Liquid oxygen tank for space gas station

Abstract

The invention relates to the technical field of propellant storage and management, in particular to a liquid oxygen tank for a space gas station, the liquid oxygen tank comprises a pressure-resistant shell, a mixing channel assembly, a superconducting coil assembly and an exhaust port, the mixing channel assembly is of a double-layer thin-wall circular tube structure and comprises an inner-layer circular tube and an outer-layer circular tube; one end of the inner-layer circular tube is in clearance fit with an assembly hole in the inner wall of the pressure-resistant shell, and the other end of the inner-layer circular tube extends out of the pressure-resistant shell to form a liquid inlet; the outer-layer circular pipe integrally surrounds the outer part of the inner-layer circular pipe, and one end, close to the liquid inlet, of the outer-layer circular pipe extends out of the pressure-resistant shell to form a liquid outlet; the superconducting coil assembly is wound on the outer wall of the inner-layer circular tube; and the exhaust port is formed in the pressure-resistant shell. According to the device, liquid oxygen can be injected or discharged in a microgravity environment, a container for storing and managing a liquid oxygen propellant is provided for a space gas station, and therefore on-orbit liquid oxygen discharging management and repeated liquid oxygen filling of a spacecraft are achieved.

Description

Technical Field

[0001] The present application relates to the technical field of propellant storage and management, and in particular to a liquid oxygen tank for a space refueling station. Background Art

[0002] The amount of fuel a spacecraft carries directly determines its lifespan. Adding extra propellant before launch not only increases launch costs but also significantly increases the likelihood of launch errors. A spacecraft typically costs hundreds of millions of dollars, sometimes even billions. Being able to refuel in space would bring significant economic benefits.

[0003] Liquid oxygen, as a highly efficient aerospace propellant, has been widely used in space chemical propulsion systems. However, as one of the core components of a space refueling station, liquid oxygen tanks need to be able to store liquid oxygen for a long time, manage liquid oxygen emissions, repeatedly fill liquid oxygen, and discharge gaseous oxygen at overpressure in a space environment. Existing liquid oxygen tanks do not have the above functions. Summary of the Invention

[0004] The present application provides a liquid oxygen tank for a space refueling station, which has the function of managing the discharge of liquid oxygen to a spacecraft on orbit and repeatedly filling it with liquid oxygen.

[0005] In order to achieve the above-mentioned objectives, the present application provides a liquid oxygen tank for a space refueling station, comprising a pressure-resistant shell, a mixing channel assembly, a superconducting coil assembly and an exhaust port, wherein: the mixing channel assembly is a double-layer thin-walled circular tube structure, arranged in the middle position inside the pressure-resistant shell, comprising an inner circular tube and an outer circular tube; one end of the inner circular tube is gap-fitted with the assembly hole on the inner wall of the pressure shell, and the other end extends out of the pressure shell to form a liquid inlet; the outer circular tube as a whole surrounds the outside of the inner circular tube, and its end close to the liquid inlet extends out of the pressure shell to form a liquid outlet; the superconducting coil assembly is axially wound on the outer wall of the inner circular tube along the mixing channel assembly; the exhaust port is arranged on the pressure shell, close to the fitting end of the inner circular tube and the assembly hole.

[0006] Furthermore, a heat insulating layer is provided on the outer surface of the pressure hull.

[0007] Furthermore, a plurality of flow channels are provided on the inner circular tube, and the plurality of flow channels are located at the closed end surface between the inner circular tube and the outer circular tube.

[0008] Furthermore, a group of corrugated tubes are arranged along the axial direction of the center of the outer circular tube.

[0009] Furthermore, multiple groups of injection channels are arranged along the circumferential direction of the outer circular tube, and the apertures of the injection channels close to the two ends of the outer circular tube and the two ends of the corrugated tube are larger than the apertures of other injection channels.

[0010] Furthermore, the superconducting coil assembly is formed by curing multiple groups of superconducting coils through low-temperature resin glue, and the material of each group of superconducting coils is yttrium barium copper oxide material.

[0011] Furthermore, each group of superconducting coils is powered and controlled in parallel.

[0012] Furthermore, a safety valve is provided on the exhaust port.

[0013] The liquid oxygen tank for a space refueling station provided in this application has the following beneficial effects:

[0014] This application can fill or discharge liquid oxygen in a microgravity environment, providing a container for storing and managing liquid oxygen propellant for a space refueling station, thereby realizing on-orbit management of liquid oxygen discharge and repeated filling of liquid oxygen to spacecraft, with the advantages of compact structure, light weight and diverse functions. 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 1 is a schematic structural diagram of a liquid oxygen tank for a space refueling station according to an embodiment of the present application;

[0017] Figure 2 is a schematic diagram of storing liquid oxygen in a liquid oxygen tank for a space refueling station according to an embodiment of the present application;

[0018] Figure 3 is a schematic diagram of filling a liquid oxygen tank for a space refueling station with liquid oxygen according to an embodiment of the present application;

[0019] Figure 4 is a schematic diagram of discharging liquid oxygen from a liquid oxygen tank for a space refueling station according to an embodiment of the present application;

[0020] In the figure: 1-pressure-resistant shell, 2-inner circular tube, 3-outer circular tube, 4-superconducting coil assembly, 5-exhaust port, 6-liquid inlet, 7-liquid outlet, 8-insulation layer, 9-flow channel, 10-bellows, 11-injection channel, 12-safety valve. DETAILED DESCRIPTION

[0021] 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.

[0022] 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.

[0023] 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.

[0024] 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.

[0025] Additionally, the term "plurality" shall mean two or more.

[0026] 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.

[0027] like Figure 1As shown, the present application provides a liquid oxygen tank for a space refueling station, comprising a pressure shell 1, a mixing channel assembly, a superconducting coil assembly 4 and an exhaust port 5, wherein: the mixing channel assembly is a double-layer thin-walled circular tube structure, arranged in the middle position inside the pressure shell 1, comprising an inner circular tube 2 and an outer circular tube 3; one end of the inner circular tube 2 is gap-fitted with the assembly hole on the inner wall of the pressure shell 1, and the other end extends out of the pressure shell 1 to form a liquid inlet 6; the outer circular tube 3 as a whole surrounds the outside of the inner circular tube 2, and its end close to the liquid inlet 6 extends out of the pressure shell 1 to form a liquid outlet 7; the superconducting coil assembly 4 is axially wound on the outer wall of the inner circular tube 2 along the mixing channel assembly; the exhaust port 5 is arranged on the pressure shell 1, close to the fitting end of the inner circular tube 2 and the assembly hole.

[0028] Specifically, the embodiment of the present application is mainly used to provide a storage and management container for liquid oxygen propellant for a space refueling station, and has the function of managing the discharge of liquid oxygen to a spacecraft in orbit and repeatedly filling liquid oxygen. Among them, the pressure shell 1 is used to bear the internal pressure load to ensure the stable and reliable operation of the liquid oxygen tank during service; the mixing channel assembly is a double-layer thin-walled circular tube structure, including an inner circular tube 2 and an outer circular tube 3. The wall thickness of the inner circular tube 2 is greater than the wall thickness of the outer circular tube 3, which provides a certain rigidity for the installation and fixation of the mixing channel assembly and resistance to mechanical environment; one end of the inner circular tube 2 is in clearance with the assembly hole on the inner wall of the pressure shell 1 to adapt to the thermal expansion and cold contraction deformation of the mixing channel assembly, and the other end is welded and fixed to the pressure shell 1, and extends out of the outside of the pressure shell 1 to form a liquid inlet 6; the outer circular tube 3 The whole is wrapped around the outside of the inner circular tube 2, and its end close to the liquid inlet 6 also extends out of the outside of the pressure-resistant shell 1 to form a liquid outlet 7; the mixing channel assembly integrates the liquid inlet 6 and the liquid outlet 7 together, which is used to cool the superconducting coil assembly 4 on the one hand, and to mix the gaseous oxygen and liquid oxygen in the liquid oxygen tank on the other hand to reduce the temperature of the gaseous oxygen; the superconducting coil assembly 4 is axially wound on the outer wall of the inner circular tube 2 along the mixing channel assembly, and is used to control the distribution state of liquid oxygen in the liquid oxygen tank, so as to realize the filling or discharge of liquid oxygen in the liquid oxygen tank in a microgravity environment; the exhaust port 5 is used to discharge the gas inside the liquid oxygen tank.

[0029] Furthermore, the outer surface of the pressure hull 1 is provided with a heat insulating layer 8. The heat insulating layer 8 is used to block external heat and prevent it from entering the interior of the liquid oxygen tank.

[0030] Furthermore, multiple sets of flow channels 9 are provided on the inner circular tube 2, and the multiple sets of flow channels 9 are located at the closed end surface between the inner circular tube 2 and the outer circular tube 3. In the embodiment of the present application, the inner circular tube 2 near the exhaust port 5 is closed at the end surface of the outer circular tube 3, and five sets of flow channels 9 are preferably provided near the closed end surface at intervals of 60 degrees along the circumferential direction.

[0031] Furthermore, a group of bellows 10 are provided along the axial direction of the center of the outer circular tube 3. The bellows 10 are mainly used to reduce the stress concentration caused by the thermal expansion and cold contraction of the outer circular tube 3.

[0032] Furthermore, multiple groups of injection channels 11 are circumferentially arranged along the outer circular tube 3, and the apertures of the injection channels 11 near the ends of the outer circular tube 3 and the ends of the bellows 10 are larger than the apertures of the other injection channels 11. In the embodiment of the present application, except for the position of the bellows 10, 10 groups of injection channels 11 are preferably evenly distributed along the circumferential direction of the outer circular tube 3, and the apertures of the injection channels 11 near the ends of the outer circular tube 3 and the ends of the bellows 10 are larger than the apertures of the other injection channels 11, so as to meet the requirements of the injection flow rate at these locations.

[0033] Furthermore, the superconducting coil assembly 4 is formed from multiple sets of superconducting coils, each made of yttrium barium copper oxide (YBCO) material, cured with a low-temperature resin adhesive. In this embodiment, six sets of superconducting coils are preferably provided. These six sets of superconducting coils are wound around the outer wall of the inner circular tube 2 along the axial direction of the mixing channel assembly and then cured by applying a low-temperature resin adhesive.

[0034] Furthermore, each set of superconducting coils is powered and controlled in parallel. Each superconducting coil is powered and controlled in parallel.

[0035] Furthermore, a safety valve 12 is provided on the exhaust port 5. The safety valve 12 is used to control the on-off of the exhaust port 5. When the pressure in the liquid oxygen tank exceeds a safe value, the exhaust port 5 and the safety valve 12 are used to discharge the gaseous oxygen therein.

[0036] Specifically, such as Figure 2 As shown, in a space microgravity environment, when the liquid oxygen tank for a space refueling station provided by an embodiment of the present application stores liquid oxygen for a long time, the same current is passed through each superconducting coil. Under the action of a strong magnetic field, the paramagnetic liquid oxygen is adsorbed near the mixing channel assembly and takes an ellipsoidal shape. In this state, the liquid oxygen can be prevented from contacting the inner wall of the pressure-resistant shell 1 with a higher temperature, thereby slowing down the increase in the temperature of the liquid oxygen. When the internal pressure in the liquid oxygen tank increases to a certain level due to the evaporation of liquid oxygen, on the one hand, the safety valve 12 opens to discharge part of the gaseous oxygen. On the other hand, superheated liquid oxygen is extracted from the liquid outlet 7, cooled by a refrigerator to form subcooled liquid oxygen, which is circulated and pumped into the liquid inlet 6 and injected through 10 groups of injection channels 11 to a position with a higher temperature in the tank, thereby further reducing the temperature of the gaseous oxygen in the tank.

[0037] More specifically, Figure 3 As shown, when liquid oxygen is needed for spacecraft such as satellites and spacecraft, the current of each superconducting coil is changed. The closer the superconducting coil is to the liquid inlet 6, the greater the current is. This forms a magnetic field with decreasing strength from the exhaust port 5 to the liquid inlet 6, and the liquid oxygen without mixed gaseous oxygen is gathered at the end of the liquid outlet 7, and the liquid oxygen is pumped out by a cryogenic pump. Figure 4 As shown, when the liquid oxygen in the liquid oxygen tank has been used to a certain extent and needs to be refilled with liquid oxygen, only the two superconducting coils near the liquid inlet 6 are opened, and the current of the superconducting coil closer to the liquid inlet 6 is greater; at this time, liquid oxygen gathers at one end of the liquid inlet 6 and gaseous oxygen gathers at the other end. After the safety valve 12 is opened to exhaust, liquid oxygen can be refilled from the liquid inlet 6.

[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 liquid oxygen tank for a space refueling station, characterized in that: It includes a pressure-resistant shell, a mixing channel assembly, a superconducting coil assembly and an exhaust port, wherein: The mixing channel assembly is a double-layer thin-walled circular tube structure, arranged in the middle position inside the pressure-resistant shell, and includes an inner circular tube and an outer circular tube; One end of the inner circular tube is loosely fitted into the assembly hole on the inner wall of the pressure-resistant shell, and the other end extends out of the pressure-resistant shell to form a liquid inlet; The outer circular tube as a whole surrounds the outside of the inner circular tube, and one end of the outer circular tube close to the liquid inlet extends out of the pressure-resistant shell to form a liquid outlet; The superconducting coil assembly is axially wound on the outer wall of the inner circular tube along the mixing channel assembly; The exhaust port is arranged on the pressure-resistant shell, close to the matching end of the inner circular tube and the assembly hole.

2. The liquid oxygen tank for a space refueling station according to claim 1, characterized in that: The outer surface of the pressure-resistant shell is provided with a heat insulation layer.

3. The liquid oxygen tank for a space refueling station according to claim 2, characterized in that: The inner circular tube is provided with a plurality of flow channels, and the plurality of flow channels are located at the closed end surface between the inner circular tube and the outer circular tube.

4. The liquid oxygen tank for a space refueling station according to claim 3, characterized in that: A group of corrugated tubes are arranged along the axial direction of the center of the outer circular tube.

5. The liquid oxygen tank for a space refueling station according to claim 4, characterized in that: A plurality of injection channels are arranged along the outer circular tube in an annular direction, and the apertures of the injection channels close to the two ends of the outer circular tube and the two ends of the corrugated tube are larger than the apertures of other injection channels.

6. The liquid oxygen tank for a space refueling station according to claim 5, characterized in that: The superconducting coil assembly is formed by curing multiple groups of superconducting coils with low-temperature resin glue, and the material of each group of superconducting coils is yttrium barium copper oxide material.

7. The liquid oxygen tank for a space refueling station according to claim 6, characterized in that: Each group of superconducting coils is powered and controlled in parallel.

8. The liquid oxygen tank for a space refueling station according to claim 7, characterized in that: The exhaust port is also provided with a safety valve.

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