Multipurpose structure thermal control integrated computing satellite and distributed large space computing center
By adopting an integrated structural and thermal control design and a distributed starlink system in the computing satellite, the problems of low heat dissipation efficiency and high weight of existing computing satellites have been solved, realizing a space computing system with efficient heat dissipation, multi-purpose adaptability, and safety and environmental protection.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- TSINGHUA UNIVERSITY
- Filing Date
- 2026-04-07
- Publication Date
- 2026-07-31
AI Technical Summary
In existing computing satellite designs, the structure and thermal control system are separate, resulting in poor heat dissipation efficiency, high weight, large overall satellite mass, and insufficient on-orbit reliability and multi-purpose adaptability, which increases launch costs and the potential risk of reentry debris.
It adopts a multi-purpose integrated thermal control design, which tightly integrates the computing board with the main structure of the satellite to form an integrated thermal control component. It utilizes high specific strength materials and radiative heat dissipation, combined with internal liquid return pipelines, to achieve efficient heat dissipation and weight optimization, and builds a large space computing center through distributed starlink.
It achieves efficient heat dissipation, reduces the overall weight of the satellite, improves on-orbit operational reliability and multi-purpose adaptability, reduces launch costs, and reduces the risk of re-entry debris, thus adapting to diverse space mission requirements.
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Figure CN122481982A_ABST
Abstract
Description
Technical Field
[0001] This application relates to the fields of aerospace technology and space infrastructure, and in particular to a multi-purpose integrated thermal control computing satellite and a distributed large-scale space computing center. Background Technology
[0002] With the rapid development of commercial aerospace and space technology, and the significant and rapid increase in ground-based computing power demand, the demand for space computing power is growing. New space missions such as space computing centers and space AI computing place higher demands on the computing performance and operational reliability of satellites.
[0003] Currently, existing computing satellite designs generally copy the form of ground-based computing centers. Simply put, it's moving ground-based server racks into space, employing a separate design for the structure and thermal control system. Structural components only bear the load, while the thermal control system is separate. Given the absence of air in space, traditional air-cooling and liquid-cooling methods are completely ineffective; heat can only be dissipated into space through radiation. If the traditional ground-based computing center construction method is adopted, it will face severe heat dissipation problems and require additional liquid piping, liquid pumps, and external heat sinks, thus increasing the satellite's complexity and weight. This results in low satellite integration, high overall satellite mass, and increased launch costs. Summary of the Invention
[0004] This application provides a multi-purpose integrated thermal control computing satellite and a distributed large-scale space computing center to solve at least some of the problems in related technologies.
[0005] In a first aspect, embodiments of this application provide a multi-purpose integrated thermal control computing satellite, comprising: The main structure of the satellite, which constitutes the main structure of the satellite's external structure, is made of a high specific strength material that has thermal conductivity and space radiation protection function; The space computing module includes at least one computing board for realizing on-orbit computing operations; each computing board is disposed inside the main structure of the satellite and is closely attached to the inner surface of the main structure of the satellite, so that the heat sink of the space computing module and the main structure of the satellite form an integrated structural thermal control component. At least one payload module for performing multi-purpose space missions; the payload module is disposed outside the main structure of the satellite; An energy supply module, located on the main structure of the satellite, is used to provide power support for the space computing module and each of the payload modules.
[0006] Optionally, the satellite main structure of the integrated structural thermal control component is externally constructed as a radiant heat sink, which serves as the heat sink for the computing board, thus forming the integrated structural thermal control component.
[0007] Optionally, the structure in which the computing board is installed has an embedded liquid return pipe for conducting heat from the computing board to the main structure of the satellite and dissipating it into space through radiation.
[0008] Optionally, the space computing module provides computing power to ground users while also providing data processing functions to various payload modules on the satellite. The space computing module also includes a computing power control unit, which is electrically connected to each computing power board and each payload module. The computing power control unit is used to schedule computing power resources, monitor the operating status of the space computing module, and work in coordination with each payload module.
[0009] Optionally, the load module includes at least one of the following: A ground communication antenna, used to enable data transmission to the ground; Inter-satellite communication antenna, used to enable data transmission between satellites; An optical remote sensing camera is used to observe the Earth and acquire image data below the satellite, which is then transmitted to the space computing module for on-orbit processing. A ground-to-ground laser transmission payload is used to realize laser energy transmission and high-speed laser communication for ground-to-ground laser receiving devices; Inter-satellite laser communication payload, used to achieve high-speed laser communication between satellites.
[0010] Optionally, the ground-to-ground laser transmission payload has a ground-to-ground laser receiver tracking function to enable pointing and tracking of the ground-to-ground laser receiver during satellite in-orbit flight.
[0011] Optionally, the energy supply module includes a solar array, an energy storage unit, and a power control unit. The solar array includes a sun-facing side and is located on top of the satellite's main structure, with the satellite's main structure situated on the other side of the sun-facing side of the solar array. The energy storage unit is electrically connected to the solar array, the space computing module, and each of the payload modules, and is used to store the electrical energy collected by the solar array to provide power support for the space computing module and each of the payload modules. The power control unit is electrically connected to the energy storage unit and is used to control the energy storage unit to distribute power.
[0012] Optionally, the surface dimensions and shape of the solar array meet the requirements of the computing satellite for solar shading while having the minimum structural rotational inertia; and / or A synthetic aperture radar antenna is mounted on the side of the solar array that faces away from the sun.
[0013] Optionally, depending on the satellite's main function, the solar array consists of multiple parts, including an adjustable attitude solar-orienting solar array and a fixed solar array; the connection between the solar array and the satellite's main structure includes at least one of rigid connection, flexible connection, and non-contact connection.
[0014] Optionally, the computing satellite includes at least one of the following: a satellite orbiting the Earth in a sun-synchronous orbit, a spacecraft, a space orbiter, and a space station.
[0015] Secondly, embodiments of this application provide a distributed large-scale space computing center, including multiple multi-purpose structured thermal control integrated computing satellites as described in the first aspect. Each of the computing satellites forms a computing satellite star chain, star group, or constellation in orbit. The computing satellites transmit data to each other through laser communication and data antennas to achieve coordinated scheduling and joint operation of computing resources.
[0016] The computing satellite provided in this application places each computing board directly inside the main structure of the satellite, and the computing boards are tightly attached to the inner surface of the main structure of the satellite. This makes the space computing module and the main structure of the satellite form an integrated structural and thermal control component, realizing the coordinated optimization of structural load-bearing, thermal control and heat dissipation and space computing power. There is no need to set up an additional independent heat sink, which effectively reduces the weight of the entire satellite and solves the problems of existing computing satellites with separate structure and thermal control, poor heat dissipation efficiency and high weight, thereby improving the reliability of satellite operation in orbit.
[0017] It should be understood that the above general description and the following detailed description are exemplary and explanatory only, and do not limit this application. Attached Figure Description
[0018] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this application and, together with the description, serve to explain the principles of this application.
[0019] Figure 1 The diagram shown is a structural schematic of a computing satellite according to an exemplary embodiment of this application.
[0020] Figure 2 The diagram shown is a structural block diagram of a computing satellite according to an exemplary embodiment of this application.
[0021] Figure 3 The diagram shown is a structural schematic of the integrated thermal control component of a computing satellite according to an exemplary embodiment of this application.
[0022] Figure 4 The diagram shown is a structural schematic of a computing satellite according to an exemplary embodiment of this application.
[0023] Figure 5The diagram shown is a structural schematic of a computing satellite according to an exemplary embodiment of this application.
[0024] Figure 6 The diagram shown is a structural schematic of a computing satellite according to an exemplary embodiment of this application. Detailed Implementation
[0025] Exemplary embodiments will now be described in detail, examples of which are illustrated in the accompanying drawings. When the following description relates to the drawings, unless otherwise indicated, the same numbers in different drawings denote the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with this application. Rather, they are merely examples of apparatuses and methods consistent with some aspects of this application as detailed in the appended claims.
[0026] To better understand the technical solution of this application, the multi-purpose integrated thermal control computing satellite and distributed large-scale space computing center of this application will be described in detail below with reference to the accompanying drawings. Unless otherwise specified, the features in the following embodiments and implementation methods can be combined with each other.
[0027] See Figures 1 to 3 As shown, embodiments of this application provide a multi-purpose integrated thermal control computing satellite, belonging to the field of aerospace technology and space infrastructure. The computing satellite can include satellites, spacecraft, space orbiters, and space stations orbiting the Earth in sun-synchronous orbits; that is, a collective term for all spacecraft orbiting the Earth, including satellites, spacecraft, space orbiters, and space stations. The computing satellite can include: a main satellite structure 10, a space computing module 20, at least one payload module 30, and an energy supply module 40.
[0028] The satellite's main structure 10 constitutes the core of the satellite's external structure. It can be manufactured using high-strength materials with both thermal conductivity and space radiation protection capabilities, thus reducing the satellite's structural weight while achieving effective heat dissipation and space radiation protection. High-strength materials refer to materials with a high strength-to-density ratio (i.e., specific strength), which are lighter while meeting the same strength requirements. Examples include high thermal conductivity metal-based carbon fiber composites, aluminum-tantalum composites (Al-Ta), and novel high-radiation-resistant aluminum alloys. In this way, the satellite's main structure 10, as the core load-bearing component of the entire satellite, and thus a structural component, can both bear the load and provide heat dissipation and radiation protection.
[0029] The space computing module 20 includes at least one computing board 21 for on-orbit computing operations. Each computing board 21 is disposed inside the satellite main structure 10 and is tightly fitted to the inner surface of the satellite main structure 10, so that the heat sink of the space computing module 20 and the satellite main structure 10 form an integrated structural thermal control assembly, ensuring that the heat generated by the computing board 21 during operation can be directly conducted to the satellite main structure 10. Figure 3 As shown. It should be noted that the number of computing boards 21 can be set according to actual needs. It is understood that the computing boards 21 may include heat sinks as part of the main structure 10 of the satellite, forming an integrated multi-functional structure for load-bearing and heat dissipation.
[0030] Understandably, the satellite's main structure 10 can directly serve as a radiator for the computing boards 21. Each computing board 21 and the satellite's main structure 10 become an integrated component, forming a structural thermal control assembly. This creates an integrated load-bearing and heat dissipation structure, achieving synergy between structural load-bearing and thermal control, eliminating the need for separate heat sinks. This efficiently solves the heat dissipation problem while significantly reducing the overall satellite weight. Furthermore, the external structure of the computing satellite utilizes high-strength materials with strong thermal conductivity and space radiation protection capabilities. This improves heat dissipation efficiency while also enhancing the radiation resistance of the satellite's internal electronic equipment, including the computing boards, making it better suited to the complex space environment.
[0031] The payload module 30 is used to perform multi-purpose space missions. The payload module 30 is located outside the main structure 10 of the satellite and communicates with the space computing module. Optionally, the payload module 30 includes at least one of the following: a ground communication antenna for data transmission to the ground; an inter-satellite communication antenna for data transmission between satellites; an optical remote sensing camera for observing the Earth and acquiring image data below the satellite, transmitting it to the space computing module 20 for on-orbit processing; a ground laser transmission payload for laser energy transmission and high-speed laser communication to a ground laser receiving device; and an inter-satellite laser communication payload for high-speed inter-satellite laser communication.
[0032] Optionally, the ground-to-ground laser transmission payload has a ground-to-ground laser receiver tracking function to achieve pointing and tracking of the ground-to-ground laser receiver during satellite orbit, thereby improving data transmission capability and accuracy. The ground-to-ground communication antenna and the inter-satellite communication antenna are respectively installed at different locations on the satellite's main structure to achieve data transmission to the ground and between satellites. The ground-to-ground laser communication payload and the inter-satellite laser communication payload are used to achieve high-speed laser communication, improving data transmission efficiency.
[0033] In this way, by mounting multiple payload modules on the main structure of the satellite, the computing satellite can achieve an integrated design of multiple functions such as communication, navigation, remote sensing, and tracking with space computing power, and has multi-purpose adaptability. It can take into account diverse space missions such as communication and remote sensing, meet the current development trend of satellite multi-purpose transformation, and meet the collaborative needs of multiple missions such as space exploration, Earth observation, space-to-ground communication, navigation, and tracking.
[0034] The energy supply module 40 is mounted on the satellite's main structure 10. The energy supply module 40 is electrically connected to the space computing module 20 and each of the payload modules 30, providing power to them. In other words, the energy supply module 40 can provide stable power to all components and modules of the entire satellite. The modules work collaboratively to achieve integrated functionality encompassing structure, thermal control, computing power, and multiple applications.
[0035] Through the above embodiments, the computing power satellite provided in this application directly sets each computing power board 21 inside the satellite main structure 10 and closely fits it with the inner surface of the satellite main structure 10, so that the space computing power module 20 and the satellite main structure 10 form an integrated structural and thermal control component. This ensures that the heat generated by the computing power board during operation can be directly conducted to the satellite main structure, realizing the synergistic optimization of structural load-bearing, thermal control and heat dissipation and space computing power. There is no need to set up an additional independent heat sink, which effectively reduces the weight of the entire satellite and solves the problems of poor heat dissipation efficiency and high weight in the existing computing power satellite structure and thermal control. This improves the reliability of the satellite in orbit.
[0036] Furthermore, considering that satellites need to re-enter the atmosphere and return to Earth after their service life expires in order to provide orbital resources for new satellites, designing computing satellites in the form of traditional ground data centers may lead to problems if the satellites are too large and the materials in the middle that are resistant to high-temperature heating and ablation have a high proportion of weight. This could result in large satellite debris crashing into the Earth's surface, causing unpredictable and catastrophic consequences for the Earth and humanity.
[0037] The computing satellite of this application directly houses each computing board 21 inside the main structure 10 of the satellite. The heat sink of the space computing module 20 and the main structure 10 of the satellite form an integrated structural and thermal control component, which optimizes the overall satellite structure design, reduces the satellite volume and weight, and can minimize the volume and weight of the residual objects after the satellite re-enters the atmosphere after the end of its service life, avoiding catastrophic impacts on the Earth's environment and human safety. It is safer and more environmentally friendly, and overcomes the technical defects such as the potential safety hazards of satellite re-entry debris.
[0038] Combination Figure 3As shown, in some optional embodiments, the satellite main structure 10 is provided with a plurality of reinforcing ribs 11 inside. The reinforcing ribs 11 are used to improve the structural rigidity and load-bearing capacity of the satellite main structure 10 and to prevent structural deformation of the satellite during launch and on-orbit operation.
[0039] Furthermore, the satellite main body structure 10, which forms the integrated structural thermal control component, has an external radiative heat sink structure (i.e., a thermal radiation structure). This structure serves as the heat sink for the computing board 21, forming the integrated structural thermal control component. Thus, the satellite main body structure 10, which forms the integrated structural thermal control component, can function as both a satellite structure and a heat sink for the computing board 21. In space, due to the lack of convection media, heat dissipation mainly relies on thermal radiation. Therefore, setting the external structure of the satellite main body structure 10 as a radiative heat sink achieves effective heat dissipation and radiation. A liquid return pipe can be embedded inside the structure housing the computing board 21 to conduct heat from the computing board to the satellite main body structure and dissipate it into space through radiation, further enhancing heat transfer efficiency. Optionally, the liquid return pipe can employ a heat pipe structure, such as aluminum / ammonia tube-fin type, single-channel type, thermal diode type, lightweight controllable type, etc. The heat pipe achieves efficient temperature uniformity through phase change heat transfer, enhancing the temperature consistency of the radiating panel.
[0040] In this way, the heat generated by the computing boards can be efficiently conducted to the surface of the satellite's main structure, and then dissipated into space through radiation, completely solving the heat dissipation problem in the space environment. The integrated structural thermal control design significantly reduces the complexity and weight of the satellite, thereby lowering launch costs.
[0041] It should be noted that, in Figure 3 In the given embodiment, the satellite main structure 10 adopts a circular cross-section structure, taking into account that typical orbiter designs, including space station module designs, primarily use circular cross-sections. However, in other embodiments, the satellite main structure 10 can adopt a flat plate structure mounted on a frame structure, forming a polygonal cross-section structure. In such... Figure 3 Other equipment can also be installed inside the main satellite structure 10 shown, including a computing power scheduling system, attitude control system, other onboard electronic computer equipment, and batteries.
[0042] In some optional implementations, the space computing module 20 provides computing power to ground users while also providing data processing functions for various payload modules 30 on the satellite. The space computing module 20 also includes a computing power control unit, electrically connected to each computing power board 21 and each payload module 30. The computing power control unit is used to schedule computing resources, monitor the operating status of the space computing module 20, and work collaboratively with each payload module 30. Thus, the computing power control unit, electrically connected to each computing power board, enables dynamic scheduling of computing resources, real-time monitoring of the operating status of the space computing module, and collaborative work with multi-purpose payload modules to provide data processing support for the payload modules, improving the overall satellite's mission coordination capabilities. This allows the space computing module to provide computing power to ground users while also providing data processing functions for various payloads on the satellite.
[0043] In some optional embodiments, the energy supply module 40 includes a solar panel 41, an energy storage unit, and a power control unit. The solar panel 41 has a sun-facing side, i.e., the side facing the sun. The solar panel 41 is disposed on the top of the satellite main structure 10 for collecting solar energy. The satellite main structure 10 is located on the other side of the sun-facing side of the solar panel 41, and the solar panel 41 can provide shade for the satellite main structure 10. The energy storage unit is electrically connected to the solar panel 41, the space computing module 20, and each of the payload modules 30, for storing the electrical energy collected by the solar panel 41 and providing power support for the space computing module 20 and each of the payload modules 30. The power control unit is electrically connected to the energy storage unit for controlling the power distribution of the energy storage unit. Optionally, the energy storage unit may include a battery. In this way, the solar panel 41, while providing energy, can also provide shade for the satellite, blocking direct sunlight from hitting the satellite structure, and can form a localized cool surface for the satellite main structure 10 on the other side of the sun-facing side, improving the heat dissipation conditions for the computing boards.
[0044] In related technologies, some computing satellites use solar panels with a large aspect ratio. This results in extremely low stiffness of the solar panels and increases the rotational inertia provided by the solar panel structure. This affects the control stability of the satellite's attitude and requires the attitude control actuator to output a larger control torque, which further increases the weight of the satellite.
[0045] In some optional embodiments, the surface dimensions and shape of the solar array 41 of this application meet the requirements of the computing satellite for sun shading while having the minimum structural rotational inertia. This minimizes the rotational inertia generated by the solar array 41. Ideally, the aspect ratio of the solar array 41 is close to 1, which makes the attitude control of the computing satellite more stable. Furthermore, a synthetic aperture radar antenna is installed on the side of the solar array 41 facing away from the sun (which can be understood as the lower part), forming an integrated structure, further improving the integration of the satellite and reducing the overall weight of the satellite.
[0046] In some alternative implementations, depending on the satellite's main function, the solar array 41 may consist of multiple parts, including an adjustable attitude-oriented solar array and a fixed solar array. The connection between the solar array 41 and the satellite's main structure 10 may be at least one of a rigid connection, a flexible connection, or a non-contact connection.
[0047] The fixed solar array is located on top of the satellite's main structure 10, while the adjustable attitude-oriented solar array can adjust its attitude for solar orientation according to the sun's position. The number of fixed and adjustable attitude-oriented solar arrays can be set according to actual requirements.
[0048] The solar array, positioned atop the satellite's main structure, is designed to account for the constraints imposed by attitude control on the structure's natural frequency and minimize its moment of inertia. This reduces the torque requirements of the attitude control actuators, thereby lowering the satellite's weight and power consumption. Ideally, the solar array's aspect ratio should be close to 1. A synthetic aperture radar antenna can be selectively mounted on the lower part of the solar array, forming an integrated structure that further enhances the satellite's integration and reduces its overall weight. While collecting solar energy and providing power to the entire satellite, the solar array also provides shade for the main structure, blocking direct sunlight and creating a localized cooling surface. This helps the computing boards dissipate heat through the satellite's main structure, improving heat dissipation efficiency.
[0049] The following is combined with Figure 1 , Figure 4 , Figure 5 and Figure 6 This paper introduces the different satellite configurations and different payload modules of the computing satellite in this application.
[0050] See Figure 1 As shown, the satellite's main structure 10 is made of aluminum alloy, which combines high thermal conductivity with space radiation protection. Internal structural reinforcing ribs 11 enhance structural rigidity. The exterior of the satellite's main structure 10 is designed for thermal radiation, eliminating the need for internal liquid return pipes; heat dissipation from the computing boards is achieved through radiation.
[0051] The space computing module 20 consists of numerous computing boards 21, integrating a computing control unit. It is tightly fitted to the inner surface of the satellite's main structure 10, forming an integrated structural and thermal control component. This enables basic on-orbit computing operations and provides basic data processing support for the payload module. The payload module 30 includes an inter-satellite laser communication payload 31, an inter-satellite communication antenna 32 (e.g., an inter-satellite data transmission antenna), and a ground communication antenna 33. The inter-satellite laser communication payload 31 and the inter-satellite communication antenna 32 are mounted on one side of the top of the satellite's main structure, while the ground communication antenna 33 is mounted on the bottom of the satellite's main structure, enabling inter-satellite and ground data transmission.
[0052] The energy supply module 40 includes solar panels 41 and an energy storage unit. The solar panels 41 are fixed solar panels 411, located on top of the satellite's main structure 10. They have a surface aspect ratio of 1 and a small moment of inertia. While providing power, they also provide shade for the satellite's main structure and assist in heat dissipation for the computing boards. The energy storage unit uses batteries that meet space usage requirements to store excess energy and ensure a stable power supply for the entire satellite.
[0053] Understandably, the satellite's main structure 10 (i.e., the satellite's main structure) houses the computing power board 21, and externally it is equipped with an inter-satellite laser communication payload 31, an inter-satellite communication antenna 32, and a ground communication antenna 33. The solar panels 41 of the energy supply module 40 are fixed solar panels 411, which have a simple structure and can be used to realize the satellite-to-ground and inter-satellite communication functions of the on-orbit computing power system. They are suitable for scenarios where computing power services are the main focus. Figure 1 The computing satellite in this embodiment can be regarded as a basic type of computing satellite, which can operate independently in orbit and provide on-orbit computing systems and satellite-to-ground and inter-satellite communication services.
[0054] See Figure 4 As shown, the satellite's main structure 10 is made of aluminum alloy and may include an aluminum alloy plate and a carbon fiber composite main frame, enhancing load-bearing capacity and rigidity. The space computing module 20 consists of a single computing board 21, mounted on the aluminum alloy plate and then on the carbon fiber main frame, forming an integrated structural and thermal control assembly. The external structure of the satellite's main structure 10 is designed for thermal radiation, while the internal structure incorporates liquid return pipes to further improve heat transfer efficiency and ensure the cooling requirements of the computing board during high-load operation.
[0055] Payload module 30 includes an inter-satellite laser communication payload 31, an inter-satellite communication antenna 32 (e.g., an inter-satellite data transmission antenna), a ground communication antenna 33, and an optical remote sensing camera 34. Space computing module 20 integrates a high-performance computing control unit, enabling large-scale on-orbit data processing and providing image data processing support for optical remote sensing camera 34, thus improving the efficiency of on-orbit processing of remote sensing data. The inter-satellite laser communication payload 31 is mounted on the top of the satellite's main structure 10, the inter-satellite communication antenna 32 is mounted on one side of the satellite's main structure 10, the optical remote sensing camera 34 is mounted on the bottom of the satellite's main structure 10, and the ground communication antenna 33 is mounted on the other side of the satellite's main structure 10. The payload modules are staggered to avoid signal interference. The ground laser-related payload (i.e., the ground laser transmission payload 35) can be integrated into the optical remote sensing camera 34, providing ground laser receiver tracking capabilities and improving the accuracy of remote sensing data transmission.
[0056] The energy supply module 40 includes solar panels 41 and an energy storage unit. The solar panels 41 consist of a fixed solar panel 411 and two adjustable attitude-oriented solar panels 412. The two adjustable attitude-oriented solar panels 412 are mounted on both sides of the satellite's main structure 10 and can dynamically adjust their attitude according to the sun's position. The fixed solar panels 411 are mounted on the top of the spacecraft structure 10. The energy storage unit can use lithium-ion battery packs or graphene battery packs to meet the power demands of the entire satellite under high load operation.
[0057] Understandably, the satellite's main structure 10 (i.e., the satellite's main structure) contains a computing board 21, and externally it is equipped with an inter-satellite laser communication payload 31, an inter-satellite communication antenna 32, a ground communication antenna 33, and an optical remote sensing camera 34. The solar array 41 of the energy supply module 40 adopts one fixed solar array 411 and two adjustable attitude solar arrays 412, with the two adjustable attitude solar arrays 412 respectively located on both sides of the fixed solar array 411.
[0058] In this embodiment, the computing satellite, besides enabling on-orbit computing systems and inter-satellite and space-to-ground communication, can also be used for Earth remote sensing observation and on-orbit computing processing, while also possessing inter-satellite and Earth-to-space communication capabilities. In this example, the primary function is remote sensing, with space computing capabilities as a secondary function. High-resolution remote sensing satellites, due to their limited field of view, typically employ agile and maneuverable satellite attitude control schemes, achieving large-area imaging of the base station through large-angle side-swinging and forward / backward swaying. To provide sufficient power and shaded area during this process, the solar array is divided into three sections: a fixed solar array 411 in the middle section is fixed to the top of the satellite, while two adjustable attitude-oriented solar arrays 412 on either side can rotate in solar orientation. Figure 4The computing satellite in this embodiment can be regarded as an agile satellite integrating computing power and remote sensing. It can realize functions such as Earth remote sensing observation, on-orbit computing power processing, inter-satellite and Earth communication, and is suitable for mission scenarios such as real-time processing of remote sensing data and regional monitoring. It can operate independently or form a starlink with other satellites to improve computing power and remote sensing coverage.
[0059] See Figure 5 As shown, the payload module 30 includes an inter-satellite laser communication payload 31, an inter-satellite communication antenna 32 (e.g., an inter-satellite data transmission antenna), a ground communication antenna 33, an optical remote sensing camera 34, and a ground laser transmission payload 35 (e.g., a ground multi-purpose laser payload). It can be understood that the satellite main structure 10 (i.e., the satellite main structure) houses the computing board 21, while the external configuration includes the inter-satellite laser communication payload 31, the inter-satellite communication antenna 32, the ground communication antenna 33, the optical remote sensing camera 34, and the ground laser transmission payload 35. The solar array 41 of the energy supply module 40 employs one fixed solar array 411 and two adjustable attitude sun-oriented solar arrays 412, with the two adjustable attitude sun-oriented solar arrays 412 respectively located on both sides of the fixed solar array 411.
[0060] In addition to enabling on-orbit computing and inter-satellite communication, as well as remote sensing observation and on-orbit computing, the computing satellite in this embodiment can also be used for inter-satellite and ground communication, and can also be used for ground communication and navigation, thus providing both remote sensing and computing services. Figure 5 The computing satellite in the embodiment can be regarded as a ground communication-navigation-remote sensing-computing integrated satellite.
[0061] See Figure 6 As shown, the computing satellite is a space orbiter, a design that modifies an orbiter to simultaneously possess space computing capabilities. The payload module 30 includes an inter-satellite communication antenna 32 (e.g., an inter-satellite data transmission antenna), a ground communication antenna 33, an optical remote sensing camera 34, and a ground laser transmission payload 35 (e.g., a multi-purpose omnidirectional laser payload). Understandably, the main satellite structure 10 (i.e., the satellite's main body) houses the computing power board 21, while the external components include the inter-satellite communication antenna 32, the ground communication antenna 33, the optical remote sensing camera 34, and the ground laser transmission payload 35. The solar panels 41 of the energy supply module 40 are fixed solar panels 411. To provide the necessary low-temperature shaded area for heat dissipation, the solar panels are changed from the traditional sail form to body-mounted solar panels, installed on top of the main structure.
[0062] The space orbiter in this embodiment can be considered an integrated orbiter combining space computing power and multi-functional payloads. It can not only perform space computing functions but also form a large-scale space computing center by working with multiple computing satellites or orbiters. Furthermore, it is multi-purpose, suitable for various tasks such as orbital data processing, multi-directional laser communication, and Earth observation and tracking. Here, the multi-purpose omnidirectional laser payload has the ability to track the laser receiver, maintaining its pointing accuracy and directionality throughout the satellite's orbital motion or attitude maneuvers.
[0063] In all the above configurations, the ground-to-laser transmission payload has a ground-to-laser receiver tracking function, which can achieve precise pointing and tracking of the ground-to-laser receiver during the satellite's on-orbit flight, improving the stability and accuracy of data transmission; the ground-to-communication antenna and the inter-satellite communication antenna are installed in different positions on the main structure of the satellite to avoid signal interference and ensure smooth data transmission.
[0064] In existing technologies, some computing satellite designs employ a combination of multiple computing satellites. Individual satellites are first launched into sun-synchronous orbits and then assembled in orbit to form a large computing satellite. This approach presents several problems: it requires both docking equipment and orbit control systems for docking, increasing the satellite's launch weight. Furthermore, since attitude control is crucial during docking, an attitude control system is indispensable, thus failing to save costs or reduce weight. Additionally, if one satellite in the combination malfunctions, it is difficult to separate it from the combination and replace it with a new satellite unit.
[0065] This application also provides a distributed large-scale space computing center, comprising multiple multi-purpose, thermally controlled integrated computing satellites as described in the above embodiments and implementation methods. These computing satellites form a computing satellite starlink, constellation, or cluster in orbit. The computing satellites transmit data via laser communication and data antennas, enabling coordinated scheduling and collaborative operation of computing resources. Thus, by constructing starlinks, constellations, or clusters using multiple satellites in orbit, a distributed large-scale space computing center is built, further enhancing the overall computing power and adapting to diverse space mission requirements.
[0066] The distributed large-scale space computing center provided in this application forms a computing satellite star chain, constellation, or cluster through multiple satellites in orbit. The satellites transmit data via laser communication and data antennas, enabling coordinated scheduling and collaborative operation of computing resources, thus forming a distributed large-scale space computing center and increasing the overall computing power scale. This achieves coordinated scheduling and sharing of computing resources, constructs a distributed space computing center, and significantly increases the overall computing power scale.
[0067] In some alternative implementations, multiple such... Figure 4The integrated computing power and remote sensing agile satellite shown in the embodiment establishes a space computing power star chain in orbit. The satellites achieve high-speed data interaction through the inter-satellite laser communication payload 31 and the inter-satellite communication antenna 32. The computing power control units work together to realize the dynamic scheduling and sharing of computing power resources. While building a distributed space computing power center, it forms a continuous space remote sensing detection capability.
[0068] The attitude of each satellite in Starlink is controlled collaboratively by the adjustable attitude-oriented solar array 412 and attitude control actuators. Due to the small moment of inertia of the solar array, the attitude adjustment is flexible and stable, and agile attitude maneuvering can be achieved with a relatively low attitude control cost. The optical remote sensing cameras 34 of each satellite work together to achieve a wider range of Earth observation. The observation data is processed collaboratively through Starlink's computing resources, which greatly improves data processing efficiency and can meet the needs of complex tasks such as large-scale space AI computing and global remote sensing monitoring.
[0069] Compared with existing technologies, this application provides a computing satellite and distributed space computing center that integrates structure and thermal control, is multi-purpose, safe, easy to control in attitude, and environmentally friendly to humans. It solves the problems of existing computing satellites, such as separate structure and thermal control, poor heat dissipation efficiency, high weight, poor attitude stability control, single purpose, and potential catastrophic consequences for Earth. It achieves synergistic optimization of structural load-bearing capacity, thermal control and heat dissipation, and space computing power, improving the reliability of satellite operation in orbit, possessing multiple functions, reducing launch costs, and avoiding catastrophic consequences for Earth and humanity. It has the following beneficial effects: 1. Integrated structural thermal control design solves heat dissipation problems and reduces weight: The satellite's main structure serves as a heat sink for the computing power board, forming an integrated structural thermal control component. This eliminates the need for separate heat dissipation components. Furthermore, the external thermal radiation structure of the satellite's main structure and the optional internal embedded liquid reflux pipeline enable efficient heat dissipation, completely solving the heat dissipation problem in the space environment. The integrated structural thermal control component design significantly reduces the satellite's complexity and overall weight, thereby lowering launch costs.
[0070] 2. Versatile Configuration and Diverse Applications: Designed with multiple satellite configurations, different payload modules can be configured according to mission requirements, enabling flexible integration of computing power with remote sensing, communication, navigation, tracking and other functions. It adapts to various scenarios, from basic computing power services to high-end multi-mission collaboration, solving the problem of the single application of existing computing power satellites.
[0071] 3. Stable attitude control and high operational reliability: Optimized solar array design, controlling the aspect ratio to be close to 1, reducing rotational inertia, and increasing the first-order natural frequency of the solar array structure, effectively improving the stability of satellite attitude control, reducing the energy consumption and weight of attitude control actuators, and improving the overall on-orbit operational reliability of the satellite.
[0072] 4. Safe and environmentally friendly, reducing potential risks: Optimize the overall satellite structure design, control the satellite volume and reduce weight, minimize the volume and weight of residual objects after the satellite re-enters the atmosphere at the end of its service life, avoid catastrophic impacts on the Earth's environment and human safety, and make it safer and more environmentally friendly.
[0073] 5. Strong scalability: By forming starlink, star cluster or constellation by multiple satellites, a distributed space computing center can be built to realize the coordinated scheduling of computing resources. The overall computing power scale can be flexibly expanded according to needs to adapt to the future growth of space computing power demand.
[0074] It should be understood that this application is not limited to the precise structure described above and shown in the accompanying drawings, and various modifications and changes can be made without departing from its scope. The scope of this application is limited only by the appended claims.
Claims
1. A multi-mission structural thermal control integrated computing satellite, characterized in that, include: The main structure of the satellite, which constitutes the main structure of the satellite's external structure, is made of a high specific strength material that has thermal conductivity and space radiation protection function; The space computing module includes at least one computing board for realizing on-orbit computing operations; each computing board is disposed inside the main structure of the satellite and is closely attached to the inner surface of the main structure of the satellite, so that the heat sink of the space computing module and the main structure of the satellite form an integrated structural thermal control component. At least one payload module for performing multi-purpose space missions; the payload module is disposed outside the main structure of the satellite; An energy supply module, located on the main structure of the satellite, is used to provide power support for the space computing module and each of the payload modules.
2. The multi-mission structural thermal control integrated computing satellite of claim 1, wherein, The satellite main structure of the integrated thermal control component is externally constructed as a radiating heat sink, which serves as the heat sink for the computing board, thus forming the integrated thermal control component. and / or The internal embedded liquid return pipe of the structure in which the computing board is installed is used to conduct heat from the computing board to the main structure of the satellite and dissipate it into space through radiation.
3. The multi-mission structural thermal control integrated computing satellite of claim 1, wherein, The space computing module provides computing power to ground users while also providing data processing functions to various payload modules on the satellite. The space computing module also includes a computing power control unit, which is electrically connected to each computing power board and each payload module. The computing power control unit is used to schedule computing resources, monitor the operating status of the space computing module, and work in coordination with each payload module.
4. The multi-mission structural thermal control integrated computing satellite of claim 1, wherein, The load module includes at least one of the following: A ground communication antenna, used to enable data transmission to the ground; Inter-satellite communication antenna, used to enable data transmission between satellites; An optical remote sensing camera is used to observe the Earth and acquire image data below the satellite, which is then transmitted to the space computing module for on-orbit processing. A ground-to-ground laser transmission payload is used to realize laser energy transmission and high-speed laser communication for ground-to-ground laser receiving devices; Inter-satellite laser communication payload, used to achieve high-speed laser communication between satellites.
5. The multi-mission structural thermal control integrated computing satellite of claim 4, wherein, The ground-to-laser transmission payload has a ground-to-laser receiver tracking function to achieve pointing tracking of the ground-to-laser receiver during satellite in-orbit flight.
6. The multi-mission structural thermal control integrated computing satellite of claim 1, wherein, The energy supply module includes a solar array, an energy storage unit, and a power control unit. The solar array has a sun-facing side and is located on top of the satellite's main structure, with the main structure situated on the other side of the sun-facing side of the solar array. The energy storage unit is electrically connected to the solar array, the space computing module, and each of the payload modules, and is used to store the electrical energy collected by the solar array to provide power support for the space computing module and each of the payload modules. The power control unit is electrically connected to the energy storage unit and is used to control the energy storage unit to distribute power.
7. The multi-mission structural thermal control integrated computing satellite of claim 6, wherein, The surface dimensions and shape of the solar array meet the requirements of the computing satellite for solar shading while having the minimum structural moment of inertia; and / or A synthetic aperture radar antenna is mounted on the side of the solar array that faces away from the sun.
8. The multi-purpose integrated thermal control computing satellite according to claim 6, characterized in that, According to the main functions of the satellite, the solar array is composed of multiple parts, including an adjustable attitude solar array and a fixed solar array; the connection between the solar array and the main structure of the satellite includes at least one of rigid connection, flexible connection and non-contact connection.
9. The multi-purpose integrated thermal control computing satellite according to claim 1, characterized in that, The computing satellite includes at least one of the following: a satellite orbiting the Earth in a sun-synchronous orbit, a spacecraft, a space orbiter, and a space station.
10. A distributed large-scale space computing center, characterized in that, It includes multiple multi-purpose integrated thermal control computing satellites as described in any one of claims 1-9, each of which forms a computing satellite star chain, star group or constellation in orbit, and the computing satellites transmit data to each other through laser communication and data antennas to achieve coordinated scheduling and joint operation of computing resources.