Flat panel satellite

Abstract

This disclosure relates to a flat-panel satellite, including a cabin. The cabin is generally a flat rectangular body. The cabin includes a first, second, third, fourth, fifth, and sixth cabin panel that are detachably arranged to form a compartment. Different functional systems are respectively installed on the first, second, third, fourth, fifth, and sixth cabin panels. These functional systems include: a payload antenna system, with the payload antenna integrated on the outer side of the first cabin panel; and a platform control system, located inside the cabin and integrated on the inner side of the second cabin panel. This disclosure eliminates the complex support structure of traditional flat-panel satellite payload antennas by making the cabin panels detachably connected and integrating the payload antenna onto one of the cabin panels. The modular design reduces the integration difficulty of the flat-panel satellite, shortens the production cycle, and reduces testing workload and costs.

Description

Technical Field

[0001] This disclosure relates to the field of satellite technology, specifically to a flat-panel satellite. Background Technology

[0002] As the core hub responsible for information exchange within the entire satellite system, the payload antenna of a flat-panel satellite undertakes the crucial functions of two-way wireless communication and data exchange. Its performance directly determines the efficiency and reliability of the satellite's on-orbit missions. The payload antenna needs to establish a stable radio frequency channel, enabling the satellite to continuously receive telemetry command signals sent by ground control stations. These commands may involve critical operations such as satellite attitude adjustment, payload mode switching, or fault recovery. Simultaneously, the antenna also needs to transmit the satellite's own power supply voltage, temperature sensor data, attitude angle information, and other status parameters back to the ground in real time, forming the basic link for closed-loop control of the flat-panel satellite.

[0003] Since the payload antenna of a flat-panel satellite is the core component for its communication, remote sensing, or data transmission functions, its design needs to strike a balance between performance, weight, size, and environmental adaptability. In traditional flat-panel satellite designs, the payload antenna layout often adopts a distributed architecture, installing different types of antennas in different parts of the satellite. This design approach is acceptable for large satellites, but as aerospace technology advances towards miniaturization and integration, the drawbacks of distributed payload antenna layouts are becoming increasingly apparent. Flat-panel satellites, with their flat structural features and highly integrated design concept, pose a significant challenge to traditional payload antenna layout methods.

[0004] The distributed payload antenna layout also brings many inconveniences to satellite manufacturing and testing. Each independently installed antenna requires separate structural support and mounting interface. During manufacturing, each payload antenna component needs to be processed and assembled separately, extending the production cycle. In the testing phase, the distributed payload antennas need to undergo performance testing and environmental trials separately, increasing the workload and cost of testing. For mass-produced flat-panel satellites, this non-standardized design is clearly not conducive to achieving economies of scale.

[0005] From a technological development perspective, traditional distributed payload antenna layouts are no longer sufficient to meet the needs of future space missions. With the diversification of satellite applications, the requirements for the multi-functionality of payload antennas are increasing. At the same time, the trend towards miniaturization of flat-panel satellites is irreversible, placing higher demands on the integration of payload antenna systems.

[0006] Against this backdrop, the traditional distributed antenna layout of flat-panel satellites has encountered numerous problems in use, including difficulties in system integration, manufacturing, and testing. Currently, satellites in fields such as remote sensing and communication are trending towards constellation and networking. Traditional flat-panel satellites contain many subsystems, with deep coupling between systems and complex assembly processes. To achieve low-cost, mass production and streamlined manufacturing of flat-panel satellites, modular design of subsystems is necessary from the design stage to meet the increasing demands of research, development, and launch. With the continuous improvement of space mission requirements and changes in satellite platform characteristics, there is an urgent need to break through traditional design thinking and develop new flat-panel satellite payload antenna integration solutions. Utility Model Content

[0007] This disclosure provides a flat-panel satellite to address the problems existing in the prior art.

[0008] According to a first aspect of this disclosure, a flat-panel satellite is provided, comprising:

[0009] The cabin is generally a flat rectangular body. The cabin includes a first, second, third, fourth, fifth, and sixth compartment panel that are detachably arranged to form a compartment. The first compartment panel is located at the bottom of the cabin. The second compartment panel is arranged parallel to the first compartment panel and located at the top of the cabin. The third, fourth, fifth, and sixth compartment panels are perpendicular to the second compartment panel to form the sides of the cabin.

[0010] The first, second, third, fourth, fifth, and sixth compartments are each equipped with different functional systems, which include:

[0011] A payload antenna system, comprising a payload antenna integrated on the outside of the first compartment and configured to transmit or receive signals;

[0012] A platform control system is configured to be located within the cabin and integrated into the inner side of the second cabin panel.

[0013] In one embodiment of this disclosure, a solar array system integrated into the third panel is also included, the solar array system being configured to provide power to the flat-panel satellite;

[0014] The solar array system includes a solar array; a connector is pre-installed on the third panel, and the connector is provided with threaded holes and positioning pin holes; the solar array is positioned with the third panel through the positioning pin holes and is fixedly connected to the third panel through the threaded holes.

[0015] In one embodiment of this disclosure, a plurality of connectors are provided, the plurality of connectors are distributed on the third compartment plate, at least four connectors are configured to be located at the four corners of a rectangle, and at least one connector is located inside the rectangle.

[0016] In one embodiment of this disclosure, the locating pin hole is located at the center of the connector, and multiple threaded holes are provided, which are distributed in the circumferential direction on the outer side of the connector; a locating groove is provided on the connector outside the locating pin hole, and the locating groove is configured to engage with the flange at the corresponding position of the solar panel.

[0017] In one embodiment of this disclosure, the fourth compartment is configured to be located on the opposite side of the third compartment, and the fifth compartment is configured to be located on the opposite side of the sixth compartment; the functional system further includes:

[0018] The propulsion system is integrated into the fourth compartment.

[0019] The remote control and telemetry system is integrated into the fifth compartment panel;

[0020] An optical camera system is integrated into the sixth compartment panel.

[0021] In one embodiment of this disclosure, a support plate is provided between the first compartment and the second compartment, the support plate being configured to connect with the first compartment and the second compartment; at least one support plate is provided, the support plate being configured to divide the compartment into areas for accommodating different functional components.

[0022] In one embodiment of this disclosure, the four corners of the second compartment are connected to two adjacent compartments via corner connectors.

[0023] In one embodiment of this disclosure, the corner connector includes a bottom plate fixed to the second compartment plate, and a first side plate and a second side plate perpendicular to the bottom plate; two compartment plates adjacent to the second compartment plate are respectively fixed to the first side plate and the second side plate.

[0024] In one embodiment of this disclosure, the corner connector further includes a triangular plate parallel to the base plate, with the two sides of the triangular plate fixed to the inner walls of the first side plate and the second side plate, respectively; the first side plate and the second side plate are respectively provided with a plurality of connecting holes, which are arranged in layers above and below the triangular plate.

[0025] In one embodiment of this disclosure, the corner connector further includes a support block disposed at the right trihedral angle formed by the base plate, the first side plate, and the second side plate, and configured to connect with the inner wall surfaces of the base plate, the first side plate, and the second side plate.

[0026] One beneficial effect of this disclosure is that by making the flat-panel satellite's modules detachably connected and integrating the payload antenna onto one of the modules, the complex support structure of traditional flat-panel satellite payload antennas is eliminated. At the same time, the modular design reduces the integration difficulty of the flat-panel satellite, shortens the production cycle, and reduces testing workload and costs, laying the foundation for subsequent mass production and assembly line manufacturing of flat-panel satellites.

[0027] Other features and advantages of this disclosure will become clear from the following detailed description of exemplary embodiments with reference to the accompanying drawings. Attached Figure Description

[0028] The accompanying drawings, which are incorporated in and form a part of this specification, illustrate embodiments of the present disclosure and, together with their description, serve to explain the principles of the present disclosure.

[0029] Figure 1 This is an exploded view of a flat-panel satellite module provided in an embodiment of this disclosure;

[0030] Figure 2 This is a schematic diagram of the entire cabin provided in one embodiment of the present disclosure;

[0031] Figure 3 This is a schematic diagram of a corner connector provided in an embodiment of this disclosure;

[0032] Figure 4 This is a schematic diagram of a solar panel mounting plate provided in one embodiment of the present disclosure;

[0033] Figure 5 This is a schematic diagram of a connector provided in one embodiment of the present disclosure.

[0034] Figures 1 to 5 The one-to-one correspondence between the component names and the reference numerals in the figures is as follows:

[0035] 1. Hull; 10. Compartment; 11. First compartment plate; 12. Second compartment plate; 13. Third compartment plate; 131. Connector; 1311. Threaded hole; 1312. Locating pin hole; 1313. Locating groove; 14. Fourth compartment plate; 15. Fifth compartment plate; 16. Sixth compartment plate; 17. Support plate; 18. Angle connector; 180. Base plate; 181. First side plate; 182. Second side plate; 183. Triangular plate; 184. Connecting hole; 185. Support block; 21. Payload antenna system; 211. Payload antenna; 22. Platform control system; 23. Solar array system; 231. Solar array; 24. Propulsion system; 25. Remote control and telemetry system; 26. Optical camera system. Detailed Implementation

[0036] Various exemplary embodiments of the present disclosure will now be described in detail with reference to the accompanying drawings. It should be noted that, unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these embodiments do not limit the scope of the present disclosure.

[0037] The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit this disclosure or its application or use.

[0038] Techniques, methods, and equipment known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and equipment should be considered part of the specification.

[0039] It should be noted that similar labels and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be discussed further in subsequent figures.

[0040] In this article, terms such as "up," "down," "front," "back," "left," and "right" are used only to indicate the relative positional relationship between related parts, rather than to define the absolute position of these related parts.

[0041] In this article, "first," "second," etc., are used only to distinguish one another, and not to indicate degree of importance, order, or prerequisite for each other.

[0042] In this document, terms such as “equal” and “same” are not strict mathematical and / or geometric limitations, but also include errors that are understandable to those skilled in the art and permissible in manufacturing or use.

[0043] The distributed layout of payload antennas in existing technologies increases the structural complexity and weight burden of satellites. Each additional independent antenna requires supporting structures, cables, and interface equipment, which not only increases the weight of flat-panel satellites but also increases the difficulty of system integration. In the manufacturing and testing phase, independently installed antennas require separate structural support and testing verification, leading to increased design complexity, extended production cycles, and increased testing costs, which seriously restricts the economies of scale of mass production.

[0044] To address the shortcomings of existing technologies, this disclosure provides a flat-panel satellite. This flat-panel satellite adopts a modular flat-panel satellite configuration layout with subsystems. The functions of the flat-panel satellite are implemented by different subsystems. In a specific embodiment of this disclosure, the six subsystems of the networking satellite can be: payload antenna system, solar array system, propulsion system, remote control and telemetry system, optical camera system, and platform control system.

[0045] refer to Figure 1 and Figure 2The flat-panel satellite disclosed herein includes: a cabin 1, which is a flat rectangular body. The cabin 1 includes a first cabin panel 11 (positive Z-panel), a second cabin panel 12 (negative Z-panel), a third cabin panel 13 (positive X-panel), a fourth cabin panel 14 (negative X-panel), a fifth cabin panel 15 (negative Y-panel), and a sixth cabin panel 16 (positive Y-panel) that are detachably arranged to form a compartment 10.

[0046] In one specific embodiment of this disclosure, the first panel 11 is located at the bottom of the cabin 1 (when the flat-panel satellite is in orbit, its payload antenna system 21 needs to maintain a ground-pointing orientation; the bottom of the cabin 1 referred to in this disclosure is the panel where the payload antenna system 21 is located), the second panel 12 is arranged parallel to the first panel 11 and located at the top of the cabin 1, and the third panel 13, fourth panel 14, fifth panel 15, and sixth panel 16 are perpendicular to the second panel 12, forming the sides of the cabin 1. It can be understood that in a specific embodiment where the cabin 10 is a flat rectangle, the first panel 11 and the second panel 12 have the same area, the third panel 13 and the fourth panel 14 have the same area, and the fifth panel 15 and the sixth panel 16 have the same area; as... Figure 1 and Figure 2 As shown, in this embodiment, the two largest side panels are defined as the first side panel 11 and the second side panel 12, the second largest long side panels are defined as the third side panel 13 and the fourth side panel 14, and the smallest short side panels are defined as the fifth side panel 15 and the sixth side panel 16.

[0047] Different functional systems are installed on the first panel 11, the second panel 12, the third panel 13, the fourth panel 14, the fifth panel 15, and the sixth panel 16. The modular design reduces the integration difficulty of the flat-panel satellite, shortens the production cycle, and reduces the testing workload and cost, laying the foundation for the subsequent mass production and assembly line production of flat-panel satellites.

[0048] The functional system includes a payload antenna system 21, which comprises a first panel 11 and a payload antenna 211. The payload antenna 211 is integrated on the outside of the first panel 11 and is responsible for signal transmission, reception, and processing. Specifically, the payload antenna 211 undertakes high-speed data transmission, broadcast communication, or relay tasks, ensuring efficient and stable information transmission. Integrating the payload antenna 211 into a detachable panel of the flat-panel satellite eliminates the complex support structure of traditional flat-panel satellite payload antennas 211 and facilitates independent testing and rapid replacement during the final assembly stage. This modular integration scheme not only optimizes the internal space utilization of the flat-panel satellite but also allows the payload antenna system 21 to be flexibly configured according to mission requirements. For example, for different frequency bands or beam coverage requirements, functional upgrades can be achieved simply by replacing the corresponding payload antenna system 21 panel, without redesigning the entire flat-panel satellite platform.

[0049] It should be noted that the payload antenna 211 of the flat-panel satellite must be kept pointing towards the ground during flight. This ground pointing ensures that a stable and reliable communication link is established between the antenna and the ground station or other ground terminals. This is the foundation for the satellite to realize its core functions such as data transmission, telemetry and remote control, and information relay.

[0050] To ensure the thermal stability of the payload antenna 211 during continuous Earth-facing operation, a heat dissipation component can be installed inside the flat-panel satellite compartment 10 to prevent temperature changes in the payload antenna 211 caused by solar radiation. From a system design perspective, this constraint also affects the satellite configuration layout. Typically, the payload antenna 211 needs to be installed outside the first panel 11 facing Earth, and it must be ensured that it is not obstructed by components such as the solar array 231 throughout the satellite's entire lifespan.

[0051] Specifically, the first panel 11 of the flat-panel satellite integrated payload antenna 211 provided in this disclosure has a thermal control component embedded inside its body, which can control the temperature of the payload antenna system 21. When the temperature of the payload antenna 211 exceeds a set threshold, the first panel 11 can improve heat dissipation efficiency. The first panel 11 can adopt a sandwich structure, thus ensuring lightweight design while providing installation space for various functional components. In a specific embodiment, a waveguide transmission system can be designed in the sandwich structure, which is composed of precision-machined metal pipes. These pipes not only serve as structural supports but, more importantly, provide a low-loss propagation channel for the electromagnetic waves of the payload antenna 21. The entire first panel 11 achieves coordinated optimization of thermal management, structural support, and signal transmission through modular design, completing multifunctional integration within a limited space.

[0052] In addition, such as Figure 2 As shown, the payload antenna 211 of the flat-panel satellite provided in this disclosure is composed of subarray elements. The subarray elements are the basic radiating modules that constitute the payload antenna system 21, and are usually composed of multiple small radiating elements arranged and combined according to a specific pattern. These subarray elements have modular features in structure, and each element contains an independent feed network and phase control circuit, which can realize the directional radiation or reception of electromagnetic waves.

[0053] like Figure 1As shown, the functional system also includes a platform control system 22, which is located within the compartment 10 of the flat-panel satellite and integrated into the inner side of the second panel 12. Those skilled in the art will understand that the platform control system 22 may include components such as gyroscopes, star sensors, and platform control units. The platform control system 22 is used to maintain the on-orbit attitude stability of the flat-panel satellite, and also undertakes tasks such as flight trajectory control, energy management, temperature environment regulation, and coordination of the overall system operation. Integrating the platform control system 22 into the inner side of the second panel 12 of the flat-panel satellite fully utilizes the space of the compartment 10, optimizes the internal layout of the satellite, and improves signal transmission efficiency and reliability. This compact integration not only enhances the overall integrity of the platform control system 22, but also effectively leverages the protective function of the panel for the platform control system 22, reducing the impact of external electromagnetic interference and thermal environment fluctuations on the platform control system 22, thereby improving the stability and control accuracy of the satellite's on-orbit operation. Furthermore, the integrated design facilitates ground testing and maintenance, simplifies the satellite assembly process, and helps improve development efficiency and reduce system weight.

[0054] like Figure 2 As shown, the flat-panel satellite provided in this disclosure includes a solar array system 23, which is integrated onto a third panel 13. As a core component of the flat-panel satellite's energy system, the solar array system 23 is responsible for continuously providing energy to the flat-panel satellite during its on-orbit operation. Specifically, the solar array system 23 can be a flexible, rollable solar array. Integrating the solar array system 23 onto a detachable panel significantly improves the compactness and integration of the satellite structure, reduces the size and weight of the flat-panel satellite, and helps reduce launch costs and improve space utilization. Furthermore, the integrated solar array 231 panel can serve as a standardized module for the satellite, facilitating mass production and rapid assembly, while also supporting on-orbit maintenance or upgrades—for example, by replacing solar array 231 panels with different power generation efficiencies, it can flexibly adapt to the energy needs of different missions.

[0055] In one embodiment of this disclosure, reference is made to Figure 4 and Figure 5The third module 13 of the flat-panel satellite provided in this disclosure has a pre-installed connector 131, which has a threaded hole 1311 and a positioning pin hole 1312. The solar array 231 in the solar array system 23 is positioned with the third module 13 through the positioning pin hole 1312 and is fixedly connected to the third module 13 through the threaded hole 1311. The positioning pin hole 1312 ensures quick and accurate alignment between the solar array 231 and the module, avoiding misalignment or angular deviation during installation. The threaded hole 1311 provides a rigid mechanical connection, which, together with the positioning pin hole 1312, ensures connection strength and resists the sudden and violent force or energy input that the flat-panel satellite experiences in a very short time during launch vibration or operation in orbit, which could cause instantaneous deformation, vibration, or even damage to the flat-panel satellite.

[0056] In one embodiment of this disclosure, a plurality of connectors 131 are provided on the flat satellite module 13. These connectors 131 are distributed on the third module 13, with at least four connectors 131 configured to be located at the four corners of a rectangle, and at least one connector 131 located inside the rectangle. Specifically, as... Figure 4 As shown, four of the connectors 131 can form a rectangular shape (i.e., Figure 4 As shown by the dashed line, at least one connector 131 is also provided inside the rectangle. This distributed arrangement of connectors 131 significantly improves the overall structural stability and load distribution uniformity. The connectors 131 at the four corners of the rectangle form a rigid support frame, effectively resisting vibrations, impacts, and unexpected situations in the space environment during launch, ensuring a reliable connection between the solar array 231 and the third panel 13. The additional connectors 131 inside the rectangle further disperse the concentrated load, reducing the risk of localized stress concentration and preventing deformation of the third panel 13 or loosening of the connection between the third panel 13 and the solar array 231. This design not only optimizes the force transmission path but also enhances the flat-panel satellite's ability to withstand risks. Even if individual connectors 131 malfunction, the remaining connectors 131 can still maintain the structural integrity, thereby ensuring the long-term reliable operation of the flat-panel satellite under complex conditions.

[0057] Specifically, such as Figure 4 As shown, in this embodiment, the connector 131 can be set to seven, with three arranged horizontally inside the rectangle and four placed at the four corners of the rectangle. Each connection point is designed with four threaded holes 1311 and one mounting and positioning pin hole 1312 for the sun wing 231.

[0058] In one embodiment of this disclosure, such as Figure 5As shown, the locating pin hole 1312 on the connector 131 provided on the third compartment 13 of this disclosure is located at the center of the connector 131, and multiple threaded holes 1311 are provided, distributed in the circumferential direction on the outer side of the connector 131. This design of the connector 131 enables high-precision positioning and stable connection between the solar panel 231 and the compartment. The locating pin hole 1312 ensures the initial alignment of the connector 131 and the solar panel 231, while the circumferentially distributed threaded holes 1311 enhance shear and torsional resistance through multiple bolt fastening, thereby improving structural rigidity.

[0059] In one embodiment of this disclosure, such as Figure 5 As shown, a positioning groove 1313 is provided on the connector 131 outside the positioning pin hole 1312. The positioning groove 1313 is configured to engage with the flange of the corresponding position of the solar array 231. The engagement between the positioning groove 1313 and the flange (not shown in the figure) of the solar array 231 further restricts the radial displacement of the solar array 231 relative to the third panel 13, which can prevent the connection from loosening and ensure that a stable connection can be maintained under complex conditions such as launch vibration and thermal deformation, thereby improving the reliability and long-term stability of the satellite in orbit.

[0060] In one embodiment of this disclosure, the functional system further includes a propulsion system 24, which is integrated on a fourth panel 14 located on the opposite side of the third panel 13. The propulsion system 24 may include thrusters, gas cylinders, valve blocks, etc., and is responsible for providing precise and controllable thrust in a microgravity environment to meet the satellite's power requirements throughout its entire lifecycle from orbit insertion to failure. This relative arrangement reduces thermal and electromagnetic interference between the solar array 231 and the propulsion system 24, ensures synergistic optimization of energy supply and propulsion efficiency, and ultimately improves the reliability and control accuracy of the satellite's on-orbit operation.

[0061] In one embodiment of this disclosure, the functional system further includes a remote telemetry system 25 integrated on a fifth panel 15 and an optical camera system 26 integrated on a sixth panel 16, with the fifth panel 15 located on the opposite side of the sixth panel 16. The remote telemetry system 25 performs multiple functions including command transmission, status monitoring, and task management; the optical camera system 26 is responsible for achieving functions such as Earth observation, environmental monitoring, or target identification through high-resolution imaging in the visible or near-infrared bands. This integrated design, by centrally arranging the antennas and communication equipment in the remote telemetry system 25 and the optical components and data processing units in the optical camera system 26, effectively simplifies cable routing and structural design, reduces system complexity, and improves integration and maintenance convenience.

[0062] In one embodiment of this disclosure, reference is made to Figure 1The flat-panel satellite disclosed herein includes a support plate 17 disposed between the first panel 11 and the second panel 12, the support plate 17 being connected to the first panel 11 and the second panel 12. The support plate 17 significantly enhances the rigidity and stability of the overall structure of the flat-panel satellite, effectively resisting vibrations and impacts during launch, as well as thermal deformation and microgravity effects during on-orbit operation. This design avoids localized stress concentration by rationally distributing loads, while providing a more stable mounting platform for internal equipment and reducing performance deviations caused by structural deformation.

[0063] In one embodiment of this disclosure, the flat-panel satellite provided by this disclosure has at least one support plate 17. Specifically, in the embodiment provided by this disclosure, there are five support plates 17, which divide the compartment 10 into areas accommodating different functional components. By rationally dividing the internal areas of the compartment 10, the support plates 17 can achieve efficient utilization of the satellite's internal space, thereby avoiding mutual interference between devices. In addition, the divided compartment 10 can be designed differently for the environmental requirements of specific devices, such as providing vibration isolation or temperature control isolation for sensitive optical payloads. Moreover, this division design also reserves flexibility for future functional expansion, and new devices can be directly integrated into the reserved compartment 10, avoiding complex modifications to the original structure.

[0064] In one embodiment of this disclosure, reference is made to Figure 1 and Figure 3 The second module 12 of the flat-panel satellite disclosed herein is connected to two adjacent modules at its four corners via corner connectors 18, which significantly improves the stability of the structure. This design constrains the degree of freedom of the modules through rigid nodes, effectively reducing the relative displacement between adjacent modules. The concentrated force characteristics of the corner connectors 18 optimize the load transfer path, making the stress distribution more uniform and avoiding failure of the connectors 131 due to local stress concentration. At the same time, the modular connection method simplifies the assembly process, facilitates quick disassembly and maintenance, and improves the reset accuracy, ensuring the reset effect after disassembly and reassembly of the modules.

[0065] Specifically, four corner connectors 18 can be provided, such as... Figure 3As shown, each corner connector 18 adopts a layered design, consisting of four planes. Plane A directly mates with the second compartment plate 12, and a positioning through-hole is located at the center of plane A to ensure assembly accuracy. Plane D can be parallel to plane A, and together with plane A, they divide the corner connector 18 into two layers to increase its strength. Planes B and C respectively mate with the third compartment plate 13, fourth compartment plate 14, fifth compartment plate 15, and sixth compartment plate 16. Eight connecting holes 184, distributed four per layer, can be set on these two planes, and these connecting holes 184 can be high-precision threaded holes, forming a stable multi-point connection system. During the assembly of the flat-panel satellite compartment 10, the negative Z plate, positive and negative X plates, and positive and negative Y plates are precisely aligned with the corner connectors 18 through pre-machined connecting holes 184, ultimately assembling into the compartment 1 structure. This design, through the layered distribution of connecting holes 184, achieves multi-directional force balance, ensuring both rigid connections between the compartment plates and the technological feasibility of the overall assembly.

[0066] In one embodiment of this disclosure, such as Figure 3 As shown, the corner connector 18 includes a base plate 180 fixed to the second compartment plate 12, and a first side plate 181 and a second side plate 182 perpendicular to the base plate 180; two compartment plates adjacent to the second compartment plate 12 are respectively fixed to the first side plate 181 and the second side plate 182. Figure 3 As shown, the base plate 180 is plane A, the first side plate 181 is plane B, and the second side plate 182 is plane C. The base plate 180 can be made of carbon steel, stainless steel, or other steel materials, or it can be made of aluminum alloy or titanium alloy, etc. This disclosure does not limit the material of the base plate 180. The first side plate 181 and the second side plate 182 can be made of the same material as the base plate 180, or they can be made of different materials. The vertically arranged first side plate 181 and second side plate 182 ensure accurate positioning and alignment between the various compartment plates, which helps maintain the geometric accuracy of the overall structure, thereby improving assembly efficiency and quality.

[0067] In one embodiment of this disclosure, such as Figure 3 As shown, the corner connector 18 also includes a triangular plate 183 parallel to the base plate 180, such as... Figure 3 As shown, the triangular plate 183 is plane D. The two sides of the triangular plate 183 are fixed to the inner walls of the first side plate 181 and the second side plate 182, respectively. Multiple connecting holes 184 are respectively provided on the first side plate 181 and the second side plate 182, and these connecting holes 184 are arranged in layers above and below the triangular plate 183. The triangular plate 183 can be made of the same material as the base plate 180, or it can be made of a different material. The number of connecting holes 184 above and below the triangular plate 183 can be the same or different. The triangular structure of the triangular plate 183 enhances the connection stability between the first side plate 181 and the second side plate 182.

[0068] Specifically, the upper connecting hole 184 can be set at the connection between plane D and planes B and C, and at the same time serve to reinforce plane D. Similarly, the lower connecting hole 184 can be set at the connection between plane A and planes B and C, and serve to reinforce plane A.

[0069] In one embodiment of this disclosure, such as Figure 3 As shown, the corner connector 18 also includes a support block 185, which is disposed at the right trihedral angle formed by the base plate 180, the first side plate 181, and the second side plate 182, and is configured to connect with the inner wall surfaces of the base plate 180, the first side plate 181, and the second side plate 182. It should be noted that the right trihedral angle refers to the location of the area enclosed by the intersection of planes A, B, and C.

[0070] like Figure 3 As shown, the support block 185 can be in the shape of a triangular pyramid, or it can be a triangular pyramid-like shape formed by cutting off some of its edges. The support block 185 can be made of the same material as the base plate 180, or it can be made of a different material. The support block 185 can enhance the strength of the corner connector 18 and prevent the connection between the base plate 180, the first side plate 181, and the second side plate 182 from deforming or cracking due to stress.

[0071] In one embodiment of this disclosure, such as Figure 2 As shown, the flat-panel satellite provided in this disclosure has a generally flat rectangular body 1. The plane containing the second panel 12 is perpendicular to the planes containing the third panel 13, the fourth panel 14, the fifth panel 15, and the sixth panel 16, and parallel to the plane containing the first panel 11. Compared to traditional trapezoidal flat-panel satellites, the rectangular flat-panel satellite has higher structural symmetry. The six panels of the flat-panel satellite are all rectangular and orthogonal to each other, which makes the stress distribution of the flat-panel satellite body 1 more uniform when subjected to mechanical loads during the launch phase. This avoids the local stress concentration problem caused by the asymmetrical design of the trapezoidal structure, thereby improving the overall structural stiffness and vibration resistance.

[0072] Furthermore, the cuboid structure maximizes the use of internal space, with all panels being standard rectangles, facilitating modular layout of instruments and equipment, and is particularly suitable for payload installation using standardized interfaces. In contrast, the trapezoidal structure, due to its sloping surfaces, makes some space difficult to utilize effectively. In terms of manufacturing processes, the cuboid panels, combined with right-angle corner connectors 18, achieve high-precision assembly, significantly reducing processing and testing costs. The trapezoidal structure, involving sloping surfaces and non-standard angle connections, requires higher processing precision and assembly processes, and is prone to deviations. More importantly, the cuboid design is more conducive to close arrangement during satellite stacking and launch, reducing wasted launch vehicle envelope space. Its standardized shape also facilitates the docking of subsequent on-orbit service modules.

[0073] It should be noted that the assembly process of the flat-panel satellite disclosed herein adopts a modular design. The six modules can be distributed among different system manufacturers for parallel assembly, thereby shortening the overall manufacturing cycle. Specifically, the first module 11 and the second module 12 serve as reference modules and are first assembled with the support plate 17. Then, the remaining four modules are installed via corner connectors 18. Cable connections between the modules can be achieved in two ways: First, a gap of approximately 10 cm is left before closing the modules, and the cables are pre-connected using pluggable terminals before closing the modules. This allows for direct plugging and unplugging for replacement without complete disassembly during later maintenance. Second, the enclosure is completely sealed first, and the cables are passed through pre-drilled holes for external connection, maintaining a fixed internal structure while allowing for more flexible external wiring.

[0074] After the structural production is completed, different modular panels can be distributed to the corresponding subsystem installation units. After the subsystems are installed, the entire satellite will be assembled, integrated, and tested. This decouples the design and assembly of subsystems from the overall satellite design and assembly, significantly increasing the number of parallel processes during assembly, integration, and testing, and reducing assembly time. Modular design can save one-third of the design and assembly time, providing strong support for the mass production and low-cost development of constellation satellites.

[0075] The modular flat-panel satellite configuration disclosed herein allows for launch separation via side mounting or stacking within the rocket launch space envelope, enabling batch launches of 4-9 satellites per launch. Furthermore, by modularly designing the satellite layout and structure while meeting the functional requirements of each subsystem, the design and production time of the satellites is significantly reduced. This lays the foundation for subsequent mass production and streamlined manufacturing of satellites, thereby meeting the ever-increasingly rapid launch demands of satellite constellations.

[0076] The various embodiments of this disclosure have been described above. These descriptions are exemplary and not exhaustive, and are not limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments. The terminology used herein is chosen to best explain the principles, practical application, or technical improvements to the embodiments in the market, or to enable others skilled in the art to understand the embodiments disclosed herein. The scope of this disclosure is defined by the appended claims.

Claims

1. A flat-panel satellite, characterized in that, include: The cabin (1) is a flat rectangular body. The cabin (1) includes a first cabin plate (11), a second cabin plate (12), a third cabin plate (13), a fourth cabin plate (14), a fifth cabin plate (15), and a sixth cabin plate (16) that are detachably arranged to form a compartment (10). The first cabin plate (11) is located at the bottom of the cabin (1). The second cabin plate (12) is arranged parallel to the first cabin plate (11) and located at the top of the cabin (1). The third cabin plate (13), the fourth cabin plate (14), the fifth cabin plate (15), and the sixth cabin plate (16) are perpendicular to the second cabin plate (12) to form the side of the cabin (1). The first compartment (11), the second compartment (12), the third compartment (13), the fourth compartment (14), the fifth compartment (15), and the sixth compartment (16) are each equipped with different functional systems, which include: The payload antenna system (21) includes a payload antenna (211) integrated on the outside of the first panel (11) and configured to transmit or receive signals; Platform control system (22) is configured to be located within the compartment (10) and integrated into the inner side of the second panel (12).

2. The flat-panel satellite according to claim 1, characterized in that, It also includes a solar array system (23) integrated on the third panel (13), the solar array system (23) being configured to provide power to the flat-panel satellite; The solar array system (23) includes a solar array (231); a connector (131) is pre-installed on the third compartment (13), and the connector (131) is provided with a threaded hole (1311) and a positioning pin hole (1312); the solar array (231) is positioned with the third compartment (13) through the positioning pin hole (1312) and is fixedly connected with the third compartment (13) through the threaded hole (1311).

3. The flat-panel satellite according to claim 2, characterized in that, Multiple connectors (131) are provided, and multiple connectors (131) are distributed on the third compartment plate. At least four connectors (131) are configured to be located at the four corners of a rectangle, and at least one connector (131) is located inside the rectangle.

4. The flat-panel satellite according to claim 2, characterized in that, The positioning pin hole (1312) is located at the center of the connector (131), and multiple threaded holes (1311) are provided, with the multiple threaded holes (1311) distributed in the circumferential direction on the outer side of the connector (131). A positioning groove (1313) is provided on the connector (131) outside the positioning pin hole (1312), and the positioning groove (1313) is configured to engage with the flange at the corresponding position of the solar wing (231).

5. The flat-panel satellite according to claim 1, characterized in that, The fourth compartment (14) is configured to be located on the opposite side of the third compartment (13), and the fifth compartment (15) is configured to be located on the opposite side of the sixth compartment (16); the functional system further includes: The propulsion system (24) is integrated into the fourth compartment (14). The remote control and telemetry system (25) is integrated into the fifth compartment panel (15). An optical camera system (26) is integrated into the sixth compartment panel (16).

6. The flat-panel satellite according to claim 1, characterized in that, A support plate (17) is provided between the first compartment plate (11) and the second compartment plate (12), and the support plate is configured to connect with the first compartment plate (11) and the second compartment plate (12); The support plate (17) is provided with at least one, and the support plate (17) is configured to divide the compartment (10) into areas for accommodating different functional elements.

7. The flat-panel satellite according to claim 1, characterized in that, The four corners of the second compartment (12) are connected to the two adjacent compartments by corner connectors (18).

8. The flat-panel satellite according to claim 7, characterized in that, The corner connector (18) includes a bottom plate (180) fixed to the second compartment plate (12), and a first side plate (181) and a second side plate (182) perpendicular to the bottom plate (180); the two compartment plates adjacent to the second compartment plate (12) are respectively fixed to the first side plate (181) and the second side plate (182).

9. The flat-panel satellite according to claim 8, characterized in that, The corner connector (18) also includes a triangular plate (183) parallel to the base plate (180), with the two sides of the triangular plate (183) fixed to the inner walls of the first side plate (181) and the second side plate (182), respectively; the first side plate (181) and the second side plate (182) are respectively provided with a plurality of connecting holes (184), and the plurality of connecting holes (184) are arranged in layers above and below the triangular plate (183).

10. The flat-panel satellite according to claim 9, characterized in that, The corner connector (18) further includes a support block (185), which is located at the right trihedral angle formed by the base plate (180), the first side plate (181), and the second side plate (182), and is configured to connect with the inner wall surfaces of the base plate (180), the first side plate (181), and the second side plate (182).

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