cavities;

the first buffer cavity is used for being connected with the air inlet assembly, one surface of the first buffer cavity, which is opposite to the air inlet assembly, is sealed, and the side wall of the first buffer cavity is provided with a first air hole so as to be communicated with the second buffer cavity based on the first air hole;

and the second buffer cavity is provided with a second air hole, and except for the second air hole, the second buffer cavity is sealed based on the first buffer cavity, and the position of the second air hole is not corresponding to the position of the first air hole.

Optionally, the buffer cavity structure is an annular structure as a whole, and at least two air inlet components are circumferentially distributed and arranged based on the buffer cavity structure.

Optionally, the first buffer cavity is also in an annular structure, the radial side wall of the first buffer cavity is provided with the first air hole, and the first buffer cavity is sealed based on the cover plate in the circumferential direction except for the first air hole.

Optionally, the second buffer cavity is in an annular structure, and the second air hole is arranged on the circumference of the second buffer cavity.

Optionally, the relative positions of the second air holes in the radial direction and the relative positions of the first air holes in the radial direction are distributed in a crossed mode.

Optionally, the number of the air inlet assemblies is 2, and the air inlet assemblies are symmetrically distributed based on the first buffer cavities.

The embodiment of the application also provides a Hall thruster, which comprises the buffer cavity structure of the Hall thruster.

According to the embodiment of the application, the arrangement is based on the distribution of the first buffer cavities through at least two air inlet assemblies, and the cooperation design of other structures is adopted, so that the structure of the air supply buffer cavities of the Hall thruster is optimized, the air outlet speed of the buffer cavities is more uniform, and the uniformity of ion distribution is improved.

The foregoing description is only an overview of the technical solutions of the present application, and may be implemented according to the content of the specification in order to make the technical means of the present application more clearly understood, and in order to make the above-mentioned and other objects, features and advantages of the present application more clearly understood, the following detailed description of the present application will be given.

Drawings

Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the application. Also, like reference numerals are used to designate like parts throughout the figures. In the drawings:

FIG. 1 is a schematic cross-sectional view of a buffer chamber structure according to an embodiment of the present application;

FIG. 2 is a schematic diagram of a first buffer chamber according to an embodiment of the present application;

FIG. 3 is an example of the external structure of a first buffer chamber according to an embodiment of the present application;

FIG. 4 is a partial structural example of a junction of an air intake assembly and a first buffer chamber of a buffer chamber structure according to an embodiment of the present application;

fig. 5 is an exploded view of a buffer chamber structure according to an embodiment of the present application.

Detailed Description

Exemplary embodiments of the present disclosure will be described in more detail below 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 embodied 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.

The embodiment of the application provides a buffer cavity structure of a hall thruster, as shown in fig. 1 and 5, including:

the air inlet assemblies 4 are at least two, are provided with air inlets 41, the other ends opposite to the air inlets 41 are connected into the first buffer cavities 2, and the at least two air inlet assemblies are distributed and arranged based on the first buffer cavities 2.

The first buffer chamber 2 is used for being connected with the air inlet assembly 4, one surface of the first buffer chamber is sealed opposite to the air inlet assembly 4, and the side wall of the first buffer chamber is provided with a first air hole 22 so as to be communicated with the second buffer chamber 1 based on the first air hole 22. As shown in fig. 1, the first buffer chamber 2 may be implemented based on a corresponding first member 21, for example, the first member 21 may be closed based on the cover plate 3 to form the first buffer chamber 2.

The second buffer chamber 1 is provided with a second air hole 12, and is sealed based on the first buffer chamber 2 except for the second air hole 12, and the position of the second air hole 12 does not correspond to the position of the first air hole 21. The specific second buffer chamber 1 may form a seal based on the first member 21 of the second buffer chamber 1, for example, the first member 21 may be disposed in the second buffer chamber 1, so that the air path communication between the first buffer chamber 2 and the second buffer chamber 1 is realized based on the first air hole 21, and the similar second punching chamber 1 may also be realized based on the second member 11.

According to the embodiment of the application, the at least two air inlet assemblies 4 are distributed and arranged based on the first buffer cavity 2, and the other structures are matched, so that the structure of the air supply buffer cavity of the Hall thruster is optimized, the air outlet speed of the buffer cavity is more uniform, and the uniformity of ion distribution is improved.

In the prior art, after gas enters the first-stage buffer cavity, the gas is expected to be uniformly distributed, but the flow of the gas outlet holes of the buffer cavity far away from the gas inlet is smaller, the gas is unevenly distributed, the flow deviation of the gas outlet of the buffer cavity is large, and the expected effect cannot be achieved. In some embodiments, as shown in fig. 2, the buffer cavity structure is an annular structure as a whole, and at least two air inlet components are circumferentially distributed and arranged based on the buffer cavity structure. In particular, for example, 2, three or more sets of gas inlet assemblies may be provided, so that the uniformity of the gas distribution is improved based on the plurality of sets of gas inlet assemblies, and the first buffer chamber 2. In some embodiments, the number of air intake assemblies is 2 and is symmetrically distributed based on the first buffer chamber. Through design two sets of subassembly and symmetric distribution that admit air, can reach the even effect of anticipated gas distribution under the circumstances of being convenient for weld.

In some embodiments, as shown in fig. 2, the first buffer chamber 2 is also in an annular structure, the radial side wall of which is provided with the first air hole 22, and the first buffer chamber 2 is sealed based on the cover plate 3 in the circumferential direction except for the first air hole 22.

In some embodiments, as shown in fig. 3, the second buffer chamber 1 has a ring structure, and the second air hole 12 is disposed in the circumferential direction of the second buffer chamber.

In some embodiments, the radial relative position of the second air holes 12 is intersected by the radial relative position of the first air holes 22. In some specific examples, the first air holes 22 are uniformly distributed along the circumferential direction and symmetrically distributed on two sides of the central connecting line of the 2 air inlets. The air outlet holes (first air holes 22) of the first buffer cavity 2 are arranged on the two side walls of the inner diameter and the outer diameter of the buffer cavity, and the number of the first air holes 22 can be 12-32. As shown in fig. 3, the second air holes 12 of the second buffer cavity 1 are uniformly distributed along the circumferential direction, and the hole centers of the left and right 2 holes are positioned on the connecting line or the extension line of the centers of the

air inlets

1 and 2; the number of the air outlets of the second-stage buffer cavity is 6-16, and the number of the air outlets can be half of that of the first air holes 22, and the air outlets are distributed across the first air holes 22.

As shown in fig. 4, a first seal 23, which may be, for example, a welded seal, is provided between the cushion chamber structure air intake assembly 4 and the first cushion chamber 2, and between the first cushion chamber 2 and the cover plate 3 in the embodiment of the present application. A second seal 13, for example a welded seal, is provided between the first buffer chamber 2 and the second buffer chamber 1. Specifically, a circular continuous welding mode can be adopted to finish welding sealing.

According to the embodiment of the application, at least two groups of air inlet assemblies are designed, and the uniformity of gas distribution in the first buffer cavity is improved. And after the second buffer cavity structure is designed and gas enters the second buffer cavity from the first buffer cavity, the gas distribution uniformity is further improved. Meanwhile, a sealing mode of sealing welding is adopted, so that various faults caused by leakage are avoided.

It should be noted that, in this document, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.

The foregoing embodiment numbers of the present application are merely for describing, and do not represent advantages or disadvantages of the embodiments.

The embodiments of the present application have been described above with reference to the accompanying drawings, but the present application is not limited to the above-described embodiments, which are merely illustrative and not restrictive, and many forms may be made by those of ordinary skill in the art without departing from the spirit of the present application and the scope of the protection of the claims, which fall within the protection of the present application.

Claims

1. A buffer chamber structure of a hall thruster, comprising:

2. The buffer chamber structure of the hall thruster of claim 1, wherein the buffer chamber structure is an annular structure as a whole, and at least two air inlet assemblies are circumferentially distributed based on the buffer chamber structure.

3. The buffer chamber structure of the hall thruster according to claim 2, wherein the first buffer chamber is also in a ring-shaped structure, the first air holes are provided on the radial side wall of the first buffer chamber, and the first buffer chamber is circumferentially sealed based on a cover plate except for the first air holes.

4. The buffer chamber structure of the hall thruster of claim 3, wherein the second buffer chamber has a ring-shaped structure, and the second air hole is disposed in the circumferential direction of the second buffer chamber.

5. The buffer chamber structure of the hall thruster of claim 4, wherein the relative positions of the second air holes in the radial direction and the relative positions of the first air holes in the radial direction are distributed in a crossing manner.

6. The buffer chamber structure of the hall thruster of claim 1, wherein the number of the air intake assemblies is 2 and is symmetrically distributed based on the first buffer chamber.

7. A hall thruster comprising a buffer chamber structure of a hall thruster according to any one of claims 1-6.