A high-power wireless power supply satellite and power receiving system for on-orbit spacecraft

Abstract

This invention discloses a high-power wireless power supply satellite and power receiving system for on-orbit spacecraft. The constellation system adopts a distributed networking architecture and is mainly configured with three power supply modes: first, a wireless companion charging mode, where multiple satellites orbit routinely high-power spacecraft to provide centralized power, thereby reducing energy supply risks; second, a long-distance fast charging mode, where the power supply constellation is deployed in a sun-synchronous orbit and utilizes minute-level convergence windows to provide high-power fast charging to multiple spacecraft through multi-beamforming; and third, a simultaneous multi-ground station continuous power supply mode, where synchronous information exchange and beam control of a sparse constellation in medium and high orbits form multiple narrow beams on the ground, significantly reducing the size of the receiving antenna. Preferably, the system can supplement companion satellites equipped only with focusing reflectors to enhance power generation capabilities. In summary, this invention effectively overcomes the technical constraints of ultra-large-scale on-orbit assembly, realizing lightweight, large-scale deployment, and efficient power supply of space solar energy.

Description

Technical Field

[0001] This invention relates to the field of wireless power transmission in space, and more particularly to a high-power wireless power supply satellite and power receiving system for on-orbit spacecraft. Background Technology

[0002] Space has unique advantages in terms of solar energy resources. The intensity of light in space can be more than five times that of light on the ground. The efficient development and utilization of space solar energy can effectively promote the development of new space productivity, drive the transformation and upgrading of the energy system, and has important strategic significance for ensuring the country's long-term energy security.

[0003] With the rapid iteration and development of aerospace technology, new types of space infrastructure, such as space computing centers, high-power remote sensing satellites, and ultra-low Earth orbit long-duration spacecraft, have become the mainstream development trend in the aerospace field. Compared with traditional space payloads, the power consumption of these new types of space equipment has increased significantly, placing extremely high demands on space energy supply capabilities. Taking the AISatMini computing satellite launched by SpaceX as an example, its operating power requirement is 100kW. To meet this power supply requirement, the satellite needs to be equipped with more than 600 square meters of solar panels and about 100 square meters of heat dissipation panels. Compared with the Starlink V2Mini communication satellite, which is currently the largest deployed satellite in orbit, the solar panel area of ​​this computing satellite is about six times larger. Moreover, with the continuous upgrading of space computing power and the iterative improvement of space payload performance in the future, the area of ​​solar panels required for satellites will further increase. The traditional power supply mode that relies on large-area solar panels to collect solar energy will significantly increase the structural volume and weight of satellites, seriously restricting the miniaturization, lightweighting, and large-scale mass deployment of new satellites, and making it difficult to adapt to the power supply needs of the massive number of new space infrastructures in the future. Therefore, the industry urgently needs to break through the technical bottlenecks of traditional space solar energy utilization models, develop new space solar energy utilization paradigms, and significantly improve space power supply capabilities while controlling the area of ​​satellite energy receiving structures, thus solving the core problem of insufficient energy supply for future on-orbit spacecraft.

[0004] Currently, extensive research has been conducted both domestically and internationally on space-based solar power generation and energy transfer technologies. Most mainstream technologies focus on geostationary orbit scenarios, with centralized space-based solar power stations assembled in orbit as the primary implementation method. Among these, NASA's integrated symmetrical concentrating solar power station scheme is a typical centralized technology. This scheme constructs a giant concentrating structure by assembling 36 sets of optical mirrors, each 456 meters in diameter, at a centrally symmetrical location. Large-area photovoltaic panels at the focal point convert solar energy into electricity, which is then transmitted to the ground via a 500-meter diameter microwave antenna. The accompanying ground-based microwave receiving antenna array has a diameter of up to 8 kilometers. The overall system is massive and structurally complex.

[0005] To address the shortcomings of traditional centralized solar power systems in the United States, such as the difficulty in adjusting reflectors, high system integration complexity, and poor engineering feasibility, Xi'an University of Electronic Science and Technology in China proposed a spherical concentrating space solar power station solution (patent number CN201610126919.4), which optimizes and improves the traditional concentrating power generation structure. However, this solution still belongs to the centralized space solar power station system, and the core technical bottlenecks have not been fundamentally resolved: the system construction is highly dependent on the precise on-orbit assembly of ultra-large-scale payloads such as concentrators and microwave antennas, making engineering implementation extremely difficult; at the same time, the single-platform centralized energy harvesting and transfer mode makes its operational performance highly dependent on regular on-orbit inspections, component replacements, and maintenance, resulting in high on-orbit operation and maintenance costs and difficulties, and making it difficult to guarantee long-term operational stability.

[0006] To overcome the technical constraints of ultra-large-scale on-orbit assembly and reduce the engineering implementation difficulty of centralized power plants, Xi'an University of Electronic Science and Technology has further proposed a distributed space solar power plant solution (patent number CN202511426053). This solution breaks down the ultra-large-volume centralized spherical concentrator into several small spherical concentrator arrays, adopts a modular distributed structure design, and can achieve batch launch and segmented on-orbit assembly. A complete space power plant can be constructed through multi-array formation flight networking, effectively reducing the construction difficulty of a single on-orbit assembly.

[0007] However, existing distributed space solar power station solutions still have shortcomings: First, the envelope volume and overall weight of each subarray are still too large, making it difficult to achieve large-scale batch transmission and network deployment, thus limiting large-scale applications; Second, the solution still relies on complex on-orbit assembly processes, and core engineering technical challenges have not been completely overcome; Third, compared with traditional centralized solutions, the effective radiation area of ​​a single group or a small number of subarray combinations of transmitting antennas is significantly reduced. To ensure energy transfer efficiency, larger ground or space receiving antennas are required, which greatly increases the cost and difficulty of supporting engineering construction, hindering the lightweight and universal engineering applications of space solar power technology.

[0008] In summary, current space solar energy utilization and on-orbit power supply technologies still have many shortcomings. There is a lack of space solar power supply system technologies that can be adapted to large-scale on-orbit spacecraft power supply scenarios, have low engineering difficulty, and can be deployed on a large scale. There is an urgent need to develop new space solar power generation and power supply solutions to break through existing technological barriers. Summary of the Invention

[0009] To address the aforementioned technical problems, this invention proposes a high-power wireless power supply satellite and power receiving system for on-orbit spacecraft. Leveraging the numerical advantage of a large-scale power supply satellite constellation and multi-satellite spatial coherent power combining, it achieves improved energy acquisition capabilities while maintaining a smaller receiving antenna area for the on-orbit spacecraft. This invention differs from others in that it adopts the mass production, manufacturing, launch, and networking model of commercial internet communication satellites. The power supply satellite employs a flat structure design and is equipped with a planar phased array antenna and a large-area solar panel. The entire satellite constellation achieves network synchronization through a laser communication terminal. Due to the large number of power supply satellites, multiple coverage areas of the target space region can be achieved. The use of multiple satellites for spatial power coherent combining to form a high-gain narrow beam reduces the required receiving antenna area for the power receiving satellite. Furthermore, multi-satellite multi-beamforming enables simultaneous power supply to multiple power receiving satellites. Since the receiving antenna area of ​​the power receiving satellite is small and it needs to receive high-power microwave energy, the microwave energy is buffered through capacitors after conversion into electrical energy, and then the satellite battery is charged at a high rate.

[0010] This invention discloses a high-power wireless power supply satellite for on-orbit spacecraft and a power receiving system, comprising: A power supply satellite constellation, comprising a network of multiple flat-structured power supply satellites, each including a photovoltaic array for photoelectric conversion; A phased array antenna, which is disposed in the power supply satellite constellation and is used to transmit microwave energy; A planar power receiving system, wherein the planar power receiving system is disposed on the surface of the target spacecraft and faces the phased array antenna; A receiving antenna, which is fixed to the front end of the flat-panel power receiving system and is used to receive microwave energy; A rectifier circuit, which is connected in series with the receiving antenna to convert the received microwave energy into DC power. A capacitor is connected in series with the rectifier circuit to buffer the DC power.

[0011] In one embodiment of the present invention, it further includes: A beamforming control module is located inside the power supply satellite constellation and is connected to the phased array antenna signal to regulate the transmission phase.

[0012] In one embodiment of the present invention, it further includes: An inter-satellite laser communication networking module is connected between the power supply satellites of the power supply satellite constellation to achieve real-time data sharing of the constellation.

[0013] In one embodiment of the present invention, it includes: A wireless companion charging mode unit is configured in the power supply satellite constellation and is used to provide centralized power supply to spacecraft that routinely orbits and accompanies multiple satellites.

[0014] In one embodiment of the present invention, it includes: A long-distance fast charging mode unit is configured in the power supply satellite constellation and is used to charge the receiving spacecraft within a minute-level convergence time.

[0015] In one embodiment of the present invention, it includes: Simultaneous multi-ground station continuous power supply mode unit, the simultaneous multi-ground station continuous power supply mode unit is configured in the power supply satellite constellation and is used to implement multi-station synchronous power supply on the distributed orbital plane.

[0016] In one embodiment of the present invention, it includes: The companion satellite is deployed in the vicinity of the power supply satellite constellation and is equipped only with a focusing reflector to supplement power when the power generation capacity of a single power supply satellite is insufficient.

[0017] In one embodiment of the present invention, the power supply satellite further includes: A concentrating reflector is used to reflect sunlight to the photovoltaic array.

[0018] In one embodiment of the present invention, it includes: A narrow beamforming structure is disposed at the output end of the phased array antenna and is used to form multiple narrow beams on the ground to reduce the area of ​​the receiving antenna.

[0019] In one embodiment of the present invention, it includes: A laser communication device is installed on each power supply satellite and is signal-connected to the inter-satellite laser communication networking module.

[0020] The present invention has the following beneficial effects: (1) Unlike existing technical solutions, this invention uses a flattened structure design for the power supply satellite, which is suitable for batch stacked launch; and achieves multiple global coverage through large-scale power supply satellite constellation networking deployment, enabling multiple power supply satellites to coherently synthesize high-power power supply to spacecraft in orbit. (2) Through inter-satellite laser communication networking, the power supply satellite constellation shares data information in real time. Multiple power supply satellites can simultaneously provide high-power wireless power to multiple spacecraft through multi-beamforming technology. The spacecraft only needs to install a flat-panel power receiving system similar to traditional solar panels to receive high-power microwave energy through the antenna, and then use the rectifier circuit to convert it into electrical energy, and use capacitors for buffering and high-rate power supply to the spacecraft's energy system.

[0021] (3) This invention has advantages such as a large number of satellites in a large-scale constellation, real-time communication of constellation networking information, multi-satellite coherent power synthesis, and fast power storage and charging of the power receiving system. It avoids the difficulties of existing technical solutions, such as high on-orbit assembly technology and large size and weight of a single platform. It can improve energy acquisition capabilities while reducing the area of ​​the receiving antenna of the spacecraft in orbit. In addition, this invention can be extended to lunar scenarios, especially during the more than ten days of extreme cold lunar night, it can provide high-power power to multiple targets such as lunar bases and lunar rover mobile research stations. Attached Figure Description

[0022] Figure 1A A schematic diagram of a first configuration of a power supply satellite according to an embodiment of the present invention is shown; Figure 1B A schematic diagram of a second configuration of the power supply satellite according to an embodiment of the present invention is shown; Figure 2 A schematic diagram of a companion power supply satellite according to an embodiment of the present invention is shown; Figure 3 A schematic diagram of a powered satellite is shown in one embodiment of the present invention. Detailed Implementation

[0023] In the following description, the invention is described with reference to various embodiments. However, those skilled in the art will recognize that the embodiments may be practiced without one or more specific details or with other alternatives and / or additional methods, materials, or components. In other instances, well-known structures, materials, or operations are not shown or described in detail so as not to obscure the inventive points of the invention. Similarly, for illustrative purposes, specific quantities, materials, and configurations are set forth to provide a comprehensive understanding of embodiments of the invention. However, the invention is not limited to these specific details.

[0024] In this invention, the various embodiments are merely intended to illustrate the solutions of the invention and should not be construed as limiting.

[0025] In this specification, references to "an embodiment" or "this embodiment" mean that a particular feature, structure, or characteristic described in connection with that embodiment is included in at least one embodiment of the invention. The phrase "in one embodiment" appearing throughout this specification does not necessarily refer to the same embodiment in all instances.

[0026] Furthermore, the numbering of the steps in the methods of the present invention does not limit the execution order of the method steps. Unless otherwise specified, the method steps may be executed in different orders.

[0027] The present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0028] like Figure 1A and Figure 1BAs shown, the power supply satellite 10 adopts a highly flattened structural design to meet the requirements of mass stacking and launching rocket fairings. The power supply satellite platform adopts a flattened structural design suitable for stacked launches; the first type of power supply satellite 10 is equipped with a flexible solar photovoltaic array 11. The flexible solar photovoltaic array 11 is in a rolled-up state when folded, and presents a large-area flat shape when unfolded. The photovoltaic array 11 typically uses P-type heterojunction solar panels and perovskite tandem cells; the second type of power supply satellite 10 is equipped with a concentrator 21 and the photovoltaic array 11. The concentrator 21 focuses sunlight onto the photovoltaic array 11 to achieve photoelectric conversion. Given the stringent size and weight constraints of on-orbit deployment of spacecraft, the power supply satellite 10 significantly reduces its windward area and structural mass through a flattened configuration, thus enabling large-scale networking using standardized launch vehicles. The phased array antenna 12 incorporates a solid-state RF power amplifier array. When the DC power converted by the photovoltaic array 11 is input to the RF modulation unit, it immediately excites a high-power microwave signal. Furthermore, the power supply satellite 10 integrates an attitude control subsystem and a power management unit, both electrically connected to the phased array antenna 12 to maintain beam pointing accuracy in real time on orbit. Overall, Figure 1 fully illustrates the hardware topology and energy flow path of the power supply satellite 10. All components are secured by a combination of rigid supports and flexible cables, ensuring long-term stable operation in a microgravity environment.

[0029] like Figure 2 As shown, the companion satellite 20 is deployed in the adjacent space of the power supply satellite 10, mainly to provide auxiliary energy supplementation when the power generation capacity of a single power supply satellite is insufficient. The core component of the companion satellite 20 is the concentrating reflector 21, whose surface is coated with a high-reflectivity dielectric film and has an overall near-planar geometry. Since traditional parabolic reflectors are bulky and difficult to adapt to flat satellite platforms, this embodiment preferably adopts a near-planar concentrating reflector 21 structure. Through multi-segment splicing or micro-curvature design, sunlight is precisely focused and reflected onto the receiving surface of the photovoltaic array 11 of the adjacent power supply satellite 10. When the companion satellite 20 and the power supply satellite 10 maintain a specific relative orbital phase, the concentrating reflector 21 will adjust its tilt angle accordingly to track changes in the incident solar light vector. In addition, the companion satellite 20 only carries a lightweight attitude control thruster and an optical alignment sensor, both of which are signal-connected to the drive mechanism of the concentrating reflector 21, thereby achieving spatial transfer and power multiplication of light energy without the need for additional energy storage batteries. Figure 2 The relative spatial orientation, optical path reflection trajectory, and structural compatibility of the companion satellite 20 and the power supply satellite 10 are clearly shown.

[0030] like Figure 3As shown, a planar power receiving system 30 is mounted on the surface of the receiving satellite. This planar power receiving system 30 is arranged facing the phased array antenna 12 to ensure energy reception efficiency. A receiving antenna 31 is fixed at the front end of the planar power receiving system 30. The receiving antenna 31 is arranged using a microstrip patch or dipole array. When a high-power microwave signal reaches the effective aperture of the receiving antenna 31, a high-frequency AC signal is immediately induced. The receiving antenna 31 is connected in series with a rectifier circuit. The rectifier circuit incorporates a Schottky diode network and an impedance matching layer, which efficiently converts the high-frequency microwave energy into DC power through a nonlinear conversion mechanism. The output terminal of the DC power is coupled in series with a capacitor. The capacitor, with its high specific energy and fast charging and discharging characteristics, smooths and buffers the pulsating DC power and releases energy when the spacecraft load experiences instantaneous high power consumption. In addition, the outer shell of the planar power receiving system 30 is made of heat sink material and a low dielectric constant substrate laminated together, which not only shields against external electromagnetic interference but also accelerates the dissipation of rectification loss heat. The energy storage and charging system 32 uses capacitors to buffer electrical energy and then transmits the energy to the spacecraft's energy system through a charging interface. The application modes of high-power wireless power supply for on-orbit spacecraft based on large-scale constellations mainly include three modes. The first is the wireless companion charging mode. This mode is primarily for routinely high-power spacecraft such as space computing satellites. These spacecraft require continuous large-scale computing and storage, and energy system issues can easily lead to large-scale computing and storage failures. Using multiple power supply satellites in companion wireless power supply can significantly reduce the energy supply risk of spacecraft. The second is the long-distance fast charging mode. In this scenario, the power supply satellite constellation is deployed on a large scale in sun-synchronous orbit to supply power to spacecraft within the constellation's field of view. Since the receiving spacecraft's orbital altitude is lower than that of the power supply satellite constellation, the typical interaction between the power supply satellites and the receiving spacecraft is much faster. The first type involves a convergence time of minutes, where the power supply satellite constellation will use multiple satellites to provide high-power fast charging to multiple spacecraft, fully charging the receiving spacecraft within minutes. The second type is a simultaneous continuous power supply mode to multiple ground stations. In this scenario, power supply satellites are deployed on a large scale in medium and high orbits, enabling them to pass over designated areas on the ground for extended periods. Because the power supply satellites are distributed across different orbital planes and are far apart, synchronous information exchange between multiple satellites and multiple ground stations is achieved through satellite constellation beamforming control, enabling simultaneous continuous power supply from multiple satellites to multiple stations while significantly reducing the receiving antenna area of ​​each ground receiving station.

[0031] In one embodiment of the present invention, the present invention adopts the following technical solution: (1) A high-power wireless power supply satellite and power receiving system for an on-orbit spacecraft, comprising a flat power supply satellite that can be launched in batches and a flat power receiving system that is easy to install. The power supply satellite is deployed in a large-scale constellation network in an Earth orbit with long hours of sunlight. It directly uses a large-area flexible photovoltaic array or a large-area concentrating mirror to reflect sunlight and focus it onto the photovoltaic array to convert sunlight into electrical energy. The electrical energy is then used to drive radio frequency equipment to generate and amplify microwave signals. Finally, a high-gain beam is generated by a phased array antenna to directionally radiate the microwave signals to the power receiving system area. The on-orbit spacecraft receives microwave signals by installing the power receiving system. There are multiple power supply satellites within the spacecraft's line of sight. The power supply satellites synchronously achieve high-power coherent synthesis of the target spacecraft area through constellation networking. The spacecraft's power receiving system receives the synthesized microwave energy through a receiving antenna and converts the microwave energy into electrical energy using a rectifier circuit. Since the power receiving system acquires high-power electrical energy in a short time, it uses a capacitor to buffer the electrical energy and then charges the spacecraft's energy subsystem at a high rate.

[0032] (2) The power supply satellite mainly includes two forms: one is to install a large-area flexible photovoltaic array to achieve photoelectric conversion, and the other is to install a large-area concentrating mirror to reflect and focus sunlight onto the photovoltaic array to achieve photoelectric conversion; in addition, the power supply satellite platform includes a flat satellite structure, radio frequency equipment, phased array antenna, laser communication equipment, integrated electronic equipment, attitude and orbit control equipment, and thermal control equipment; among them, the flat satellite structure is suitable for stacked launch and can load more power supply satellites in the rocket fairing; the flexible solar photovoltaic array is used to convert sunlight into electrical energy and faces the sun through a mechanical drive mechanism; the concentrating mirror adopts the form of a concentrating thin film mirror or The system uses Fresnel lenses to focus sunlight onto a photovoltaic array, and the satellite platform rotates to ensure the focusing lens faces the sun. Radio frequency equipment converts electrical energy into high-power microwave energy. Phased array antennas form high-gain microwave beams, directionally radiating microwave energy to the power receiving system area. Laser communication equipment enables interconnection and communication between the power supply satellite constellation, achieving coherent synchronization of microwave energy transmission signals. Integrated electronic equipment, attitude and orbit control equipment, and thermal control equipment are typical subsystems of a satellite platform, respectively used for comprehensive data information management, ensuring the satellite's pointing requirements and orbit maintenance, and meeting the temperature environment requirements of different stages of the satellite mission. (3) The power receiving system includes a receiving antenna, a rectifier circuit and an energy storage and charging system, etc.; wherein, the receiving antenna is used to form a high-gain receiving beam to obtain high-power microwave energy coherently synthesized by the power supply satellite constellation; the rectifier circuit is used to convert microwave energy into electrical energy; the energy storage and charging system uses capacitors to buffer electrical energy and then transmits the electrical energy to the spacecraft's energy system through the charging interface; (4) The Earth orbit in which the power supply satellite is located includes a sun-synchronous dawn-dusk orbit below 3,000 km, an Earth orbit between 8,000 km and 12,000 km, and an Earth orbit around 36,000 km. (5) The application modes of the power supply satellites include: ① Wireless escort charging mode: Multiple power supply satellites orbit and escort a normal high-energy-consuming spacecraft, and provide centralized power supply to the spacecraft's power receiving system; ② Long-distance fast charging mode: The power supply satellite constellation transmits high-power microwave energy to the power receiving system of the spacecraft in a short period of time when it intersects with the spacecraft, and converts it into electrical energy for fast charging. In the scenario of powering multiple spacecraft at the same time, the power supply satellite constellation performs multi-beam shaping to form multiple high-gain beams that simultaneously point to multiple spacecraft for high-power charging; ③ Simultaneous continuous power supply to multiple ground stations: The power supply satellites form a sparsely deployed constellation with a large distance between them in high Earth orbit. According to the relative position of the power supply satellites, each power transmission signal is simultaneously adjusted to form multiple narrow beams on the ground, thereby reducing the antenna area of ​​the power receiving system of each ground receiving station and realizing continuous power supply to multiple ground stations at the same time. (6) When the power supply satellite is facing insufficient power generation capacity of a single satellite, one or more companion satellites can be added. The companion satellites are only equipped with concentrating reflectors to focus and reflect sunlight onto the solar panels of the power supply satellite, thereby improving the power supply satellite's ability to convert electrical energy. The concentrating reflector is an approximately flat reflector to adapt to the flat satellite structure design.

[0033] Although various embodiments of the invention have been described above, it should be understood that they are presented by way of example only and not as limitations. It will be apparent to those skilled in the art that various combinations, modifications, and alterations can be made without departing from the spirit and scope of the invention. Therefore, the breadth and scope of the invention disclosed herein should not be limited by the exemplary embodiments disclosed above, but should be defined solely by the appended claims and their equivalents.

Claims

1. A high-power wireless power supply satellite and power receiving system for an on-orbit spacecraft, characterized in that, include: A power supply satellite constellation, comprising a network of multiple flat-structured power supply satellites, each including a photovoltaic array for photoelectric conversion; A phased array antenna, which is disposed in the power supply satellite constellation and is used to transmit microwave energy; A planar power receiving system, wherein the planar power receiving system is disposed on the surface of the target spacecraft and faces the phased array antenna; A receiving antenna, which is fixed to the front end of the flat-panel power receiving system and is used to receive microwave energy; A rectifier circuit, which is connected in series with the receiving antenna to convert the received microwave energy into DC power. A capacitor is connected in series with the rectifier circuit to buffer the DC power.

2. The high-power wireless power supply satellite and power receiving system for an on-orbit spacecraft according to claim 1, characterized in that, Also includes: A beamforming control module is located inside the power supply satellite constellation and is connected to the phased array antenna signal to regulate the transmission phase.

3. The high-power wireless power supply satellite and power receiving system for an on-orbit spacecraft according to claim 1, characterized in that, Also includes: An inter-satellite laser communication networking module is connected between the power supply satellites of the power supply satellite constellation to achieve real-time data sharing of the constellation.

4. The high-power wireless power supply satellite and power receiving system for an on-orbit spacecraft according to claim 1, characterized in that, include: A wireless companion charging mode unit is configured in the power supply satellite constellation and is used to provide centralized power supply to spacecraft that routinely orbits and accompanies multiple satellites.

5. A high-power wireless power supply satellite and power receiving system for an on-orbit spacecraft according to claim 1, characterized in that, include: A long-distance fast charging mode unit is configured in the power supply satellite constellation and is used to charge the receiving spacecraft within a minute-level convergence time.

6. A high-power wireless power supply satellite and power receiving system for an on-orbit spacecraft according to claim 1, characterized in that, include: Simultaneous multi-ground station continuous power supply mode unit, the simultaneous multi-ground station continuous power supply mode unit is configured in the power supply satellite constellation and is used to implement multi-station synchronous power supply on the distributed orbital plane.

7. A high-power wireless power supply satellite and power receiving system for an on-orbit spacecraft according to claim 1, characterized in that, include: The companion satellite is deployed in the vicinity of the power supply satellite constellation and is equipped only with a focusing reflector to supplement power when the power generation capacity of a single power supply satellite is insufficient.

8. A high-power wireless power supply satellite and power receiving system for an on-orbit spacecraft according to claim 1, characterized in that, The power supply satellite also includes: A concentrating reflector is used to reflect sunlight to the photovoltaic array.

9. A high-power wireless power supply satellite and power receiving system for an on-orbit spacecraft according to claim 1, characterized in that, include: A narrow beamforming structure is disposed at the output end of the phased array antenna and is used to form multiple narrow beams on the ground to reduce the area of ​​the receiving antenna.

10. A high-power wireless power supply satellite and power receiving system for an on-orbit spacecraft according to claim 3, characterized in that, include: A laser communication device is installed on each power supply satellite and is signal-connected to the inter-satellite laser communication networking module.

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