Testing device for ion electric propulsion material air outlet induced beam flicker

Abstract

The invention relates to the technical field of spaceflight space electric propulsion, in particular to a testing device for ion electric propulsion material air outlet induced beam flicker, which comprises a vacuum chamber, an ion thruster, a vacuum gauge, a control computer, an adjustable radio frequency power supply, a three-dimensional moving structure, a radio frequency heater, a tray, an air outlet material and a thermocouple sensor, wherein the ion thruster is hung at the upper part in the vacuum cabin; the three-dimensional moving structure comprises a fixed part and a moving part; the radio frequency heater is fixed on the moving part; the tray is fixed above the radio frequency heater; the vacuum gauge is arranged above the tray, and the thermocouple sensors are arranged on the outer surfaces of the two sides of the tray; the air outlet material is arranged on the tray; and the adjustable radio frequency power supply and the control computer are arranged outside the vacuum chamber. According to the method, the air outlet material is heated, and the heater temperature and the local air pressure are controlled, so that the air outlet simulation and the air outlet rate control of the material of the ion thruster in the space environment are realized on the ground.

Description

Technical Field

[0001] The present application relates to the field of aerospace electric propulsion technology, and in particular to a test device for beam flickering induced by outgassing of ion electric propulsion materials. Background Art

[0002] Ion electric propulsion for space is an advanced aerospace propulsion technology. Its principle is to use space electrical energy to ionize the propellant to produce high-density plasma, and then extract, accelerate and discharge the ions through a high-voltage grid system to generate thrust.

[0003] In the early days of ion electric propulsion on-orbit, due to the physical adsorption of gases in the atmosphere by some of its own materials (ceramics, graphite, connectors, 3D printing materials, etc.), when the thruster operates in the high vacuum environment of space for a long time, the high heat of the components and the pressure difference (4 to 7 orders of magnitude) induce material outgassing, resulting in a sudden increase in local air pressure and a change in gas composition. This in turn easily induces unexpected discharge of vacuum low pressure (i.e., beam flicker) in local areas of the thruster. Beam flicker can cause a temporary loss of thrust output in mild cases, and can lead to damage or even failure of the ion electric propulsion grid in severe cases, restricting the improvement of the life and reliability of ion electric propulsion products and limiting their widespread application. Summary of the Invention

[0004] The present application provides an experimental device for ion electric propulsion material outgassing induced beam scintillation, which solves the problems that existing ground simulation experiments of ion electric propulsion material outgassing induced beam scintillation are difficult to carry out, the characteristics of material outgassing induced beam scintillation are not understood, and the protection measures for material outgassing induced beam scintillation are not in place.

[0005] In order to achieve the above-mentioned objectives, the present application provides an experimental device for beam flickering induced by outgassing of ion electric propulsion materials, comprising a vacuum chamber, an ion thruster, a vacuum gauge, a control computer, an adjustable RF power supply, a three-dimensional movable structure, an RF heater, a tray, outgassing material and a thermocouple sensor, wherein: the ion thruster is suspended above the interior of the vacuum chamber by a metal suspension rod; the three-dimensional movable structure comprises a fixed component and a movable component, the fixed component is arranged below the interior of the vacuum chamber, and the movable component is arranged on the fixed component; the RF heater is fixed on the movable component; the tray is fixed above the RF heater; the vacuum gauge is arranged at the edge position above the tray, and the thermocouple sensors are arranged on the outer surfaces of both sides of the tray; the outgassing material is arranged on the tray; the adjustable RF power supply is arranged outside the vacuum chamber, and is connected to the RF heater on the one hand by a cable passing through a flange below the vacuum chamber, and is electrically connected to the control computer on the other hand; the control computer is arranged outside the vacuum chamber, and is electrically connected to the vacuum gauge, the thermocouple sensor and the three-dimensional movable structure respectively by a cable passing through the flange below the vacuum chamber.

[0006] Furthermore, the three-dimensional moving structure is aligned with the ion thruster outlet in the vertical direction.

[0007] Furthermore, the radio frequency heater, the tray, the vacuum gauge and the thermocouple sensor form an integral structure, are fixed together on the moving component, and move along with the moving component.

[0008] Furthermore, the outgassing material is ceramic, connector, resistance wire, ceramic glue, 3D printing material or graphite.

[0009] Furthermore, the gas outlet material is located 2 to 5 cm below the front end of the ion thruster grid.

[0010] Furthermore, the heating temperature of the radio frequency heater is 50-300°C.

[0011] Furthermore, the vacuum degree inside the vacuum chamber is ≥5×10 -5 Pa.

[0012] Furthermore, the material of the tray is carbon fiber with high thermal conductivity.

[0013] The present application provides a test device for beam scintillation induced by outgassing of ion electric propulsion materials, which has the following beneficial effects:

[0014] This application realizes the simulation of ion thruster's own material outgassing and its outgassing rate control in space environment on the ground by heating outgassing material and combining it with the method of controlling heater temperature and local air pressure, providing an engineering feasible experimental device for ground simulation of material outgassing-induced ion electric propulsion beam flickering in high vacuum and high temperature environment in space. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The drawings that constitute part of this application are used to provide a further understanding of this application and make other features, objects and advantages of this application more apparent. The illustrative embodiment drawings of this application and their descriptions are used to explain this application and do not constitute an improper limitation of this application. In the drawings:

[0016] Figure 1 Schematic diagram of an experimental device for ion electric propulsion material outgassing-induced beam scintillation according to an embodiment of the present application;

[0017] In the figure: 1-vacuum chamber, 2-ion thruster, 3-vacuum gauge, 4-control computer, 5-adjustable RF power supply, 6-three-dimensional mobile structure, 7-RF heater, 8-tray, 9-outgassing material, 10-thermocouple sensor, 11-metal hanger, 12-flange. DETAILED DESCRIPTION

[0018] In order to enable those skilled in the art to better understand the present invention, the following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts should fall within the scope of protection of this application.

[0019] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects and are not necessarily used to describe a specific order or sequential order. It should be understood that the data used in this way can be interchanged where appropriate, so that the embodiments of the present application described here. In addition, the terms "including" and "having" and any of their variations are intended to cover non-exclusive inclusions. For example, a process, method, system, product or device that includes a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0020] In this application, terms such as "upper," "lower," "left," "right," "front," "back," "top," "bottom," "inner," "outer," "center," "vertical," "horizontal," "transverse," and "longitudinal" indicate positions or locations based on the positions or locations shown in the accompanying drawings. These terms are primarily intended to better describe this application and its embodiments and are not intended to limit the devices, elements, or components indicated to having a specific orientation, or to being constructed or operated in a specific orientation.

[0021] Furthermore, some of the above terms may be used to express other meanings besides indicating a position or location. For example, the term "on" may also be used to indicate a dependency or connection in certain circumstances. Those skilled in the art will understand the specific meanings of these terms in this application based on the specific circumstances.

[0022] Additionally, the term "plurality" shall mean two or more.

[0023] It should be noted that, in the absence of conflict, the embodiments and features of the embodiments in this application can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0024] like Figure 1As shown, the present application provides an experimental device for beam scintillation induced by outgassing of ion electric propulsion materials, comprising a vacuum chamber 1, an ion thruster 2, a vacuum gauge 3, a control computer 4, an adjustable RF power supply 5, a three-dimensional movable structure 6, an RF heater 7, a tray 8, an outgassing material 9, and a thermocouple sensor 10, wherein: the ion thruster 2 is suspended above the interior of the vacuum chamber 1 by a metal suspension rod 11; the three-dimensional movable structure 6 includes a fixed component and a movable component, the fixed component is arranged at the bottom of the interior of the vacuum chamber 1, and the movable component is arranged on the fixed component; the RF heater 7 is fixed to the movable component; The tray 8 is fixed above the RF heater 7; the vacuum gauge 3 is arranged at the edge position above the tray 8, and the thermocouple sensor 10 is arranged on the outer surfaces of both sides of the tray 8; the outgassing material 9 is arranged on the tray 8; the adjustable RF power supply 5 is arranged outside the vacuum chamber 1, and is connected to the RF heater 7 through a cable passing through the flange 12 below the vacuum chamber 1 on the one hand, and is electrically connected to the control computer 4 on the other hand; the control computer 4 is arranged outside the vacuum chamber 1, and is electrically connected to the vacuum gauge 3, the thermocouple sensor 10 and the three-dimensional movable structure 6 respectively through a cable passing through the flange 12 below the vacuum chamber 1.

[0025] Specifically, the experimental device for beam scintillation induced by outgassing of ion electric propulsion materials provided in the embodiment of the present application solves the problem of beam scintillation induced by outgassing of high-temperature materials in the high vacuum and plasma environment of ground-based simulated space, overcomes the technical shortcoming that ion electric propulsion has long been unable to conduct experimental research on the ground due to the changes in local air pressure and gas composition caused by outgassing of its own materials, and provides basic conditions for the study of the consistency of beam scintillation of ion electric propulsion systems between the sky and the earth.

[0026] More specifically, in the embodiment of the present application, the vacuum chamber 1 is used to simulate a vacuum environment; the vacuum gauge 3 is a high-sensitivity vacuum gauge 3, which is used to measure air pressure; the radio frequency heater 7 is used to heat the outgassing material 9; the adjustable radio frequency power supply 5 is used to adjust the electric power of the radio frequency heater 7; the tray 8 is used to fix the outgassing material 9; the thermocouple sensor 10 is used to measure the heating temperature; the three-dimensional movable structure 6 includes fixed parts and movable parts, and the position of the outgassing material 9 can be adjusted by using the movable parts; the control computer 4 is used to regulate the temperature and air pressure, and is connected to the vacuum gauge 3, the thermocouple sensor 10, the adjustable radio frequency power supply 5 and the three-dimensional movable structure 6 through a dedicated cable and a dedicated cabin flange 12, so as to transmit electrical signals inside and outside the vacuum chamber 1.

[0027] Furthermore, the three-dimensional movable structure 6 is vertically aligned with the outlet of the ion thruster 2. The three-dimensional movable structure 6 is primarily used to adjust the position between the outlet material 9 and the ion thruster 2 according to actual test conditions, thereby enabling the tray 8 and the outlet material 9 to move in the up-down, left-right, and front-to-back directions.

[0028] Furthermore, the RF heater 7, tray 8, vacuum gauge 3, and thermocouple sensor 10 form an integrated structure, which is fixed to the moving part and moves with it. The tray 8, thermocouple sensor 10, vacuum gauge 3, RF heater 7, and the moving part of the three-dimensional movable structure 6 are integrated and move as a whole. The vacuum gauge 3 and tray 8 are insulated with high-heat-resistant insulation material.

[0029] Furthermore, the gas outlet material 9 is ceramic, connector, resistance wire, ceramic glue, 3D printing material or graphite. According to the test requirements, the gas outlet material 9 can be selected from different materials, preferably ceramic, connector, resistance wire, ceramic glue, 3D printing material and graphite.

[0030] Furthermore, the gas outlet material 9 is located 2 to 5 cm below the front end of the grid of the ion thruster 2. The distance between the gas outlet material 9 and the front end of the grid of the ion thruster 2 is preferably 2 to 5 cm, so that there is no potential passage and the normal extraction of the ion electric propulsion beam is not affected.

[0031] Furthermore, the heating temperature of the RF heater 7 is 50-300° C. The RF heater 7 heats the outgassing material 9 on the tray 8, and the outgassing rate of the outgassing material 9 is achieved by adjusting the power of the RF heater 7 based on the real-time feedback signal from the thermocouple sensor 10 and the vacuum gauge 3.

[0032] Furthermore, the vacuum degree inside the vacuum chamber 1 is ≥5×10 -5 Before the experiment, the vacuum chamber 1 was evacuated according to the requirements of the actual vacuum degree simulation.

[0033] Furthermore, the material of the tray 8 is carbon fiber with high thermal conductivity.

[0034] Specifically, during the test of the embodiment of the present application, when the ion thruster 2 enters steady-state operation, the vacuum gauge 3 and the thermocouple sensor 10 are respectively turned on to collect air pressure and temperature signals; based on the feedback signal, the control computer 4 is used to turn on the adjustable RF power supply 5 and input RF power, and the RF heater 7 starts to operate and heats the outgassing material 9; the air pressure and temperature signals are monitored in real time to control the material outgassing rate within the required range; at the same time, the control computer 4 is used to operate the three-dimensional movable structure 6 to adjust the spatial position of the outgassing material 9; finally, the influence characteristics of the material outgassing on the ion electric propulsion and the beam scintillation and its evolution law are observed and recorded.

[0035] The above description is merely a preferred embodiment of the present application and is not intended to limit the present application. Various modifications and variations are possible for those skilled in the art. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present application shall be included within the scope of protection of the present application.

Claims

1. A test device for beam scintillation induced by outgassing of ion electric propulsion materials, characterized in that: It includes a vacuum chamber, an ion thruster, a vacuum gauge, a control computer, an adjustable radio frequency power supply, a three-dimensional mobile structure, a radio frequency heater, a tray, an outgassing material, and a thermocouple sensor, wherein: The ion thruster is suspended above the interior of the vacuum chamber via a metal suspension rod; The three-dimensional moving structure includes a fixed component and a moving component, wherein the fixed component is arranged below the interior of the vacuum chamber, and the moving component is arranged on the fixed component; The radio frequency heater is fixed on the moving part; The tray is fixed above the radio frequency heater; The vacuum gauge is arranged at an edge position above the tray, and the thermocouple sensors are arranged on the outer surfaces of both sides of the tray; The gas outlet material is arranged on the tray; The adjustable RF power supply is arranged outside the vacuum chamber, and is connected to the RF heater via a cable passing through a flange below the vacuum chamber, and is electrically connected to the control computer on the other hand; The control computer is arranged outside the vacuum chamber, and is electrically connected to the vacuum gauge, the thermocouple sensor and the three-dimensional movable structure respectively through cables passing through a flange below the vacuum chamber.

2. The test device for beam scintillation induced by outgassing of ion electric propulsion materials according to claim 1, characterized in that: The three-dimensional moving structure is consistent with the ion thruster outlet in the vertical direction.

3. The test device for beam scintillation induced by outgassing of ion electric propulsion materials according to claim 2, characterized in that: The radio frequency heater, the tray, the vacuum gauge, and the thermocouple sensor form an integral structure, are fixed together on the moving component, and move along with the moving component.

4. The test device for beam scintillation induced by outgassing of ion electric propulsion materials according to claim 3, characterized in that: The gas outlet material is ceramic, connector, resistance wire, ceramic glue, 3D printing material or graphite.

5. The test device for beam scintillation induced by outgassing of ion electric propulsion materials according to claim 4, characterized in that: The gas outlet material is located 2 to 5 cm below the front end of the ion thruster grid.

6. The test device for beam scintillation induced by outgassing of ion electric propulsion materials according to claim 5, characterized in that: The heating temperature of the radio frequency heater is 50-300°C.

7. The test device for beam scintillation induced by outgassing of ion electric propulsion materials according to claim 6, characterized in that: The vacuum degree inside the vacuum chamber is ≥5×10 -5 Pa.

8. The test device for beam scintillation induced by outgassing of ion electric propulsion materials according to claim 7, characterized in that: The material of the tray is carbon fiber with high thermal conductivity.

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