High-emissivity ion thruster discharge chamber anode cylinder

Abstract

The invention relates to the technical field of spaceflight electric propulsion, in particular to a high-emissivity ion thruster discharge chamber anode cylinder which comprises an anode cylinder body, topological protruding ribs, dot matrix protruding structures and a micro-arc oxidation coating, the anode cylinder body is an anode of an ion thruster, and the whole anode cylinder body is of a thin-wall rotary body structure; the topological convex ribs are distributed on the outer surface of the anode cylinder body in a criss-cross manner; the dot matrix bulge structures are distributed on the outer surface of the anode cylinder body and are positioned in areas between the adjacent staggered topological bulge ribs; and the micro-arc oxidation coating is coated on the outer surfaces of the topological convex ribs and the dot matrix convex structures. The micro convex prismatic table and convex rib structures are designed on the outer surface of the anode cylinder of the discharge chamber, so that the heat dissipation area of the anode cylinder is increased, and meanwhile, the outer surface of the anode cylinder is coated with the micro-arc oxidation coating with high emissivity, so that the heat transfer efficiency of the whole discharge chamber is improved, and the temperature of the anode cylinder of the discharge chamber when the ion thruster works is effectively reduced.

Description

Technical Field

[0001] The present application relates to the field of aerospace electric propulsion technology, and more specifically, to an anode cylinder of a high-emissivity ion thruster discharge chamber. Background Art

[0002] An ion thruster is an advanced space power device, mainly used to perform tasks such as spacecraft orbit transfer, position holding, orbit maintenance, and deep space exploration. When the ion thruster ignites, the internal plasma continuously heats the discharge chamber, causing the temperature of the discharge chamber parts to be relatively high, resulting in thermal deformation of high-precision mechanical structures such as the grid system, leading to a decrease in the beam extraction efficiency of the ion thruster, a reduction in thrust and specific impulse, and affecting the mission of the model.

[0003] The on-orbit working environment of the ion thruster is in a high-vacuum state, and heat dissipation can only be achieved through radiation. In the fields of all-electric propulsion orbit transfer, deep space exploration, and interplanetary transfer, etc., the ion thruster is required to work with long-term ignition. To ensure the stable operation of the thruster, it is required that the discharge chamber of the ion thruster applied to the above fields has good heat dissipation performance. Summary of the Invention

[0004] The present application provides an anode cylinder of a high-emissivity ion thruster discharge chamber, which can effectively improve the heat transfer efficiency of the discharge chamber and solve the problem of excessive temperature of the discharge chamber parts caused by the long-term operation of the ion thruster.

[0005] To achieve the above object, the present application provides an anode cylinder of a high-emissivity ion thruster discharge chamber, including an anode cylinder body, topological convex ribs, a dot matrix convex structure, and a micro-arc oxidation coating, wherein: the anode cylinder body is the anode of the ion thruster, and the overall structure is a thin-walled rotating body; the topological convex ribs are distributed on the outer surface of the anode cylinder body in a criss-cross manner; the dot matrix convex structure is distributed on the outer surface of the anode cylinder body in the area between adjacent and intersecting topological convex ribs; the micro-arc oxidation coating is coated on the outer surfaces of the topological convex ribs and the dot matrix convex structure.

[0006] Furthermore, the anode cylinder body, the topological convex ribs, and the dot matrix convex structure are an integrated structure and are prepared by an additive manufacturing-based process.

[0007] Furthermore, the width of the topological convex ribs is 3-4 mm, and the thickness is 1 mm.

[0008] Furthermore, the dot matrix convex structure is composed of multiple hexagonal prisms with the same height. The height of the hexagonal prism is 0.2 mm, the diameter of the circumscribed circle is 0.5 mm, and the center distance between the circumscribed circles of adjacent two hexagonal prisms is 0.75 mm.

[0009] Furthermore, the micro-arc oxidation coating is prepared from a high-emissivity material, and the emissivity > 0.90.

[0010] The anode cylinder of the discharge chamber of the high-emissivity ion thruster provided by this application has the following beneficial effects:

[0011] This application is an integrated discharge chamber part processed based on the additive manufacturing process. It has a simple structure. By designing micro-protruding frustum and protruding rib structures on the outer surface of the anode cylinder of the discharge chamber, the heat dissipation area of the anode cylinder is increased. At the same time, a micro-arc oxidation coating with high emissivity is coated on its outer surface, improving the heat transfer efficiency of the overall discharge chamber and effectively reducing the temperature of the anode cylinder of the discharge chamber when the ion thruster is working. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] The drawings forming a part of this application are used to provide a further understanding of this application, making other features, objectives, and advantages of this application more obvious. The schematic embodiments and descriptions of the drawings of this application are used to explain this application and do not constitute an improper limitation of this application. In the drawings:

[0013] Figure 1 is a schematic diagram of the anode cylinder of the high-emissivity ion thruster discharge chamber provided according to an embodiment of this application;

[0014] Figure 2 is a schematic diagram of the dot matrix protruding structure provided according to an embodiment of this application;

[0015] In the figure: 1 - anode cylinder body, 2 - topological protruding rib, 3 - dot matrix protruding structure. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0016] In order to enable those skilled in the art to better understand the solution of this application, the technical solutions in the embodiments of this application will be clearly and completely described below in conjunction with the drawings in the embodiments of this application. Obviously, the described embodiments are only a part of the embodiments of this application, rather than all the embodiments. Based on the embodiments in this application, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the scope of protection of this application.

[0017] It should be noted that the terms "first", "second", etc. in the specification and claims of this application and the above drawings are used to distinguish similar objects and do not necessarily need to describe a specific order or sequence. It should be understood that such data can be interchanged under appropriate circumstances for the embodiments of this application described here. In addition, the terms "include" and "have" and any variations thereof are intended to cover non-exclusive inclusion. For example, a process, method, system, product, or device that includes a series of steps or units does not necessarily need to be limited to those steps or units clearly listed, but may include other steps or units not clearly listed or inherent to these processes, methods, products, or devices.

[0018] In this application, the orientation or positional relationship indicated by terms such as "upper", "lower", "left", "right", "front", "rear", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal", etc. is based on the orientation or positional relationship shown in the drawings. These terms are mainly used to better describe this application and its embodiments, and are not used to limit that the indicated devices, elements, or components must have a specific orientation, or be constructed and operated in a specific orientation.

[0019] Moreover, in addition to being able to represent the orientation or positional relationship, some of the above terms may also be used to represent other meanings. For example, the term "upper" may also be used to represent a certain attachment relationship or connection relationship in some cases. For those of ordinary skill in the art, the specific meanings of these terms in this application can be understood according to the specific circumstances.

[0020] In addition, the meaning of the term "a plurality of" should be two or more.

[0021] It should be noted that, without conflict, the embodiments in this application and the features in the embodiments can be combined with each other. The following will describe this application in detail with reference to the drawings and in combination with the embodiments.

[0022] As Figure 1 shown, this application provides a high-emissivity ion thruster discharge chamber anode cylinder, including an anode cylinder body 1, topological convex ribs 2, a dot matrix convex structure 3, and a micro-arc oxidation coating. Among them: The anode cylinder body 1 is the anode of the ion thruster, and is an overall thin-walled rotary body structure; The topological convex ribs 2 are distributed crisscross on the outer surface of the anode cylinder body 1; The dot matrix convex structure 3 is distributed on the outer surface of the anode cylinder body 1, in the area between adjacent and intersecting topological convex ribs 2; The micro-arc oxidation coating is coated on the outer surfaces of the topological convex ribs 2 and the dot matrix convex structure 3.

[0023] Specifically, the high-emissivity ion thruster discharge chamber anode cylinder provided by the embodiments of this application mainly optimizes the structure of the discharge chamber anode cylinder, increases the heat dissipation area of the discharge chamber, and applies the high-emissivity micro-arc oxidation coating technology to improve the heat dissipation efficiency of the discharge chamber, and solves the problem of excessive temperature of the discharge chamber caused by the long-term operation of the ion thruster.

[0024] Furthermore, the anode cylinder body 1, the topological convex ribs 2, and the dot matrix convex structure 3 are of an integrated structure and are prepared by an additive manufacturing-based process. In the embodiment of the present application, the anode cylinder body 1 of the ion thruster discharge chamber is a thin-walled rotating body structure processed based on the additive manufacturing process, and the topological convex ribs 2 and the dot matrix convex structure 3 are arranged on its outer surface. Among them, the topological convex ribs 2 and the dot matrix convex structure 3 and the anode cylinder body 1 are of an integrated structure and are jointly prepared by the additive manufacturing process, shortening the processing cycle of the discharge chamber; the topological convex ribs 2 are arranged vertically and horizontally along the anode cylinder body 1, and the dot matrix convex structure 3 is arranged inside the intersecting area thereof, that is, the dot matrix convex structure 3 is distributed in the area of the outer surface of the anode cylinder body 1 without the topological convex ribs 2.

[0025] Furthermore, the width of the topological convex rib 2 is 3-4 mm, and the thickness is 1 mm. The topological convex ribs 2 are distributed on the outer surface of the anode cylinder. On the one hand, it can increase the heat dissipation area of the discharge chamber. On the other hand, it can act as a reinforcing rib, effectively suppressing the thermal deformation of the discharge chamber during operation and ensuring the stable operation of the ion thruster.

[0026] Furthermore, as Figure 2 shown, the dot matrix convex structure 3 is composed of multiple hexagonal prisms with the same height. The height of the hexagonal prism is 0.2 mm, the diameter of the circumscribed circle is 0.5 mm, and the center distance of the circumscribed circles of two adjacent hexagonal prisms is 0.75 mm. The dot matrix convex structure 3 also plays a role in increasing the heat dissipation area. The dot matrix convex structure 3 is formed by an array of multiple hexagonal prisms with the same height, and its side and top surfaces both have the function of heat dissipation; among them, the height of the hexagonal prism is preferably 0.2 mm, the diameter of the circumscribed circle is preferably 0.5 mm, and the center distance of the circumscribed circles of two adjacent hexagonal prisms is preferably 0.75 mm, which can increase the heat dissipation area of the discharge chamber by 2.85 times.

[0027] Furthermore, the micro-arc oxidation coating is prepared from a material with a high emissivity, and the emissivity > 0.90. The micro-arc oxidation coating is integrally coated on the outer surfaces of the topological convex ribs 2 and the dot matrix convex structure 3. On the one hand, it can improve the overall emissivity of the anode cylinder. On the other hand, it is jointly superimposed with the topological convex ribs 2 and the dot matrix convex structure 3, greatly improving the heat dissipation efficiency of the discharge chamber.

[0028] The above are only the preferred embodiments of the present application and are not used to limit the present application. For those skilled in the art, various changes and modifications can be made to the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A high-emissivity anode cylinder of an ion thruster discharge chamber, characterized in that, It includes an anode cylinder body, topological raised ribs, a lattice raised structure and a micro-arc oxidation coating, wherein: The anode cylinder body is the anode of the ion thruster, and is a thin-walled rotating body structure as a whole; The topological raised ribs are distributed in a crisscross pattern on the outer surface of the anode cylinder body; The dot matrix protrusion structure is distributed on the outer surface of the anode cylinder body, and is located in the area between the adjacent staggered topological protrusion ribs; The micro-arc oxidation coating is coated on the outer surfaces of the topological raised ribs and the lattice raised structures.

2. The anode cylinder of the discharge chamber of the high-emissivity ion thruster according to claim 1, wherein The anode cylinder body, the topological raised ribs and the lattice raised structure are an integrated structure, which are manufactured by a process based on additive manufacturing.

3. The anode cylinder of the discharge chamber of the high-emissivity ion thruster according to claim 2, characterized in that, The topological raised ribs have a width of 3-4 mm and a thickness of 1 mm.

4. The anode cylinder of the discharge chamber of the high-emissivity ion thruster according to claim 3, characterized in that, The dot matrix protrusion structure is composed of a plurality of hexagonal pyramids of equal height, the height of the hexagonal pyramid is 0.2 mm, the diameter of the circumscribed circle is 0.5 mm, and the distance between the centers of the circumscribed circles of two adjacent hexagonal pyramids is 0.75 mm.

5. The anode cylinder of the discharge chamber of the high-emissivity ion thruster according to claim 4, characterized in that, The micro-arc oxidation coating is made of high-emissivity material, and the emissivity is greater than 0.90.

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