Space charging station and space energy system

Abstract

The invention relates to the technical field of space energy, in particular to a space charging station and a space energy system. The space charging station comprises a charging station main body, an energy acquisition device, an electric energy transmission device and a control device. The charging station body is provided with an energy conversion device and an energy storage device. The energy acquisition device is used for acquiring energy; the electric energy transmission device is connected with the energy storage device; the control device is connected with the energy acquisition device, the energy conversion device, the energy storage device and the electric energy transmission device. According to the space charging station and the space energy system provided by the invention, a power mode of carrying independent power generation or charging equipment on each spacecraft is replaced, and the spacecrafts in a space environment can be charged. Multiple energy forms are fully utilized, the energy utilization rate is high, and on-orbit long-time stable operation is achieved; safe, reliable, fast and efficient electric energy supply is provided for various spacecrafts with adjacent orbits or short-time approaching, and the flexibility and sustainability of on-orbit tasks are improved.

Description

Technical Field

[0001] This invention relates to the field of space energy technology, and in particular to a space charging station and a space energy system. Background Technology

[0002] With the rapid development of aerospace technology, the number and mission complexity of various types of spacecraft in orbit are continuously increasing. Typical examples include large space stations, manned spacecraft, deep space probes, small satellite constellations, and in-orbit servicing spacecraft. These spacecraft are increasingly reliant on electrical energy for propulsion, attitude and orbit control, telemetry and communication, payload operation, and module environmental maintenance, resulting in a significant increase in their power consumption per unit time. To meet mission requirements, individual spacecraft need to carry increasingly large-area solar cell arrays and high-capacity battery packs, leading to increased overall satellite structural complexity, weight, and volume, thereby increasing launch costs and consuming valuable payload resources.

[0003] Currently, the power systems of spacecraft in orbit typically adopt a distributed power supply model, where each spacecraft is independently equipped with power generation and energy storage units. Power is generated locally via solar cells, nuclear batteries, or other power generation devices, and stored using chemical batteries, flywheel energy storage, and other methods. While this model is technologically mature and widely used, it suffers from low resource utilization, high redundancy, and difficulties in maintenance and upgrades. On the one hand, to ensure power supply security under extreme conditions, individual spacecraft often require a large design margin, resulting in idle and wasted power generation and storage capacity during most operating conditions. On the other hand, when individual spacecraft are under conditions such as solar eclipses, deep space environments, or temporary high loads, they may face the risk of short-term power shortages or even power outages, lacking effective means of on-orbit peak shaving and replenishment.

[0004] Therefore, there is an urgent need for a new form of on-orbit energy infrastructure that can break through the traditional design concept of self-sufficient power supply for a single spacecraft and realize centralized production, networked distribution and flexible use of space energy. Summary of the Invention

[0005] This invention provides a space charging station and a space energy system to solve the defects of existing technologies where spacecraft in orbit are independently equipped with power generation and energy storage units, resulting in low resource utilization, high redundancy, and difficulties in maintenance and upgrading.

[0006] This invention provides a space charging station, comprising: The main body of the charging station is equipped with an energy conversion device and an energy storage device, and the energy conversion device and the energy storage device are connected. An energy harvesting device, used to harvest energy, and connected to the energy conversion device; An electrical power transmission device is connected to the energy storage device; The control device is connected to the energy acquisition device, the energy conversion device, the energy storage device and the power transmission device respectively, and controls the power transmission device to output power according to the spacecraft recharge signal.

[0007] According to the space charging station provided by the present invention, the energy harvesting device includes: a space nuclear energy unit and / or a solar power generation unit; the space nuclear energy unit is connected to the energy conversion device, and the solar power generation unit is connected to the energy conversion device; When the space nuclear energy unit and the solar power generation unit are used simultaneously, the space nuclear energy unit and the solar power generation unit are controlled by the control device.

[0008] According to the space charging station provided by the present invention, the energy harvesting device includes: the space nuclear energy unit includes: a space nuclear reactor or a nuclear battery stack.

[0009] According to the space charging station provided by the present invention, the solar power generation unit includes any one of the following: a deployable truss photovoltaic array structure, a thin-film flexible solar panel structure, and a photovoltaic integrated structure.

[0010] According to the space charging station provided by the present invention, the energy storage device includes at least one of: a chemical battery pack, a flywheel energy storage unit, and a thermal energy storage unit; The energy conversion device converts electrical energy into at least one of chemical energy, mechanical energy, and thermal energy, and stores chemical energy through the chemical battery pack, mechanical energy through the flywheel energy storage unit, and thermal energy through the thermal energy storage unit.

[0011] According to the space charging station provided by the present invention, the power transmission device includes: Directed energy beam transmitting unit, used to transmit electrical energy via laser or microwave; A beam control unit, connected to the directional energy beam transmitting unit, is used to control the attitude and / or pointing of the directional energy beam and to shape the directional energy beam.

[0012] According to the space charging station provided by the present invention, the power transmission device includes: An electromagnetic charging module is used to wirelessly charge nearby target spacecraft.

[0013] According to the space charging station provided by the present invention, the electromagnetic charging module includes: A primary excitation coil is disposed on the main body of the charging station; The secondary receiving coil is located on the target spacecraft; among which... When the target spacecraft approaches the space charging station, a near-field magnetic coupling is formed between the primary excitation coil and the secondary receiving coil. By driving the primary excitation coil to establish an alternating magnetic field in the coupling region, a voltage is induced in the secondary receiving coil.

[0014] According to the space charging station provided by the present invention, the power transmission device includes: The charging interface is used to match the interface on the target spacecraft for wired charging.

[0015] The present invention also provides a space energy system, including: the space charging station of the present invention.

[0016] This invention provides a space charging station, comprising: a charging station main body, an energy harvesting device, a power transmission device, and a control device. The charging station main body is equipped with an energy conversion device and an energy storage device, which are connected together. The energy harvesting device is used to harvest energy and is connected to the energy conversion device. The power transmission device is connected to the energy storage device. The control device is connected to the energy harvesting device, the energy conversion device, the energy storage device, and the power transmission device respectively, and controls the power transmission device to output power according to the spacecraft's recharge signal. This invention provides a space charging station that replaces the traditional method of carrying independent power generation or charging equipment on each spacecraft, enabling the charging of spacecraft in the space environment. On the one hand, the space charging station is not constrained by the spacecraft design. It can be designed with high-power, high-specific-power generation and energy storage equipment, making full use of energy forms such as space solar energy and nuclear energy, with high energy utilization and stable operation in orbit for a long time. On the other hand, through the power transmission device, it can provide safe, reliable, fast and efficient power supply to various spacecraft that are nearby or approaching for a short time in orbit, relieving the design pressure of the power system on the spacecraft, reducing the launch cost of the spacecraft, and improving the flexibility and sustainability of on-orbit missions.

[0017] Furthermore, the space energy system provided by the present invention, since it includes the space charging station of the embodiments of the present invention, has the same advantages as described above. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in this invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0019] Figure 1 This is a schematic diagram of the structure of a space charging station provided in one embodiment of the present invention.

[0020] Figure 2 This is a schematic diagram of the main structure of the charging station provided in one embodiment of the present invention.

[0021] Figure label: 1. Main body of the charging station; 2. Solar power generation unit; 3. Space nuclear energy unit; 4. Directional energy beam transmission unit; 5. Electromagnetic charging module; 6. Charging interface; 7. Parking platform entrance. Detailed Implementation

[0022] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of this invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this invention. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0023] In the description of this embodiment, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this embodiment and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this embodiment.

[0024] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this embodiment, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0025] In this embodiment, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," "link," and "fix" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this embodiment based on the specific circumstances.

[0026] In embodiments of the present invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0027] The following is combined with Figures 1-2 This invention describes a space charging station. The space charging station includes: a charging station body 1, an energy harvesting device, an energy transmission device, and a control device.

[0028] The main body 1 of the charging station is equipped with an energy conversion device and an energy storage device, which are connected together; an energy acquisition device is used to acquire energy and is connected to the energy conversion device; an electrical energy transmission device is connected to the energy storage device; and a control device is connected to the energy acquisition device, the energy conversion device, the energy storage device, and the electrical energy transmission device respectively, and controls the electrical energy transmission device to output electrical energy according to the spacecraft's recharge signal.

[0029] The present invention provides a space charging station, which is set up in space to realize centralized power generation and unified energy management in the space environment. It serves as an independent on-orbit energy node, which centrally collects and stores energy in space and uses it to replenish the energy of various types of spacecraft in the surrounding area on demand, thereby making up for the shortcomings of existing technologies in centralized supply and rapid replenishment of on-orbit power.

[0030] Specifically, the main body 1 of the charging station serves as the main structure of the space charging station, integrating an energy conversion device and an energy storage device. The energy conversion device is mainly used to convert the energy acquired by the energy acquisition device into other forms of energy, such as chemical energy, mechanical energy, and thermal energy; the energy storage device is used to store the converted energy.

[0031] Specifically, the energy harvesting device is used to harvest energy in the space environment. Preferably, it can generate electricity by harvesting solar energy in space or by generating electricity through space nuclear power technology. After being converted into electrical energy, it is converted into other forms of energy by an energy conversion device for easy storage and is stored by an energy storage device.

[0032] Specifically, an electrical power transmission device is used to output energy stored in an energy storage device to a designated spacecraft for use, generally in the form of electrical energy. Understandably, an electrical power transmission device is equipped with a conversion module to convert the chemical energy, mechanical energy, thermal energy, or other forms of energy stored in the energy storage device into electrical energy for output. For example, chemical energy can be converted into electrical energy using a chemical battery; mechanical energy can be converted into electrical energy using a generator; and thermal energy can be converted into electrical energy using a Stirling engine or a thermophotovoltaic cell, etc.

[0033] Specifically, the control device is mainly used to control the operating status of various devices in the space charging station. For example, it adjusts the operating status of the energy harvesting device according to the operating conditions, adjusts the operating status of the energy conversion device and the energy storage device according to the energy acquired by the energy harvesting device, and controls the power transmission device to output electrical energy according to the spacecraft's recharging signal. When the spacecraft approaches or docks with the charging interface 6, electrical energy is output to the spacecraft through the power transmission device for charging.

[0034] Therefore, this invention provides a space charging station that replaces the traditional method of carrying independent power generation or charging equipment on spacecraft, enabling the charging of spacecraft in the space environment. On one hand, the space charging station is not constrained by spacecraft design; it can be designed with high-power, high-specific-power generation and energy storage equipment, fully utilizing energy forms such as space solar energy and nuclear energy, resulting in high energy utilization and long-term stable operation in orbit. On the other hand, through power transmission devices, it provides safe, reliable, fast, and efficient power replenishment to various spacecraft orbiting nearby or in short-term proximity, alleviating the design pressure on spacecraft power systems, reducing launch costs, and improving the flexibility and sustainability of on-orbit missions.

[0035] In terms of power generation methods, space nuclear power technology and giant space solar power technology have been developing gradually in recent years. Space nuclear reactors and nuclear battery reactors can provide stable and continuous high-power power, suitable for long-life, high-power missions; giant space solar power can collect solar energy in orbit through ultra-large-scale deployable photovoltaic structures, and is expected to form large-scale power generation capacity. However, these power generation devices are mostly for specific missions or single platforms, and have not yet formed an on-orbit energy infrastructure that can be shared by multiple platforms.

[0036] Against the above background, the present invention proposes an embodiment: an energy harvesting device comprising a space nuclear energy unit 3 and / or a solar power generation unit 2; the space nuclear energy unit 3 is connected to an energy conversion device, and the solar power generation unit 2 is connected to the energy conversion device. When the space nuclear energy unit 3 and the solar power generation unit 2 are used simultaneously, they are controlled by a control device to form a complementary energy harvesting method. Specifically, the two energy forms of the space nuclear energy unit 3 and the solar power generation unit 2 can be configured independently, or they can be configured into a nuclear-solar complementary or redundant combination according to mission requirements, thereby improving the reliability and mission adaptability of the system operation.

[0037] When the two energy sources work together to generate electricity, the space nuclear energy unit 3 has a stable power supply capability that is continuous day and night and independent of solar radiation conditions; the solar power generation unit 2 uses a large-area deployable solar cell array, combined with a high-efficiency tracking and pointing mechanism, to achieve high specific power harvesting of solar energy. Specifically, the solar power generation unit 2 is used to efficiently capture solar energy in orbit and provide high-power electrical energy to the main charging station 1; the space nuclear energy unit 3 is used to provide stable and continuous basic power to the space charging station under conditions of limited sunlight, solar eclipse, or far-from-the-sun distance. It can be seen that during system operation, by capturing solar energy through the solar power generation unit 2 and supplementing and redundantly supporting solar power generation by the space nuclear energy unit 3, stable energy acquisition can be achieved.

[0038] In one embodiment of the present invention, the energy harvesting device includes: a space nuclear energy unit 3 comprising a space nuclear reactor or a nuclear battery stack. Preferably, the space nuclear energy unit 3 may include a sodium-based or lead-based fast reactor and future fusion power generation equipment; through the complementary configuration of the space nuclear energy unit 3 and the solar power generation unit 2, stable energy supply can be achieved under different orbital positions and operating conditions, improving the overall mission adaptability of the space charging station.

[0039] Furthermore, the solar power generation unit 2 is connected to the busbar of the main body 1 of the charging station via a cable or a slip ring mechanism inside a rotating joint, ensuring continuous power delivery while adjusting its orientation. To improve system reliability, a multi-wing independently controlled array configuration can be adopted, so that when some arrays fail, the remaining arrays can still maintain the basic power supply capacity of the charging station.

[0040] In one embodiment of the present invention, the solar power generation unit 2 includes any one of the following: an unfoldable truss photovoltaic array structure, a thin-film flexible solar panel structure, and a photovoltaic integrated structure.

[0041] Specifically, the unfoldable truss photovoltaic array structure uses folded / rolled photovoltaic modules, which unfold to form a large-area array after entering the track via a hinged truss; a one-degree-of-freedom or multi-degree-of-freedom drive joint is set at the root of the truss to realize the yaw / pitch tracking of the solar cell array; the photovoltaic modules can use high-efficiency multi-junction gallium arsenide cells to generate electricity on one or both sides.

[0042] Specifically, the thin-film flexible solar panel structure uses flexible thin-film photovoltaic materials to form a large-scale solar sail through a roll-up method; it is suitable for mission scenarios with high power requirements and extreme sensitivity to weight; and it can be combined with tensioning cables / telescopic rods to achieve in-plane tensioning and shape retention.

[0043] Specifically, the integrated photovoltaic structure involves placing a reflector or Fresnel lens in front of a regular photovoltaic array to achieve moderate concentration of incident sunlight; by optimizing the concentration factor and heat dissipation structure, the power generation per unit area is increased without significantly increasing the heat load.

[0044] In one embodiment of the present invention, the energy storage device includes at least one of a chemical battery pack, a flywheel energy storage unit, and a thermal energy storage unit. The energy conversion device converts electrical energy into at least one of chemical energy, mechanical energy, and thermal energy, storing chemical energy through the chemical battery pack, mechanical energy through the flywheel energy storage unit, and thermal energy through the thermal energy storage unit. Specifically, the energy conversion device mainly includes a power conversion and distribution module to realize the conversion of electrical energy at different voltage levels and in different systems, as well as bus management; the energy storage device adopts a multi-element energy storage module, which may include a chemical battery pack, a flywheel energy storage unit, and a thermal energy storage unit, storing electrical energy by converting it into chemical energy, mechanical energy, or thermal energy respectively, to meet the energy needs of peak-valley regulation, emergency backup, and long-term missions at different time scales. In this embodiment, the energy storage device and the energy conversion device are controlled by a controller, achieving a dynamic balance between energy acquisition and energy output through reasonable capacity configuration and control strategies.

[0045] In terms of power transmission and replenishment, laser / microwave wireless power transmission technology, electromagnetic short-range power transmission technology, and wired fast charging technology are developing rapidly. Laser and microwave power transmission can achieve cross-platform and cross-distance power transfer through directional energy beams, with advantages such as no rigid connection required and long-distance power supply. However, technical challenges remain in areas such as pointing accuracy, energy beam scattering, transmission efficiency, and safety protection for other orbital targets and personnel. Electromagnetic short-range power transmission technology transmits energy through magnetic field coupling between transmitting and receiving coils. Wired fast charging technology typically relies on mechanical docking mechanisms. After the two spacecraft complete a rigid connection, rapid charging is achieved through high-power cables. This method has high transmission efficiency and reliability, but it is limited by docking conditions, relative orbital constraints, and inconsistent standard interfaces, making it difficult to flexibly cover multiple types and multiple orbital targets.

[0046] Against the above background, the present invention proposes an embodiment of a power transmission device comprising: a directional energy beam transmitting unit 4 and a beam control unit. The directional energy beam transmitting unit 4 is used to transmit electrical energy via laser or microwave; the beam control unit is connected to the directional energy beam transmitting unit 4 and is used to control the attitude and / or pointing of the directional energy beam, as well as beam shaping. Specifically, the power transmission device in this embodiment employs a wireless power transmission module, which includes the directional energy beam transmitting unit 4 and the beam control unit; preferably, the directional energy beam transmitting unit 4 employs a laser or microwave directional energy beam transmitting device, and utilizes the beam control unit to achieve short-to-medium distance cross-platform power transmission through high-precision attitude / pointing control and beam shaping, while simultaneously providing safety protection and a beam shutdown mechanism to prevent accidental illumination of other spacecraft or personnel.

[0047] Specifically, the directed energy beam transmitting unit 4 is disposed on the outer surface of the charging station body 1 and is used to wirelessly transmit energy to the spacecraft carrying the energy receiving unit. The directed energy beam transmitting unit 4 may include a laser energy emitting unit and / or a microwave energy emitting unit.

[0048] Against the above background, the present invention proposes an embodiment: a power transmission device comprising an electromagnetic charging module 5, which is used to wirelessly charge a nearby target spacecraft. The electromagnetic charging module 5 is based on the principle of near-field electromagnetic coupling. When the space charging station and the target spacecraft are relatively close and their attitudes are relatively stable, an alternating magnetic field coupling channel is formed between them by arranging mutually coupled primary and secondary coils, along with a matching compensation network, power rectification, and control circuitry, thereby achieving contactless power transmission.

[0049] Specifically, the electromagnetic charging module 5 includes: a primary excitation coil, a magnetic core assembly and a compensation circuit, as well as a secondary receiving coil and a rectifier filter circuit arranged on the target spacecraft. The primary excitation coil is located on the charging station body 1; the secondary receiving coil is located on the target spacecraft. When the target spacecraft approaches the space charging station, a near-field magnetic coupling is formed between the primary excitation coil and the secondary receiving coil. By driving the primary excitation coil to establish an alternating magnetic field in the coupling region, a voltage is induced in the secondary receiving coil.

[0050] When the target spacecraft is charged by the electromagnetic charging module 5, the target spacecraft is positioned on the parking platform or approaches the space charging station at a predetermined attitude and distance. Near-field magnetic coupling is formed between the primary coil and the secondary coil. The primary excitation coil is driven by high-frequency AC to establish an alternating magnetic field in the coupling region, thereby inducing a voltage in the secondary receiving coil. After rectification, filtering and voltage regulation, the voltage is used to charge the spacecraft's battery pack or DC bus.

[0051] Against the above background, the present invention proposes an embodiment: the power transmission device includes a charging interface 6, which is used to match an interface on a target spacecraft for wired charging. This embodiment employs a wired energy transmission module, based on a mechanical docking mechanism, to achieve rapid energy transmission using a high-power cable after the space charging station and the target spacecraft have completed a flexible or rigid connection. Preferably, the charging interface 6 includes two types of interfaces: a flexible hose-cone sleeve docking system and a rigid tube docking system, which can be configured according to mission requirements or a combination of both. The charging interface 6 is structurally designed with a standardized mounting surface and consistent electrical and communication standards, so that different types of spacecraft only need to have a matching interface pre-installed on their bodies to connect to the wired charging network of the space charging station.

[0052] In one embodiment of the present invention, the space charging station further includes a parking platform entrance 7, which is located outside the main body 1 of the charging station and is used to guide the spacecraft into the parking platform to complete docking and charging. Through the parking platform docking structure, the space charging station of the present invention can not only achieve short-term rapid charging, but also serve as an on-orbit energy and service hub, providing long-term docking, energy replenishment, and maintenance support for multiple spacecraft.

[0053] The present invention also provides a space energy system. This space energy system includes the space charging station described in the above embodiments of the present invention.

[0054] The space energy system provided by this invention has the same advantages as described above because it includes the space charging station of the embodiments of this invention.

[0055] Furthermore, energy receiving devices are installed on various spacecraft requiring recharging to receive energy from space charging stations and convert it into electrical energy that can be directly used by the spacecraft's power system. To enable cross-platform and cross-model applications, the energy receiving devices preferably adopt standardized structural dimensions, electrical parameters, and communication protocols, allowing spacecraft of different countries and models to connect to the space charging station network with minimal modifications or pre-configuration.

[0056] In summary, the space charging station and space energy system provided by this invention effectively solves the shortcomings of long-term rapid replenishment of space power through an overall configuration of centralized power generation—multi-element energy storage—multi-mode transmission—standard reception—unified management, and has the following beneficial effects: 1. Centralized Power Generation and On-Demand Space Energy Network Architecture: This architecture proposes the construction of a dedicated energy node (space charging station) operating independently in space, revolutionizing the traditional distributed power supply model for spacecraft. The core idea of ​​this architecture is to centrally collect space energy (solar / nuclear energy) and, through unified management and control, provide on-demand, efficient power replenishment services to various types and missions of spacecraft in orbit, thereby reducing the burden on single-satellite power systems and launch costs. 2. Complementary and Redundant Integrated System of Nuclear and Solar Energy: The space nuclear energy unit 3 (such as a small nuclear reactor or nuclear battery stack) and the solar power generation unit 2 (a large-area deployable photovoltaic array) are integrated on the same platform. This design achieves the complementary advantages of the two energy forms (nuclear energy provides a stable base load, and solar energy provides a high power peak) and mutual redundancy, significantly improving the charging station's continuous and stable power supply capability and mission adaptability under different orbital environments (such as sunshine periods, solar eclipses, and deep space).

[0057] 3. Multi-functional composite energy storage system for space applications: The energy conversion and storage device integrates multiple energy storage forms such as chemical battery packs, flywheel energy storage units, and thermal energy storage units. This composite system aims to optimize and dynamically manage energy demands at different time scales (instantaneous, short-term, long-term) and different power levels (peak power, continuous power) in space missions, achieving efficient energy storage and flexible scheduling to meet the sudden, periodic, or continuous refueling needs of spacecraft.

[0058] 4. Multimodal Energy Transfer Interface and Flexible Replenishment Methods: The power transfer device integrates three technical approaches: a wireless power transfer module (laser / microwave), an electromagnetic charging module (non-contact near-field coupling), and a wired power transfer module (mechanical docking). This multimodal design allows the system to flexibly select or combine the most suitable replenishment methods based on the type of target spacecraft, relative orbital state, docking conditions, and safety requirements, achieving efficient and reliable energy transfer coverage for a wide range of on-orbit targets.

[0059] 5. Standardized and universal spacecraft-side energy receiving interface: This requires spacecraft requiring refueling to be equipped with a unified energy receiving device (corresponding to wireless, electromagnetic, and wired modes), emphasizing standardized design in structural dimensions, electrical parameters, and communication protocols. This design aims to promote the formation of a standard for space energy refueling interfaces, enabling spacecraft of different countries and models to connect to the charging station network with limited modifications. This is crucial for the widespread application and commercialization of space charging stations.

[0060] 6. Platform-based design integrating energy replenishment and on-orbit services: The space charging station not only provides power transmission but also features a docking platform entrance 7 and corresponding docking mechanisms. This allows it to simultaneously serve as an on-orbit "energy hub" and "service port," providing comprehensive support for spacecraft, including long-term berthing, energy replenishment, and potential condition monitoring and maintenance, thus expanding the platform's functionality and value.

[0061] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A space charging station, characterized in that, include: The main body of the charging station (1) is equipped with an energy conversion device and an energy storage device, and the energy conversion device and the energy storage device are connected; An energy harvesting device, used to harvest energy, and connected to the energy conversion device; An electrical power transmission device is connected to the energy storage device; The control device is connected to the energy acquisition device, the energy conversion device, the energy storage device and the power transmission device respectively, and controls the power transmission device to output power according to the spacecraft recharge signal.

2. The space charging station according to claim 1, characterized in that, The energy harvesting device includes: a space nuclear energy unit (3) and / or a solar power generation unit (2); the space nuclear energy unit (3) is connected to the energy conversion device, and the solar power generation unit (2) is connected to the energy conversion device; When the space nuclear energy unit (3) and the solar power generation unit (2) are used simultaneously, the space nuclear energy unit (3) and the solar power generation unit (2) are controlled by the control device.

3. The space charging station according to claim 2, characterized in that, The energy harvesting device includes: the space nuclear energy unit (3) includes: a space nuclear reactor or a nuclear battery stack.

4. The space charging station according to claim 2, characterized in that, The solar power generation unit (2) includes any one of the following: a deployable truss photovoltaic array structure, a thin-film flexible solar panel structure, and a photovoltaic integrated structure.

5. The space charging station according to claim 1, characterized in that, The energy storage device includes at least one of the following: a chemical battery pack, a flywheel energy storage unit, and a thermal energy storage unit; The energy conversion device converts electrical energy into at least one of chemical energy, mechanical energy, and thermal energy, and stores chemical energy through the chemical battery pack, mechanical energy through the flywheel energy storage unit, and thermal energy through the thermal energy storage unit.

6. The space charging station according to any one of claims 1 to 5, characterized in that, The power transmission device includes: Directional energy beam transmitting unit (4) is used to transmit electrical energy via laser or microwave; The beam control unit is connected to the directional energy beam transmitting unit (4) and is used to control the attitude and / or pointing of the directional energy beam and the shaping of the directional energy beam.

7. The space charging station according to any one of claims 1 to 5, characterized in that, The power transmission device includes: An electromagnetic charging module (5) is used to wirelessly charge a nearby target spacecraft.

8. The space charging station according to claim 7, characterized in that, The electromagnetic charging module (5) includes: A primary excitation coil is disposed on the main body (1) of the charging station; The secondary receiving coil is located on the target spacecraft; among which... When the target spacecraft approaches the space charging station, a near-field magnetic coupling is formed between the primary excitation coil and the secondary receiving coil. By driving the primary excitation coil to establish an alternating magnetic field in the coupling region, a voltage is induced in the secondary receiving coil.

9. The space charging station according to any one of claims 1 to 5, characterized in that, The power transmission device includes: The charging interface (6) is used to match the interface on the target spacecraft for wired charging.

10. A space energy system, characterized in that, include: The space charging station according to any one of claims 1 to 9.

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