Micro light-weight electric thruster gas path insulation device

Abstract

The application relates to the technical field of space electric propulsion, in particular to a micro lightweight electric thruster gas path insulation device, which comprises a first gas path joint, a second gas path joint and a ceramic gas path main insulation body, wherein: the ceramic gas path main insulation body is integrally formed based on additive manufacturing processing, an internal cavity of the ceramic gas path main insulation body is provided with a spiral-shaped slender gas supply channel; the first gas path joint is welded at the front end of the ceramic gas path main insulation body, and the second gas path joint is welded at the rear end of the ceramic gas path main insulation body; a working medium gas sequentially passes through the first gas path joint, the gas supply channel of the ceramic gas path main insulation body and the second gas path joint, and enters the electric thruster. The application can directly realize the integrally formed manufacturing of the spiral-shaped slender internal cavity gas supply channel of the ceramic insulation material, significantly reduces the structural complexity of the electric thruster, improves the insulation voltage resistance performance of the gas path insulation device on the basis of light weight and miniaturization, and improves the on-orbit reliability of the electric thruster.

Description

TECHNICAL FIELD

[0001] The application relates to the technical field of space electric propulsion, in particular to a micro lightweight electric thruster gas path insulation device. BACKGROUND

[0002] Electric propulsion has become a symbol of advanced satellite platforms due to its high specific impulse and long service life, and provides power for spacecraft. In the field of interstellar deep space exploration, electric thrusters are universally valued and applied in engineering. Electric thrusters generate thrust by ionizing gas working medium into plasma and accelerating the ions. The gas working medium needs a gas path insulation device to achieve high-voltage reliable insulation between the electric thruster storage and supply system and the electric thruster.

[0003] Currently, the gas path insulation device using the multi-stage voltage division principle needs to increase the number of insulation stages when the voltage resistance requirement is higher, which will lead to an increase in the axial length of the gas path insulation device, a decrease in the mechanical strength, an increase in the weight, and the use of the single-stage voltage division principle. The ceramic main insulation body of the gas path insulation device is processed and combined into a gas supply channel by means of engraving, polishing and other methods, which has a large volume, a heavy weight, a complex structure, a complex process, and cannot be integrally formed, and has a risk of gas leakage in actual application, and cannot meet the higher voltage resistance performance.

[0004] Currently, electric thrusters are developing rapidly, and especially the application of nuclear power in the future has put forward urgent needs for gas path insulation devices and design methods with small size, light weight and higher voltage resistance performance. SUMMARY

[0005] The application provides a micro lightweight electric thruster gas path insulation device, and the main insulation body is integrally formed based on additive manufacturing, which improves the overall insulation voltage resistance performance.

[0006] In order to achieve the above purpose, the application provides a micro lightweight electric thruster gas path insulation device, which comprises a first gas path joint, a second gas path joint and a ceramic gas path main insulation body, wherein: the ceramic gas path main insulation body is integrally formed based on additive manufacturing processing, and the internal cavity is provided with a spiral-shaped slender gas supply channel; the first gas path joint is welded at the front end of the ceramic gas path main insulation body, and the second gas path joint is welded at the rear end of the ceramic gas path main insulation body; the working gas passes through the first gas path joint, the gas supply channel of the ceramic gas path main insulation body and the second gas path joint in sequence, and enters the electric thruster.

[0007] Further, the first gas path joint comprises a first joint, a first fastening nut, a first gas channel and a first welding fixing part, wherein: the first gas channel and the first welding fixing part are integrally formed; 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; and the first welding fixing part is welded at the front end of the ceramic gas path main insulation body.

[0008] Further, the second gas joint comprises a second joint, a second fastening nut, a second gas channel and a second welding fixing part, wherein: the second gas channel is integrally formed with the second welding 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; and the second welding fixing part is welded at the rear end of the ceramic gas main insulator.

[0009] Further, the first gas channel and the second gas channel are both in communication with the spiral gas supply channel in the internal cavity of the ceramic gas main insulator.

[0010] Further, the cross-sectional area of the spiral gas supply channel is ≤4.5mm 2 .

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

[0012] Further, the materials of the first gas joint and the second gas joint are both Kovar alloy.

[0013] The micro lightweight electric thruster gas insulation device provided by the application has the following beneficial effects:

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

[0015] The accompanying drawings, which form a part of this application, are intended to provide further understanding of the application and are incorporated herein for a purpose of explanations and are not intended as an undue limitation of the application. In the drawings:

[0016] Figure 1 is a schematic view of the micro lightweight electric thruster gas insulation device provided by the embodiment of the application;

[0017] Figure 2 is a schematic view of the first gas joint (second gas joint) provided by the embodiment of the application;

[0018] In the drawings: 1-first gas joint, 11-first joint, 12-first fastening nut, 13-first gas channel, 14-first welding fixing part, 2-second gas joint, 21-second joint, 22-second fastening nut, 23-second gas channel, 24-second welding fixing part, 3-ceramic gas main insulator, 4-gas supply channel. DETAILED DESCRIPTION

[0019] In the following, the technical solutions in the embodiments of the present application will be described clearly and completely with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all the other embodiments obtained by a person of ordinary skill in the art without creative effort should fall into the protection scope of the present application.

[0020] It should be noted that the terms "first", "second" and the like in the description and claims of the present application and the above drawings are used to distinguish similar objects, and do not necessarily indicate a specific order or sequence. It should be understood that the data thus used can be interchanged under appropriate circumstances, so that the embodiments of the present application described herein can be implemented. In addition, the terms "comprise" and "have" and any variations thereof are intended to cover non-exclusive inclusion, for example, a process, method, system, product or device that comprises a list of steps or units does not necessarily limit to those clearly listed steps or units, but can include other steps or units not clearly listed or inherent to these processes, methods, products or devices.

[0021] In the present application, the terms "upper", "lower", "left", "right", "front", "back", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings. These terms are mainly used to better describe the present application and its embodiments, and are not used to limit the indicated devices, elements or components to have a specific orientation, or to be constructed and operated in a specific orientation.

[0022] In addition, in addition to indicating the orientation or positional relationship, the above-mentioned part of the terms can also be used to indicate other meanings, for example, the term "upper" can also be used to indicate a certain dependent relationship or connection relationship in some cases. For a person of ordinary skill in the art, the specific meaning of these terms in the present application can be understood according to the specific situation.

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

[0024] It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict. The present application will be described in detail below with reference to the drawings and in combination with the embodiments.

[0025] As Figure 1As shown, the application provides a micro lightweight electric thruster gas path insulation device, which comprises a first gas path joint 1, a second gas path joint 2 and a ceramic gas path main insulation body 3, wherein: the ceramic gas path main insulation body 3 is integrally formed based on additive manufacturing processing, and the internal cavity is provided with a spiral-shaped slender gas supply channel 4; the first gas path joint 1 is welded at the front end of the ceramic gas path main insulation body 3, and the second gas path joint 2 is welded at the rear end of the ceramic gas path main insulation body 3; the working gas passes through the first gas path joint 1, the gas supply channel 4 of the ceramic gas path main insulation body 3 and the second gas path joint 2 in sequence, and enters the electric thruster.

[0026] Specifically, the micro lightweight electric thruster gas path insulation device provided by the embodiment of the application is mainly arranged between the electric thruster storage and supply system and the electric thruster, and is used for realizing reliable insulation of the working gas. Among them, the ceramic gas path main insulation body 3 is used as the main structure of the insulation device, and the whole is based on additive manufacturing processing, that is, the ceramic gas path main insulation body 3 is a hollow cylinder, and a spiral-shaped gas supply channel 4 is arranged around the inside, and the whole structure is integrally formed by 3D printing technology without mold, good sealing performance, good pressure resistance; the first gas path joint 1 is fixedly welded at the front end of the ceramic gas path main insulation body 3 and connected with the gas storage and supply device; the second gas path joint 2 is fixedly welded at the rear end of the ceramic gas path main insulation body 3 and connected with the electric thruster; during work, the working gas in the gas storage and supply device enters the internal cavity of the ceramic gas path main insulation body 3 through the first gas path joint 1, passes through the spiral-shaped gas supply channel 4, and then enters the electric thruster through the second gas path joint 2, thereby realizing high-pressure insulation of the gas.

[0027] Further, the first gas path joint 1 comprises a first joint 11, a first fastening nut 12, a first gas channel 13 and a first welding fixing part 14, wherein: the first gas channel 13 and the first welding fixing part 14 are integrally formed; 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; and the first welding fixing part 14 is welded at the front end of the ceramic gas path main insulation body 3.

[0028] Further, the second gas path joint 2 comprises a second joint 21, a second fastening nut 22, a second gas channel 23 and a second welding fixing part 24, wherein: the second gas channel 23 and the second welding fixing part 24 are integrally formed; 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; and the second welding fixing part 24 is welded at the rear end of the ceramic gas path main insulation body 3.

[0029] Specifically, as shown in FIG. 1, the first gas path joint 1 and the second gas path joint 2 are respectively arranged at the front end and the rear end of the ceramic gas path main insulation body 3, and the working gas passes through the first gas path joint 1, the gas supply channel 4 of the ceramic gas path main insulation body 3 and the second gas path joint 2 in sequence, and enters the electric thruster. Figure 2As shown, the first gas joint 1 is used for the entry of gas, the first joint 11 is used for assembly connection with the working gas supply device, the first fastening nut 12 is used for fixing the whole joint, the first gas passage 13 is used for the flow of working gas, the first welding fixing part 14 is integrally formed with the first gas passage 13 and is used for welding and fixing the front end of the ceramic gas main insulation body 3; the second gas joint 2 is used for the discharge of gas, the second joint 21 is used for assembly connection with the electric thruster, the second fastening nut 22 is used for fixing the whole joint, the second gas passage 23 is used for the flow of working gas, so that it enters the inside of the electric thruster, and the second welding fixing part 24 is integrally formed with the second gas passage 23 and is used for welding and fixing the rear end of the ceramic gas main insulation body 3.

[0030] Further, the first gas passage 13 and the second gas passage 23 are both in communication with the spiral gas supply passage 4 in the internal chamber of the ceramic gas main insulation body 3.

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

[0032] Specifically, the internal chamber of the ceramic gas main insulation body 3 is provided with an integrally formed spiral gas supply passage 4, which is mainly used to prolong the path of the gas, uniformly distribute the gas, suppress the backflow of the plasma, and enhance the overall insulation performance. In the embodiment of the present application, the cross-sectional area of the spiral gas supply passage 4 is not more than 4.5mm 2 .

[0033] Further, the material of the ceramic gas main insulation body 3 is alumina.

[0034] Further, the materials of the first gas joint 1 and the second gas joint 2 are Kovar alloy.

[0035] Specifically, the pressure resistance experiment is carried out under a vacuum degree of 1x10 -3 Pa, at the working gas flow rate test points 0, 1.088, 2.04, 3.264, 4.08, 5.168, 6.528 mg / s, and under the examination time of 120s, the micro light-weight electric thruster gas insulation device provided by the present application passes the 3000V pressure resistance test, meets the pressure resistance requirement of the 10kW electric thruster, and passes the 1600g mechanical impact experiment. It can be seen that the micro light-weight electric thruster gas insulation device provided by the present application not only significantly reduces the complexity of the electric thruster structure, but also greatly improves the insulation pressure resistance performance of the gas insulation device on the basis of light weight and miniaturization, and improves the on-orbit reliability of the electric thruster.

[0036] The above descriptions are only the preferred embodiments of the present application, and are not intended to limit the present application. The present application can have various modifications and changes for those skilled in the art. Any modifications, equivalent replacements, improvements, 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 micro light-weight electric thruster gas path insulation device, characterized by, The first gas path joint, the second gas path joint and the ceramic gas path main insulator, wherein: The ceramic gas path main insulator is integrally formed based on additive manufacturing processing, and an internal cavity is provided with a spiral-shaped elongated gas supply channel; 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; The working gas passes through the first gas path joint, the gas supply channel of the ceramic gas path main insulator and the second gas path joint in sequence and enters the electric thruster; The first gas path joint includes a first joint, a first fastening nut, a first gas channel and a first welded fixing part, wherein: The first gas channel is integrally formed with the first welded 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 welded fixing part is welded at the front end of the ceramic gas path main insulator; The second gas path joint includes a second joint, a second fastening nut, a second gas channel and a second welded fixing part, wherein: The second gas channel is integrally formed with the second welded 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 welded fixing part is welded at the rear end of the ceramic gas path main insulator; The first gas channel and the second gas channel are in communication with the spiral-shaped gas supply channel of the internal cavity of the ceramic gas path main insulator.

2. The micro light-weight electric thruster gas path insulation device according to claim 1, characterized in that Cross-sectional area of helical gas supply channel < 4.5 mm 2 .

3. The micro light-weight electric thruster gas path insulation device according to claim 2, characterized in that The material of the ceramic gas path main insulator is alumina.

4. The micro light-weight electric thruster gas path insulation device according to claim 3, characterized in that The materials of the first gas path joint and the second gas path joint are Kovar alloy.

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