A satellite design method

Abstract

The application provides a module unit for a satellite, comprising a shell, at least one standard interface and a management module. The standard interface is arranged on the surface and comprises a power transmission interface for providing power transmission, a communication module for realizing data interaction and communication, and a magnetic attraction module for realizing physical connection between different module units. The management module is arranged in the interior of the shell and comprises a node self-identification chip communicatively connected with the power transmission interface, which is used for identifying other module units connected with the module unit, a wireless module used for transmitting backup data in each module unit, a lithium battery module electrically connected with the magnetic attraction module, a power management module used for providing basic power supply for the module unit, a power source management module used for managing power source use of the module unit and providing 5V internal power, and an electromagnetic unlocking module communicatively connected with the magnetic attraction module and used for managing the magnetic attraction module of each standard interface of the module unit.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace technology, in particular to a module unit for a satellite. BACKGROUND

[0002] With the continuous development of satellite technology, the functions that can be achieved by a single satellite are more and more. In order to achieve more functions, the number of subsystems or functional modules configured in the satellite increases, and the structure of the satellite is more complex. In order to meet the launch conditions, the layout of each module or subsystem is crucial, so it leads to the continuous increase of the development cost and period of the satellite. In order to reduce the development period of the satellite and realize the rapid layout of the satellite structure, the modular design method is more and more applied to the satellite research and development center. For example, the patent CN106628253 provides a kind of modular satellite platform architecture of column, which sets standard interface on each module of satellite, realizes the design of satellite system by self-configuration various modules. For example, the patent CN106516161 provides a kind of modular satellite of magic mode, which builds satellite system by referring to the structure of magic cube, divides each subsystem of spacecraft into physically and functionally independent functional modules, and separately assembles in a magic cube. And any magic cube adopts standardized mechanical and electrical interface, thermal control interface and data interface.

[0003] Although the above two kinds of satellite structures can quickly realize the design of satellite, the standard interfaces of the module units are fixedly arranged on the specified surface, and the connection between the module units is relatively complex, which makes it impossible to build a satellite with a specific shape by using the module units. At the same time, the entire assembly process must be completed on the ground. SUMMARY

[0004] In view of part or all of the problems in the prior art, the present application provides a module unit for a satellite, comprising:

[0005] a shell;

[0006] at least one standard interface arranged on the surface of the shell, comprising:

[0007] a power-on interface for providing power transmission;

[0008] a communication module for realizing data interaction and communication; and

[0009] a magnetic attraction module for realizing physical connection between different module units; and

[0010] a management module arranged in the interior of the shell, comprising:

[0011] a node self-identification chip communicatively connected with the power-on interface, for identifying other module units connected with the module unit;

[0012] a wireless module for backup data transmission within each module unit;

[0013] a lithium battery module electrically connected to the magnetic module, for providing basic power supply for the module unit;

[0014] a power management module for managing power usage of the module unit and providing 5V internal power supply; and

[0015] an electromagnetic unlocking module communicatively connected to the magnetic module, for managing the magnetic module of each standard interface of the module unit.

[0016] Further, the power-on interface comprises:

[0017] a pogo pin arranged on the surface of the shell and retractable; and

[0018] a spring piece electrically connected to the management module and corresponding to the pogo pin, the pogo pin retracts to contact the spring piece.

[0019] Further, the communication module comprises a data interface supporting LVDS protocol.

[0020] Further, the magnetic module comprises a plurality of positive and negative magnetic poles arranged alternately and at intervals.

[0021] Further, the positive and negative magnetic poles form a circular ring, and the communication module and the power-on interface are located inside the circular ring.

[0022] Further, the data interface comprises two annular data interfaces.

[0023] Further, the module unit is a cube, and the standard interface is arranged at the center of any surface of the cube.

[0024] Further, the management module is in the form of a board card, and the node self-identification chip, the wireless module, the lithium battery module, the power management module, and the electromagnetic unlocking module are integrated on the same board card.

[0025] Further, the module unit further comprises a turntable arranged inside the module unit, and the standard interface is connected to the rotating shaft of the turntable through a transmission mechanism, so that it can rotate with the turntable.

[0026] Further, the turntable comprises a one-dimensional motor.

[0027] The application provides a module unit for a satellite, which is a standard structure, and any of the module units can independently perform one or more functions of a satellite platform, such as mission planning, energy distribution, attitude control, satellite propulsion, etc., by installing corresponding modules or devices in the module unit, and different function module units can form a satellite product library, and in the design of a satellite, different module units are selected according to tasks and requirements for assembly. In addition, the module units are connected by magnetic adsorption, so that the assembly operation of the satellite using the module units is simpler, and the assembly can be performed on the ground or in orbit by operating a robot or the like, which improves the satellite assembly efficiency and greatly improves the in-orbit expandability of the satellite and provides the possibility of in-orbit life extension of the satellite. BRIEF DESCRIPTION OF DRAWINGS

[0028] To further clarify the above and other advantages and features of the embodiments of the present application, a more particular description of embodiments of the application will be rendered by reference to specific drawings. It is appreciated that these drawings depict only typical embodiments of the application and are therefore not to be considered limiting of its scope. The drawings will be described with additional specificity and detail in the following description.

[0029] Figure 1 A cell satellite capable of in-orbit modular assembly and reconstruction is shown in an embodiment of the application;

[0030] Figures 2a-2c Structural schematic diagrams of cell satellites in other embodiments of the application are shown respectively;

[0031] Figure 3 A structural schematic diagram of a cell unit for a cell satellite is shown in an embodiment of the application;

[0032] Figure 4 A structural schematic diagram of a comprehensive electronic unit is shown in an embodiment of the application;

[0033] Figure 5 A structural schematic diagram of an energy unit is shown in an embodiment of the application;

[0034] Figure 6 A structural schematic diagram of a propulsion unit is shown in an embodiment of the application;

[0035] Figures 7a-7c Structural schematic diagrams of attitude control units in multiple embodiments of the application are shown respectively;

[0036] Figure 8 A structural schematic diagram of a three-axis rotation unit is shown in an embodiment of the application;

[0037] Figure 9 A connection schematic diagram of a solar wing and the three-axis rotation unit is shown in an embodiment of the application;

[0038] Figure 10 Structure diagram of a plate unit according to an embodiment of the present application; and

[0039] Figure 11 Connection diagram of a plate unit and a module unit according to an embodiment of the present application. DETAILED DESCRIPTION

[0040] In the following description, reference is made to specific embodiments of the application. Those skilled in the art will recognize that the application can be practiced with one or more of the specific details set forth herein without such specific details. In other instances, well-known structures, materials or operations are not shown or described in detail in order to avoid obscuring aspects of the application. Similarly, like reference numerals refer to like elements throughout. It will be appreciated that for simplicity and clarity of illustration, elements shown in the drawings have not necessarily been drawn to scale. For example, the dimensions of some of the elements are exaggerated relative to each other.

[0041] In this specification, reference to "one embodiment" or "the embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment of the application. The appearances of the phrase "in one embodiment" in various places in the specification are not necessarily all referring to the same embodiment.

[0042] It should be noted that the embodiments of the present application are described in a particular order of process steps, however, this is only for the purpose of illustrating the specific embodiment and does not limit the order of the steps. Instead, in different embodiments of the present application, the order of the steps can be adjusted according to the adjustment of the process.

[0043] To achieve the long-term on-orbit maintenance and continuous upgrade capability of satellites, the present application provides a module unit for a satellite, which can also be referred to as a cell unit, which can constitute a cell satellite, which can realize on-orbit modular assembly and reconfiguration under the cooperation of an operating robot, wherein the operating robot can be installed on the surface of the cell unit to perform the assembly of the cell satellite. The cell unit has a unified form and a corresponding standard interface, and different devices or modules are configured thereon, so that any cell unit can independently perform one or more functions of a satellite platform, such as task planning, energy distribution, attitude control, satellite propulsion, etc., and different functional cell units can form a satellite product library, and in the design of a satellite, different cell units are selected according to the task and requirements for assembly. With the help of the operating robot, the assembly of the satellite can be performed on the ground or in space. The scheme of the present application is further described below in combination with the embodiment drawings.

[0044] In the present application, the "first surface" refers to the outer surface of the cell unit shell, and the "second surface" refers to the inner surface of the cell unit shell.

[0045] Figure 1 A cell satellite capable of on-orbit modular assembly and reconfiguration is shown in one embodiment of the present application. As shown in Figure 1 A cell satellite capable of on-orbit modular assembly and reconfiguration includes a main structure 001 and a solar wing 002, wherein the main structure 001 includes a plurality of cell units 101 connected and communicated through standard interfaces. In an embodiment of the present application, the arrangement of the cell units is not limited, that is, the shape of the main structure is not limited, and can be set according to the number and functions of the cell units contained. For example, the cell units can be arranged in one row; for another example, the cell units can be arranged in multiple rows, and the number of cell units contained in each row can be the same or different; for another example, the cell units can be combined into a multi-layer structure, and the number of cell units contained in any layer can be the same or different, Figures 2a-2c The structural schematic diagrams of cell satellites in other embodiments of the present application are shown respectively, and it should be understood that in actual applications, the number of cell units contained in the cell satellite and the assembly mode can be different from those shown in Figure 1 、 Figures 2a-2c The solar wing is arranged on both sides of the main structure 001 and connected and communicated with the cell units through standard interfaces. In one embodiment of the present application, the cell satellite further includes a patch thermal control module arranged on the surface of the cell unit for heat dissipation of the cell unit.

[0046] In another embodiment of the present application, the cell satellite further includes a patch antenna 1300 connected with the cell unit through a standard interface for realizing radio propagation function. In one embodiment of the present application, the cell unit is a cubic structure including a shell, at least one standard interface and a management module, wherein the standard interface can be arranged on the first surface of any side of the shell, the standard interface is used for bearing mechanical connection, communication connection, power supply and the like, and the management module is arranged inside the cell unit. Figure 3 A structural schematic diagram of a cell unit for a cell satellite in one embodiment of the present application is shown. As shown in Figure 3 The standard interface includes a power-on interface 311, a communication module 312 and a magnetic attraction module, wherein:

[0047] The power-on interface 311 includes a thimble and an elastic sheet, wherein the elastic sheet is arranged inside the standard interface and connected with the management module 302, the thimble is arranged corresponding to the position of the elastic sheet, and when two cell units are connected, the thimble is retracted to contact the elastic sheet, thereby being in communication with the management module to realize the identification of the module identity and the in-place state and provide power transmission.

[0048] The communication module 312 includes a data interface, in an embodiment of the present application, the data interface includes two annular data interfaces, and the data interface realizes data interaction and communication by adopting an LVDS protocol.

[0049] The magnetic attraction module includes a positive magnetic pole and a negative magnetic pole, and is used for mechanical connection between cell units, in an embodiment of the present application, as shown in the figure, the positive magnetic pole 331 and the negative magnetic pole 332 are alternately and spacedly arranged to form a magnetic attraction module in a circular ring shape and surround the outside of the communication module 312. Figure 3

[0050] In an embodiment of the present application, the standard interface can also be connected with a motor through a transmission device, thereby enabling the standard interface to rotate along the axis of the shell.

[0051] The management module 302 is arranged inside the cell unit and includes:

[0052] A node self-identification chip 321 is communicatively connected with the power-on interface 311 and is used for identifying and managing other connected cell units.

[0053] A wireless module 322 is used for backup data transmission inside each cell unit.

[0054] A lithium battery module 323 is electrically connected with the magnetic attraction module and is used for providing basic power supply for the cell unit, so as to ensure the basic power supply and electromagnetic interface power supply demand inside the cell unit without external power supply.

[0055] A power management module 324 is used for managing the power supply use of the cell unit and providing 5V internal power supply.

[0056] An electromagnetic unlocking module 325 is communicatively connected with the magnetic attraction module and is mainly used for managing the magnetic attraction module of each standard interface of the cell unit, thereby controlling the mechanical connection between the cell unit and other cell units.

[0057] In an embodiment of the present application, each module and chip of the management module is integrated on a standard board card and is inserted into the inside of the cell unit through a slot.

[0058] ​It should be understood that according to different functions of different cell units, corresponding modules or devices can be added in the management module according to requirements to realize more functions.

[0059] In the embodiment of the application, the cell units included in the main structure of the cell satellite generally include a comprehensive electronic unit, an energy unit, a propulsion unit, an attitude control unit and a three-axis rotation unit.

[0060] The comprehensive electronic unit is used for controlling information processing and interaction of the whole satellite, realizing algorithms of each subsystem, energy allocation, GNSS signal receiving and processing, functional evolution and upgrade, cell satellite reconfiguration path planning and other tasks. The comprehensive electronic unit is a core component of in-orbit expansion and reconfiguration of the cell satellite, and is also a main body of software task planning and data processing. Therefore, each surface of the comprehensive electronic unit is provided with a standard interface, i.e., each surface of the comprehensive electronic unit can be connected with other cell units. The comprehensive electronic unit is a cell unit that needs to be assembled first in the cell satellite assembly process. The comprehensive electronic unit adopts a plug-in card form, specifically, each functional module is made into a same standard board card form and is inserted into a shell of the comprehensive electronic unit. Figure 4 A structure schematic diagram of the comprehensive electronic unit of one embodiment of the application is shown in FIG. 4. Figure 4 As shown in FIG. 4, in the embodiment of the application, the comprehensive electronic unit includes but is not limited to:

[0061] The star computer 401 is used for collecting data calculation and distributing control instructions.

[0062] The storage module 402 is used for storing star computer calculation data, payload data and the like.

[0063] The data processing module 403 is used for analyzing and centrally calculating collected data on the satellite.

[0064] The TT&C transponder 404 is used for being responsible for telemetry, ranging, speed measurement and time difference measurement functions.

[0065] The GNSS receiver 405 is an independent unit, is connected with a PCB of the comprehensive electronic system, is placed in a comprehensive electronic system box, and except for an antenna interface, other signals are internal signals of the comprehensive electronic system box.

[0066] The data transmission transmitter 406 is a communication relay device of a controller and a terminal equipment speed sensor.

[0067] The energy unit can be formed by additionally installing a battery pack in the cell unit. The energy unit is used for energy supply of the whole satellite, Figure 5 A structure schematic diagram of the energy unit of one embodiment of the application is shown in FIG. 5. Figure 5As shown, in the embodiment of the present application, the energy unit comprises a battery pack 501. The battery pack 501 is configured by a plurality of batteries, and the number of the batteries can be configured according to the actual demand of the satellite. In an embodiment of the present application, the batteries are arranged on one side of the shell, and gradually arranged to the center as the number of the batteries increases. The battery pack 501 releases electric energy to supply power to the on-board equipment during the on-orbit operation and the safe mode. The management of the primary power supply and the secondary power supply can be realized by the power management module in the cell unit management module. The primary power management refers to the power management of the energy unit, and the secondary power supply refers to the power supply management of other units or modules of the satellite. The power management module comprises the control of the charging and discharging of the battery pack and the interface required by the power subsystem.

[0068] The propulsion unit is formed by installing thrusters on the surface of the cell unit and arranging a fuel tank in the cell unit. The propulsion unit is used for the propulsion and orbit change of the whole satellite. Figure 6 The structure diagram of the propulsion unit in an embodiment of the present application is shown in FIG. 6. Figure 6 As shown, in the embodiment of the present application, the propulsion unit comprises thrusters 601 and a fuel tank 602. In an embodiment of the present application, the thrusters 601 comprise four thrusters arranged on the first surface of the shell on one side of the propulsion unit, and the thrusters 601 can rotate freely within a certain angle to provide thrust for the satellite to maintain the orbit and adjust the attitude. The fuel tank 602 is arranged in the interior of the propulsion unit to store corresponding fuel to supply energy for the thrusters. In order to better provide propulsion for the cell satellite, the propulsion unit is preferably arranged on the outermost layer of the cell satellite, and the side on which the thrusters are installed is arranged vertically to the flight direction.

[0069] The attitude control unit is formed by installing momentum wheel, magnetic torque device, star sensor and three-axis gyroscope inside the cell unit. The attitude control unit is used to adjust the whole satellite attitude. One or more attitude control units can be contained in a satellite, and the multiple attitude control units can be combined in three-axis orthogonal to achieve three-degree-of-freedom control capability. The attitude control unit comprises momentum wheel 701, magnetic torque device 702, star sensor 703 and three-axis gyroscope 704. The momentum wheel 701 is installed inside the attitude control unit and is used to control the satellite attitude to keep the system angular momentum constant. The magnetic torque device 702 is installed inside the attitude control unit and can interact with the geomagnetic field to generate a magnetic control torque to control the satellite attitude or unload the momentum wheel. The star sensor 703 is arranged inside the attitude control unit, but its photosensitive part is exposed on the surface of the shell through the hole in the shell. The star sensor 703 can determine the three-axis attitude of the satellite relative to the celestial coordinate system by sensing the radiation of the fixed star and output the data to the integrated electronic unit to determine the attitude adjustment scheme. The three-axis gyroscope 704 is installed inside the attitude control unit and is used to sense the attitude change of the satellite and transmit the related data to the integrated electronic unit to form the attitude adjustment scheme. In the embodiments of the application, the number of the momentum wheel 701, the magnetic torque device 702, the star sensor 703 and the three-axis gyroscope 704 can be set according to actual needs, Figures 7a-7c The structural schematic diagrams of the attitude control units of multiple embodiments of the application are shown respectively. As shown in Figure 7a In one embodiment of the application, the attitude control unit comprises a momentum wheel 701 and a magnetic torque device 702. The momentum wheel 701 is installed at the center of the second surface of the one side shell of the attitude control unit, and the magnetic torque device 702 is arranged at the edge of the second surface of the other side shell of the attitude control unit. In this embodiment, the six-sided shell of the attitude control unit can be replaced by a standard interface. As shown in Figure 7b In another embodiment of the application, the attitude control unit comprises a momentum wheel 701, a magnetic torque device 702, a star sensor 703 and a three-axis gyroscope 704. Since the hole needs to be arranged on the shell corresponding to the photosensitive part of the star sensor 703, the side of the attitude control unit where the star sensor 703 is installed cannot generally be replaced by the standard interface in this embodiment. In order to meet the demand of the satellite task with large momentum wheel, in the embodiments of the application, multiple attitude control units as shown in Figure 7a and 7b can be installed on the satellite and combined in three-axis orthogonal to achieve three-degree-of-freedom control capability. Figure 7cA structural schematic diagram of an attitude control unit in another embodiment of the present application is shown, in which the attitude control unit comprises three momentum wheels 701, three magnetic torque devices 702, a star sensor 703 and a three-axis gyroscope 704, the three momentum wheels 701 and the three magnetic torque devices 702 are arranged in three axes, so that the attitude control unit can realize full attitude control module integration and can meet the design requirements of satellites with weak attitude control capability.

[0070] By arranging a one-dimensional turntable inside the cell unit, the standard interface of the cell unit can be rotated, i.e., a rotating unit is formed, and if one one-dimensional turntable is arranged in each of three orthogonal directions, a three-axis rotating unit is formed. The three-axis rotating unit can be used to install a solar wing, for example, and can meet the rotating requirements in different directions. Figure 8 A structural schematic diagram of a three-axis rotating unit in an embodiment of the present application is shown, as shown in Figure 8 In the embodiment of the present application, the three-axis rotating unit comprises three one-dimensional turntables, which are arranged inside the three-axis rotating unit and distributed in three orthogonal directions. Any one of the one-dimensional turntables comprises a motor 8011 and a transmission mechanism 8012, one end of the transmission mechanism 8012 is connected with the rotating shaft of the motor 8011, and the other end is connected with the standard interface, so that the standard interface can be rotated under the driving of the motor 801. Figure 9 A connection schematic diagram of a solar wing and the three-axis rotating unit in an embodiment of the present application is shown. As shown in Figure 9 The solar wing comprises a standard interface 901 and a sail plate 902. The standard interface 901 has the same structure as the standard interface of the cell unit, can be mechanically connected with the three-axis rotating unit by magnetic adsorption, and can communicate and be powered through a communication module and a power supply interface. In order to reduce the volume during launching, in an embodiment of the present application, the sail plate 902 adopts a foldable sail plate, which is in a folded state during launching and is unfolded during operation. The foldable sail plate can comprise a plurality of battery plates, and any one of the battery plates is connected with an adjacent battery plate in a rotatable manner.

[0071] The standard interface of the cell unit can also be used to connect operation robots, solar wings, patch solar modules, heat insulation components, heat dissipation components, patch antennas and the like, and the operation robots, solar wings, patch solar modules, heat insulation components, heat dissipation components and patch antennas all comprise standard interfaces. The structures of the patch solar modules, heat insulation components, heat dissipation components and patch antennas are shown in Figure 10 The connection of the cell unit is shown in Figure 11As shown in the figure, the patch solar module, the heat insulation assembly, the heat dissipation assembly, and the patch antenna are all plate units, and a standard interface is arranged on the second surface thereof for mechanical connection with the standard interface on the cell unit through magnetic adsorption. The first surface of the cell unit is provided with a solar panel, heat insulation material, heat dissipation material, or array antenna according to the corresponding requirements, thereby forming the patch solar module, the heat insulation assembly, the heat dissipation assembly, and the patch antenna. In order to facilitate disassembly, in an embodiment of the present application, a handle 1303 is further arranged on the first surface of the plate unit. The handle 1303 can be multiple and is preferably arranged at both ends of the plate unit.

[0072] As described above, the cell satellite composed of the cell units can be assembled in orbit. Therefore, the satellite system has the function of on-orbit reconfiguration. After the satellite is launched, the integrated electronic unit can receive the ground task command, and then control the operation robot to replace the various cell units and / or loads in orbit. Based on the original satellite platform, the corresponding cell units can be replaced, increased, or deleted to expand the satellite task in orbit, so as to realize the on-orbit reconfiguration and expansion function of the satellite system. In addition, the cell satellite can be launched as a whole or launched separately and assembled in space.

[0073] Taking the cell satellite of the minimum unit as an example, the process of on-orbit assembly of the cell satellite is introduced. The cell satellite of the minimum unit includes an integrated electronic unit, a propulsion unit, an energy unit, an attitude control unit, a solar wing, and a patch antenna. The assembly includes the following steps:

[0074] First, the operation robot is used to grab the propulsion unit to the first side of the integrated electronic unit. After the node self-identification chip in the integrated electronic unit identifies the propulsion unit, an instruction is transmitted to the standard interface on the side of the integrated electronic unit close to the propulsion unit. At the same time, after the node self-identification chip in the propulsion unit identifies the integrated electronic unit, an instruction is transmitted to the standard interface on the side of the propulsion unit close to the integrated electronic unit.

[0075] Next, the two standard interfaces are mechanically connected. At this time, the electromagnetic unlocking module receives a direct current instruction to open the electromagnetic lock in the locked state, thereby connecting the integrated electronic unit and the propulsion unit.

[0076] Next, the energy unit is connected to the second side of the integrated electronic unit in a similar manner as described above. The second side is preferably the side opposite to the first side. After the connection is completed, the integrated electronic unit can control the energy unit, thereby realizing task allocation and energy allocation.

[0077] Next, two attitude control cells are connected to the third side and the fourth side of the integrated electronic unit respectively, and a patch antenna is connected to one side of the energy unit in a similar way as the aforementioned steps, wherein the attitude control cells are connected to the motors inside the attitude control cells relative to the standard interfaces connected to the side of the integrated electronic unit, so that the standard interfaces can rotate along the axis of the side shell; and

[0078] Finally, the solar wing is connected to the standard interface connected to the motor, so that it can adjust the angle in real time according to the satellite attitude and position, and store energy.

[0079] After the cell satellite is launched into orbit, the integrated electronic unit will assign tasks to each cell unit according to the initial task instructions, and the energy unit will assign energy to each cell unit. After each cell unit is powered on, it will start normal work after receiving the task. As mentioned above, in the embodiment of the present application, the energy and task allocation and data transmission process are completed through the standard interface on the surface of each cell unit. The standard interface is not only the key load-bearing structure between cell units, but also the general interface between cell units for transmitting power, information, machinery, heat conduction and data.

[0080] Although the embodiments of the present application are described above, it should be understood that they are presented only as examples, not as limitations. It is obvious to those skilled in the relevant art that various combinations, modifications and changes can be made without departing from the spirit and scope of the present application. Therefore, the width and scope of the present application disclosed herein should not be limited by the above disclosed exemplary embodiments, but should be defined only according to the appended claims and their equivalent replacements.

Claims

1. A satellite design method, characterized in that, Based on the required satellite functions, different functional cell units are selected from the satellite product library for assembly, wherein the cell units have a uniform morphology and include: case; At least one standard interface is provided on the surface of the housing, including: A power interface configured to provide power transmission includes a pin and a spring, wherein the pin is disposed on the surface of the housing and is retractable, the spring is electrically connected to the management module and is disposed corresponding to the pin, and the pin contacts the spring after retraction; A communication module, configured to enable data interaction and communication; and The magnetic module is configured to enable physical connections between different cell units; The management module, located inside the housing, includes: A node self-identification chip is communicatively connected to the power-on interface and configured to identify other cell units connected to the cell unit; A wireless module, configured to transmit backup data within each cell unit; A lithium battery module is electrically connected to the magnetic module and is configured to provide basic power to the cell unit; A power management module configured to manage the power usage of the cell unit and provide 5V internal power; and An electromagnetic unlocking module is communicatively connected to the magnetic module and is configured to manage the various standard interfaces of the cell unit. Different functional devices or modules are configured within the cell units, enabling any cell unit to independently perform one or more functions of the satellite platform. Different cell units are selected and assembled according to the mission and requirements to obtain different satellites; and A turntable, which is located inside the cell unit, has a standard interface configured to be connected to the turntable's shaft via a transmission mechanism and rotate with the turntable.

2. The satellite design method as described in claim 1, characterized in that, The communication module includes a data interface, and the data interface supports the LVDS protocol.

3. The satellite design method as described in claim 1, characterized in that, The magnetic module includes several alternating positive and negative magnetic poles.

4. The satellite design method as described in claim 3, characterized in that, The positive and negative magnetic poles form a ring, and the communication module and power interface are located inside the ring.

5. The satellite design method as described in claim 2, characterized in that, The data interface includes two ring-shaped data interfaces, and the data interface supports the LVDS protocol.

6. The satellite design method as described in claim 1, characterized in that, The cell unit is a cube, and the standard interface is located at the center of any surface of the cube.

7. The satellite design method as described in claim 1, characterized in that, The management module is in the form of a board, and the node self-identification chip, wireless module, lithium battery module, power management module, and electromagnetic unlocking module are integrated on the same board.

8. The satellite design method as described in claim 1, characterized in that, The turntable includes a one-dimensional motor.

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