An electric propulsion system, an electric propulsion gas supply device and a gas supply method

Abstract

The application discloses an electric propulsion system, an electric propulsion gas supply device and a gas supply method. The electric propulsion gas supply device comprises a control module, a low-temperature gas suction module, a refrigeration module and a gas storage module. The low-temperature gas suction module is used for sublimating gas into solid working medium after contacting with the gas in the space environment, and also converts the solid working medium into fluid working medium into the gas storage module. The refrigeration module is used for refrigerating the low-temperature gas suction module to make the low-temperature gas suction module sublimate the contacted gas into solid working medium. The control module is used for controlling the refrigeration module to stop refrigerating the low-temperature gas suction module when the solid working medium in the low-temperature gas suction module is greater than a preset value, and controlling the low-temperature gas suction module to convert the solid working medium in the low-temperature gas suction module into fluid working medium. The gas storage module is used for storing the fluid working medium. The application can absorb the gas in the low orbit, can not carry working medium or carry a small amount of working medium, can prolong the on-orbit operation time of the satellite, and can also ensure the accurate control of the operation attitude and operation track of the satellite.

Description

Technical Field

[0001] This invention relates to the field of space electric propulsion technology, and in particular to an electric propulsion system, an electric propulsion gas supply device, and a gas supply method. Background Technology

[0002] In recent years, with the rapid development of satellite technology, low Earth orbit has become an emerging research hotspot due to its unique application value. Electric propulsion systems, as one of the most advanced space propulsion technologies currently available, have attracted widespread attention and in-depth research due to their significant advantages such as high specific impulse, precise and controllable thrust, re-startability, and long lifespan.

[0003] Electric propulsion is a technology that uses electrical energy to ionize a propellant to generate plasma and then uses an electromagnetic field to accelerate the propellant to produce thrust. However, the low Earth orbit (LEO) environment is not an ideal vacuum, and atmospheric drag in space poses a severe challenge to satellite operation. When operating in LEO, satellites are constantly affected by atmospheric drag, requiring frequent activation of the electric propulsion system to generate thrust in order to maintain orbital altitude and meet orbital maneuvering requirements. This frequent activation leads to rapid consumption of propellant, while the satellite's own propellant capacity is limited. Insufficient propellant will ultimately cause the satellite to fall prematurely, severely restricting the on-orbit lifespan of LEO satellites. Summary of the Invention

[0004] This invention provides an electric propulsion system, an electric propulsion gas supply device, and a gas supply method, which can absorb gas in low orbit, eliminate the need for or reduce the amount of working propellant required, extend the on-orbit operation time of the satellite, and ensure precise control of the satellite's attitude and trajectory.

[0005] According to one aspect of the present invention, an electric propulsion gas supply device is provided, the electric propulsion gas supply device comprising: a control module, a cryogenic gas intake module, a refrigeration module and a gas storage module;

[0006] The cryogenic gas intake module is used to condense the gas into a solid working medium after contacting the gas in the space environment, and is also used to convert the solid working medium in the cryogenic gas intake module into a fluid working medium and transport it to the gas storage module; wherein, the fluid working medium includes at least one of gaseous working medium and liquid working medium;

[0007] The refrigeration module is used to refrigerate the low-temperature gas intake module so that the low-temperature gas intake module condenses the gas it comes into contact with into the solid working fluid;

[0008] The control module is used to control the refrigeration module to stop refrigerating the low-temperature gas intake module when the solid working fluid in the low-temperature gas intake module is greater than a preset value, and to control the low-temperature gas intake module to convert the solid working fluid in it into a fluid working fluid.

[0009] The gas storage module is used to store the fluid working medium transmitted by the cryogenic gas intake module and convert the fluid working medium into a gaseous working medium for transmission to the electric propulsion module.

[0010] Optionally, the cooling module includes a magnetocaloric material unit, a magnetic field generating unit, and a magnetic field control unit;

[0011] The magnetic field control unit is used to control the magnetic field generating unit to apply a magnetic field to the magnetocaloric material unit so that the magnetocaloric material unit heats the internal temperature of the low-temperature air intake module, and is also used to control the magnetic field generating unit to remove the magnetic field from the magnetocaloric material unit so that the magnetocaloric material unit lowers the internal temperature of the low-temperature air intake module.

[0012] Optionally, the cryogenic intake module includes:

[0013] A vacuum shell, with an air intake chamber formed inside;

[0014] An intake valve, located on the vacuum housing, is used to control the flow of gas into the intake chamber.

[0015] The first stage cold head is thermally coupled to the magnetocaloric material unit and is used to receive the cooling energy generated by the magnetocaloric material unit.

[0016] The first and second stage cold heads are in contact with the first stage cold head and are used to receive the cooling energy transmitted by the first stage cold head;

[0017] The first cold umbrella is disposed inside the intake chamber and is fixedly connected to the first secondary cold head for sublimating gas.

[0018] A heat shield is installed in the air intake chamber to block heat radiation.

[0019] Optionally, the gas storage module includes:

[0020] Gas storage tanks are used to store fluid working materials;

[0021] The second-stage cold head is thermally coupled to the magnetocaloric material unit and is used to receive the cooling energy generated by the magnetocaloric material unit.

[0022] The second-stage cold head is in contact with the second-stage cold head and is used to receive the cooling energy transmitted by the second-stage cold head;

[0023] The second cooling umbrella is installed inside the gas storage tank and is fixedly connected to the second and second stage cooling heads, and is used to convert the fluid working medium in the gas storage tank into a solid working medium.

[0024] Optionally, the electric propulsion gas supply device provided in this embodiment further includes a first working fluid transmission module;

[0025] The first working fluid transfer module includes a first transfer pipe and a first one-way valve located in the first transfer pipe;

[0026] The first working fluid transfer module is located between the low-temperature gas intake module and the gas storage module;

[0027] The control module is used to control the first one-way valve to close when the refrigeration module cools the low-temperature gas intake module, and is also used to control the first one-way valve to open when the low-temperature gas intake module heats, and to control the refrigeration module to cool the gas storage module when the first one-way valve is open so that the fluid working medium in the gas storage tank is converted into a solid working medium.

[0028] Optionally, the electric propulsion gas supply device provided in this embodiment further includes a second working fluid transmission module;

[0029] The second working fluid transfer module includes a second transfer pipeline and a second one-way valve located in the second transfer pipeline;

[0030] The second working fluid transfer module is located between the gas storage module and the electric propulsion module;

[0031] The control module is also used to control the solid working medium in the gas storage tank to sublimate into a gaseous working medium when the second one-way valve is turned on.

[0032] Optionally, the electric propulsion gas supply device provided in this embodiment also includes a solar power module;

[0033] The solar power module is used to receive solar energy and convert it into electrical energy to supply power to the control module, the low-temperature air intake module, and the refrigeration module.

[0034] According to another aspect of the present invention, an electric propulsion gas supply method is provided, which is applied in an electric propulsion gas supply device provided in any embodiment of the present invention;

[0035] The electric propulsion gas supply method includes:

[0036] The cooling module cools the low-temperature intake module, and the low-temperature intake module condenses the gas into a solid working fluid after contacting the gas in the space environment.

[0037] When the solid working fluid in the low-temperature intake module exceeds a preset value, the control module controls the refrigeration module to stop refrigerating the low-temperature intake module, and controls the low-temperature intake module to convert the solid working fluid into a fluid working fluid, and transfer the fluid working fluid to the gas storage module; wherein, the fluid working fluid includes at least one of gaseous working fluid and liquid working fluid;

[0038] The gas storage module stores the fluid working medium transmitted by the cryogenic gas intake module and converts the fluid working medium into a gaseous working medium for transmission to the electric propulsion module.

[0039] According to another aspect of the present invention, an electric propulsion system is provided, the electric propulsion system including an electric propulsion module and an electric propulsion air supply device provided in any embodiment of the present invention;

[0040] The electric propulsion module is used to ionize the gaseous working fluid transmitted by the gas storage module to generate plasma.

[0041] Optionally, the electric propulsion module includes a radio frequency ion source and a neutralizer;

[0042] The radio frequency ion source is used to receive the gaseous working fluid transmitted by the gas storage module and ionize the gaseous working fluid into plasma;

[0043] The neutralizer is used to output a negative charge to neutralize the plasma generated by the radio frequency ion source.

[0044] This invention provides an electric propulsion gas supply device. The cryogenic gas-absorbing module in this device acquires gas from low Earth orbit through self-absorption, ensuring continuous operation of the electric propulsion system without carrying a working propellant. By replacing the molecular pump with a cryogenic gas-absorbing module, gas is captured through physical adsorption, eliminating moving parts and fundamentally solving the micro-vibration problem. This avoids the vibration of moving parts in the molecular pump that could cause the satellite to deviate from its preset orbit, ensuring precise control of the satellite's attitude. This invention also includes a gas storage module to store the working propellant. The gas storage module ensures the gas flow rate of the electric propulsion system, mitigating gas supply fluctuations caused by uneven atmospheric density in low Earth orbit and ensuring stable operation of the electric propulsion system. In summary, this invention provides an electric propulsion gas supply device that can self-absorb gas from low Earth orbit, eliminating the need for or reducing the amount of working propellant required. It also extends the satellite's on-orbit operating time and ensures precise control of the satellite's attitude and trajectory.

[0045] It should be understood that the description in this section is not intended to identify key or essential features of the embodiments of the present invention, nor is it intended to limit the scope of the invention. Other features of the invention will become readily apparent from the following description. Attached Figure Description

[0046] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0047] Figure 1This is a schematic diagram of the structure of an electric propulsion gas supply device according to an embodiment of the present invention;

[0048] Figure 2 This is a schematic diagram of the structure of another electric propulsion gas supply device provided according to an embodiment of the present invention;

[0049] Figure 3 This is a schematic diagram of the structure of another electric propulsion gas supply device provided according to an embodiment of the present invention;

[0050] Figure 4 This is a schematic diagram of the structure of another electric propulsion gas supply device provided according to an embodiment of the present invention;

[0051] Figure 5 This is a schematic flowchart of an electric propulsion gas supply method according to an embodiment of the present invention;

[0052] Figure 6 This is a schematic diagram of an electric propulsion system according to an embodiment of the present invention;

[0053] Figure 7 This is a schematic diagram of another electric propulsion system provided according to an embodiment of the present invention. Detailed Implementation

[0054] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of the present invention.

[0055] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this invention are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of the invention described herein can be implemented in orders other than those illustrated or described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover a non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0056] To enable satellites to operate continuously for extended periods, researchers have developed a self-absorbing electric propulsion system. This system addresses the problem of satellites crashing due to insufficient propellant by absorbing gas from low Earth orbit. Current self-absorbing electric propulsion systems primarily employ mechanical gas-absorbing structures, such as molecular pumps to collect gas. While this method can solve the problem of insufficient propellant, mechanical gas-absorbing structures include rotating units. These rotating units generate micro-vibrations that can easily cause the satellite to deviate from its preset orbit during operation, resulting in difficulties in precisely controlling the satellite's attitude and trajectory.

[0057] This embodiment provides an electric propulsion gas supply device that can absorb gas in low orbit, eliminating the need for a working propellant, extending the satellite's on-orbit operation time, and ensuring precise control of the satellite's attitude and trajectory.

[0058] Figure 1 This is a schematic diagram of an electric propulsion gas supply device according to an embodiment of the present invention, with reference to... Figure 1 The electric propulsion gas supply device provided in this embodiment includes: a control module 110, a cryogenic gas intake module 120, a cooling module 130, and a gas storage module 140. The cryogenic gas intake module 120 is used to condense the gas into a solid working fluid after contacting the gas in the space environment, and is also used to convert the solid working fluid in the cryogenic gas intake module 120 into a fluid working fluid and transport it to the gas storage module 140. The cooling module 130 is used to cool the cryogenic gas intake module 120 so that the cryogenic gas intake module 120 condenses the contacting gas into a solid working fluid. The control module 110 is used to control the cooling module 130 to stop cooling the cryogenic gas intake module 120 when the solid working fluid in the cryogenic gas intake module 120 is greater than a preset value, and to control the cryogenic gas intake module 120 to convert the solid working fluid in it into a fluid working fluid. The gas storage module 140 is used to store the fluid working fluid transported by the cryogenic gas intake module 120, and convert the fluid working fluid into a gaseous working fluid and transport it to the electric propulsion module. The fluid working fluid includes at least one of a gaseous working fluid and a liquid working fluid.

[0059] Specifically, "the solid working fluid in the cryogenic intake module 120 is greater than a preset value" can mean that the amount of solid working fluid accumulated in the cryogenic intake module 120 is greater than a preset value. The accumulated amount refers to the weight of the current solid working fluid in the cryogenic intake module 120. The preset value can be the maximum allowable accumulated amount in the cryogenic intake module 120. Both the maximum accumulated amount and the current accumulated amount of solid working fluid are based on temperature feedback, and the preset value corresponds to a preset temperature. For example, the control module 110 is used to detect the surface temperature of the solid working fluid. When the surface temperature of the solid working fluid is greater than the preset temperature, it indicates that the amount of solid working fluid accumulated in the cryogenic intake module 120 is greater than the preset value.

[0060] The space environment in this embodiment can refer to low Earth orbit or very low Earth orbit. The main gases in low Earth orbit and very low Earth orbit are oxygen and nitrogen. When the temperature is below 48K, oxygen in the space environment can condense into solid oxygen, and when the temperature is below 40K, nitrogen in the space environment can condense into solid nitrogen. In this embodiment, the temperature inside the cryogenic gas intake module 120 can be as low as 10~20K. Therefore, the cryogenic gas intake module 120 can condense oxygen and nitrogen in the space environment into a solid working fluid (this solid working fluid includes solid oxygen and solid nitrogen). The gaseous working fluid in the fluid working fluid includes nitrogen and oxygen, and the liquid working fluid includes liquid oxygen and liquid nitrogen.

[0061] The control module 110 is electrically connected to the cooling module 130 and the cryogenic air intake module 120. The cryogenic air intake module 120 is mechanically connected to the gas storage module 140, which can be mechanically connected to the electric propulsion module. The cooling module 130 can be a magnetic cooling module, thus eliminating the need for a compressor to cool the cryogenic air intake module 120 and avoiding the problem of the satellite deviating from its preset orbit due to compressor vibration.

[0062] The working principle of the cryogenic intake module 120 in this embodiment is basically the same as that of the cryogenic pump, and the cryogenic intake module 120 can be a component of the cryogenic pump. The pressure application range of the cryogenic intake module 120 in this embodiment is 10. -9 Pa~10 -1 Pa, allowing normal operation in low orbit. The cryogenic gas intake module 120 stores gas in a solid state, with a gas volume compression ratio of up to 10. 9 :1. This compression ratio is much greater than that of a mechanical intake structure. It can be seen that the low-temperature intake module 120 in this embodiment can capture a sufficient amount of gas.

[0063] The working principle of the electric propulsion gas supply device in this embodiment is as follows: the control module 110 controls the cooling module 130 to cool the gas. The cooling module 130 generates cold energy which is transferred to the cryogenic gas intake module 120 to reduce the temperature inside the cryogenic gas intake module 120 to less than 40K. During the operation of the low-Earth orbit satellite, gas in the low orbit continuously enters the interior of the cryogenic gas intake module 120. The internal units of the cryogenic gas intake module 120 contact the gas and condense the gas into a solid working fluid. When the amount of solid working fluid accumulated exceeds a preset value, the control module 110 closes the intake valve in the cryogenic gas intake module 120, making the interior of the cryogenic gas intake module 120 a closed space. It also controls the cooling module 130 to stop cooling the cryogenic gas intake module 120 and controls the temperature inside the cryogenic gas intake module 120 to rise, converting the solid working fluid into a fluid working fluid. This also opens the transmission channel between the cryogenic gas intake module 120 and the gas storage module 140, allowing the fluid working fluid in the high-pressure environment of the cryogenic gas intake module 120 to move into the low-pressure environment of the gas storage module 140. Once the fluid working medium in the cryogenic gas-breathing module 120 has been almost entirely moved into the gas storage module 140, the transmission channel between the cryogenic gas-breathing module 120 and the gas storage module 140 is blocked. The gas-breathing valve in the cryogenic gas-breathing module 120 is then reopened, and the module continues to be cooled to allow it to continue sublimating gases from the space environment. This process is repeated to ensure that the gas storage module 140 always contains fluid working medium, thereby guaranteeing that the electric propulsion module has sufficient gaseous working medium to ionize and generate enough plasma, thus further ensuring the satellite's sustainable operation.

[0064] After the cryogenic gas intake module 120 stores a certain amount of solid working fluid, the internal temperature of the cryogenic gas intake module 120 is increased by the self-heating function of the cryogenic gas intake module 120 or by external heating control, so that the solid working fluid is converted into gaseous working fluid and / or liquid working fluid. The converted gaseous and liquid working fluids are transported to the gas storage module 140. When the electric propulsion module needs gaseous working fluid, the control module 110 controls the refrigeration module 130 to heat so that the gas storage module 140 outputs gaseous working fluid into the reaction chamber in the electric propulsion module.

[0065] This embodiment provides an electric propulsion gas supply device. The cryogenic gas-absorbing module in this device acquires gas from the space environment through self-absorption, ensuring continuous operation of the electric propulsion system without carrying a working propellant. By replacing the molecular pump with a cryogenic gas-absorbing module, gas is captured through physical adsorption, eliminating moving parts and fundamentally solving the micro-vibration problem. This avoids the vibration of moving parts in the molecular pump that could cause the satellite to deviate from its preset orbit, ensuring precise control of the satellite's attitude. This embodiment also includes a gas storage module to store the fluid working propellant. The gas storage module ensures the gas supply flow rate of the electric propulsion system, mitigating gas supply fluctuations caused by uneven atmospheric density in low Earth orbit and ensuring stable operation of the electric propulsion system. In summary, this embodiment provides an electric propulsion gas supply device that can self-absorb gas in low Earth orbit, eliminating the need for or reducing the amount of working propellant required. It also extends the satellite's on-orbit operating time and ensures precise control of the satellite's attitude and trajectory.

[0066] Optional, Figure 2 This is a schematic diagram of another electric propulsion air supply device according to an embodiment of the present invention, with reference to... Figure 2 The cooling module 130 includes a magnetocaloric material unit 131, a magnetic field generating unit 132, and a magnetic field control unit 133. The magnetic field control unit 133 is used to control the magnetic field generating unit 132 to apply a magnetic field to the magnetocaloric material unit 131 so that the magnetocaloric material unit 131 heats the internal temperature of the low-temperature intake module 120, and is also used to control the magnetic field generating unit 132 to remove the magnetic field from the magnetocaloric material unit 131 so that the magnetocaloric material unit 131 lowers the internal temperature of the low-temperature intake module 120.

[0067] Specifically, the control module 110 is electrically connected to the magnetic field control unit 133 in the cooling module 130, and the magnetic field control unit 133 is electrically connected to the magnetic field generating unit 132.

[0068] The control module 110 is used to control the magnetic field control unit 133 to send a first signal to the magnetic field generating unit 132 when the solid working fluid in the cryogenic gas-absorbing module 120 is less than or equal to a preset value, so that the magnetic field generating unit 132 removes the magnetic field from the magnetocaloric material unit 131, thereby enabling the cryogenic gas-absorbing module 120 to condense the gas in the space environment into a solid working fluid. The control module 110 is also used to control the magnetic field control unit 133 to send a second signal to the magnetic field generating unit 132 when the solid working fluid in the cryogenic gas-absorbing module 120 is greater than a preset value, so that the magnetic field generating unit 132 applies a magnetic field to the magnetocaloric material unit 131, thereby enabling the cryogenic gas-absorbing module 120 to heat up and convert the solid working fluid into a fluid working fluid.

[0069] The magnetic field control unit 133 can periodically change the magnetic field strength of the magnetic field generating unit 132, causing the magnetocaloric material unit 131 to undergo magnetization and demagnetization cycles, thereby achieving heating or cooling. The higher the magnetocaloric effect of the magnetic material in the magnetocaloric material unit 131, the higher the coefficient of performance (COP) of the cooling module 130. The magnetic material in the magnetocaloric material unit 131 can include rare-earth permanent magnet materials, ferromagnetic materials, antiferromagnetic materials, etc.

[0070] The refrigeration module 130 provided in this embodiment is based on the magnetic refrigeration principle of magnetocaloric effect. Theoretically, the magnetic refrigeration cycle efficiency can be more than 30% higher than that of traditional compressor refrigeration, making it suitable for cryogenic or space environments. Magnetic refrigeration has no moving parts and has a wide temperature range (1K to 300K), making it suitable for applications involving the adsorption of gases at low temperatures. The operating mode of the refrigeration module 130 in this embodiment can be easily switched, such as heating mode (magnetizing) or cooling mode (demagnetizing), thereby realizing the conversion between gas sublimation (cooling) and sublimation or melting (heating). The refrigeration module 130 in this embodiment can also use magnetic refrigeration in conjunction with other refrigeration methods, or adopt a multi-stage series refrigeration method.

[0071] In this embodiment, the control module 110, the cryogenic intake module 120, and the refrigeration module 130 can form a novel cryogenic pump without moving parts. This refrigeration method has the characteristics of no moving parts and no refrigerant leakage. Applying the electric propulsion gas supply device provided in this embodiment to the electric propulsion system can further improve the working performance of the electric propulsion system.

[0072] Optional, Figure 3 This is a schematic diagram of another electric propulsion air supply device according to an embodiment of the present invention, with reference to... Figure 3 The cryogenic gas intake module 120 provided in this embodiment includes: a vacuum housing 121, a gas intake valve 122, a first-stage cold head 123, a first-stage cold head 124, a first-stage cold umbrella 125, and a heat shield 126; a gas intake chamber 1211 is formed inside the vacuum housing 121; the gas intake valve 122 is disposed on the vacuum housing 121 and is used to control the opening and closing of gas entering the gas intake chamber 1211; the first-stage cold head 123 is thermally coupled to the magnetocaloric material unit 131 and is used to receive the cold energy generated by the magnetocaloric material unit 131; the first-stage cold head 124 is in contact with the first-stage cold head 123 and is used to receive the cold energy transmitted by the first-stage cold head 123; the first-stage cold umbrella 125 is disposed inside the gas intake chamber 1211 and is fixedly connected to the first-stage cold head 124 for sublimating gas; the heat shield 126 is disposed inside the gas intake chamber 1211 for blocking thermal radiation.

[0073] Specifically, after the intake valve 122 is opened, gas in the space environment can enter the intake chamber 1211. The cooling module 130 transfers cooling energy to the first-stage cold head 123 and the first-stage cold head 124, lowering the temperature of the first-stage cold head 124 and the first cold umbrella 125. This causes the gas in the intake chamber 1211 to condense into a solid working fluid, which then adheres to the outer surfaces of the first cold umbrella 125 and the first-stage cold head 124. As the amount of solid working fluid increases, the sublimation capacity of the low-temperature intake module 120 decreases. When the amount of solid working fluid in the low-temperature intake module 120 exceeds a preset value, the control module controls the intake valve 122 to close. At this time, the intake chamber 1211 is sealed, and the cooling module 130 can still transfer heat to the first-stage cold head 123 and the first-stage cold head 124, converting the solid working fluid into a fluid working fluid, and then transferring the fluid working fluid to the gas storage module 140.

[0074] In this embodiment, the first-stage cold head 123 functions similarly to the first-stage cold head in a cryogenic pump, and the first-stage cold head 124 functions similarly to the second-stage cold head in a cryogenic pump. A heat shield 126 at the opening of the suction chamber 1211 isolates heat exchange between space and the cold heads in the cryogenic suction module 120. A double-layer insulation structure may be provided in the vacuum housing 121 to prevent heat exchange between the inside and outside of the suction chamber 1211.

[0075] Optional, continue to refer to Figure 3 The gas storage module 140 includes a gas storage tank 141, a second-stage cold head 142, a second-stage cold head 143, and a second cold umbrella 144. The gas storage tank 141 is used to store a fluid working medium. The second-stage cold head 142 is thermally coupled to the magnetocaloric material unit 131 and is used to receive the cooling energy generated by the magnetocaloric material unit 131. The second-stage cold head 143 is in contact with the second-stage cold head 142 and is used to receive the cooling energy transmitted by the second-stage cold head 142. The second cold umbrella 144 is disposed inside the gas storage tank 141 and is fixedly connected to the second-stage cold head 143, and is used to convert the fluid working medium in the gas storage tank 141 into a solid working medium.

[0076] Specifically, the gas storage tank 141 is used to receive the fluid working medium transferred from the intake chamber 1211 for storage and backup, so that the fluid working medium can be converted into a gaseous working medium and transferred to the electric propulsion module at any time.

[0077] The gas storage tank 141 can withstand high-pressure gas and, connected to the refrigeration module 130, can achieve refrigeration at temperatures below 40K. The temperature of the second-stage cold head 143 can be below 40K, thereby converting the fluid working medium in the gas storage tank 141 into a solid working medium. The solid working medium can be adsorbed onto the outer surfaces of the second cooling umbrella 144 and the second-stage cold head 143. Converting the fluid working medium in the gas storage tank 141 into a solid working medium facilitates the storage of more working medium, and the solid working medium in the gas storage tank 141 will not flow back into the intake chamber 1211 during the flow of the fluid working medium.

[0078] The refrigeration module 130 can also be used to heat the second-stage cold head 142 and the second-stage cold head 143 to convert the solid working fluid in the gas storage tank 141 into a gaseous working fluid.

[0079] The magnetocaloric material unit in the cooling module 130 may include a first magnetocaloric material subunit and a second magnetocaloric material subunit. The first magnetocaloric material subunit can be used for thermal coupling with the low-temperature gas intake module 120, and the second magnetocaloric material subunit can be used for thermal coupling with the gas storage module 140. The cooling module 130 also includes a first heat conversion unit 134 and a second heat conversion unit 135. The first heat conversion unit 134 is located between the first stage cold head 123 and the first magnetocaloric material subunit, and is used to transfer the cold and heat generated by the first magnetocaloric material subunit. The second heat conversion unit 135 is located between the second stage cold head 142 and the second magnetocaloric material subunit, and is used to transfer the cold and heat generated by the second magnetocaloric material subunit. The first and second magnetocaloric material subunits do not affect each other. For example, while the first magnetocaloric material subunit generates cold energy, the second magnetocaloric material subunit releases heat. This allows the internal temperature of the gas storage module 140 to rise and deliver gaseous working fluid to the electric propulsion module without affecting the low-temperature gas intake module 120's condensation of gas in the space environment into solid working fluid.

[0080] Optional, continue to refer to Figure 3 The electric propulsion gas supply device provided in this embodiment also includes a first working fluid transmission module; the first working fluid transmission module includes a first transmission pipe 162 and a first one-way valve 161 located in the first transmission pipe 162; the first working fluid transmission module is located between the cryogenic gas intake module 120 and the gas storage module 140; the control module is used to control the first one-way valve 161 to close when the refrigeration module 130 refrigerates the cryogenic gas intake module 120, and is also used to control the first one-way valve 161 to open when the cryogenic gas intake module 120 heats, and is also used to control the refrigeration module 130 to refrigerate the gas storage module 140 when the first one-way valve 161 is open so that the fluid working fluid in the gas storage tank 141 is converted into a solid working fluid.

[0081] Specifically, the first transmission pipe 162 is used to transmit the fluid medium. When the first one-way valve 161 is open, the fluid medium flows from the suction chamber 1211 in the cryogenic suction module 120 to the gas storage tank 141. The control module can control the opening and closing of the first one-way valve 161. Furthermore, when the solid working medium in the cryogenic suction module 120 is greater than a preset value, the control module can control the cryogenic suction module 120 to heat up, thereby converting the solid working medium into a fluid working medium, and control the first one-way valve 161 to open, allowing the fluid working medium to flow into the gas storage tank 141. To prevent the fluid working medium in the gas storage tank 141 from flowing back into the suction chamber 1211, this embodiment also includes a control module that controls the cooling module 130 to cool the second-stage cold head 142 and the second-stage cold head 143 in the gas storage module 140, so that the fluid working medium in the gas storage tank 141 is converted into a solid working medium. The solid working medium will not flow into the suction chamber 1211, thereby ensuring that the fluid working medium in the suction chamber 1211 is efficiently transferred to the gas storage tank 141.

[0082] Optional, continue to refer to Figure 3 The electric propulsion gas supply device provided in this embodiment also includes a second working fluid transmission module; the second working fluid transmission module includes a second transmission pipeline 172 and a second one-way valve 171 located in the second transmission pipeline 172; the second working fluid transmission module is located between the gas storage module 140 and the electric propulsion module; the control module is also used to control the solid working fluid in the gas storage tank 141 to sublimate into a gaseous working fluid when the second one-way valve 171 is turned on.

[0083] Specifically, when the second check valve 171 is open, the first check valve 161 can be closed.

[0084] The control module is connected to the second one-way valve 171, and the control module can control the opening and closing of the second one-way valve 171. The second transmission pipeline 172 is used to transmit gaseous media. When the second one-way valve 171 is open, the gaseous media flows from the gas storage tank 141 into the electric propulsion module.

[0085] When the electric propulsion module needs to generate plasma, the control module controls the cooling module 130 to heat the second-stage cold head 142 and the second-stage cold head 143 in the gas storage tank 141 so that the solid working fluid in the gas storage tank 141 sublimates into a gaseous working fluid, and controls the second one-way valve 171 to open so that the gaseous working fluid can flow into the electric propulsion module.

[0086] Optionally, when the refrigeration module cools the low-temperature suction module, the temperature of the first and second stage cold heads is less than 40K; when the refrigeration module cools the gas storage module, the temperature of the second and second stage cold heads is less than 40K.

[0087] Optional, Figure 4 This is a schematic diagram of another electric propulsion air supply device according to an embodiment of the present invention, with reference to... Figure 4 The electric propulsion gas supply device provided in this embodiment also includes a solar power module 180; the solar power module 180 is used to receive solar energy and convert solar energy into electrical energy to supply power to the control module, the low temperature intake module 120 and the refrigeration module 130.

[0088] Specifically, solar energy is inexhaustible in space. As long as there is sunlight, the solar power module 180 can continuously generate electricity. In this embodiment, the solar power module 180 is set up to supply power to the power-consuming modules in the electric propulsion gas supply device, which can ensure sufficient power supply, ensure the continuous operation of the electric propulsion gas supply device, and reduce the manufacturing cost of the electric propulsion gas supply device.

[0089] This embodiment also provides an electric propulsion gas supply method, which is applied to the electric propulsion gas supply device provided in any embodiment of the present invention. Figure 5 This is a schematic flowchart of an electric propulsion gas supply method according to an embodiment of the present invention, with reference to... Figure 5 The electric propulsion gas supply method provided in this embodiment includes the following steps:

[0090] S110, the cooling module cools the low-temperature intake module, and the low-temperature intake module condenses the gas into a solid working fluid after contacting the gas in the space environment.

[0091] S120. When the solid working fluid in the low-temperature intake module is greater than the preset value, the control module controls the refrigeration module to stop refrigerating the low-temperature intake module, and controls the low-temperature intake module to convert the solid working fluid in it into a fluid working fluid, and then transfers the fluid working fluid to the gas storage module.

[0092] The working fluid includes at least one of gaseous and liquid working fluids.

[0093] S130, the gas storage module stores the fluid working medium transmitted by the cryogenic gas intake module and converts the fluid working medium into a gaseous working medium for transmission to the electric propulsion module.

[0094] The electric propulsion gas supply method provided in the embodiments of the present invention has the same technical effect as the electric propulsion gas supply device provided in any embodiment of the present invention. For details not described in the electric propulsion gas supply method provided in the embodiments of the present invention, please refer to the content of the electric propulsion gas supply device provided in any embodiment of the present invention.

[0095] Figure 6 This is a schematic diagram of an electric propulsion system according to an embodiment of the present invention, with reference to... Figure 6 The electric propulsion system provided in this embodiment includes an electric propulsion module 210 and an electric propulsion gas supply device 100 provided in any embodiment of the present invention; the electric propulsion module 210 is used to ionize the gaseous working fluid transmitted by the gas storage module 140 to generate plasma.

[0096] Specifically, the gaseous working fluid transmitted by the gas storage module 140 includes nitrogen and oxygen.

[0097] The electric propulsion system provided in this embodiment includes the electric propulsion gas supply device provided in any embodiment of the present invention. Therefore, it has the beneficial effects of the electric propulsion gas supply device provided in any embodiment of the present invention, which will not be described in detail here.

[0098] Optional, Figure 7 This is a schematic diagram of another electric propulsion system provided according to an embodiment of the present invention, with reference to... Figure 7 The electric propulsion module 210 includes a radio frequency ion source 211 and a neutralizer 212. The radio frequency ion source 211 is used to receive the gaseous working fluid transmitted by the gas storage module 140 and ionize the gaseous working fluid into plasma. The neutralizer 212 is used to output negative charge to neutralize the plasma generated by the radio frequency ion source 211.

[0099] Specifically, this embodiment uses a radio frequency ion source 211 to generate positively charged plasma. To prevent the satellite surface from becoming negatively charged, a neutralizer 212 is also provided to generate negative charges to neutralize the positively charged plasma, thereby enabling the electric propulsion module 210 to generate uncharged plasma. In this embodiment, the electric propulsion module 210 has a thrust ≥5mN, a specific impulse ≥3000s, and the output current of the neutralizer 212 is between 1A and 1.5A.

[0100] It should be understood that the various forms of processes shown above can be used, with steps reordered, added, or deleted. For example, the steps described in this invention can be executed in parallel, sequentially, or in different orders, as long as the desired result of the technical solution of this invention can be achieved, and this is not limited herein.

[0101] The specific embodiments described above do not constitute a limitation on the scope of protection of this invention. Those skilled in the art should understand that various modifications, combinations, sub-combinations, and substitutions can be made according to design requirements and other factors. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this invention should be included within the scope of protection of this invention.

Claims

1. An electric propulsion air supply device, characterized in that, include: Control module, low-temperature intake module, refrigeration module and gas storage module; The cryogenic gas intake module is used to condense the gas into a solid working medium after contacting the gas in the space environment, and is also used to convert the solid working medium in the cryogenic gas intake module into a fluid working medium and transport it to the gas storage module; wherein, the fluid working medium includes at least one of gaseous working medium and liquid working medium; The refrigeration module is used to refrigerate the low-temperature gas intake module so that the low-temperature gas intake module condenses the gas it comes into contact with into the solid working fluid; The control module is used to control the refrigeration module to stop refrigerating the low-temperature gas intake module when the solid working fluid in the low-temperature gas intake module is greater than a preset value, and to control the low-temperature gas intake module to convert the solid working fluid in it into a fluid working fluid. The gas storage module is used to store the fluid working medium transported by the cryogenic gas intake module and convert the fluid working medium into a gaseous working medium for transport to the electric propulsion module; The refrigeration module includes a magnetocaloric material unit, a magnetic field generating unit, and a magnetic field control unit; The magnetic field control unit is used to control the magnetic field generating unit to apply a magnetic field to the magnetocaloric material unit so that the magnetocaloric material unit heats the internal temperature of the low-temperature air intake module. It is also used to control the magnetic field generating unit to remove the magnetic field from the magnetocaloric material unit so that the magnetocaloric material unit lowers the internal temperature of the low-temperature air intake module. The low-temperature intake module includes: A vacuum shell, with an air intake chamber formed inside; An intake valve, located on the vacuum housing, is used to control the flow of gas into the intake chamber. The first stage cold head is thermally coupled to the magnetocaloric material unit and is used to receive the cooling energy generated by the magnetocaloric material unit. The first and second stage cold heads are in contact with the first stage cold head and are used to receive the cooling energy transmitted by the first stage cold head; The first cold umbrella is disposed inside the intake chamber and is fixedly connected to the first secondary cold head for sublimating gas. A heat shield is installed in the air intake chamber to block heat radiation.

2. The electric propulsion air supply device according to claim 1, characterized in that, The gas storage module includes: Gas storage tanks are used to store fluid working materials; The second-stage cold head is thermally coupled to the magnetocaloric material unit and is used to receive the cooling energy generated by the magnetocaloric material unit. The second-stage cold head is in contact with the second-stage cold head and is used to receive the cooling energy transmitted by the second-stage cold head; The second cooling umbrella is installed inside the gas storage tank and is fixedly connected to the second and second stage cooling heads, and is used to convert the fluid working medium in the gas storage tank into a solid working medium.

3. The electric propulsion air supply device according to claim 2, characterized in that, It also includes the first working fluid transmission module; The first working fluid transfer module includes a first transfer pipe and a first one-way valve located in the first transfer pipe; The first working fluid transfer module is located between the low-temperature gas intake module and the gas storage module; The control module is used to control the first one-way valve to close when the refrigeration module cools the low-temperature gas intake module, and is also used to control the first one-way valve to open when the low-temperature gas intake module heats, and to control the refrigeration module to cool the gas storage module when the first one-way valve is open so that the fluid working medium in the gas storage tank is converted into a solid working medium.

4. The electric propulsion air supply device according to claim 3, characterized in that, It also includes a second working fluid transmission module; The second working fluid transfer module includes a second transfer pipeline and a second one-way valve located in the second transfer pipeline; The second working fluid transfer module is located between the gas storage module and the electric propulsion module; The control module is also used to control the solid working medium in the gas storage tank to sublimate into a gaseous working medium when the second one-way valve is turned on.

5. The electric propulsion air supply device according to any one of claims 1-4, characterized in that, It also includes a solar power module; The solar power module is used to receive solar energy and convert it into electrical energy to supply power to the control module, the low-temperature air intake module, and the refrigeration module.

6. A method for supplying air to electric propulsion, characterized in that, The electric propulsion gas supply method is applied in the electric propulsion gas supply device according to any one of claims 1-5; The electric propulsion gas supply method includes: The cooling module cools the low-temperature intake module, and the low-temperature intake module condenses the gas into a solid working fluid after contacting the gas in the space environment. When the solid working fluid in the low-temperature intake module exceeds a preset value, the control module controls the refrigeration module to stop refrigerating the low-temperature intake module, and controls the low-temperature intake module to convert the solid working fluid into a fluid working fluid, and transfer the fluid working fluid to the gas storage module; wherein, the fluid working fluid includes at least one of gaseous working fluid and liquid working fluid; The gas storage module stores the fluid working medium transmitted by the cryogenic gas intake module and converts the fluid working medium into a gaseous working medium for transmission to the electric propulsion module; The refrigeration module includes a magnetocaloric material unit, a magnetic field generating unit, and a magnetic field control unit; The magnetic field control unit controls the magnetic field generating unit to apply a magnetic field to the magnetocaloric material unit so that the magnetocaloric material unit heats the internal temperature of the low-temperature air intake module. It also controls the magnetic field generating unit to remove the magnetic field from the magnetocaloric material unit so that the magnetocaloric material unit lowers the internal temperature of the low-temperature air intake module. The low-temperature intake module includes: A vacuum shell, with an air intake chamber formed inside; An intake valve is installed on the vacuum housing to control the flow of gas into the intake chamber; The first stage cold head is thermally coupled to the magnetocaloric material unit and receives the cooling energy generated by the magnetocaloric material unit. The first and second stage cold heads are in contact with the first stage cold head and receive the cooling energy transmitted by the first stage cold head; The first cold umbrella is disposed inside the intake chamber and is fixedly connected to the first secondary cold head for sublimating gas. A heat shield is installed in the air intake chamber to block heat radiation.

7. An electric propulsion system, characterized in that, Includes an electric propulsion module and an electric propulsion air supply device as described in any one of claims 1-5; The electric propulsion module is used to ionize the gaseous working fluid transmitted by the gas storage module to generate plasma.

8. The electric propulsion system according to claim 7, characterized in that, The electric propulsion module includes a radio frequency ion source and a neutralizer; The radio frequency ion source is used to receive the gaseous working fluid transmitted by the gas storage module and ionize the gaseous working fluid into plasma; The neutralizer is used to output a negative charge to neutralize the plasma generated by the radio frequency ion source.

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