Miniature light-weight electric thruster gas circuit insulation device

Abstract

The invention relates to the technical field of spaceflight electric propulsion, in particular to a miniature light-weight electric thruster gas circuit insulation device which comprises a first gas circuit connector, a second gas circuit connector and a ceramic gas circuit main insulator. A spiral slender air supply channel is arranged in an inner cavity of the shell; the first gas path joint is welded at the front end of the ceramic gas path main insulator, and the second gas path joint is welded at the rear end of the ceramic gas path main insulator; working medium gas sequentially passes through the first gas path connector, the gas supply channel of the ceramic gas path main insulator and the second gas path connector and enters the electric thruster. According to the electric thruster, the ceramic insulation material spiral slender inner cavity air supply channel can be directly integrally formed and manufactured, the structural complexity of the electric thruster is remarkably reduced, the insulation and pressure resistance of the air path insulation device is improved on the basis of light weight and miniaturization, and the on-orbit reliability of the electric thruster is improved.

Description

Technical Field

[0001] The present application relates to the field of aerospace electric propulsion technology, and more particularly, to a gas path insulation device for a micro lightweight electric thruster. Background Art

[0002] Electric propulsion has become a hallmark of advanced satellite platforms due to its advantages such as high specific impulse and long life, providing power for spacecraft. In the field of interstellar deep space exploration, electric thrusters have received widespread attention from various countries and have been applied in engineering. Electric thrusters generate thrust by ionizing a gas working medium into plasma and accelerating and extracting ions. The working medium gas requires a gas path insulation device to achieve reliable high-voltage insulation between the electric thruster storage and supply system and the electric thruster.

[0003] Currently, gas path insulation devices using the multi-stage voltage division principle require an increase in the number of insulation stages when higher voltage withstand requirements are needed, which will lead to an increase in the axial length of the gas path insulation device, a decrease in mechanical strength, and an increase in weight. Gas path insulation devices using the single-stage voltage division principle have their ceramic main insulators processed and combined into a gas supply channel by means of engraving, grinding, etc. They are large in volume, heavy in mass, complex in structure, and complex in process. Moreover, due to the inability to be integrally formed, there is a risk of air leakage in practical applications, and they cannot meet the higher voltage withstand performance requirements.

[0004] Currently, electric thrusters are developing rapidly, especially with the application of nuclear power in the future, there is an urgent need for gas path insulation devices and design methods with smaller volume, lighter weight, and higher voltage withstand performance. Summary of the Invention

[0005] The present application provides a gas path insulation device for a micro lightweight electric thruster. The main insulator is integrally formed based on additive manufacturing, improving the overall insulation voltage withstand performance.

[0006] To achieve the above object, the present application provides a gas path insulation device for a micro lightweight electric thruster, including a first gas path joint, a second gas path joint, and a ceramic gas path main insulator, wherein: the ceramic gas path main insulator is integrally formed by additive manufacturing, and a spiral-shaped slender gas supply channel is provided in its internal cavity; the first gas path joint is welded to the front end of the ceramic gas path main insulator, and the second gas path joint is welded to the rear end of the ceramic gas path main insulator; the working medium gas sequentially passes through the first gas path joint, the gas supply channel of the ceramic gas path main insulator, and the second gas path joint and enters the electric thruster.

[0007] Further, the first gas path joint includes a first joint, a first fastening nut, a first gas channel, and a first welding and fixing portion, wherein: the first gas channel is integrally formed with the first welding and fixing portion; the first joint is provided at the front end of the first gas channel; the first fastening nut is sleeved on the outer wall of the first gas channel; the first welding and fixing portion is welded to the front end of the ceramic gas path main insulator.

[0008] Further, the second gas path connector includes a second connector, a second fastening nut, a second gas channel, and a second welding and fixing portion, where: the second gas channel is integrally formed with the second welding and fixing portion; the second connector is arranged at the rear end of the second gas channel; the second fastening nut is sleeved on the outer wall of the second gas channel; the second welding and fixing portion is welded to the rear end of the ceramic gas path main insulator.

[0009] Further, both the first gas channel and the second gas channel communicate with the spiral air supply channel in the inner cavity of the ceramic gas path main insulator.

[0010] Further, the cross-sectional area of the spiral air supply channel ≤ 4.5 mm 2 。

[0011] Further, the material of the ceramic gas path main insulator is alumina.

[0012] Further, the materials of both the first gas path connector and the second gas path connector are kovar alloy.

[0013] A gas path insulation device for a micro lightweight electric thruster provided by the present application has the following beneficial effects:

[0014] The present application can directly realize the integrally formed manufacturing of the spiral slender inner cavity air supply channel of the ceramic insulation material, significantly reduce the structural complexity of the electric thruster, improve the insulation withstand voltage performance of the gas path insulation device on the basis of lightweight and miniaturization, and enhance the on-orbit reliability of the electric thruster. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The drawings constituting a part of the present application are used to provide a further understanding of the present application, making other features, objects, and advantages of the present application more obvious. The schematic embodiments and descriptions thereof of the present application are used to explain the present application and do not constitute an improper limitation of the present application. In the drawings:

[0016] Figure 1 is a schematic diagram of a gas path insulation device for a micro lightweight electric thruster provided by an embodiment of the present application;

[0017] Figure 2 is a schematic diagram of the first gas path connector (second gas path connector) provided by an embodiment of the present application;

[0018] In the figure: 1 - first gas path connector, 11 - first connector, 12 - first fastening nut, 13 - first gas channel, 14 - first welding and fixing portion, 2 - second gas path connector, 21 - second connector, 22 - second fastening nut, 23 - second gas channel, 24 - second welding and fixing portion, 3 - ceramic gas path main insulator, 4 - air supply channel. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0019] 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 with reference to the accompanying 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. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in this application without creative efforts shall fall within the scope of protection of this application.

[0020] It should be noted that the terms "first", "second", etc. in the specification, claims and the above-mentioned drawings of this application 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 herein. In addition, the terms "comprising" and "having" 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 have 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.

[0021] In this application, the orientation or positional relationship indicated by the terms "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 accompanying 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.

[0022] Moreover, in addition to being able to represent an 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 specific circumstances.

[0023] In addition, the meaning of the term "plurality" should be two or more.

[0024] 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 detail this application with reference to the drawings and in combination with the embodiments.

[0025] Such as Figure 1As shown in the figure, the present application provides a gas path insulation device for a micro lightweight electric thruster, which includes a first gas path joint 1, a second gas path joint 2, and a ceramic gas path main insulator 3, where: the ceramic gas path main insulator 3 is integrally formed by additive manufacturing, and its internal chamber is provided with a spiral slender gas supply channel 4; the first gas path joint 1 is welded to the front end of the ceramic gas path main insulator 3, and the second gas path joint 2 is welded to the rear end of the ceramic gas path main insulator 3; the working medium gas sequentially passes through the first gas path joint 1, the gas supply channel 4 of the ceramic gas path main insulator 3, and the second gas path joint 2 and enters the electric thruster.

[0026] Specifically, the gas path insulation device for the micro lightweight electric thruster provided in the embodiment of the present application is mainly arranged between the propellant storage and supply system of the electric thruster and the electric thruster, and is used to achieve reliable insulation of the working medium gas. Among them, the ceramic gas path main insulator 3 is the main structure of the insulation device, and is integrally processed by additive manufacturing, that is, the ceramic gas path main insulator 3 is a hollow cylinder, and a spiral gas supply channel 4 is arranged inside it. The overall structure is integrally formed by 3D printing technology, without a mold, with good sealing performance and good pressure resistance; the first gas path joint 1 is fixedly welded to the front end of the ceramic gas path main insulator 3 and is connected to the gas storage supply device; the second gas path joint 2 is fixedly welded to the rear end of the ceramic gas path main insulator 3 and is connected to the electric thruster; during operation, the working medium gas in the gas storage supply device enters the internal chamber of the ceramic gas path main insulator 3 through the first gas path joint 1, passes through the spiral gas supply channel 4, and then enters the electric thruster through the second gas path joint 2 to achieve high-pressure insulation of the gas.

[0027] Furthermore, the first gas path joint 1 includes a first joint 11, a first fastening nut 12, a first gas channel 13, and a first welding and fixing part 14, where: the first gas channel 13 is integrally formed with the first welding and fixing part 14; the first joint 11 is arranged at the front end of the first gas channel 13; the first fastening nut 12 is sleeved on the outer wall of the first gas channel 13; the first welding and fixing part 14 is welded to the front end of the ceramic gas path main insulator 3.

[0028] Furthermore, the second gas path joint 2 includes a second joint 21, a second fastening nut 22, a second gas channel 23, and a second welding and fixing part 24, where: the second gas channel 23 is integrally formed with the second welding and fixing part 24; the second joint 21 is arranged at the rear end of the second gas channel 23; the second fastening nut 22 is sleeved on the outer wall of the second gas channel 23; the second welding and fixing part 24 is welded to the rear end of the ceramic gas path main insulator 3.

[0029] Specifically, as Figure 2As shown in the figure, the first gas path connector 1 is used for the entry of gas. The first connector 11 is used for assembling and connecting with the gas storage and supply device of the working medium gas. The first fastening nut 12 is used for fixing the whole connector. The first gas channel 13 is used for the flow entry of the working medium gas. The first welding and fixing part 14 is integrally formed with the first gas channel 13 and is used for welding and fixing with the front end of the ceramic gas path main insulator 3. The second gas path connector 2 is used for the discharge of gas. The second connector 21 is used for assembling and connecting with the electric thruster. The second fastening nut 22 is used for fixing the whole connector. The second gas channel 23 is used for the flow discharge of the working medium gas to make it enter the interior of the electric thruster. The second welding and fixing part 24 is integrally formed with the second gas channel 23 and is used for welding and fixing with the rear end of the ceramic gas path main insulator 3.

[0030] Further, both the first gas channel 13 and the second gas channel 23 are communicated with the spiral gas supply channel 4 in the inner chamber of the ceramic gas path main insulator 3.

[0031] Further, the cross-sectional area of the spiral gas supply channel 4 ≤ 4.5mm 2 .

[0032] Specifically, the inner chamber of the ceramic gas path main insulator 3 is provided with an integrally formed spiral gas supply channel 4, mainly to extend the path of the gas, evenly distribute the gas, inhibit the plasma backflow, and enhance the overall insulation performance. In the embodiment of the present application, the maximum cross-sectional area of the spiral gas supply channel 4 does not exceed 4.5mm 2 .

[0033] Further, the material of the ceramic gas path main insulator 3 is alumina.

[0034] Further, the materials of both the first gas path connector 1 and the second gas path connector 2 are kovar alloy.

[0035] Specifically, under a vacuum degree of 1×10 -3 Pa, a withstand voltage test is carried out. At the working medium gas flow rate test points of 0, 1.088, 2.04, 3.264, 4.08, 5.168, 6.528mg / s and a test time of 120s, the micro lightweight electric thruster gas path insulation device provided by the embodiment of the present application has passed the 3000V withstand voltage test, meets the withstand voltage requirements of a 10kW electric thruster, and has passed the 1600g mechanical shock experiment. It can be seen from this that the micro lightweight electric thruster gas path insulation device provided by the embodiment of the present application not only significantly reduces the complexity of the electric thruster structure, but also greatly improves the insulation withstand voltage performance of the gas path insulation device on the basis of lightweight and miniaturization, and improves the on-orbit reliability of the electric thruster.

[0036] The above are only the preferred embodiments of the present application and are not intended 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 within the protection scope of the present application.

Claims

1. A gas path insulation device for a micro lightweight electric thruster, characterized in that It includes a first gas path joint, a second gas path joint, and a ceramic main gas path insulator, where: The ceramic main gas path insulator is integrally formed by additive manufacturing, and a spiral slender gas supply channel is arranged in its internal cavity; The first gas path joint is welded to the front end of the ceramic main gas path insulator, and the second gas path joint is welded to the rear end of the ceramic main gas path insulator; The working medium gas sequentially passes through the first gas path joint, the gas supply channel of the ceramic main gas path insulator, and the second gas path joint and enters the electric thruster.

2. The gas path insulation device of the micro lightweight electric thruster according to claim 1, characterized in that, The first gas path joint includes a first joint, a first fastening nut, a first gas channel, and a first welding and fixing part, where: The first gas channel is integrally formed with the first welding and fixing part; The first joint is arranged at the front end of the first gas channel; The first fastening nut is sleeved on the outer wall of the first gas channel; The first welding and fixing part is welded to the front end of the ceramic main gas path insulator.

3. The gas path insulation device of the micro lightweight electric thruster according to claim 2, characterized in that The second gas path joint includes a second joint, a second fastening nut, a second gas channel, and a second welding and fixing part, where: The second gas channel is integrally formed with the second welding and fixing part; The second joint is arranged at the rear end of the second gas channel; The second fastening nut is sleeved on the outer wall of the second gas channel; The second welding and fixing part is welded to the rear end of the ceramic main gas path insulator.

4. The gas path insulation device of the micro lightweight electric thruster according to claim 3, characterized in that Both the first gas channel and the second gas channel are communicated with the spiral gas supply channel in the internal cavity of the ceramic main gas path insulator.

5. The gas path insulation device of the micro lightweight electric thruster according to claim 4, characterized in that, The cross-sectional area of the spiral air supply channel ≤ 4.5 mm 2 .

6. The gas path insulation device of the micro lightweight electric thruster according to claim 5, characterized in that The material of the ceramic main gas path insulator is alumina.

7. The gas path insulation device of the micro lightweight electric thruster according to claim 6, characterized in that The materials of both the first gas path joint and the second gas path joint are kovar alloy.

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