Gas collection efficiency measuring system

Abstract

The invention relates to the technical field of spacecraft propulsion, in particular to a gas collection efficiency measuring system which comprises an ion source, a Faraday probe array, a gas collection supercharging device, an electric thruster, a base and an upper computer system which are arranged in a vacuum cabin. The generated beam ions are collected and pressurized by the gas collecting and pressurizing device and then enter the electric thruster, and the electric thruster ignites to lead out the ions to generate a beam; the Faraday probe array is arranged at an inlet of the gas collecting and pressurizing device and is fixed on the base through the support frame; the gas collecting and pressurizing device and the electric thruster are fixed on the base through a support frame; and the upper computer system is electrically connected with the Faraday probe array. The mass flow rate of the gas entering the gas collecting and pressurizing device and the mass flow rate of the output gas of the gas collecting and pressurizing device can be accurately measured, so that the gas collecting efficiency of the gas collecting and pressurizing device is accurately obtained.

Description

Technical Field

[0001] The present application relates to the field of spacecraft propulsion technology, and in particular to a gas collection efficiency measurement system. Background Art

[0002] The air-breathing electric propulsion system uses solar cells to provide energy and utilizes the rarefied nitrogen, oxygen and oxygen atoms in the ultra-low Earth orbit environment as a source of working fluid. The processes of ionization and accelerated ejection generate thrust, which serves as the power for maintaining the orbit of ultra-low Earth orbit spacecraft. This allows the spacecraft to stay and maneuver in ultra-low Earth orbit with less or no working fluid. This can solve the problem that existing technologies cannot enable aircraft to stay and maneuver in ultra-low Earth orbit for a long time. It can be widely used in spacecraft platforms such as high-resolution Earth observation satellites, Earth gravity field measurement satellites and ultra-high-speed communication satellites.

[0003] When an air-breathing electric propulsion system operates in space, orbital ambient gas enters a gas collection and pressurization device. The gas, collected and pressurized, enters the electric thruster, which generates thrust. Because the ambient gas in orbits suitable for air-breathing electric propulsion systems is very rarefied, the electric thruster requires a certain discharge chamber pressure, meaning it must achieve a certain mass flow rate. Therefore, the gas collection and pressurization device must have a high gas collection efficiency. This is a crucial metric for gas collection and pressurization devices, and its accurate measurement facilitates their optimized design.

[0004] The gas collected and pressurized by a gas collection and pressurization device is neutral. Since the diameter of the output gas pipeline is several centimeters, and the diameter of the gas delivery pipeline of a flow meter is typically in the millimeter range, it is not suitable to use a flow meter to measure the output mass flow rate of a gas collection and pressurization device. The gas pressure in the output gas pipeline of a gas collection and pressurization device can be measured using a vacuum gauge, but measuring the gas velocity is difficult. Therefore, the output mass flow rate of a gas collection and pressurization device is not suitable for measuring gas pressure in combination with the collective gas velocity. Summary of the Invention

[0005] The present application provides a gas collection efficiency measurement system, which can obtain the output gas mass flow rate of the gas collection and pressurization device based on the measured electric thruster beam value.

[0006] In order to achieve the above-mentioned objectives, the present application provides a gas collection efficiency measurement system, comprising an ion source, a Faraday probe array, a gas collection and pressurization device, an electric thruster, a base, and a host computer system, all of which are arranged inside a vacuum chamber, wherein: the gas collection and pressurization device is arranged between the ion source and the electric thruster; the ion source is a Hall-type ion source, and the beam ions generated by it are collected and pressurized by the gas collection and pressurization device and then enter the electric thruster, and the electric thruster ignites and extracts the ions to generate a beam; the Faraday probe array is arranged at the entrance of the gas collection and pressurization device and is fixed to the base by a support frame; the gas collection and pressurization device and the electric thruster are both fixed to the base by a support frame; the host computer system is electrically connected to the Faraday probe array for collecting beam density distribution data.

[0007] Furthermore, the ion source includes an anode, a discharge power supply, a hollow cathode and multiple electromagnets, wherein: a first gas supply pipeline is provided at the anode; the discharge power supply is electrically connected to the anode and the hollow cathode respectively; a discharge area is formed between the anode and the hollow cathode; and multiple electromagnets are arranged around the discharge area to form a magnetic field.

[0008] Furthermore, a mixed gas is delivered to the anode through the first gas delivery pipeline, and the mixed gas includes N2, Ar and O2.

[0009] Furthermore, the Faraday probe array is in a Mi shape.

[0010] Furthermore, the gas collection and pressurization device includes a honeycomb tube array and a profile collector, wherein: the honeycomb tube array is arranged in front of the profile collector; the profile collector is a conical structure, and the cone mouth is connected to the electric thruster through a second gas pipeline.

[0011] Furthermore, the second gas pipeline is a large-diameter gas pipeline.

[0012] Furthermore, a moving mechanism is provided on the base, and the entire base is arranged on the guide rail via a rotating wheel, and the moving mechanism is electrically connected to the rotating wheel.

[0013] Furthermore, the host computer system includes a data acquisition system and a motion control system. The data acquisition system is electrically connected to the Faraday probe array, and the motion control system is electrically connected to the motion mechanism.

[0014] The gas collection efficiency measurement system provided in this application has the following beneficial effects:

[0015] This application can accurately measure the gas mass flow rate entering the gas collection and boosting device and the gas mass flow rate output from the gas collection and boosting device, thereby accurately obtaining the gas collection efficiency of the gas collection and boosting device, providing an important reference for the design and optimization of the gas collection and boosting device. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] 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:

[0017] Figure 1 is a schematic diagram of a gas collection efficiency measurement system provided according to an embodiment of the present application;

[0018] Figure 2 is a schematic diagram of a Faraday probe array provided according to an embodiment of the present application;

[0019] In the figure: 1-vacuum chamber, 2-ion source, 21-anode, 22-discharge power supply, 23-hollow cathode, 24-electromagnet, 25-first gas pipeline, 3-Faraday probe array, 4-gas collection and pressurization device, 41-honeycomb tube array, 42-surface collector, 43-second gas pipeline, 5-electric thruster, 6-base, 61-moving mechanism, 62-rotor, 7-host computer system, 71-data acquisition system, 72-movement control system, 8-support frame, 9-guide rail. DETAILED DESCRIPTION

[0020] 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.

[0021] 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.

[0022] 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.

[0023] 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 express 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.

[0024] Additionally, the term "plurality" shall mean two or more.

[0025] 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.

[0026] like Figure 1 As shown, the present application provides a gas collection efficiency measurement system, including an ion source 2, a Faraday probe array 3, a gas collection and pressurizing device 4, an electric thruster 5, a base 6 and a host computer system 7 arranged inside a vacuum chamber 1, wherein: the gas collection and pressurizing device 4 is arranged between the ion source 2 and the electric thruster 5; the ion source 2 is a Hall-type ion source 2, and the beam ions generated by it are collected and pressurized by the gas collection and pressurizing device 4 and then enter the electric thruster 5, and the electric thruster 5 ignites and extracts ions to generate a beam; the Faraday probe array 3 is arranged at the entrance of the gas collection and pressurizing device 4 and is fixed to the base 6 through a support frame 8; the gas collection and pressurizing device 4 and the electric thruster 5 are both fixed to the base 6 through the support frame 8; the host computer system 7 is electrically connected to the Faraday probe array 3 for collecting beam density distribution data.

[0027] Specifically, the gas collection efficiency measurement system provided in the embodiments of the present application is primarily used to measure the gas collection efficiency of the gas collection and boosting device 4 in an air-breathing electric propulsion system. The system obtains the mass flow rate output by the gas collection and boosting device 4 based on the beam current, and obtains the input mass flow rate into the gas collection and boosting device 4 based on the beam ion density distribution measured by the Faraday probe array 3, thereby obtaining the gas collection efficiency of the gas collection and boosting device 4. Specifically, the ion source 2 is used to generate beam ions; the gas collection and boosting device 4 is used to collect and boost orbital ambient gas and make the collected and boosted gas neutral; the electric thruster 5 extracts the beam ions to generate thrust; the Faraday probe array 3 is used to measure the beam density distribution at the inlet of the gas collection and boosting device 4; the base 6 is used to fix and support the overall structure; and the host computer system 7 is used for control and data processing.

[0028] Furthermore, the ion source 2 includes an anode 21, a discharge power supply 22, a hollow cathode 23 and a plurality of electromagnets 24, wherein: a first gas supply pipeline 25 is provided at the anode 21; the discharge power supply 22 is electrically connected to the anode 21 and the hollow cathode 23 respectively; a discharge region is formed between the anode 21 and the hollow cathode 23; and a plurality of electromagnets 24 are arranged around the discharge region to form a magnetic field.

[0029] Specifically, in the embodiment of the present application, the ion source 2 is preferably a Hall-type ion source 2. Since the velocity of ambient gas particles relative to the gas collection and pressurization device 4 is approximately 7.9 km / s when the air-breathing electric propulsion system is operating in space, the use of a Hall-type ion source 2 couples the ion generation and acceleration processes, thereby balancing the size and velocity of the ion beam, i.e., an ion velocity close to 7.9 km / s. At the same time, the mass flow rate corresponding to the beam size can meet the operating requirements of the electric thruster 5. Furthermore, the use of multiple electromagnets 24 to form a magnetic field allows for more precise adjustment of the ion velocity by adjusting the magnetic field generated by the electromagnets 24, while still meeting the mass flow rate requirements of the electric thruster 5. This allows for more precise adjustment of the ion velocity by adjusting the magnetic field generated by the electromagnets 24, combined with voltage regulation of the discharge power supply 22, to achieve a velocity closer to 7.9 km / s, achieving greater accuracy than adjusting only the mass flow rate of the input working fluid and the voltage of the discharge power supply 22.

[0030] Furthermore, a mixed gas is delivered to the anode 21 through the first gas delivery pipeline 25, and the mixed gas includes N2, Ar and O2. In the embodiment of the present application, the Hall type ion source 2 adopts a mixed gas supply, and the mixed gas is preferably composed of 54.7% N2, 39.0% Ar and 6.3% O2, which is closer to the composition of the space environment gas at an orbital altitude of 180 km. Since the orbital environment gas composition at this altitude is 54.7% N2, 39.0% AO (atomic oxygen) and 6.3% O2, Ar is used instead of AO because atomic oxygen is difficult to store on the ground and cannot be mixed with other gases, while the collision ionization energy of Ar is very close to that of AO over a wide energy range.

[0031] Further, such as Figure 2 As shown, the Faraday probe array 3 is in the shape of a 'P'. Using a 'P'-shaped Faraday probe array 3 can more accurately measure the ion flow entering the gas collection and pressurization device 4 than a linear Faraday probe array. This is because the beam current of the Hall-type ion source 2 is uneven and not completely axisymmetric. Therefore, using a 'P'-shaped array can improve the accuracy of the gas collection efficiency of the gas collection and pressurization device 4.

[0032] Furthermore, the gas collection and pressurization device 4 includes a honeycomb tube array 41 and a profiled collector 42. The honeycomb tube array 41 is positioned in front of the profiled collector 42. The profiled collector 42 has a conical structure, with the conical opening connected to the electric thruster 5 via a second gas pipe 43. The honeycomb tube array 41 and profiled collector 42 within the gas collection and pressurization device 4 are primarily used to neutralize and pressurize the beam ions. Ions entering the gas collection and pressurization device 4 collide with the walls of the honeycomb tube array 41 and the profiled collector 42, resulting in neutralization.

[0033] Furthermore, the second gas pipeline 43 is a large-diameter gas pipeline. The electric thruster 5 uses a large-diameter (approximately 8 cm) gas pipeline intake method. That is, the diameter of the electric thruster 5's gas intake pipeline is the same as the diameter of the gas output pipeline of the gas collection and boosting device 4. Compared with the traditional small-diameter (approximately 1 cm) intake method, the mass flow rate of the working fluid entering the electric thruster 5 is the same as the mass flow rate of the working fluid output from the gas collection and boosting device 4, ensuring the accuracy of the gas collection efficiency measurement of the gas collection and boosting device 4.

[0034] Furthermore, a movable mechanism 61 is provided on the base 6, and the entire base 6 is mounted on the guide rail 9 via a rotating wheel 62, with the movable mechanism 61 being electrically connected to the rotating wheel 62. The Faraday probe array 3, the gas collecting and pressurizing device 4, and the electric thruster 5 are arranged on the movable guide rail 9. The movable mechanism 61 can be used to adjust the distance of the gas collecting and pressurizing device 4 relative to the Hall-type ion source 2, thereby adjusting the mass flow rate of the working fluid entering the electric thruster 5 to ensure that it is within the normal operating mass flow rate range of the electric thruster 5. The electric thruster 5 has certain mass flow rate requirements for operation; if the mass flow rate is too high or too low, the electric thruster 5 will not function properly.

[0035] Furthermore, the host computer system 7 includes a data acquisition system 71 and a motion control system 72. The data acquisition system 71 is electrically connected to the Faraday probe array 3, and the motion control system 72 is electrically connected to the motion mechanism 61. The host computer system 7 is capable of calculating the mass flow rate entering the gas collection and pressurization device 4 based on the collected beam density distribution data. Based on the mass flow rate range of the normal operation of the electric thruster 5, the position of the base 6 is adjusted, thereby adjusting the mass flow rate of the working fluid of the electric thruster 5.

[0036] Specifically, when the gas collection efficiency measurement system provided in the embodiment of the present application is working, the Hall type ion source 2 uses the mixed gas (mainly including N2, Ar and O2) input by the first gas pipeline 25 to generate an ion beam (mainly composed of N2 + 、Ar + and O2 + ), by adjusting the magnetic field strength and the discharge power supply 22 voltage, the ion velocity is closer to 7.9 km / s (the nitrogen component in the mixed gas accounts for a relatively large proportion, and the ion velocity is N2 +speed); the beam ions pass through the Mi-shaped Faraday probe array 3 and the gas collecting and boosting device 4 in sequence, wherein the Faraday probe array 3 is close to the upstream of the gas collecting and boosting device 4, and the beam ions pass through the honeycomb tube array 41 and the profile collector 42 in the gas collecting and boosting device 4 in sequence. After neutralization and boosting, the mixed gas (mainly including N2, Ar and O2) enters the electric thruster 5 through the large-diameter second gas pipeline 43, and the electric thruster 5 generates an ion beam; the upper computer system 7 calculates the beam density distribution measured by the Mi-shaped Faraday probe array 3 to obtain the mass flow rate entering the gas collecting and boosting device 4, and obtains the input gas mass flow rate of the electric thruster 5 according to the calibrated beam-mass flow rate relationship of the electric thruster 5, that is, the output gas mass flow rate of the gas collecting and boosting device 4; the ratio of the output gas mass flow rate of the gas collecting and boosting device 4 to the input gas mass flow rate is the gas collection efficiency of the gas collecting and boosting device 4. In addition, according to the beam-mass flow rate relationship of the electric thruster 5, if the mass flow rate of the gas entering the electric thruster 5 is not within the normal working range of the electric thruster 5, the mobile control system 72 of the upper computer system 7 drives the mobile mechanism 61 connected to the base 6 to change the distance between the gas collecting and boosting device 4 and the Hall-type ion source 2, thereby changing the mass flow rate entering the gas collecting and boosting device 4, that is, changing the mass flow rate of the gas entering the electric thruster 5.

[0037] More specifically, the gas collection efficiency measurement system provided in the embodiment of the present application can accurately measure the input gas mass flow rate and the output gas mass flow rate of the gas collection and boosting device 4, thereby accurately obtaining the gas collection efficiency of the gas collection and boosting device 4, providing an important reference for the design and optimization of the gas collection and boosting device 4 of the air-breathing electric propulsion system.

[0038] 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 gas collection efficiency measurement system, characterized in that: It includes an ion source, a Faraday probe array, a gas collection and pressurization device, an electric thruster, a base, and a host computer system arranged inside a vacuum chamber, wherein: The gas collecting and pressurizing device is arranged between the ion source and the electric thruster; The ion source is a Hall type ion source, and the beam ions generated by the ion source are collected and pressurized by the gas collecting and pressurizing device and then enter the electric thruster, and the electric thruster ignites and extracts ions to generate a beam; The Faraday probe array is arranged at the inlet of the gas collecting and pressurizing device and is fixed to the base via a support frame; The gas collecting and pressurizing device and the electric thruster are both fixed to the base via a support frame; The host computer system is electrically connected to the Faraday probe array and is used to collect beam density distribution data.

2. The gas collection efficiency measurement system according to claim 1, characterized in that: The ion source comprises an anode, a discharge power supply, a hollow cathode and a plurality of electromagnets, wherein: A first gas transmission pipeline is provided at the anode; The discharge power supply is electrically connected to the anode and the hollow cathode respectively; A discharge region is formed between the anode and the hollow cathode; A plurality of electromagnets are arranged around the discharge area to form a magnetic field.

3. The gas collection efficiency measurement system according to claim 2, characterized in that: A mixed gas is delivered to the anode through the first gas delivery pipeline, where the mixed gas includes N2, Ar and O2.

4. The gas collection efficiency measurement system according to claim 3, characterized in that: The Faraday probe array is in a Mi shape.

5. The gas collection efficiency measurement system according to claim 4, characterized in that: The gas collection and pressurization device includes a honeycomb tube array and a profiled collector, wherein: The honeycomb tube array is arranged in front of the profile collector; The profiled catcher is a conical structure, and the cone mouth is connected to the electric thruster through a second air transmission pipeline.

6. The gas collection efficiency measurement system according to claim 5, characterized in that: The second gas transmission pipeline is a large-diameter gas transmission pipeline.

7. The gas collection efficiency measurement system according to claim 6, characterized in that: The base is provided with a moving mechanism, and the base as a whole is arranged on a guide rail via a rotating wheel, and the moving mechanism is electrically connected to the rotating wheel.

8. The gas collection efficiency measurement system according to claim 7, characterized in that: The host computer system includes a data acquisition system and a motion control system. The data acquisition system is electrically connected to the Faraday probe array, and the motion control system is electrically connected to the motion mechanism.

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