Energy system for a computing satellite in a dawn-dusk orbit

Abstract

This invention discloses an energy system for a computing satellite in a dawn-dusk orbit, comprising a power generation unit, an energy storage unit, and a power control unit. The power generation unit includes a main battery array and an auxiliary battery array; the energy storage unit includes payload and platform battery packs; and the power control unit includes payload and platform power control units. The main battery array employs a deployable concentrating solar array, with its output connected to the payload power control unit to power the computing payload and charge the payload battery pack. The auxiliary battery array's output is connected to the platform power control unit to power the platform equipment and charge the platform battery pack. The discharge terminals of the two battery packs supply power to their respective loads through corresponding power control units. The dual power control units dynamically adjust the charging and discharging strategy and power allocation according to the orbital phase. This invention, through a physically isolated dual-channel power supply architecture, solves the problems of periodic energy interruption and load interference in dawn-dusk orbits, achieving independent and stable power supply for high-power computing payloads and highly reliable platform equipment.

Description

Technical Field

[0001] This invention relates to the field of spacecraft energy technology, specifically to an energy system for a computing satellite in a dawn-dusk orbit. Background Technology

[0002] Dawn-dusk orbit satellites operate in sun-synchronous orbits near the Earth's terminator, and their orbital characteristics cause them to periodically experience alternating periods of illumination and shadow. With the rapid growth in demand for space-based information processing, dawn-dusk orbit computing satellites equipped with high-performance computing payloads (such as GPU clusters) have attracted widespread attention. These satellites aim to achieve "daytime data processing and intelligent analysis," that is, to complete real-time data processing and intelligent analysis in orbit, thereby reducing the transmission latency and bandwidth limitations of the traditional "daytime data processing and ground-based analysis" model.

[0003] However, the high-power operation of computing payloads places higher power requirements on onboard energy systems compared to conventional satellites. In dawn-dusk orbit environments, existing energy systems face the following technical challenges:

[0004] First, there is a contradiction between energy density and launch envelope. Traditional solar arrays are limited by photoelectric conversion efficiency, resulting in relatively limited power output per unit mass. To meet the higher power consumption requirements of computing payloads, a larger area of ​​solar array is needed, but this is constrained by the limited space of the rocket fairing.

[0005] Secondly, the adaptability of orbital periodic energy management is insufficient. Dawn-dusk orbit satellites frequently experience alternating periods of illumination and shadow. In the illuminated period, the satellite primarily relies on solar arrays to generate electricity and charge its energy storage system; however, once in the shadow, it must rely on batteries to maintain system operation. This periodic energy input characteristic requires the energy system to have autonomous and smooth mode switching capabilities. Existing energy systems still have room for improvement in switching power supply modes in response to orbital phase changes, and face challenges in maintaining continuous operation of computing payloads and achieving dynamic optimization of energy allocation during the shadow period.

[0006] Furthermore, the reliability and independence of the system architecture need to be strengthened. Computing loads and platform equipment typically share a power supply architecture, necessitating improvements in independent energy management and power regulation mechanisms. This situation may raise concerns about power supply stability under high load conditions and also places higher demands on the reliability of the energy system.

[0007] Therefore, it is necessary to develop energy systems suitable for computing satellites in dawn-dusk orbits to address the technical challenges of energy systems in terms of energy density, launch adaptability, orbital phase management, and system reliability under dawn-dusk orbit conditions, and to meet the requirements of space-based computing platforms for continuous and stable energy supply. Summary of the Invention

[0008] The purpose of this invention is to propose a computing power satellite energy system for dawn-dusk orbits, aiming to solve the technical bottlenecks that are difficult to overcome in existing technologies, such as insufficient energy density, launch volume constraints, poor orbital adaptability, and low system reliability.

[0009] To achieve the above objectives, the present invention adopts the following technical solution:

[0010] An energy system for a dawn-dusk orbit computing satellite includes: a power generation unit, an energy storage unit, and a power control unit. The power generation unit includes a main battery array and an auxiliary battery array; the energy storage unit includes a payload battery pack and a platform battery pack; and the power control unit includes a payload power control unit and a platform power control unit.

[0011] The output of the main battery array is connected to the load power control unit, and the output of the load power control unit is connected to the computing load and the load battery pack respectively.

[0012] The output of the auxiliary battery array is connected to the platform power control unit, and the output of the platform power control unit is connected to the platform equipment and the platform battery pack respectively.

[0013] The discharge terminal of the load battery pack supplies power to the computing load through the load power control unit.

[0014] The platform battery pack supplies power to the platform equipment through the platform power control unit.

[0015] The main battery array is a deployable concentrating solar cell array;

[0016] Both the payload power control unit and the platform power control unit are configured to dynamically adjust the charging and discharging strategies of the corresponding battery packs and the power allocation of the corresponding loads according to the satellite's orbital phase.

[0017] Compared with existing technologies, the energy system proposed in this invention has the following advantages:

[0018] 1) To improve power supply and system reliability, two relatively independent power supply channels were established: "main battery array - payload power control unit - computing power payload / payload battery pack" and "auxiliary battery array - platform power control unit - platform equipment / platform battery pack". This dual-channel architecture effectively isolates the mutual interference between high-power, dynamically changing computing power payloads and power quality-sensitive platform equipment (such as attitude and orbit control systems), ensuring the operational safety of the satellite platform. It also provides fault isolation capabilities, helping to reduce the impact of single-point failures on the overall satellite power system and improving system operational stability.

[0019] 2) In terms of overcoming energy supply bottlenecks, the main battery array adopts a deployable concentrating design, which combines the high power density advantage of concentrating technology with the spatial adaptability of the deployable structure to the emission volume constraint. Under limited mass and space constraints, it achieves a significant improvement in power generation capacity compared to traditional solutions, providing a feasible energy foundation for supporting high-power computing loads.

[0020] 3) In terms of energy management, by configuring a power control unit that can be dynamically adjusted according to orbital phase, the payload and platform power control unit can dynamically adjust the charging and discharging strategy of the battery pack and the load power allocation according to different stages (illuminated / shadowed) of the satellite's diurnal orbit cycle. This management strategy responds to orbital periodic energy changes, helps maintain power supply continuity throughout the orbital cycle, and optimizes system mission adaptability through priority management during energy shortages.

[0021] 4) In terms of system-level redundancy and lightweight design, the architecture of dual power generation units, dual energy storage units, and dual control units provides inherent redundancy backup. Meanwhile, the application of concentrating technology reduces the cell area required to achieve the same power output, and combined with the deployable design, this contributes to an optimized balance between power generation, reliability, and weight.

[0022] In summary, this invention constructs an efficient, reliable, and adaptable energy system by organically combining a physically isolated dual-channel power supply architecture, high-power-density concentrated photovoltaic power generation technology, and orbital phase-based energy management, providing a feasible energy solution for deploying high-power computing satellites in dawn-dusk orbit environments. Attached Figure Description

[0023] The accompanying drawings, which form part of this specification, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0024] Figure 1 This is a block diagram of the energy system architecture of a dawn-dusk orbit computing satellite proposed in this invention;

[0025] Figure 2 This is a schematic diagram of the on-orbit deployment structure of a concentrating solar cell array proposed in this invention.

[0026] Figure 3 This is a schematic diagram of the structure of a solar cell array panel proposed in this invention;

[0027] Figure 4 This is a schematic diagram of a focusing array proposed in this invention;

[0028] Figure 5 This is a schematic diagram of the structure of a light-concentrating module proposed in this invention;

[0029] Figure 6 This is a schematic diagram of the heat dissipation path of the solar cell in the concentrating module proposed in this invention;

[0030] Figure 7 This is a schematic diagram of the outward thermal radiation path of the primary mirror substrate of the focusing module proposed in this invention.

[0031] In the diagram: 10. Satellite platform; 20. Solar array panel; 21. Lightweight high-strength frame; 22. Concentrating array; 23. Concentrating module; 1. Primary mirror; 101. Primary mirror substrate; 102. Reflective layer; 103. Transparent infrared radiation layer; 104. Thermally conductive radiation layer; 3. Secondary mirror; 4. Secondary mirror support; 5. Solar cell; 6. Light funnel; 7. Heat diffuser; 41. Mounting plane; 42. Cutout section. Detailed Implementation

[0032] The technical solutions in the embodiments of the present invention will now be clearly and completely described with reference to the accompanying drawings. The described embodiments are only a part of the implementation of the present invention, not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0033] It should be noted that, in the description of this invention, "an embodiment" or "an embodiment of the invention" refers to a specific feature, structure, or characteristic that can be included in at least one implementation of the invention. The phrase "in one embodiment" appearing in different places in the specification does not necessarily refer to the same embodiment, nor are they mutually exclusive individual or selective embodiments. This invention can also be implemented in ways other than those described herein, and any equivalent modifications made by those skilled in the art without departing from the concept of the invention fall within the scope of protection of this invention.

[0034] A computing satellite is an integrated system consisting of a satellite platform and a computing payload. The satellite platform, as the basic carrier, includes subsystems such as structure, power supply, propulsion, attitude and orbit control, thermal control, and data management. It provides the necessary structural support, energy supply, thermal management, attitude control, and data services to the computing payload, ensuring its operational stability in complex space environments such as dawn / dusk orbits. Platform equipment, the functional units of the satellite platform, includes attitude and orbit control devices, thermal control components, and energy equipment, serving the operational objectives of each subsystem. The computing payload, as a dedicated computing unit, is the core component for performing intensive computing tasks. Although independent of the platform subsystems, it is physically integrated with the satellite platform.

[0035] Computing satellites operating in dawn-dusk orbits face specific energy supply challenges: the satellites periodically traverse illuminated and shadowed zones, resulting in intermittent energy input; simultaneously, the coexistence of high-power computing payloads and platform equipment with high reliability requirements places stringent demands on power quality and system reliability. Existing energy systems mostly employ centralized power supply architectures, which have room for improvement in meeting the following requirements: firstly, the ability to dynamically manage periodic energy interruptions in orbit; secondly, the ability to isolate mutual interference between high-power payloads and sensitive platform equipment; and thirdly, the ability to provide sufficient power density under limited launch envelope constraints.

[0036] To address the aforementioned technical challenges, this invention proposes a zone-coordinated energy system architecture. Its main design concept is to construct an energy supply system with high reliability, adaptability, and efficiency through a system design method that combines physical isolation and functional coordination. Specific improvements include the following three aspects:

[0037] A zoned power supply architecture is established to achieve fault isolation. By setting up independent load power supply channels and platform power supply channels with emergency backup functions, the interference problem between high-power loads and sensitive devices is effectively solved, while providing system-level fault tolerance capabilities.

[0038] Concentrating technology and deployable structures are employed to enhance power density. The main solar array utilizes a deployable concentrating solar array, which, while meeting emission envelope constraints, obtains sufficient light-receiving area through on-orbit deployment, and, combined with concentrating technology, achieves a significant increase in power generation per unit mass.

[0039] An energy management strategy based on orbital phase is introduced. A power control unit that can sense the orbital phase and autonomously adjust its operating mode is configured, enabling the system to adapt to the periodic energy changes unique to the dawn-dusk orbit and achieve optimized energy distribution throughout the entire orbital cycle.

[0040] See Figure 1 This invention proposes an energy system for a computing satellite in a dawn-dusk orbit, comprising: a power generation unit, an energy storage unit, and a power control unit. The power generation unit includes a main battery array and an auxiliary battery array; the energy storage unit includes a payload battery pack and a platform battery pack; and the power control unit includes a payload power control unit and a platform power control unit.

[0041] The output of the main battery array is connected to the load power control unit, and the output of the load power control unit is connected to the computing load and the load battery pack, respectively.

[0042] The output of the auxiliary battery array is connected to the platform power control unit, and the output of the platform power control unit is connected to the platform equipment and the platform battery pack, respectively.

[0043] The discharge terminal of the load battery pack supplies power to the computing load through the load power control unit.

[0044] The platform's battery pack discharges through the platform's power control unit, supplying power to the platform equipment.

[0045] The main battery array uses a deployable concentrating solar cell array;

[0046] Both the payload power control unit and the platform power control unit are configured to dynamically adjust the charging and discharging strategies of the corresponding battery packs and the power allocation of the corresponding loads according to the satellite's orbital phase.

[0047] Based on the above physical connection relationship, the main battery array is configured to power the computing load and charge the load battery pack during the sunshine period, the auxiliary battery array is configured to power the platform equipment and charge the platform battery pack during the sunshine period, and the load / platform battery pack is configured to power the computing load / platform equipment during the shadow period.

[0048] Compared to traditional satellite energy systems, the technical improvements and corresponding technical effects of the energy system of this invention include the following:

[0049] 1) Adopting a physically isolated dual-channel power supply system architecture

[0050] This invention establishes two relatively independent power supply channels: a "main battery array - payload power control unit - computing power payload / payload battery pack" and an "auxiliary battery array - platform power control unit - platform equipment / platform battery pack." Through physically isolated power supply paths, the transmission path of power interference generated by high-power, dynamically changing computing loads to platform equipment (especially the attitude and orbit control system, which is sensitive to power quality) is effectively blocked, ensuring the stable operation of the platform equipment. Simultaneously, this dual-channel power supply system architecture provides a natural fault isolation mechanism; a fault in a single channel is less likely to propagate to the entire energy system, improving the overall reliability of the system.

[0051] 2) The main battery array adopts a deployable concentrating solar cell array.

[0052] The main solar array combines the high power density of concentrated solar power technology with the adaptability of its deployable structure to the launch volume. Concentrated solar power technology enhances the power output per unit area of ​​the solar cells through optical focusing, achieving high power density and enabling the support of high-power computing payloads. The deployable design allows the array to fold during launch to accommodate rocket envelope constraints and unfold after orbit to obtain a large effective light-receiving area, thus resolving the conflict between high power requirements and limited launch space.

[0053] 3) Implement dynamic energy management based on orbital phase.

[0054] The payload and platform power control unit is configured to dynamically adjust the charging and discharging strategies of the corresponding battery banks and the power allocation to the load based on the satellite's orbital phase (sunlight period / shadow period) in the twilight orbit. This allows the energy system to proactively adapt to the unique periodic energy input variations of the twilight orbit. During the sunlight period, the main and auxiliary battery arrays provide power and charge the payload and platform battery banks respectively. During the shadow period or when energy is scarce, the payload and platform battery banks discharge to ensure the execution of critical missions, improving the system's energy utilization efficiency and mission adaptability throughout the entire orbital cycle.

[0055] In summary, this invention enhances system reliability through a dual-system independent power supply architecture for the payload and platform, improves power density by employing a focused and deployable design, and optimizes orbital adaptability by implementing dynamic energy management based on orbital phase, thus providing an effective energy solution for computing satellites in dawn-dusk orbits.

[0056] In one embodiment, see still Figure 1 The present invention further proposes:

[0057] The load power control unit is also connected to the output of the auxiliary battery array to receive its power input;

[0058] The platform power control unit is also connected to the output of the load power control unit to receive the combined power input.

[0059] When the auxiliary battery array fails, the electrical energy generated by the main battery array will supply power to the platform equipment in sequence through the load power control unit and the platform power control unit.

[0060] When the main battery array fails, the load battery pack discharges to provide emergency power to the computing load, ensuring that it can perform data saving and smooth shutdown operations.

[0061] By connecting the load power control unit to the output of the auxiliary battery array and the platform power control unit to the output of the load power control unit, a controlled cross-boundary power supply path is established on the basis of a physically isolated dual-channel architecture. This design enables the system to provide emergency power support for the critical computing load through another normally functioning power generation unit when a single power generation unit of the main battery array or the auxiliary battery array fails, thereby enhancing the system's continuous operation capability under fault conditions.

[0062] When the main battery array fails, the system can automatically switch to discharge from the load battery bank to provide emergency power for the computing load. The energy stored in the battery bank is sufficient to ensure that the computing load completes the data saving and orderly shutdown process, effectively avoiding data loss and hardware damage that may be caused by the sudden failure of the power generation system, and providing important security protection for high-value computing systems.

[0063] In the event of a failure in the auxiliary battery array, the main battery array can channel its surplus power sequentially through the payload power control unit and the platform power control unit to provide emergency power to critical platform equipment such as attitude and orbit control and the satellite computer. This design prevents a failure in the auxiliary battery array from directly causing the satellite platform to malfunction, significantly improving the platform system's survivability in the event of a power generation unit failure.

[0064] In summary, by introducing a bidirectional emergency power supply path into an independent power supply architecture, this embodiment of the invention achieves functional complementarity and cross-backup between power generation units while maintaining the advantages of physical isolation. This elevates the design from static reliability to dynamic resilience, further enhancing the energy system's ability to cope with sudden failures on orbit.

[0065] In one embodiment, the auxiliary battery array adopts a bulk solar cell array, and the output circuit array includes a load power supply circuit and a platform power supply circuit.

[0066] The auxiliary battery array uses a bulk-mounted solar cell array, which has a relatively simple structure without complex deployment mechanisms and high mechanical reliability. This characteristic enables it to serve as a stable base power source, providing continuous power support when the main battery array malfunctions and stops working, reducing the overall satellite energy system's dependence on a single power generation unit and enhancing the system's redundancy and backup capabilities.

[0067] By setting independent load power supply circuits and platform power supply circuits at the output of the auxiliary battery array, power path isolation between the computing load and platform equipment is achieved at the power distribution level. This design helps suppress large current fluctuations or harmonic interference generated during the operation of the computing load, preventing them from affecting critical platform equipment with high power quality requirements through the power bus, and ensuring the stable operation of each power system.

[0068] The bulk-mounted solar array is directly installed on the surface of the satellite's main structure, eliminating the need for additional deployment mechanisms and external envelope space, thus contributing to a compact system design. Simultaneously, the partitioned design of the power supply circuit provides a basis for independent management and protection of loads with different characteristics, facilitating system layout optimization and maintenance.

[0069] In summary, the embodiments of the present invention provide further technical support in terms of system reliability, equipment compatibility, and structural layout optimization through the selection of auxiliary battery arrays and the architecture design of their output circuits.

[0070] In one embodiment, the load power supply circuit adopts a redundant design with multiple series and multiple parallel connections, while the platform power supply circuit adopts a grouped independent output design.

[0071] The load power supply circuit adopts a redundant design with multiple series and parallel connections. When one battery string fails due to external impact or internal fault, although the output power of its parallel branch will decrease, the other parallel branches can still continue to supply power to the computing load. This design reduces the possibility of power outage of the entire computing system due to the failure of a single battery string, and improves the continuity of power supply to core computing tasks and the system's fault tolerance.

[0072] The platform power supply circuit adopts a grouped independent output design, configuring key platform equipment with different functions (such as attitude and orbit control system, satellite computer, etc.) into different power supply groups. When a power supply group fails (such as a short circuit), the protection device of that group can isolate it from the system, thereby preventing the fault from affecting platform equipment in other power supply groups, preventing the spread of local faults in the power system, and helping to ensure the continuous operation of the satellite platform's basic functions.

[0073] To address the differentiated power demands of the load and platform equipment, corresponding circuit designs are employed to achieve refined power management. The load power supply ensures continuous high-power supply through redundancy design, while the platform power supply meets the high-reliability operation requirements of multiple devices through grouping design. Together, they construct a robust and efficient energy distribution system.

[0074] In summary, the embodiments of the present invention, through differentiated design of the power supply circuits for the load and platform, have achieved further improvements in power supply reliability, fault isolation, and system power management optimization, providing circuit-level assurance for the stable operation of the energy system under different load conditions.

[0075] In one embodiment, both the main battery array and the auxiliary battery array employ triple-junction gallium arsenide solar cells.

[0076] Triple-junction gallium arsenide solar cells employ a GaInP / GaAs / Ge multilayer structure and achieve segmented absorption of the solar spectrum through bandgap engineering, resulting in significantly higher photoelectric conversion efficiency than traditional silicon-based solar cells. For the main array, the high initial efficiency combined with concentrating technology can generate considerable power gain; for the auxiliary array, it can provide relatively sufficient backup power within a limited installation area, jointly enhancing the overall power generation capacity of the system.

[0077] Triple-junction gallium arsenide (GaAs) solar cells employ a wide-bandgap top cell structure, using GaInP as the top cell material, to achieve effective absorption of high-energy photons and current matching. This provides some protection against high-energy particle radiation in the space environment, and its power decay rate at the end of its lifespan is relatively low. This characteristic allows the main and auxiliary cell arrays to maintain relatively stable power output even after long-term radiation exposure in the dawn-dusk orbit, helping to maintain the satellite's energy supply capability throughout its entire lifespan.

[0078] Higher conversion efficiency means that smaller solar cells can be used for the same power demand, which not only directly reduces the weight of the cell itself but also helps to reduce the mass of the related support structure. At the same time, triple-junction gallium arsenide cells have a low temperature coefficient, enabling them to maintain relatively stable output performance in the drastic temperature fluctuations of the day-night orbit, reducing power loss caused by temperature fluctuations.

[0079] In summary, the embodiments of the present invention achieve synergistic optimization in terms of power generation efficiency, environmental adaptability, and weight control by uniformly selecting triple-junction gallium arsenide solar cells in the main and auxiliary battery arrays, providing a high-performance and reliable power generation unit for the energy system.

[0080] In one embodiment, see Figures 2-4 As shown, after the concentrating solar array is deployed in orbit, it forms a symmetrical arrangement of two solar panels on both sides of the satellite platform. Each solar panel includes at least one solar array panel 20, which includes a lightweight, high-strength frame 21 and m×m concentrating arrays 22 disposed thereon; each concentrating array 22 consists of n×n concentrating modules 23, where m and n are both integers ≥2.

[0081] After the concentrated solar array is deployed in orbit, it forms symmetrically arranged dual solar panels on both sides of the satellite platform 10. This symmetrical layout helps achieve mass balance of the satellite structure. When the solar panels are fully deployed, their center of mass is close to that of the satellite itself. In contrast, asymmetrical or large-area single-sided solar panel configurations may produce static and dynamic imbalances, placing an additional burden on the satellite's attitude control system, requiring more fuel for attitude correction, and potentially causing attitude jitter, affecting computing load and communication link stability. This embodiment of the invention, through its symmetrical dual-sided arrangement, achieves a larger power generation area while helping to reduce the disturbance torque caused by uneven mass distribution, maintaining the satellite's attitude stability and control accuracy, and providing favorable conditions for satellite attitude control.

[0082] The solar array panel 20 employs a lightweight, high-strength frame 21 as its main support structure, which, while ensuring necessary stiffness and strength, contributes to the lightweight design of the system. Preferably, this lightweight, high-strength frame 21 can be a thin-walled carbon fiber tube frame, utilizing the high specific strength and high specific stiffness characteristics of carbon fiber composite materials to provide the necessary support stiffness for the entire panel while achieving structural lightweighting, enabling it to withstand the mechanical loads during the launch phase and provide a stable optical reference surface for the concentrator array 22 after on-orbit deployment.

[0083] A two-tiered modular design, consisting of an m×m concentrator array and n×n concentrator modules, decomposes the solar array into multiple standardized, mass-producible sub-units. This modular architecture possesses inherent redundancy; if individual concentrator modules or arrays fail due to space debris impacts or other factors, it typically only causes a localized decrease in system power, helping to control the risk of overall system failure. Compared to non-modular designs, this design simplifies production, testing, and assembly processes, and improves system maintainability and scalability.

[0084] In one specific implementation example, after the concentrating solar array is deployed in orbit, it forms a pair of symmetrically arranged solar wings on both sides of the satellite platform 10. Each solar wing includes two solar array panels 20, and each solar array panel 20 can contain 16 concentrating arrays 22 in a 4×4 pattern. Each concentrating array 22 can be composed of 25 concentrating modules 23 in a 5×5 pattern. During orbital illumination, the concentrating solar array converts solar energy into electrical energy through its distributed concentrating modules. After being regulated by the collector, the electrical energy is converted into a power supply that meets the load requirements and outputs it to the power control unit.

[0085] In summary, the embodiments of the present invention achieve synergistic optimization in terms of structural stability, lightweighting, and system reliability through the combination of a bilaterally symmetrical configuration, a lightweight and high-strength frame, and a multi-level modular design, providing an effective structural solution for the engineering implementation of concentrated solar cell arrays.

[0086] In one embodiment, see Figure 4 and Figure 5 As shown, the focusing module 23 includes a primary mirror 1, a secondary mirror 3, a light funnel 6, a solar cell 5, and a heat spreader 7;

[0087] The primary mirror 1 includes a primary mirror base 101, which forms the sun-facing opening of the light-concentrating module 23. Its optical working surface is set towards the secondary mirror 3 for receiving and reflecting incident sunlight.

[0088] The secondary mirror 3 is fixed above the primary mirror 1 by the secondary mirror bracket 4 and is located in the convergence area of ​​the reflected light path of the primary mirror 1. Its reflective surface faces the entrance of the light funnel 6 and is used to reflect the light reflected by the primary mirror 1 a second time.

[0089] The light funnel 6 has a conical cavity structure. Its inlet receives the reflected light path of the secondary mirror 3, and its outlet corresponds to the light-receiving surface of the solar cell 5. It is used to guide the light reflected by the secondary mirror 3 to the solar cell 5.

[0090] The battery cell 5 is positioned below the light path outlet of the light funnel 6 and is used to convert light energy into electrical energy;

[0091] The heat-dissipating plate 7 is tightly attached between the battery cell and the main mirror substrate 101 to conduct the heat generated by the battery cell 5 to the main mirror substrate 101, and then the main mirror substrate 101 radiates heat to the space environment.

[0092] See Figure 4 As shown, the optical components in the concentrating module 23 are spatially integrated to form a complete concentrating power generation unit, independently completing the concentrating-photovoltaic conversion process, providing a structural foundation for the large-scale deployment of the system. In operation, sunlight is concentrated by the concentrating module, forming a high light energy flux density on the surface of the solar cells. The solar cells absorb photons and generate photoelectrons, forming an effective photocurrent and achieving photovoltaic conversion. During the orbital illumination period, multiple concentrating modules 23 distributed on both sides of the solar array work collaboratively. The electrical energy generated by each module is collected and combined through a cable network to form a power output that meets the requirements.

[0093] In the focusing module 23, the primary mirror 1, secondary mirror 3, and light funnel 6 constitute a secondary reflection optical path. The primary mirror 1 acts as a light collector, reflecting and converging sunlight to the secondary mirror 3. The secondary mirror 3 shapes the beam and guides it to the light funnel 6, which in turn guides the light to the micro-solar cell 5 through its conical cavity. The specific optical path is: sunlight → primary mirror → secondary mirror → light funnel → solar cell. This secondary reflection optical path design helps improve focusing efficiency, achieving higher energy density while reducing the area of ​​the required semiconductor solar cell.

[0094] The conical cavity structure of the light funnel 6 has a certain ability to adapt to small changes in the solar incidence angle. When sunlight is incident perpendicularly, the reflected light directly illuminates the solar cells; when the incidence angle is slightly deviated, some light can be reflected through the conical sidewalls and directed to the central region of the solar cells, which helps to enhance the system's adaptability to on-orbit attitude fluctuations.

[0095] The heat spreader 7, as a key heat-conducting element, is tightly bonded between the solar cell 5 and the primary mirror substrate 101, constructing a heat conduction path from the high-density point heat source of the solar cell 5 to the large-area heat sink of the primary mirror substrate 101. The heat spreader 7 reduces the local heat flux density of the solar cell through lateral diffusion, helping to reduce the risk of localized high temperatures and ensuring that the solar cell 5 operates within a safe temperature range, while simultaneously promoting heat transfer to the primary mirror substrate 101. Ultimately, the heat is radiated into space through the surface of the primary mirror substrate 101. This integration of optical and heat dissipation functions avoids the need for a separate, bulky heat dissipation component for the solar cell 5, contributing to a more compact and lightweight structure.

[0096] In summary, the embodiments of the present invention achieve synergistic performance of the focusing module in terms of light energy collection, heat dissipation, and environmental adaptability through the integrated design of optical path structure optimization and thermal management path.

[0097] In one embodiment, see still Figure 5 The primary mirror substrate 101 adopts a near-parabolic spherical structure with a quadrilateral outline. This near-parabolic spherical structure has a relatively large effective light-receiving area and good structural rigidity for the same aperture, and can effectively reflect parallel incident sunlight to the secondary mirror 3 position, providing an optical basis for high-magnification light concentration. At the same time, the quadrilateral outline provides a structural boundary for modular integration, allowing multiple concentrating modules to be arranged in a matrix on the surface of the solar cell array. The quadrilateral outline structure facilitates stable connection with adjacent modules and support frames, enhances the overall structural rigidity, and this configuration is adaptable to manufacturing processes, which is beneficial for processing, assembly, and testing.

[0098] The concave surface of the primary mirror substrate 101 serves as the optical working surface, and a reflective layer 102 and a transparent infrared radiation layer 103 covering the reflective layer 102 are sequentially provided. The reflective layer 102 provides high reflectivity to sunlight, while the transparent infrared radiation layer 103, while maintaining optical transmittance, can dissipate the heat absorbed by the primary mirror substrate 101 into the space environment in the form of infrared radiation.

[0099] The convex surface of the primary mirror substrate 101 is provided with a thermally conductive radiation layer 104. This thermally conductive radiation layer 104, utilizing its high in-plane thermal conductivity, can diffuse the heat absorbed by the primary mirror substrate, especially the localized heat flow conducted from the solar cells, along the planar direction of the primary mirror substrate 101. Simultaneously, the thermally conductive radiation layer 104 also serves as a radiative heat dissipation surface, radiating heat into the space environment in the form of infrared radiation.

[0100] The primary mirror substrate 101 achieves bi-directional heat dissipation through the coordinated use of its concave and convex functional layers. During operation, sunlight passes through the concave transparent infrared radiation layer 103 and is reflected by the reflective layer 102 to the secondary mirror 3. The heat generated by the solar cell 5 during operation is conducted to the primary mirror substrate 101 through the heat spreader 7. Part of this heat is directly radiated and dissipated through the concave transparent infrared radiation layer 103, while the other part is radiated and dissipated laterally through the convex heat-conducting radiation layer 104. This dual-path heat dissipation mechanism increases the effective heat dissipation area, improves temperature uniformity, and helps ensure the thermal stability and optical surface accuracy of the primary mirror substrate.

[0101] It should be noted that the reflective layer 102 is preferably a silver-plated layer. The silver-plated layer has a high reflectivity (typically >95%) in the visible to near-infrared band, which can reflect most of the solar energy to the secondary mirror, while reducing the absorption of light energy by the primary mirror substrate 101, thus helping to reduce the heat generation of the primary mirror substrate itself.

[0102] The transparent infrared radiation layer 103 can be a ceramic-based functional coating deposited on the reflective layer 102, which has high visible light transmittance and infrared emissivity. This coating not only provides space environment protection for the reflective layer 102 and slows down its performance degradation in the space environment, but also effectively dissipates the heat absorbed by the primary mirror substrate through infrared radiation, so that the concave surface has both high reflectivity and efficient heat dissipation functions.

[0103] The thermally conductive radiation layer 104 is preferably a graphene film layer. This graphene film is a two-dimensional nanomaterial composed of carbon atoms and possesses the following excellent properties: ① The graphene film has high in-plane thermal conductivity (>1500 W / m·K), allowing it to work in conjunction with the heat spreader to rapidly diffuse the high-density heat generated by the solar cell and laterally conducted through the heat spreader to the entire primary mirror substrate, thus achieving uniform temperature, helping to avoid localized overheating, ensuring the safety of the solar cell, and providing a large surface area for heat radiation into space. ② The graphene film itself is also an excellent infrared radiation material with a certain infrared emissivity (>0.9), allowing it to directly radiate some heat. ③ The graphene film has a thickness on the micrometer scale and its mass is almost negligible, having a minimal impact on the system's weight gain. ④ The flexible nature of the graphene film allows it to adapt to thermal deformation under temperature changes, avoiding interfacial delamination caused by thermal stress.

[0104] Therefore, the concave surface of the primary mirror substrate, composed of a reflective layer 102 and a transparent infrared radiating layer 103, possesses both high reflectivity and infrared emissivity, facilitating the integration of the optical surface and the radiative heat dissipation surface. The thermally conductive radiating layer 104 on the convex surface of the primary mirror substrate works in conjunction with the heat spreader 7 to construct a low thermal resistance heat conduction path from the battery cell 5 to the primary mirror substrate 101. The specific heat transfer process includes:

[0105] ① First-stage lateral heat diffusion: The high-density heat flow generated by the battery cell 5 is first absorbed by the heat diffusion plate 7 attached to it and diffused laterally to reduce the heat flow density and avoid the formation of local hot spots under the battery cell 5.

[0106] ② Secondary lateral temperature uniformity: After the heat is conducted to the primary mirror substrate 101 through the heat spreader 7, the heat-conducting radiation layer 104 attached to the convex surface of the primary mirror substrate uses its ultra-high in-plane thermal conductivity to rapidly diffuse the heat laterally to the entire primary mirror substrate to achieve temperature uniformity.

[0107] The heat is ultimately radiated into the space environment through the convex and concave dual surfaces of the primary mirror substrate 101, forming an efficient heat dissipation path for the solar cell from "solar cell → heat spreader → primary mirror substrate (convex surface + concave surface) → space environment". See [link to solar cell heat dissipation path] for details. Figure 6 As shown.

[0108] This dual-layer design of the primary lens allows it to perform its light-gathering function while also possessing good heat dissipation capabilities. (See also...) Figure 7 When the focusing module is working, sunlight penetrates the transparent infrared radiation layer 103, is reflected by the reflective layer 102 towards the secondary mirror 3, and is then reflected a second time by the secondary mirror 3 to the solar cell 5. The high-density heat flow generated by the photoelectric conversion of the solar cell 5 is first absorbed by the heat spreader 7 immediately below it and undergoes primary lateral diffusion. Then, the heat is conducted through the heat spreader 7 to the primary mirror substrate 101. The solar radiation heat absorbed by the primary mirror substrate 101 itself and the heat conducted from the solar cell 5 are dissipated through two paths: one is direct outward thermal radiation through the concave transparent infrared radiation layer 103 (thermal path B1); the other is outward thermal radiation through the convex thermal conductive radiation layer 104 after secondary lateral temperature equalization (thermal path B2). This dual-sided heat dissipation collaborative design of "concave reflection + heat dissipation, convex thermal conduction + heat dissipation" improves heat dissipation efficiency while ensuring the optical performance of the primary mirror, helps to suppress the thermal deformation of the primary mirror, and ensures the stability of the focusing optical path.

[0109] In summary, the primary mirror substrate of this invention integrates effective thermal management capabilities while achieving the function of focusing and reflecting light. The combination of the concave reflective layer and the transparent infrared radiating layer provides heat dissipation while ensuring reflective performance, while the convex thermally conductive radiating layer enhances lateral heat conduction and radiative heat dissipation capabilities. This integrated design avoids the use of additional heat dissipation components, contributing to a compact and lightweight structure and providing a technical foundation for the stable operation of the focusing module.

[0110] In one embodiment, the secondary mirror has a near-hyperboloid surface structure, with a reflective medium film on its optical working surface and a heat dissipation coating on its non-optical working surface.

[0111] The secondary mirror adopts a near-hyperboloid design, forming a synergistic optical system with the primary mirror's near-parabolic spherical surface. This effectively corrects the optical path, improves beam converging effect, and helps optimize beam quality, forming a suitable light spot on the surface of the solar cell.

[0112] The reflective medium film on the optical working surface of the secondary mirror is a multilayer interference thin film prepared through processes such as vacuum deposition. This reflective medium film is optimized for the solar spectrum and has high reflectivity, which can reduce the loss of light energy during the reflection process of the secondary mirror.

[0113] The heat dissipation coating on the non-optical working surface of the secondary mirror uses materials with high infrared emissivity and low solar absorptivity, such as aerospace-grade inorganic white paint. Although the reflective dielectric film on its optical working surface significantly reduces light absorption, the secondary mirror will still heat up due to external heat flow and residual energy absorption. This heat dissipation coating enhances the infrared emissivity of the non-optical working surface of the secondary mirror, promoting the dissipation of accumulated heat from the secondary mirror into the space environment.

[0114] In summary, the embodiments of the present invention, by adopting a near-hyperbolic surface shape and combining it with a double-sided functional coating design, achieve beam conduction while also taking into account the requirements for operating temperature control, which helps to maintain the optical performance stability of the focusing module.

[0115] In one embodiment, see still Figure 5 The primary mirror base 101 has mechanical mounting surfaces 41 at its four corners. The secondary mirror support 4 adopts a long, rod-shaped structure and has a hollowed-out portion 42. The two ends of the support are fixedly connected to two mounting surfaces on opposite diagonals of the primary mirror base 101.

[0116] The mounting planes at the four vertices of the quadrilateral outline of the primary mirror base 101 provide defined mounting interfaces for the secondary mirror bracket 4. Fixing both ends of the secondary mirror bracket to the diagonal mounting planes creates a support structure with a large span. The hollow design of the secondary mirror bracket 4 helps reduce obstruction of the incident and reflected light paths while maintaining structural functionality.

[0117] The secondary mirror 3 and the secondary mirror support 4 are secured together by a threaded connector with an anti-loosening structure. This connection method can suppress loosening of the threaded pair that may be caused by emission vibration and on-orbit temperature changes, maintaining the stability of the connection. The threaded connection allows for appropriate adjustment of the angle of the secondary mirror during assembly to meet optical alignment requirements.

[0118] In summary, the embodiments of the present invention provide a stable support structure for the secondary mirror through the combination design of the mounting plane, the bracket with the hollow part, and the anti-loosening threaded connection, while providing solutions for reducing light shading and maintaining alignment accuracy.

[0119] In one embodiment, the secondary mirror and the secondary mirror support are fixed together by a threaded connector with an anti-loosening structure.

[0120] By setting anti-loosening structures (such as anti-loosening nuts, locking agents, etc.) at the threaded connection, the loosening of the threaded pair that may be caused by the severe vibration during the launch phase of the spacecraft and the temperature alternation environment during operation in orbit can be effectively suppressed. This helps to ensure a long-term stable mechanical connection between the secondary mirror 3 and the secondary mirror support 4 and prevents the secondary mirror 3 from shifting position due to loose connection.

[0121] The threaded connection allows for precise adjustment and calibration of the pitch and yaw angles of the secondary mirror 3 during assembly by accurately controlling the tightening torque. This adjustability helps to achieve precise alignment of the optical working surface of the secondary mirror 3 with respect to the primary mirror 1 and the optical funnel 6, providing a process guarantee for establishing and maintaining a precise secondary reflection optical path.

[0122] In addition, as a detachable rigid connection, threaded connections provide sufficient fastening force to ensure structural integrity, while also offering convenience for possible disassembly, maintenance, or replacement compared to permanent connection methods such as bonding or welding.

[0123] In summary, by adopting a threaded connection method with an anti-loosening structure, the embodiments of the present invention achieve synergistic improvement in connection reliability, assembly adjustability, and maintenance convenience, providing an effective guarantee for the long-term positional stability of the secondary mirror in the space environment.

[0124] In one embodiment, the light funnel is machined from aluminum alloy, and its inner surface is provided with a reflective medium film.

[0125] The conical cavity of the optical funnel guides the secondary reflected light from the secondary mirror to the solar cell, and its internal geometry and surface quality affect the light transmission effect. Manufacturing the optical funnel using aluminum alloy and a machining process allows for lightweight design while ensuring the necessary structural rigidity and geometric accuracy of the cavity. This process facilitates high dimensional accuracy and surface finish of the cavity, providing the necessary conditions for precise light guidance.

[0126] The reflective dielectric film deposited on the inner surface of the conical cavity is prepared by physical vapor deposition, which effectively reduces energy loss due to multiple reflections of light within the conical cavity, thereby improving the efficiency of light transmission to the solar cells. Simultaneously, this reflective property reduces light absorption, helping to minimize the temperature rise of the light funnel itself due to heat absorption, thus reducing its burden on the system's thermal management.

[0127] In addition, the reflective medium film has a certain barrier effect against space environment factors such as atomic oxygen, which can provide surface protection for aluminum alloy substrates, slow down their surface oxidation, and maintain the long-term stability of the optical performance of the inner surface of the light funnel.

[0128] In summary, the embodiments of the present invention achieve synergistic optimization in terms of lightweight structure, light energy transmission efficiency, and environmental adaptability by comprehensively designing the material selection, molding process, and internal surface optical treatment of the light funnel, thus providing a reliable guarantee for the long-term stable operation of the focusing module.

[0129] In one embodiment, the heat spreader is an aluminum nitride heat spreader with a layer of thermally conductive interface material on its surface.

[0130] The thermal interface material can be selected from materials such as aerospace-grade thermally conductive grease, gel, or phase change thermally conductive thin film. Microscopic gaps exist at the contact surfaces between the heat spreader, the solar cell, and the primary mirror substrate. Applying a layer of thermally conductive interface material to these surfaces fills these gaps, reduces contact thermal resistance, and achieves thermal coupling between the heat spreader, the solar cell, and the primary mirror substrate, improving the consistency of heat diffusion. Simultaneously, this thermally conductive interface material possesses a certain degree of flexibility, capable of absorbing micron-level warping deformation caused by space thermal cycling, avoiding increased thermal resistance due to rigid contact.

[0131] Aluminum nitride was chosen as the material for the heat spreader primarily based on the following properties:

[0132] 1) In terms of thermal conductivity, aluminum nitride has high thermal conductivity, which can quickly diffuse the high-density heat flow generated by the solar cell laterally to the entire heat spreader and even the main mirror substrate connected to it, avoiding the formation of local high-temperature hot spots under the solar cell and providing a uniform temperature distribution working environment for the solar cell.

[0133] 2) In terms of electrical insulation performance, aluminum nitride, as a ceramic material, inherently possesses electrical insulation properties, allowing it to directly contact the electrical connection points of the solar cell without the need for an additional insulation layer. This characteristic simplifies structural design, avoids introducing additional thermal resistance due to the addition of an insulation layer, and achieves a balance between electrical isolation and efficient thermal conduction.

[0134] 3) Regarding thermal expansion matching, the coefficient of thermal expansion of aluminum nitride is well-matched with that of commonly used solar cell materials, which helps reduce interfacial stress caused by differences in thermal expansion during temperature cycling. The use of surface thermally conductive interface materials further improves the distribution of interfacial stress and enhances the long-term stability of the interface under space thermal cycling conditions.

[0135] 4) In terms of weight control, aluminum nitride material has a moderate density while ensuring good thermal conductivity, which helps to control the weight of the heat spreader components. Combined with its direct mounting characteristics, it supports the compact and lightweight design of the focusing module.

[0136] In summary, the embodiments of the present invention, by selecting aluminum nitride material and combining it with the application of thermally conductive interface materials, have achieved comprehensive improvements in reducing contact thermal resistance, optimizing heat diffusion, maintaining electrical insulation, improving thermal matching, and achieving lightweighting, thus establishing a stable and reliable thermal management interface for the focusing module.

[0137] The above are merely preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. For those skilled in the art, the present invention can have various modifications and variations. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. An energy system for a dawn-dusk orbiting computing satellite, characterized in that, The energy system comprises: a power generation unit, an energy storage unit and a power supply control unit, the power generation unit comprises a main battery array and an auxiliary battery array, the energy storage unit comprises a load battery pack and a platform battery pack, and the power supply control unit comprises a load power supply control unit and a platform power supply control unit; an output end of the main battery array is connected to the load power supply control unit, output ends of the load power supply control unit are respectively connected to a computing load and the load battery pack, and a discharge end of the load battery pack supplies power to the computing load through the load power supply control unit, forming a load power supply channel; an output end of the auxiliary battery array is connected to the platform power supply control unit, output ends of the platform power supply control unit are respectively connected to a platform device and the platform battery pack, and a discharge end of the platform battery pack supplies power to the platform device through the platform power supply control unit, forming a platform power supply channel; wherein the load power supply channel and the platform power supply channel constitute a physically isolated double-channel power supply system architecture; the main battery array adopts an expandable light-concentrating solar cell array; the load power supply control unit and the platform power supply control unit are both configured to dynamically switch working modes between an illumination period and a shadow period according to an orbit phase of the satellite in a dawn-dusk orbit, and adjust charging and discharging strategies of corresponding battery packs and power distribution of corresponding loads accordingly; and the load power supply control unit is further connected to an output end of the auxiliary battery array for receiving power input therefrom, and the platform power supply control unit is further connected to output ends of the load power supply control unit for receiving power input therefrom after being converged, so as to constitute a bidirectional emergency power supply path.

2. The energy system according to claim 1, wherein when the auxiliary battery array fails, the power generated by the main battery array is sequentially supplied to the platform device through the load power supply control unit and the platform power supply control unit; when the main battery array fails, the load battery pack is discharged to provide emergency power for the computing load, so as to ensure data saving and smooth shutdown operation of the computing load.

3. The energy system of claim 2, wherein, The auxiliary battery array adopts a bulk solar cell array, and an output circuit of the auxiliary battery array comprises a load power supply circuit and a platform power supply circuit.

4. The energy system of claim 3, wherein, The load power supply circuit adopts a redundant design of multiple strings and multiple parallel connections, and the platform power supply circuit adopts a design of independent output in groups.

5. The energy system according to any of claims 1-4, characterized in that, The main battery array and the auxiliary battery array both adopt three-junction gallium arsenide solar cells.

6. The energy system of claim 1, wherein, The light-concentrating solar cell array, after being expanded in orbit, constitutes symmetrical double-sided solar wings arranged on both sides of a satellite platform. Each solar wing comprises at least one solar cell array panel, and each solar cell array panel comprises a light-weight high-strength frame and m×m light-concentrating arrays arranged on the frame; each light-concentrating array is composed of n×n light-concentrating modules, wherein m and n are both integers greater than or equal to 2.

7. The energy system of claim 6, wherein, The light-concentrating module comprises a primary mirror, a secondary mirror, a light funnel, a solar cell and a heat spreading sheet; the primary mirror comprises a primary mirror base, the primary mirror base constitutes a sun-facing opening of the light-concentrating module, and an optical working surface of the primary mirror base faces the secondary mirror and is configured to receive and reflect incident sunlight; The secondary mirror is fixed above the primary mirror by a secondary mirror support and located in the light convergence area of the primary mirror, with its optical working surface facing the entrance of the light funnel for twice reflection of the light reflected by the primary mirror. The light funnel is a conical cavity structure, with its entrance receiving the light reflected by the secondary mirror and its exit corresponding to the light receiving surface of the battery piece for guiding the light twice reflected by the secondary mirror to the battery piece. The battery piece is arranged below the light exit of the light funnel for converting light energy into electric energy. The heat spreading piece is tightly attached between the battery piece and the primary mirror base for conducting the heat generated by the battery piece to the primary mirror base, which radiates the heat to the space environment.

8. The energy system of claim 7, wherein, The primary mirror base adopts a near-parabolic spherical structure with a quadrilateral contour. Its concave surface is provided with a reflective layer and a transparent infrared radiation layer covering the reflective layer, serving to radiate the heat absorbed by the primary mirror base to the space environment in the form of infrared rays. Its convex surface is provided with a heat conducting and radiating layer for conducting the heat absorbed by the primary mirror base in the plane and radiating it to the space environment in the form of infrared rays.

9. The energy system of claim 7, wherein, The surface structure of the secondary mirror is a near hyperboloid, with its optical working surface provided with a reflective medium film and its non-optical working surface provided with a heat dissipation coating.

10. The energy system of claim 7, wherein, The primary mirror base is provided with mechanical installation planes at its four top corners. The secondary mirror support adopts a long strip-shaped rod structure, with a hollow part provided thereon; the two ends of the secondary mirror support are fixedly connected to the two installation planes on a pair of diagonal lines of the primary mirror base.

11. The energy system of claim 7, wherein, The secondary mirror and the secondary mirror support are fixed by a threaded connecting piece with an anti-loosening structure.

12. The energy system of claim 7, wherein, The light funnel adopts an aluminum alloy machine forming, with a reflective medium film provided on its inner surface.

13. The energy system of claim 7, wherein, The heat spreading piece adopts an aluminum nitride heat spreading piece, with a layer of heat conducting interface material provided on its surface.

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