Annular space on-orbit filling system and method

Abstract

The invention relates to the technical field of space on-orbit filling, and discloses an annular space on-orbit filling system and method.The filling system comprises a filling module and a power source, the filling module comprises a propellant storage box, a filling ring pipe and a filling connector, and the propellant storage box is located in the radial range of the filling ring pipe and communicates with the filling ring pipe; the propellant storage box is used for storing propellants, the filling connector is located outside the radial range of the filling ring pipe and communicates with the filling ring pipe, the filling connector is used for being in butt joint communication with a connector of a target spacecraft storage box, and the power source is in drive connection with the filling module and used for driving the filling module to rotate around the central axis of the filling ring pipe. And after the filling module is in butt joint with the target spacecraft, the filling module and the target spacecraft can rotate synchronously. The filling method comprises the steps that the power source is started to execute a filling task after butt joint, the power source is closed after filling is completed, and then unlocking is executed. According to the annular space on-orbit filling system and method, a gas source working medium is saved, and the filling efficiency is high.

Description

Technical Field

[0001] The present invention relates to the technical field of space on-orbit refueling, and in particular to an annular space on-orbit refueling system and method. Background Art

[0002] In recent years, with the continuous development of aerospace technology, the space industry has shown a rapid and vigorous development trend, and a large number of space construction projects have emerged, such as the construction of the Earth-Moon economic circle and the development of deep space resources. Large-scale space resource development is inseparable from the basic support of the space transportation system. The current space transportation system is abandoned after the payload is transported into the predetermined orbit due to the exhaustion of propellant. The one-time space transportation cost is high, which limits the frequency and progress of space resource development. The space on-orbit refueling system will make it possible to reuse the space transportation system on-orbit by replenishing the thrusters of orbiting spacecraft on-orbit, which can greatly improve the transportation efficiency of the existing space transportation system and reduce the cost of space resource development.

[0003] The current on-orbit refueling systems are all small propellant supply systems for spacecraft such as satellites and space stations. They generally use a pressurized air source as the refueling power, have a small refueling flow rate and low efficiency, and are not suitable for large-scale on-orbit refueling of spacecraft.

[0004] Therefore, there is an urgent need for an annular space on-orbit filling system and method to solve the above problems. Summary of the invention

[0005] Based on the above, the object of the present invention is to provide an annular space on-orbit filling system and method, which saves gas source working fluid and has a higher filling efficiency.

[0006] To achieve the above object, the present invention adopts the following technical solutions:

[0007] An annular space on-orbit filling system, comprising:

[0008] A filling module, comprising a propellant tank, a filling annulus and a filling joint, wherein the propellant tank is located within the radial range of the filling annulus and is communicated with the filling annulus, the propellant tank is used to store propellant, the filling joint is located outside the radial range of the filling annulus and is communicated with the filling annulus, and the filling joint is used to dock and communicate with an interface of a target spacecraft tank;

[0009] A power source is driven and connected to the filling module, and is used to drive the filling module to rotate around the central axis of the filling ring tube. Under the driving action of the power source, the filling module and the target spacecraft can rotate synchronously after docking with the filling module.

[0010] As a preferred solution of the annular space on-orbit filling system, the filling module further includes:

[0011] A base, the propellant tank is arranged on the base, and the power source is drivingly connected to the base to drive the base to rotate around the central axis of the filling ring tube.

[0012] As a preferred solution of the annular space on-orbit filling system, the power source includes:

[0013] An engine, wherein an output end of the engine is drivingly connected to the base to drive the base to rotate.

[0014] As a preferred solution for an annular space on-orbit filling system, the engine is a flywheel engine.

[0015] As a preferred solution of the annular space on-orbit filling system, the power source also includes:

[0016] A solar panel is electrically connected to the engine and is used to supply power to the engine.

[0017] As a preferred solution of the on-orbit filling system for an annular space, a plurality of the filling joints are provided, and the plurality of the filling joints are arranged at intervals along the circumference of the filling ring pipe and are all connected to the filling ring pipe.

[0018] As a preferred solution for the annular space on-orbit filling system, a plurality of propellant tanks are provided, the plurality of propellant tanks are arranged in an annular manner at intervals, and each of the propellant tanks is connected to the filling annular pipe.

[0019] As a preferred solution for an annular space on-orbit filling system, each of the propellant tanks is connected to the filling ring pipe through a filling pipe, and each of the filling pipes is provided with a first filling valve, which is used to control the opening and closing of the filling pipe.

[0020] As a preferred solution of the annular space on-orbit refueling system, it also includes an exhaust pipe assembly, which includes an exhaust pipe and an exhaust joint. One end of the exhaust pipe is connected to the propellant tank, and the exhaust joint is connected to the other end of the exhaust pipe for docking and connecting with the exhaust interface of the target spacecraft tank.

[0021] The beneficial effects of the present invention are:

[0022] The present invention provides an annular space on-orbit filling system, which includes a filling module and a power source. After the target spacecraft is docked with the filling joint, the filling module is driven by the power source to rotate around the central axis of the filling ring tube, and the target spacecraft rotates synchronously. Under the action of centrifugal force, the propellant in the propellant tank is thrown into the filling ring tube, and then enters the target spacecraft tank through the filling joint to complete the filling. Compared with the prior art that uses a pressurized air source as the filling power, the annular space on-orbit filling system loses working fluid during filling, and the filling flow rate is large, so that the filling efficiency is high, which is conducive to improving the transportation efficiency of the space transportation system.

[0023] The present invention also provides an annular space on-orbit filling method. After the target spacecraft is docked with the above-mentioned annular space on-orbit filling system, the filling module is driven to rotate by a power source to perform the filling task. The filling efficiency is high and there is no loss of working fluid. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments of the present invention. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the contents of the embodiments of the present invention and these drawings without paying any creative work.

[0025] Figure 1 It is a structural schematic diagram of an annular space on-orbit filling system provided by an embodiment of the present invention;

[0026] Figure 2 It is a flow chart of an on-orbit filling method of an annular space provided by an embodiment of the present invention.

[0027] In the figure:

[0028] 1. Target spacecraft tank;

[0029] 2. Filling module; 21. Propellant tank; 22. Filling ring pipe; 23. Filling connector;

[0030] 3. Filling pipeline; 4. First filling valve;

[0031] 5. Exhaust pipe assembly; 51. Exhaust pipe; 52. Exhaust joint; 53. Exhaust branch pipe; 54. First exhaust valve; 55. Second exhaust valve;

[0032] 6. Second filling valve. DETAILED DESCRIPTION

[0033] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the present invention, rather than to limit the present invention. It should also be noted that, for ease of description, only parts related to the present invention, rather than all structures, are shown in the accompanying drawings.

[0034] In the description of the present invention, unless otherwise clearly specified and limited, the terms "connected", "connected", and "fixed" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0035] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0036] In the description of the present embodiment, the terms "upper", "lower", "left", "right" and other directions or positional relationships are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of description and simplification of operation, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as a limitation of the present invention. In the description of the present invention, unless otherwise specified, the meaning of "plurality" is two or more. In addition, the terms "first" and "second" are only used to distinguish in the description and have no special meaning.

[0037] The space on-orbit refueling system will make it possible to reuse the space transportation system on-orbit by replenishing the thrusters of orbiting spacecraft on-orbit, which can greatly improve the transportation efficiency of the existing space transportation system and reduce the cost of space resource development. The current on-orbit refueling systems are all small propellant supply systems for spacecraft such as satellites and space stations. They generally use pressurized air sources as refueling power, with small refueling flow and low efficiency, and are not suitable for large-scale on-orbit refueling of spacecraft.

[0038] Based on the above technical problems, this embodiment provides an annular space on-orbit filling system, such as Figure 1As shown, the annular space includes a filling module 2 and a power source. The filling module 2 includes a propellant tank 21, a filling ring pipe 22 and a filling connector 23. The propellant tank 21 is located within the radial range of the filling ring pipe 22 and is connected to the filling ring pipe 22. The propellant tank 21 is used to store propellant. The filling connector 23 is located outside the radial range of the filling ring pipe 22 and is connected to the filling ring pipe 22. The filling connector 23 is used to connect with the interface of the target spacecraft tank 1. The power source drives the filling module 2 to drive the filling module 2 to rotate around the central axis of the filling ring pipe 22. Under the driving action of the power source, the filling module 2 and the target spacecraft can rotate synchronously after docking with the target spacecraft. After the target spacecraft is docked with the filling connector 23, the filling module 2 is driven by the power source to rotate around the central axis of the filling ring tube 22, and the target spacecraft rotates synchronously. Under the action of centrifugal force, the propellant in the propellant tank 21 is thrown into the filling ring tube 22, and then enters the target spacecraft tank 1 through the filling connector 23 to complete the filling. Compared with the prior art that uses a pressurized air source as the filling power, the annular space on-orbit filling system loses working fluid during filling, and the filling flow rate is large, so that the filling efficiency is high, which is conducive to improving the transportation efficiency of the space transportation system.

[0039] Specifically, the propellant tank 21 is connected to the filling ring pipe 22 through the filling pipe 3, and the filling pipe 3 is provided with a first filling valve 4, which is used to control the opening and closing of the filling pipe 3. When no filling is required, the first filling valve 4 is closed to prevent the propellant in the propellant tank 21 from leaking. When the filling task is to be performed, the first filling valve 4 is opened so that the propellant in the propellant tank 21 can smoothly enter the filling ring pipe 22.

[0040] In order to meet the needs of large-scale space industry development, multiple propellant tanks 21 are provided, and multiple propellant tanks 21 are arranged in a ring at intervals, and each propellant tank 21 is connected to the filling ring pipe 22. Preferably, each propellant tank 21 is connected through a filling pipe 3, and each filling pipe 3 is provided with a first filling valve 4 as mentioned above. Multiple propellant tanks 21 are arranged in a ring, so that when the annular space on-orbit filling system performs a filling task, the number of openings of the first filling valve 4 can be controlled according to demand. The setting of multiple propellant tanks 21 makes the upper limit of the filling amount higher, that is, it can meet a larger filling amount demand. More preferably, multiple propellant tanks 21 are spaced and evenly arranged along the circumference of the filling ring pipe 22, so that the propellant distribution in the filling ring pipe 22 is kept as uniform as possible.

[0041] In this embodiment, a plurality of filling joints 23 are provided, and the plurality of filling joints 23 are arranged at intervals along the circumference of the filling ring tube 22, and are all connected to the filling ring tube 22. Each filling joint 23 can be connected to a target spacecraft tank 1, that is, the annular space on-orbit filling system can simultaneously connect to multiple target spacecraft tanks, and simultaneously fill multiple target spacecraft tanks to achieve batch filling; and the arrangement of multiple tanks allows the propellant filling amount to meet the filling of multiple target spacecrafts.

[0042] Preferably, each filling connector 23 is provided with a second filling valve 6, which is used to control the on-off of the filling connector 23. The second filling valve 6 on the filling connector 23 that is not docked with the target spacecraft is closed, and the second filling valve 6 on the filling connector 23 that is docked with the target spacecraft is opened.

[0043] Furthermore, during refueling, the propellant in the refueling module 2 flows to the target spacecraft tank 1. In order to ensure the smooth flow of the propellant, that is, to ensure the balance of the internal pressures of the refueling module 2 and the target spacecraft tank 1, the annular space on-orbit refueling system further includes an exhaust pipe assembly 5, the exhaust pipe assembly 5 includes an exhaust pipe 51 and an exhaust joint 52, one end of the exhaust pipe 51 is connected to the propellant tank 21, and the exhaust joint 52 is connected to the other end of the exhaust pipe 51, and is used to dock and communicate with the exhaust interface of the target spacecraft tank 1. During refueling, the propellant flows from the refueling module 2 into the target spacecraft tank 1, the propellant in the propellant tank 21 flows out, so that the internal pressure decreases, and the internal space of the target spacecraft tank 1 is compressed, that is, the pressure increases, so that the gas in the target spacecraft tank 1 flows into the propellant tank 21 through the exhaust pipe 51, and the pressure balance between the propellant tank 21 and the target spacecraft tank 1 is achieved, so that the propellant can flow smoothly, and the smooth progress of the refueling task is ensured.

[0044] Preferably, a first exhaust valve 54 is provided on the exhaust connector 52, and the first exhaust valve 54 is used to control the on-off of the exhaust connector 52. When the filling task is not performed, the first exhaust valve 54 remains closed. When the filling task is performed and after the target spacecraft docks with the annular space on-orbit filling system, the first exhaust valve 54 is opened.

[0045] In this embodiment, the air inlet of each propellant tank 21 is connected to the exhaust pipe 51 through an exhaust branch pipe 53, and a second exhaust valve 55 is provided in each exhaust branch pipe 53. The second exhaust valve 55 is used to control the on-off of the exhaust branch pipe 53, so as to control the opening of the corresponding second exhaust valve 55 when the propellant tank 21 is used as needed.

[0046] For example, the filling ring pipe 22 is circular to ensure that the propellant flow rate is consistent at all locations of the filling ring pipe 22, the end of the exhaust pipe 51 away from the exhaust joint 52 is located at the center of the filling ring pipe 22, and multiple exhaust branch pipes 53 are radially connected to multiple propellant tanks 21, and the length of each exhaust branch pipe 53 is the same to ensure the stability of the internal pressure of each propellant tank 21. Of course, in other embodiments, the filling ring pipe 22 can also be other shapes, such as elliptical or irregular shapes, etc., which are specifically set according to actual needs.

[0047] Furthermore, the filling module 2 also includes a base, a propellant tank 21 is arranged on the base, and a power source drives the base to drive the base to rotate around the central axis of the filling ring tube 22. The base provides a space for the propellant tank 21 to be integrated and installed, so that the filling module 2 has better integrity and is convenient for connecting the power source, while avoiding the filling module 2 from shaking or other undesirable movements when rotating. Preferably, the filling ring tube 22, the filling pipeline 3, etc. can also be supported on the base to ensure the stability of the filling ring tube 22 and the filling pipeline 3, and improve the reliability of the annular space on-orbit filling system.

[0048] Specifically, the power source includes an engine, and the output end of the engine drives the connection base to drive the base to rotate. The filling can be achieved by driving the base to rotate by the engine. Compared with the pressurized air source method, the annular space on-orbit filling system has a simple structure, convenient operation and low cost. The filling flow rate can be controlled by controlling the speed of the engine driving the filling module 2 to switch between multiple flows to meet different working conditions. The speed of the filling module 2 and the filling flow rate are tested to obtain the following corresponding table:

[0049] Table 1 Speed-filling flow correspondence table

[0050] Speed / rpm 0.1 0.5 1 2.5 5 Flow rate / (L / s) 30 280 600 1670 3300

[0051] During actual operation, the rotation speed of the filling module 2 can be quickly adjusted according to the required filling flow rate by referring to the above rotation speed-filling flow rate correspondence table.

[0052] Preferably, the engine is a flywheel engine, which runs more smoothly and saves more effort when starting. Among them, the flywheel engine is a relatively mature prior art, so it is not described here one by one.

[0053] More specifically, the power source also includes a solar panel, which is electrically connected to the engine to supply power to the engine. The engine is charged by the solar panel and can perform the refueling task for a long time.

[0054] like Figure 2As shown, this embodiment also provides an annular space on-orbit filling method, the annular space on-orbit filling method is based on the above-mentioned annular space on-orbit filling system, and the annular space on-orbit filling method includes the following steps:

[0055] S100: The target spacecraft arrives at the annular space on-orbit filling system and docks with the annular space on-orbit filling system. The filling interface and exhaust interface of the tank on the target spacecraft are sealed and docked with the filling joint and exhaust joint of the filling module respectively, and the first filling valve and the first exhaust valve remain closed.

[0056] S200: Start the power source to rotate the filling module and the target spacecraft, and the propellant in the propellant tank flows to the target spacecraft tank under the action of centrifugal force to perform the filling task. Preferably, before performing the filling task, it is necessary to perform a pre-filling airtight state detection to ensure that the filling system works normally. After the airtight state detection is qualified, the filling task is performed. During the filling, the first filling valve, the second filling valve, the exhaust valve and the second exhaust valve are opened according to the needs.

[0057] S300: After the target spacecraft tank is filled, the power source is turned off to stop the rotation of the filling module and the target spacecraft. After the filling is completed, the first filling valve, the second filling valve, the exhaust valve and the second exhaust valve are closed, and the power source is turned off.

[0058] S400: The target spacecraft and the annular space on-orbit refueling system perform an unlocking operation, the mechanical and refueling joints are unlocked, and the target spacecraft completes refueling.

[0059] After the target spacecraft docks with the above-mentioned annular space on-orbit refueling system, the refueling module is driven to rotate by the power source to perform the refueling task. The refueling efficiency is high and there is no loss of working fluid.

[0060] Note that the above are only preferred embodiments of the present invention and the technical principles used. Those skilled in the art will understand that the present invention is not limited to the specific embodiments described herein, and that various obvious changes, readjustments and substitutions can be made by those skilled in the art without departing from the scope of protection of the present invention. Therefore, although the present invention has been described in more detail through the above embodiments, the present invention is not limited to the above embodiments, and may include more other equivalent embodiments without departing from the concept of the present invention, and the scope of the present invention is determined by the scope of the appended claims.

Claims

1. An annular space on-orbit filling system, characterized in that: include: A filling module, comprising a propellant tank, a filling annulus and a filling joint, wherein the propellant tank is located within the radial range of the filling annulus and is communicated with the filling annulus, the propellant tank is used to store propellant, the filling joint is located outside the radial range of the filling annulus and is communicated with the filling annulus, and the filling joint is used to dock and communicate with an interface of a target spacecraft tank; A power source is driven and connected to the filling module, and is used to drive the filling module to rotate around the central axis of the filling ring tube. Under the driving action of the power source, the filling module and the target spacecraft can rotate synchronously after docking with the filling module.

2. The annular space on-orbit filling system according to claim 1, characterized in that: The filling module also includes: A base, the propellant tank is arranged on the base, and the power source is drivingly connected to the base to drive the base to rotate around the central axis of the filling ring tube.

3. The annular space on-orbit filling system according to claim 2, characterized in that: The power source comprises: An engine, wherein an output end of the engine is drivingly connected to the base to drive the base to rotate.

4. The annular space on-orbit filling system according to claim 3, characterized in that: The engine is a flywheel engine.

5. The annular space on-orbit filling system according to claim 3, characterized in that: The power source also includes: A solar panel is electrically connected to the engine and is used to supply power to the engine.

6. The annular space on-orbit filling system according to claim 1, characterized in that: There are multiple filling joints, which are arranged at intervals along the circumference of the filling ring pipe and are all connected to the filling ring pipe.

7. The annular space on-orbit filling system according to claim 1, characterized in that: There are multiple propellant tanks, which are arranged in a ring at intervals, and each of the propellant tanks is connected to the filling ring pipe.

8. The annular space on-orbit filling system according to claim 7, characterized in that: Each of the propellant tanks is connected to the filling ring pipe through a filling pipeline, and each of the filling pipelines is provided with a first filling valve, and the first filling valve is used to control the opening and closing of the filling pipeline.

9. The annular space on-orbit filling system according to claim 1, characterized in that: It also includes an exhaust pipe assembly, which includes an exhaust pipe and an exhaust joint. One end of the exhaust pipe is connected to the propellant tank, and the exhaust joint is connected to the other end of the exhaust pipe for docking and connecting with the exhaust interface of the target spacecraft tank.

10. An on-orbit filling method for an annular space, based on the on-orbit filling system for annular space according to any one of claims 1 to 9, characterized in that: The annular space on-orbit filling method comprises the following steps: The target spacecraft flies to the annular space on-orbit refueling system and docks with the annular space on-orbit refueling system; Starting the power source to rotate the refueling module and the target spacecraft, so that the propellant in the propellant tank flows toward the target spacecraft tank under the action of centrifugal force, and the refueling task is performed; After the target spacecraft tank is filled, the power source is turned off to stop the rotation of the filling module and the target spacecraft; The target spacecraft and the annular space on-orbit refueling system perform an unlocking operation, the machinery and the refueling joint are unlocked, and the target spacecraft completes the refueling.

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