An on-orbit annular space refueling system and method

Abstract

The present application relates to the technical fields of space on-orbit refueling, and discloses a kind of annular space on-orbit refueling system and method, and the refueling system includes refueling module and power source, and the refueling module includes propellant storage tank, refueling ring pipe and refueling connector, propellant storage tank is located in the radial range of refueling ring pipe, and is communicated with refueling ring pipe, and propellant storage tank is used to store propellant, and refueling connector is located outside the radial range of refueling ring pipe, and is communicated with refueling ring pipe, and refueling connector is used to interface with the interface of target spacecraft storage tank, and power source is drivingly connected with refueling module, for driving refueling module to rotate around the central axis of refueling ring pipe, under the driving action of power source, after refueling module and target spacecraft are docked, refueling module and target spacecraft can rotate synchronously.The refueling method includes: after docking, power source is started to execute refueling task, after refueling is completed, power source is closed, and then unlocking is executed.The annular space on-orbit refueling system and method save gas working substance, and the refueling efficiency is higher.

Description

TECHNICAL FIELD

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

[0002] In recent years, with the continuous development of space technology, the space industry has shown a rapid and vigorous development trend, and a large number of space construction projects for the construction of the earth-moon economic circle and the development of deep space resources have emerged. Large-scale space resource development cannot be separated from the support of space transportation systems. The current space transportation system is discarded after delivering the load into the predetermined orbit due to the depletion of propellant. The high cost of one-time space transportation limits the frequency and progress of space resource development. The space on-orbit refueling system can make the on-orbit reuse of the space transportation system possible by supplementing the propeller of the on-orbit spacecraft, 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 system is a small propellant supply system for satellites, space stations and other spacecraft. It generally uses a pressurized gas source as the refueling power, and the refueling flow is small and the efficiency is low, which is not suitable for large-scale on-orbit refueling of spacecraft.

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

[0005] Based on the above, the purpose of the present application is to provide an annular space on-orbit refueling system and method, which saves the gas source working medium and has high refueling efficiency.

[0006] To achieve the above purpose, the technical scheme adopted by the present application is as follows:

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

[0008] A refueling module, comprising a propellant storage tank, a refueling ring pipe and a refueling connector, the propellant storage tank is located within the radial range of the refueling ring pipe and is in communication with the refueling ring pipe, the propellant storage tank is used for storing propellant, the refueling connector is located outside the radial range of the refueling ring pipe and is in communication with the refueling ring pipe, and the refueling connector is used for interfacing with the target spacecraft tank;

[0009] A power source, the power source is drivingly connected to the refueling module and is used for driving the refueling module to rotate around the central axis of the refueling ring pipe, and under the driving action of the power source, the refueling module and the target spacecraft can rotate synchronously after the refueling module is docked with the target spacecraft.

[0010] As a preferred scheme of the annular space on-orbit refueling system, the refueling module further comprises:

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

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

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

[0014] As a preferred scheme of the annular space on-orbit filling system, the engine is a flywheel engine.

[0015] As a preferred scheme of the annular space on-orbit filling system, the power source further comprises:

[0016] a solar panel, the solar panel is electrically connected with the engine to supply power for the engine.

[0017] As a preferred scheme of the annular space on-orbit filling system, a plurality of filling connectors are arranged, the plurality of filling connectors are arranged along the circumference of the filling ring and are all in communication with the filling ring.

[0018] As a preferred scheme of the annular space on-orbit filling system, a plurality of propellant tanks are arranged, the plurality of propellant tanks are arranged in a ring, and each of the propellant tanks is in communication with the filling ring.

[0019] As a preferred scheme of the annular space on-orbit filling system, each of the propellant tanks is in communication with the filling ring through a filling pipeline, and a first filling valve is arranged in each of the filling pipelines to control the opening and closing of the filling pipeline.

[0020] As a preferred scheme of the annular space on-orbit filling system, an exhaust pipeline assembly is further included, the exhaust pipeline assembly comprises an exhaust pipeline and an exhaust connector, one end of the exhaust pipeline is in communication with the propellant tank, and the exhaust connector is communicated at the other end of the exhaust pipeline to be in communication with the exhaust interface of the target spacecraft tank.

[0021] The present application has the following beneficial effects:

[0022] The application provides a kind of annular space on-orbit filling system, which includes filling module and power source, after target spacecraft and filling connector are docked, filling module is rotated around the central axis of filling ring pipe by power source driving, while target spacecraft is synchronously rotated, under the action of centrifugal force, propellant in propellant storage tank is thrown into filling ring pipe, then enters target spacecraft storage tank through filling connector, and filling is completed.Compared with prior art using pressurized gas source as filling power, the annular space on-orbit filling system loses working medium during filling, and filling flow is larger, so that filling efficiency is higher, which is beneficial to improve the transportation efficiency of space transportation system.

[0023] The application also provides a kind of annular space on-orbit filling method, after target spacecraft and the above-mentioned annular space on-orbit filling system are docked, filling module is rotated by power source driving, so as to perform filling task, and working medium is not lost, so that filling efficiency is higher. BRIEF DESCRIPTION OF DRAWINGS

[0024] In order to more clearly illustrate the technical solutions in the embodiments of the application, the drawings needed to be used in the description of the embodiments of the application will be briefly introduced. Obviously, the drawings in the following description are only some embodiments of the application, and other drawings can be obtained according to the contents of the embodiments of the application and the drawings by those skilled in the art without creative labor.

[0025] Figure 1 is a structural schematic diagram of an annular space on-orbit filling system provided by the embodiments of the application;

[0026] Figure 2 is a flow chart of an annular space on-orbit filling method provided by the embodiments of the application.

[0027] In the drawings:

[0028] 1, target spacecraft storage tank;

[0029] 2, filling module; 21, propellant storage 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 connector; 53, exhaust sub-pipe; 54, first exhaust valve; 55, second exhaust valve;

[0032] 6, second filling valve. DETAILED DESCRIPTION

[0033] The application will be further described below in conjunction with the drawings and embodiments. It should be understood that the specific embodiments described herein are intended to be merely illustrative of the application and not in limitation thereof. It should also be noted that, for the purpose of description, only the parts related to the application are shown in the drawings rather than all the parts.

[0034] In the description of the application, unless otherwise explicitly specified and limited, the terms "connected", "connected", "fixed" should be understood broadly, for example, it can be fixed connection, or detachable connection, or integrated; it can be mechanical connection, or electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, or the internal communication of two elements or the interaction relationship between two elements. For those skilled in the art, the specific meaning of the above terms in the application can be understood according to the specific circumstances.

[0035] In the present application, unless otherwise explicitly specified and limited, the "upper" or "lower" of the first feature to the second feature can include that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, the "upper", "above" and "on" of the first feature to the second feature includes that the first feature is directly above and obliquely above the second feature, or only indicates that the horizontal height of the first feature is higher than that of the second feature. The "below", "under" and "under" of the first feature to the second feature includes that the first feature is directly below and obliquely below the second feature, or only indicates that the horizontal height of the first feature is less than that of the second feature.

[0036] In the description of the present embodiment, the terms "upper", "lower", "left", "right" and other orientation or position relationship are based on the orientation or position relationship shown in the drawings, which is only for the convenience of description and simplification of operation, and does not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the application. In the description of the present application, unless otherwise stated, the meaning of "a plurality of" is two or more. In addition, the terms "first", "second" are only used to distinguish in the description and have no special meaning.

[0037] The on-orbit refueling system replenishes the thrusters of the on-orbit spacecraft, which makes the on-orbit reuse of the space transportation system possible, greatly improves the transportation efficiency of the existing space transportation system, and reduces the cost of space resource development. The current on-orbit refueling system is a small propellant supply system for spacecraft such as satellites and space stations, which generally uses a pressurized gas source as the refueling power, has small refueling flow and low efficiency, and is not suitable for large-scale on-orbit refueling of spacecraft.

[0038] Based on the above technical problems, the present embodiment provides an annular on-orbit refueling system, which comprises a first annular tank, a second annular tank, a first annular pipeline and a second annular pipeline. Figure 1As shown, the annular space comprises a filling module 2 and a power source, the filling module 2 comprises a propellant tank 21, a filling ring 22 and a filling connector 23, the propellant tank 21 is located in the radial range of the filling ring 22 and communicates with the filling ring 22, the propellant tank 21 is used for storing propellant, the filling connector 23 is located outside the radial range of the filling ring 22 and communicates with the filling ring 22, the filling connector 23 is used for interfacing with the target spacecraft tank 1, the power source is drivingly connected to the filling module 2 for driving the filling module 2 to rotate around the central axis of the filling ring 22, under the driving action of the power source, after the filling module 2 is docked with the target spacecraft, the filling module 2 can rotate synchronously with the target spacecraft. After the target spacecraft is docked with the filling connector 23, the filling module 2 is driven to rotate around the central axis of the filling ring 22 by the power source, 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 22, and then enters the target spacecraft tank 1 through the filling connector 23, completing the filling. Compared with the prior art which uses a pressurized gas source as a filling power, the annular space on-orbit filling system loses working medium during filling, the filling flow is large, so that the filling efficiency is high, which is beneficial to improve the transportation efficiency of the space transportation system.

[0039] Specifically, the propellant tank 21 communicates with the filling ring 22 through a filling pipeline 3, and a first filling valve 4 is arranged in the filling pipeline 3, and the first filling valve 4 is used to control the opening and closing of the filling pipeline 3. When filling is not needed, the first filling valve 4 is closed to prevent the propellant in the propellant tank 21 from leaking, and when the filling task is performed, the first filling valve 4 is opened so that the propellant in the propellant tank 21 can smoothly enter the filling ring 22.

[0040] In order to adapt to the demand of large-scale space industry development, a plurality of propellant tanks 21 are arranged, the plurality of propellant tanks 21 are arranged in intervals in a ring, and each propellant tank 21 communicates with the filling ring 22. Preferably, each propellant tank 21 communicates through one filling pipeline 3, and one first filling valve 4 is arranged in each filling pipeline 3. The plurality of propellant tanks 21 are arranged in a ring, so that the annular space on-orbit filling system can control the number of opened first filling valves 4 according to the demand when performing the filling task, and the setting of the plurality of propellant tanks 21 makes the upper limit of the filling amount higher, that is, it can meet the demand of larger filling amount. More preferably, the plurality of propellant tanks 21 are arranged in intervals and uniformly along the circumference of the filling ring 22, so that the distribution of the propellant in the filling ring 22 is as uniform as possible.

[0041] In the embodiment, the filling connector 23 is provided with a plurality of filling connectors 23, and the plurality of filling connectors 23 are arranged along the circumference of the filling ring 22 and are in communication with the filling ring 22. Each filling connector 23 can be connected to a target spacecraft tank 1, that is, the annular space-based filling system can be connected to a plurality of target spacecraft tanks at the same time, and the plurality of target spacecraft tanks can be filled at the same time, so that batch filling is realized. The plurality of tanks can meet the filling requirements of a plurality of target spacecrafts.

[0042] Preferably, a second filling valve 6 is arranged on each filling connector 23, and the second filling valve 6 is used to control the opening and closing of the filling connector 23. The second filling valve 6 on the filling connector 23 that is not connected to a target spacecraft is closed, and the second filling valve 6 on the filling connector 23 that is connected to a target spacecraft is opened.

[0043] Further, during filling, the propellant in the filling 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 filling module 2 and the target spacecraft tank 1, the annular space-based filling system further comprises an exhaust pipe assembly 5. The exhaust pipe assembly 5 comprises an exhaust pipe 51 and an exhaust connector 52. One end of the exhaust pipe 51 is in communication with the propellant tank 21, and the exhaust connector 52 is connected to the other end of the exhaust pipe 51 and is used to be connected to the exhaust interface of the target spacecraft tank 1. During filling, the propellant flows from the filling module 2 to the target spacecraft tank 1. The propellant in the propellant tank 21 flows out, so that the internal pressure decreases, 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 to 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 realized, so that the propellant can flow smoothly, and the filling task can be carried out smoothly.

[0044] Preferably, a first exhaust valve 54 is arranged on the exhaust connector 52, and the first exhaust valve 54 is used to control the opening and closing of the exhaust connector 52. When the filling task is not performed, the first exhaust valve 54 is kept closed. When the filling task is performed and after the target spacecraft is connected to the annular space-based filling system, the first exhaust valve 54 is opened.

[0045] In the embodiment, the gas 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 arranged in each exhaust branch pipe 53. The second exhaust valve 55 is used to control the opening and closing of the exhaust branch pipe 53, so that the corresponding second exhaust valve 55 can be opened when the propellant tank 21 is needed.

[0046] Exemplarily, the filling ring 22 is circular to ensure the same flow rate of the propellant at different positions of the filling ring 22. The exhaust pipe 51 is located at the center of the filling ring 22 at the end away from the exhaust joint 52, and the plurality of exhaust sub-pipes 53 are radially connected to the plurality of propellant tanks 21 respectively. The length of each exhaust sub-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 22 can also have other shapes, such as an oval shape or an irregular shape, etc., which are set according to actual needs.

[0047] Further, the filling module 2 further comprises a base, the propellant tanks 21 are 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 22. The base provides a space for integrated installation of the propellant tanks 21, so that the filling module 2 has better integrity, and the connection of the power source is facilitated, while avoiding the shaking of the filling module 2 during rotation and other adverse movement conditions. Preferably, the filling ring 22, the filling pipeline 3, etc. can also be supported on the base to ensure the stability of the filling ring 22 and the filling pipeline 3, and improve the use reliability of the annular space on-orbit refueling system.

[0048] Specifically, the power source comprises an engine, and the output end of the engine is drivingly connected to the base to drive the base to rotate. The rotation of the base driven by the engine can realize refueling, and compared with the way of using a pressurized gas source, the annular space on-orbit refueling system has simple structure, convenient operation, and low cost. The rotation speed of the filling module 2 driven by the engine can be controlled to realize the control of the refueling flow rate, so as to realize the switching of multiple flow rates to adapt to different working conditions. The corresponding table of the rotation speed-refueling flow rate is as follows:

[0049] Table 1: Corresponding table of rotation speed-refueling flow rate

[0050] Rotational speed / rpm 0.1 0.5 1 2.5 5 Flow / (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 refueling flow rate by referring to the above-mentioned corresponding table of the rotation speed-refueling flow rate.

[0052] Preferably, the engine is a flywheel engine, which is more stable in operation and more labor-saving in starting. The flywheel engine is a relatively mature prior art, and thus will not be described here.

[0053] More specifically, the power source further comprises a solar panel, and the solar panel is electrically connected to the engine to supply power to the engine. The engine can be charged by the solar panel to realize long-term execution of the refueling task.

[0054] As Figure 2As shown, the embodiment also provides an annular space on-orbit refueling method based on the above annular space on-orbit refueling system, the annular space on-orbit refueling method comprising the following steps:

[0055] S100: The target spacecraft flies to the annular space on-orbit refueling system and docks with the annular space on-orbit refueling system. The filling interface and the exhaust interface of the storage tank on the target spacecraft are respectively sealed and docked with the filling connector and the exhaust connector of the filling module. At this time, the first filling valve and the first exhaust valve are kept closed.

[0056] S200: Start the power source to rotate the filling module and the target spacecraft, and the propellant in the propellant storage tank flows to the target spacecraft storage tank under the action of centrifugal force to perform the filling task. Preferably, before performing the filling task, pre-filling air tightness detection is required to ensure that the filling system is working properly. After the air tightness 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 requirements.

[0057] S300: After the target spacecraft storage tank completes the filling, 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 performs an unlocking operation with the annular space on-orbit refueling system, and the mechanical and filling connectors are unlocked. The target spacecraft completes the filling.

[0059] After the target spacecraft docks with the above annular space on-orbit refueling system, the filling module is driven to rotate by the power source to perform the filling task, which has high filling efficiency and does not lose the working medium.

[0060] Note that the above is only the preferred embodiment of the present application and the technical principle applied. Those skilled in the art will understand that the present application is not limited to the specific embodiments described herein, and those skilled in the art can make various obvious changes, re-adjustments and substitutions without departing from the scope of the present application. Therefore, although the present application has been described in more detail through the above embodiments, the present application is not limited to the above embodiments, and can include more other equivalent embodiments without departing from the concept of the present application, and the scope of the present application is determined by the scope of the appended claims.

Claims

1. An on-orbit refueling system for a toroidal volume, characterized by, The application relates to an on-orbit refueling system and method. The on-orbit refueling system comprises a refueling module, a power source and a base. The refueling module comprises a propellant tank, a refueling ring and a refueling joint.

2. The toroidal volume in-orbit refueling system of claim 1, wherein, The propellant tank is located in the radial range of the refueling ring and communicates with the refueling ring. The refueling joint is located outside the radial range of the refueling ring and communicates with the refueling ring.

3. The toroidal volume in-orbit refueling system of claim 2, wherein, The refueling joint is used for interfacing with the target spacecraft tank. The power source is drivingly connected with the refueling module and is used for driving the refueling module to rotate around the central axis of the refueling ring.

4. The on-orbit refueling system of claim 3, wherein, Under the driving action of the power source, the refueling module and the target spacecraft can synchronously rotate after the refueling module is docked with the target spacecraft.

5. The toroidal volume in-orbit refueling system of claim 3, wherein, The refueling module further comprises the base. The propellant tank is arranged on the base.

6. The toroidal volume in-orbit refueling system of claim 1, wherein, The power source is drivingly connected with the base to drive the base to rotate around the central axis of the refueling ring.

7. The toroidal volume in-orbit refueling system of claim 1, wherein, The power source comprises an engine.

8. The toroidal volume in-orbit refuelling system according to claim 7, characterised in that, The output end of the engine is drivingly connected with the base to drive the base to rotate.

9. The toroidal volume in-orbit refueling system of claim 1, wherein, The engine is a flywheel engine.

10. A method for on-orbit refueling of an annular space based on the on-orbit refueling system of any one of claims 1 to 9, characterized in that The power source further comprises a solar panel. The solar panel is electrically connected with the engine and is used for supplying power to the engine. The refueling joint is arranged in plurality. The plurality of refueling joints are arranged along the circumference of the refueling ring and communicate with the refueling ring. The propellant tank is arranged in plurality. The plurality of propellant tanks are arranged in intervals and each communicates with the refueling ring. Each propellant tank communicates with the refueling ring through a refueling pipeline. A first refueling valve is arranged in each refueling pipeline to control the opening and closing of the refueling pipeline. The on-orbit refueling system further comprises an exhaust pipeline assembly. The exhaust pipeline assembly comprises an exhaust pipeline and an exhaust joint. One end of the exhaust pipeline communicates with the propellant tank. The exhaust joint communicates with the other end of the exhaust pipeline and is used for interfacing with the exhaust interface of the target spacecraft tank. The on-orbit refueling method of the annular space comprises the following steps. The target spacecraft flies to the on-orbit refueling system of the annular space and is docked with the on-orbit refueling system of the annular space. The power source is started to drive the refueling module and the target spacecraft to rotate. The propellant in the propellant tank flows to the target spacecraft tank under the action of centrifugal force to perform a refueling task. After the target spacecraft tank is refueled, the power source is turned off to stop the rotation of the refueling module and the target spacecraft. The target spacecraft performs an unlocking operation with the on-orbit refueling system of the annular space. The refueling joint is unlocked and the target spacecraft is refueled.

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