Bus design method and system for stacked satellites

Abstract

The invention provides a bus design method for stacked satellites, which comprises the following steps of: setting a control bus: setting the control bus to complete control information transmission on the satellites; an information bus setting step: setting an information bus, collecting all service data to a network switch of the switching system through the information bus, and storing or distributing the service data by the network switch; setting a power bus: leading out the power bus at the output end of the power supply controller and forming a power supply loop; a reconstruction step: when the transmission data is abnormal, uploading a reconstruction file, and reconstructing all modules needing to be reconstructed by the on-satellite management system according to the reconstruction file; or the on-satellite management system or the ground reconstructs the module according to the reconstruction instruction; and a bus design step: integrating the control bus, the information bus, the power bus and the reconstruction module to form the bus. An integrated control, information and power bus architecture is used, so that the load ratio, the reliability and the economical efficiency of the system can be greatly improved.

Description

Technical Field

[0001] The present invention relates to the field of aerospace and communication technology, and in particular, to a bus design method and system for stacked satellites, and in particular, to a control, information, and power bus design architecture for stacked satellites. Background Art

[0002] With the ever-changing international situation and the continuous development of my country's aerospace technology, satellite constellation has become the norm. Small and medium-sized stacked satellites are obviously more competitive in the construction of satellite constellations, but the satellite design cycle is long, and the types of single machines on the satellite vary according to the satellite mission. The control bus, information bus and power bus are essential information interaction channels and energy distribution channels on the satellite, and are an indispensable part of the normal operation of the satellite. Traditional satellites need to customize the design of the control bus, information bus and power bus for the single machine on the satellite. The process is complicated, the cable load ratio is between 14% and 20%, and the task upgrade and single machine expansion need to be redesigned. Therefore, designing a reusable and universal control, information, and power bus architecture for small and medium-sized stacked satellites is of great significance to improving satellite design efficiency and reliability, shortening the satellite development and production cycle, and quickly building satellite constellations.

[0003] In the field of onboard information system bus and power bus design, according to the retrieved patents, researchers in this field have proposed a variety of methods for satellite information system design or power bus design.

[0004] The public document "Design of Multi-bus Fusion Interface of Satellite Integrated Electronic System" Spacecraft Engineering. 2020, 29(01) discloses the design of a new fusion bus universal interface based on satellite integrated electronics and is equipped with a verification platform. It uses buses of four protocols: I2C, SPI, 1553B, and CAN. The bus communication rate can reach up to 30MBit / s. This method aims to improve the compatibility of satellite integrated electronics and is suitable for satellites with a variety of replaceable modules. However, it is not suitable for connecting nodes and devices that need to occupy the communication interface for a long time without interruption, and has certain limitations.

[0005] The public document "Overall Design of Resource-1 02D Satellite Information System" Spacecraft Engineering. 2020, 29(06) discloses a method for constructing a distributed information network with two speed levels, which are used for satellite management and data transmission respectively. The low-speed information network adopts the 1553B bus protocol, and the high-speed bus adopts LVDS and TLK2711 buses. It is not conducive to platform intensive design, product design reuse and mass production equipment, and is not conducive to system integration under rapid iteration of payload technology and products. It has poor economy and generalization capabilities.

[0006] The patent document with publication number CN201320448032.9 discloses a payload data transmission bus terminal and proposes a design and verification method for a bus terminal IP core, which consists of a bus interface module, a clock division module, a protocol processing module, a data acquisition module, etc. It is mainly used for payload equipment TWTA telemetry and remote control data transmission. It does not take into account the requirements of different mission functions on the satellite, which is easy to cause waste of resources and does not meet the plug-and-play requirements of a single machine on the satellite.

[0007] The public document "Design of Micro-satellite Bus Control System Based on FPGA Technology" Computer Measurement and Control, 2010, 18(10) discloses the use of CAN bus as the satellite field real-time bus to complete satellite operation and control, and the use of USB2.0 bus as a high-speed information bus for large-capacity data exchange. Although it has high-speed and low-speed bus designs, the reliability and flexibility of CAN bus and USB2.0 are poor, and the transmission rate of USB2.0 is limited, which is no longer suitable for current satellite payload data transmission requirements.

[0008] Patent document with publication number CN201510465808.1 discloses an electrical bus suitable for micro-satellites, which adopts parallel connection and independent transmission mode of power bus and data bus, and power and data are transmitted on the same cable. Although it saves space and reduces the complexity of cable distribution, there is a great reliability risk in using the same cable for power bus and data bus. Once the cable fails, power supply and data transmission will have problems, which is not conducive to the safe and efficient operation of single machine on the satellite.

[0009] Therefore, a universal and reliable onboard control bus, information bus and power bus design architecture is needed. Summary of the invention

[0010] In view of the defects in the prior art, an object of the present invention is to provide a bus design method and system for stacked satellites.

[0011] A bus design method for stacked satellites, comprising:

[0012] Steps for setting up the control bus: according to the path and transmission protocol for transmitting the control information to each execution unit, set up the control bus to complete the control information transmission on the satellite;

[0013] Steps for setting up the information bus: according to the business data interaction, set up the information bus so that all business data are collected to the network switch of the switching system through the information bus, and then stored or distributed by the network switch;

[0014] Steps for setting the power bus: Lead out the power bus at the output end of the power controller and form a power supply loop, so that the satellite unit can obtain voltage from the power bus through the adapter terminal;

[0015] Reconstruction step: when the transmission data is abnormal, upload the reconstruction file, and the onboard management system reconstructs all modules that need to be reconstructed according to the reconstruction file; or reconstruct through instructions, and the onboard management system or the ground reconstructs the modules that need to be reconstructed according to the reconstruction instructions;

[0016] Bus design steps: Integrate the control bus, information bus, power bus and reconstruction module to form a bus.

[0017] Preferably, the reconstruction step includes:

[0018] Platform software reconstruction steps: Through high-speed uplink and downlink transmission, the satellite stores the received platform reconstruction file in the onboard small fixed memory of the onboard management system, and then sends the platform reconstruction file to the intelligent processing system for processing through the network switch, and then sends the reconstruction file to all single machines that need to be reconstructed;

[0019] Payload software reconstruction steps: Through high-speed uplink and downlink transmission, the satellite stores the received payload reconstruction file in the onboard small fixed memory of the onboard management system, and then sends the payload reconstruction file directly to all payload units that need to be reconstructed through the network switch; if the sending of the payload unit fails, it will be sent to the intelligent processing system by the network switch, and finally sent to the payload unit that needs to be reconstructed by the intelligent processing system;

[0020] On-board local file reconstruction steps: read local files according to the instructions issued by the ground or on-board management system. The on-board management system or the ground module that needs to be reconstructed reconstructs all modules that need to be reconstructed according to the preset requirements.

[0021] Preferably, the process of uploading the reconstruction file in the reconstruction step includes:

[0022] Sending steps: The ground sends file data frames to the satellite. If the satellite detects frame loss, it sends a file packet loss request to the ground;

[0023] Packet loss processing steps: After receiving the file packet loss application, the ground will put the packet loss frame back into the sending queue until the data frame is sent. The satellite will then start to detect the integrity of the received data. If it is complete, it will send a reception error-free frame to the ground. If it is incomplete, it will continue to send the file packet loss application.

[0024] Steps to form a reconstruction file: After the ground confirms that there are no error frames in the received verification, the confirmed file is uploaded as the reconstruction file.

[0025] Preferably, it also includes:

[0026] Self-test steps: The solution for automatic detection of bus access by onboard equipment includes two aspects: functional test and communication test;

[0027] Among them, the functional test uses ground software to analyze and test various parameter indicators after the single machine is connected to the power bus, control bus and information bus to confirm whether the function of the single machine connecting to the three types of buses is normal. If it is normal, the test passes; if it is not normal, troubleshooting is carried out;

[0028] The communication test runs preset test cases through the ground software. If the expected control bus data and expected information bus data are received, the communication test passes, otherwise troubleshooting is performed.

[0029] Preferably, including:

[0030] The onboard single machine draws power directly from the middle of the power bus through the bus cable, a preset number of transfer terminals and protectors on the bus, and can be controlled through digital instructions on the digital bus.

[0031] A bus design system for stacked satellites, comprising:

[0032] Control bus module: according to the path and transmission protocol of control information transmission to each execution unit, the control bus is set to complete the control information transmission on the satellite;

[0033] Information bus module: according to the business data interaction, the information bus is set up so that all business data are collected to the network switch of the switching system through the information bus, and then stored or distributed by the network switch;

[0034] Power bus module: Lead out the power bus at the output end of the power controller and form a power supply loop, so that the single machine on the satellite can obtain voltage from the power bus through the transfer terminal;

[0035] Reconstruction module: When the transmission data is abnormal, upload the reconstruction file, and the onboard management system will reconstruct all modules that need to be reconstructed according to the reconstruction file; or reconstruct through instructions, and the onboard management system or the ground will reconstruct the modules that need to be reconstructed according to the reconstruction instructions;

[0036] Bus design module: Integrate the control bus, information bus, power bus and reconstruction module to form a bus.

[0037] Preferably, the reconstruction module includes:

[0038] Platform software reconstruction module: Through high-speed uplink and downlink transmission, the satellite stores the received platform reconstruction file in the onboard small fixed memory of the onboard management system, and then sends the platform reconstruction file to the intelligent processing system for processing through the network switch, and then sends the reconstruction file to all single machines that need to be reconstructed;

[0039] Payload software reconstruction module: Through high-speed uplink and downlink transmission, the satellite stores the received payload reconstruction file in the onboard small fixed memory of the onboard management system, and then sends the payload reconstruction file directly to all payload units that need to be reconstructed through the network switch; if the sending of the payload unit fails, it will be sent to the intelligent processing system by the network switch, and finally sent to the payload unit that needs to be reconstructed by the intelligent processing system;

[0040] On-board local file reconstruction module: reads its own local files according to the instructions issued by the ground or on-board management system. The on-board management system or the ground module that needs to be reconstructed reconstructs all modules that need to be reconstructed according to the preset requirements.

[0041] Preferably, the process of uploading the reconstruction file in the reconstruction module includes:

[0042] Sending module: The ground sends file data frames to the satellite. If the satellite detects frame loss, it sends a file packet loss request to the ground.

[0043] Packet loss processing module: After receiving the file packet loss application, the ground will put the packet loss frame back into the sending queue until the data frame is sent. The satellite will then start to detect the integrity of the received data. If it is complete, it will send a reception error-free frame to the ground. If it is incomplete, it will continue to send the file packet loss application.

[0044] Forming a reconstruction file module: After the ground confirms that there are no error frames in the reception verification, the confirmed file is uploaded as the reconstructed file.

[0045] Preferably, it also includes:

[0046] Self-test module: The solution for automatic detection of bus access by onboard equipment includes functional testing and communication testing;

[0047] Among them, the functional test uses ground software to analyze and test various parameter indicators after the single machine is connected to the power bus, control bus and information bus to confirm whether the function of the single machine connecting to the three types of buses is normal. If it is normal, the test passes; if it is not normal, troubleshooting is carried out;

[0048] The communication test runs preset test cases through the ground software. If the expected control bus data and expected information bus data are received, the communication test passes, otherwise troubleshooting is performed.

[0049] Preferably, including:

[0050] The onboard single machine draws power directly from the middle of the power bus through the bus cable, a preset number of transfer terminals and protectors on the bus, and can be controlled through digital instructions on the digital bus.

[0051] Compared with the prior art, the present invention has the following beneficial effects:

[0052] 1. The present invention makes universal and integrated design for the control bus, information bus and power bus interfaces and protocols, which are used for high-reliability management and control on satellites and are compatible with various typical buses. Specifically, the power bus power supply of the present invention adopts a centralized star network topology, and the power distribution mode is to lead out the power bus at the output end of the power controller and form a power supply loop. The single machine directly draws power from the middle of the power bus through the bus cable and standardized bus connector. Since the single machine interface and protocol are standardized and unified, the single machine can realize plug-and-play power supply, which is suitable for the rapid design of different satellites and has good versatility.

[0053] 2. The present invention designs an on-board software reconstruction process based on the control bus and the information bus, thereby ensuring the software security and reliability of the on-board platform and payload;

[0054] 3. The present invention designs a ground rapid test process based on universal control bus, information bus and power bus, shortens the satellite design and manufacturing cycle, and is conducive to satellite mass production and economy;

[0055] 4. The present invention can automatically reconstruct all modules that need to be reconstructed at the same time by uploading reconstruction information once, completing information interaction, improving reconstruction efficiency, and improving system accuracy and coordination. BRIEF DESCRIPTION OF THE DRAWINGS

[0056] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0057] Figure 1 A flow chart of a bus design method for stacked satellites according to the present invention;

[0058] Figure 2 A topological diagram of a bus design system for stacked satellites according to the present invention;

[0059] Figure 3 It is composed of the information bus data link layer protocol;

[0060] Figure 4 This is the product structure diagram of 4 power supply buses;

[0061] Figure 5 This is the information flow diagram of the control and information bus of Example 2;

[0062] Figure 6 This is the single-machine plug-and-play process of the load in Example 3. DETAILED DESCRIPTION

[0063] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0064] The example of the present invention provides a control, information, and power bus design architecture for stacked satellites. This architecture uniformly adopts a star network, and the power bus, control bus, and information bus of the centralized topology structure are serially connected to each single machine on the satellite. The single machine is connected to the control, information, and power bus cables through standardized connectors to directly communicate and draw power. Among them, the control bus performs high-reliability management and control on the satellite, is used to transmit comprehensive control information on the satellite, uses the CCSDS transmission protocol, and is compatible with various typical buses; the information bus is used for large-capacity business data throughput on the satellite, uses the standard TCP / IP protocol stack, and designs network transmission protocol specifications and wired network interface specifications for each layer.

[0065] Example 1

[0066] To achieve the above object, the present invention adopts the following technical solutions:

[0067] The satellite adopts a constellation control and information bus architecture based on a unified protocol stack. The onboard control bus is used for high-reliability onboard management and control. It uses the CCSDS transmission protocol and is compatible with typical buses such as 1553B and CAN bus. The information bus adopts an integrated network design inside and outside the satellite, and uses the Ethernet standard UDP protocol for business data transmission. It complies with the specifications in RFC768, and its packet header includes four parts: source port (2Byte), destination port (2Byte), length (2Byte) and checksum (2Byte). The power bus adopts a centralized star network topology. The power distribution mode is to lead out the power bus at the output end of the power controller and form a power supply loop. The single machine directly draws power from the middle of the power bus through bus cables and standardized bus connectors. The specific CCSDS remote control and telemetry package format table is as follows:

[0068]

[0069] The control bus is compatible with typical buses such as 1553B and CAN bus, connects the onboard management system with each single machine, processes the satellite-to-ground and on-board integrated control commands and remote control and telemetry commands, uses the standard CCSDS remote control and telemetry package protocol, and defines the data link protocol and synchronization and channel coding specifications at the data link layer. The data link protocol includes the telemetry (TM) space data link protocol, the remote control (TC) space data link protocol, the advanced on-orbit system (AOS) space data link protocol, and the Proximity-1 (Prox-1) space link protocol. The channel coding specifications include TM synchronization and channel coding, TC synchronization and channel coding, and Prox-1 coding and synchronization protocol.

[0070] The TM and TC space data link protocols are the core of the control bus. The TM packet contains three parts: the start word, the packet header and the packet data field. The TC packet contains two parts: the packet header and the packet data field.

[0071] The network data transmission protocol of the information bus adopts the standard TCP / IP protocol stack and performs five layers of data processing on the transmitted data, namely the application layer, transport layer, network layer, data link layer, and physical layer:

[0072] Specifically, the application layer protocol adds an 18-byte fixed header to the application layer data based on the general UDP data frame format. It is required that each UDP data frame must contain this 18-byte fixed header, called the 1217 UDP header. Its composition is as follows:

[0073] Flag word 1 (1B): The platform is fixed to: "10100111" or 0x57; the payload is fixed to 0xA8;

[0074] Connection word (8B): an integer value filled in by the sender, used to uniquely identify a connection process;

[0075] Message number (4B): When the connection word is the same, the message number increases by 1 for each UDP data frame sent;

[0076] Flag word 2 (1B): 0x01 indicates instruction type, 0x02 indicates data type;

[0077] Effective length (2B): indicates the actual effective length of the message content;

[0078] Reserved words (2B): All characters are filled with 0.

[0079] After adding a fixed header of 18 bytes, the sum of the frame header and frame trailer of the UDP data frame of 1217 is 64 bytes. Considering the feasibility, all UDP data frames are required to be aligned with 8 bytes. In other words, the length of the UDP data frame of 1217 can only be 64+8×n bytes (where n≤181), that is, the length is between 64 and 1512, an integer multiple of 8 bytes. Among them, the length of the instruction and message UDP data frames is 64+8×n bytes (where n≤181); the payload data length in the data class UDP data frame is fixed at 1344 bytes; the fixed AOS length is fixed at 1024 bytes. The specific meaning of the UDP data packet fields is as follows:

[0080]

[0081] Specifically, the transport layer protocol uses the Ethernet standard UDP protocol for data transmission, and the UDP protocol complies with the specifications in RFC768.

[0082] The network layer IP protocol complies with RFC791 specification, and the IP data packet header includes a 20B header. Figure 3 The data link layer protocol uses the MAC frame format in IEEE Std 802.3TM-2005; the MAC frame header contains the destination address, source address, and data type:

[0083] Destination address (6 Byte): indicates the MAC address of the destination host, which is automatically obtained through the ARP protocol;

[0084] Source address (6 Byte): indicates the MAC address of the source host to ensure legitimacy and uniqueness;

[0085] Data type (2Byte): Indicates the protocol type of the data field. When using IP packets, the type is 0x0800; when using ARP packets, the type is 0x0806;

[0086] FCS (4 Byte): indicates frame check sequence. Ethernet uses CRC32 cyclic redundancy check.

[0087] The data link layer performs frame encoding and error correction control, and the protocol adopts the MAC frame format in IEEE Std 802.3TM-2005; the MAC frame header contains the destination address, source address, data type, etc.

[0088] The physical layer is the lowest level of information bus data transmission. It does not process the transmitted data, but provides the creation, maintenance and removal of the physical links required for the transmission of data, which are specifically manifested in signal and information bus cables.

[0089] The power bus adopts a centralized star network topology, which is led out from the power controller to form a power supply circuit. The power bus is planned to adopt a cable solution, which consists of a main transmission line, a transfer terminal, a load drainage line, a terminal connector, a terminal processor, and a terminal protector. The product structure diagram is as follows Figure 4 When working, the on-board power supply and distribution unit provides rated voltage to the positive and negative busbars of the bus, and the on-board power unit obtains voltage from the power bus through the transfer terminal.

[0090] Considering that satellite work generally includes high voltage and low voltage, two sets of wire loops are designed, corresponding to the high voltage power supply loop and the low voltage power supply loop respectively. In order to reduce the number of wires, the high voltage bus load drain line and the low voltage bus bus can be reused. High voltage electrical connectors and low voltage electrical connectors can be selected according to load requirements.

[0091] The on-board software reconstruction process based on the control bus and information bus is mainly divided into platform software reconstruction, payload software reconstruction, and on-board local file reconstruction.

[0092] Platform software reconstruction, upgrade the software components of the onboard management system, including boot, kernel image, various apps, configuration files, configuration parameters, etc. Upload operating system related files through high-speed uplink and downlink. This file upload method also supports storing the reconstruction program of other stand-alone machines in the form of file storage in the onboard small solid storage of the onboard management system, and then upgrading other stand-alone machines through the control bus.

[0093] Payload software reconstruction uses high-speed uplinks and downlinks. The onboard management system acts as a gateway to process data frames and forward them directly to the payload unit or intelligent processing module through the routing switching module. Each module completes data interaction with the ground in accordance with the requirements of the payload software protocol to achieve reliable upload of the reconstructed files.

[0094] On-board local file reconstruction: the on-board management system, intelligent processing unit, and platform or payload reconfigurable processing module read their own local files according to the instructions issued by the ground or on-board management system, and realize the reconstruction of the platform or payload software according to the protocol requirements.

[0095] The solution for automatic detection, control, information and power bus access of satellite equipment includes functional testing and communication testing. The functional test uses ground software to analyze and test the various parameter indicators after the single machine is connected to the power bus, control bus and information bus to confirm that the single machine access to the three types of buses is normal, including electrical parameters such as interface voltage and current, level parameters of the control bus and information bus, load parameters, data transmission and reception rate, controller status, etc. The communication test runs the default test case through the ground software. If the expected control bus data and expected information bus data are received, the communication test passes, otherwise troubleshooting is performed.

[0096] The satellite-to-ground reconstruction file transmission includes: the source end user (ground) sends the file attributes and other related information to the target end (satellite), the target end user verifies and starts the file receiving process; the source end user (ground) finds the file data frame once to the target user (satellite); if the satellite detects frame loss, it sends a file packet loss resend request to the ground;

[0097] After the ground receives the packet loss application, it puts the packet loss frame back into the sending queue; after the ground receives the file end frame, the satellite sends an end frame handshake signal to the ground and starts to detect the integrity of the received data; after the satellite verifies the data integrity and correctness, it sends a received error-free frame to the ground; the ground confirms the reception of the verified error-free frame and sends a handshake confirmation frame to the satellite; after the satellite receives the handshake confirmation frame, the file sending is completed.

[0098] The steps of platform software reconstruction are as follows: the satellite-to-ground reconstruction file is transmitted through high-speed uplinks and downlinks. After the integrated link unit receives the platform software reconstruction package, it stores it in the onboard small solid memory of the onboard management system in the form of a file through the information bus; the onboard management system sends the platform reconstruction file to the network switch of the routing and switching system through the information bus; the network switch sends it to the intelligent processing system through the information bus, and the intelligent processing system finally sends it to all required reconfigurable platform units.

[0099] Payload software reconstruction steps: The satellite-to-ground reconstruction file is transmitted through high-speed uplinks and downlinks. The specific transmission steps are the same as the platform software reconstruction steps. After the integrated link unit receives the platform software reconstruction package, it stores it in the onboard small solid memory of the onboard management system in the form of a file through the information bus. The onboard management system sends the payload reconstruction file to the network switch of the routing and switching system through the information bus. The network switch sends the payload reconstruction file directly to the payload unit that needs to be reconstructed through the information bus. If the sending of the payload unit fails, the network switch can send it to the intelligent processing system, and the intelligent processing system will eventually send it to the payload unit that needs to be reconstructed to complete the reconstruction.

[0100] On-board local file reconstruction steps: There is no need to upload the reconstruction file. The on-board management system, intelligent processing unit and platform or payload reconfigurable processing module read their own local files according to the instructions issued by the ground or on-board management system, and realize the reconstruction of the platform or payload software according to the protocol requirements. Specifically, the ground or on-board management system sends the platform stand-alone / payload reconstruction instruction; the on-board management system reads the local file, selects the corresponding reconstruction process according to the platform stand-alone / payload, and completes the reconstruction.

[0101] Example 2:

[0102] Combination Figure 5The reconstruction feature of onboard payload function software is as follows: the payload reconstruction software package is transmitted to the integrated link unit through high-speed uplink and downlink, the integrated link unit forwards it to the onboard management system through the control bus, the onboard management system processes the data frame and forwards it to the routing switching unit through the information bus, the routing switching unit distributes it, and it can be directly forwarded to the payload module or the intelligent processing module through the information bus. Each module completes data interaction in accordance with the requirements of the payload software protocol to realize the reliable upload of the reconstruction file.

[0103] Example 3:

[0104] Combination Figure 6 First, the load unit is connected to the power, control, and information buses according to the standard connector format; secondly, the load unit is powered on; then, the control and information buses are configured. The control bus parameter configuration mainly includes: configuring the RT chip environment: base address, interrupt, etc.; calculating and writing the sub-address to send and receive data first address; writing each address control word. The information bus parameter configuration mainly includes: configuring the load IP address, subnet mask, default gateway, DNS server address, etc. After the control bus and information bus parameter configuration is completed, the control bus access self-test and information bus ping test are performed to ensure normal communication. Finally, the load unit is shut down.

[0105] The present invention makes universal and integrated design for the control bus, information bus and power bus interfaces and protocols, which are used for high-reliability management and control on board satellites and are compatible with various typical buses. The traditional technology has various types of single-machine power supply interfaces, including different connector specifications, voltage requirements, node requirements, grounding requirements, etc. The power supply and distribution subsystem needs to be customized according to various constraints. There is a very high risk of error and it is not inherited. The power bus power supply of the present invention adopts the topology of a centralized star network. The power distribution mode is to lead out the power bus at the output end of the power controller and form a power supply loop. The single machine directly draws power from the middle of the power bus through bus cables and standardized bus connectors. Since the single machine interface and protocol are standardized and unified, plug-and-play power supply can be achieved for the single machine, which is suitable for the rapid design of different satellites and has good inheritance.

[0106] The present invention also provides a bus design method for stacked satellites, which can be implemented by executing the module of the bus design system for stacked satellites. That is, those skilled in the art can understand the bus design system for stacked satellites as a preferred implementation of the bus design method for stacked satellites.

[0107] Specifically, a bus design method for stacked satellites includes: a control bus setting step: setting the control bus according to the path and transmission protocol for transmitting control information to each execution unit to complete the control information transmission on the satellite; an information bus setting step: setting the information bus according to the business data interaction situation, so that all business data are collected to the network switch of the switching system through the information bus, and then stored or distributed by the network switch; a power bus setting step: leading out the power bus at the output end of the power controller and forming a power supply loop, so that the on-board unit obtains voltage from the power bus through the adapter terminal; a reconstruction step: when the transmission data is abnormal, uploading the reconstruction file, the on-board management system reconstructs all the modules that need to be reconstructed according to the reconstruction file; or reconstructing through instructions, the on-board management system or the ground reconstructs the modules that need to be reconstructed according to the reconstruction instructions; a bus design step: integrating the control bus, the information bus, the power bus and the reconstruction module to form a bus.

[0108] Specifically, the reconstruction steps include: platform software reconstruction step: through high-speed uplink and downlink transmission, the satellite stores the received platform reconstruction file in the onboard small solid memory of the onboard management system, and then sends the platform reconstruction file to the intelligent processing system for processing through the network switch, and then sends the reconstruction file to all single machines that need to be reconstructed; payload software reconstruction step: through high-speed uplink and downlink transmission, the satellite stores the received payload reconstruction file in the onboard small solid memory of the onboard management system, and then sends the payload reconstruction file directly to all payload units that need to be reconstructed through the network switch; if the sending of the payload unit fails, it is sent to the intelligent processing system by the network switch, and finally sent to the payload unit that needs to be reconstructed by the intelligent processing system; on-board local file reconstruction step: according to the instructions issued by the ground or on-board management system, the satellite reads its own local files, and the on-board management system or the ground modules that need to be reconstructed reconstruct all modules that need to be reconstructed according to preset requirements.

[0109] Specifically, the process of uploading the reconstructed file in the reconstruction step includes: a sending step: the ground sends a file data frame to the satellite. If the satellite detects a frame loss, it sends a file packet loss application to the ground; a packet loss processing step: after the ground receives the file packet loss application, it puts the packet loss frame back into the sending queue until the data frame is sent, and the satellite starts to detect the integrity of the received data; if it is complete, it sends a reception error-free frame to the ground; if it is incomplete, it continues to send a file packet loss application; a reconstruction file forming step: after the ground confirms the reception of the verification error-free frame, it uploads the confirmed file as the reconstructed file.

[0110] Specifically, it also includes: self-test steps: the solution for automatic detection of bus access by onboard equipment includes two aspects: functional testing and communication testing; among them, the functional test analyzes and tests the various parameter indicators after the single machine is connected to the power bus, control bus and information bus through ground software to confirm whether the function of the single machine accessing the three types of buses is normal. If normal, the test passes; if abnormal, troubleshooting is performed; the communication test runs preset test cases through the ground software. If the expected control bus data and expected information bus data are received, the communication test passes, otherwise troubleshooting is performed.

[0111] Specifically, it includes: the onboard single machine directly draws power from the middle of the power bus through a bus cable, a preset number of transfer terminals and protectors on the bus, and can be controlled through digital bus digital instructions.

[0112] Those skilled in the art know that, in addition to realizing the system and its various devices, modules, and units provided by the present invention in a purely computer-readable program code, it is entirely possible to realize the same functions in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers by logically programming the method steps. Therefore, the system and its various devices, modules, and units provided by the present invention can be considered as a hardware component, and the devices, modules, and units included therein for realizing various functions can also be regarded as structures within the hardware component; the devices, modules, and units for realizing various functions can also be regarded as both software modules for realizing the method and structures within the hardware component.

[0113] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A bus design method for stacked satellites, characterized in that: include: Steps for setting up the control bus: according to the path and transmission protocol for transmitting the control information to each execution unit, set up the control bus to complete the control information transmission on the satellite; Steps for setting up the information bus: according to the business data interaction, set up the information bus so that all business data are collected to the network switch of the switching system through the information bus, and then stored or distributed by the network switch; Steps for setting the power bus: Lead out the power bus at the output end of the power controller and form a power supply loop, so that the satellite unit can obtain voltage from the power bus through the adapter terminal; Reconstruction step: when the transmission data is abnormal, upload the reconstruction file, and the onboard management system reconstructs all modules that need to be reconstructed according to the reconstruction file; or reconstruct through instructions, and the onboard management system or the ground reconstructs the modules that need to be reconstructed according to the reconstruction instructions; Bus design steps: Integrate the control bus, information bus, power bus and reconstruction module to form a bus.

2. The bus design method for stacked satellites according to claim 1, characterized in that: The reconstruction steps include: Platform software reconstruction steps: Through high-speed uplink and downlink transmission, the satellite stores the received platform reconstruction file in the onboard small fixed memory of the onboard management system, and then sends the platform reconstruction file to the intelligent processing system for processing through the network switch, and then sends the reconstruction file to all single machines that need to be reconstructed; Payload software reconstruction steps: Through high-speed uplink and downlink transmission, the satellite stores the received payload reconstruction file in the onboard small fixed memory of the onboard management system, and then sends the payload reconstruction file directly to all payload units that need to be reconstructed through the network switch; if the sending of the payload unit fails, it will be sent to the intelligent processing system by the network switch, and finally sent to the payload unit that needs to be reconstructed by the intelligent processing system; On-board local file reconstruction steps: read local files according to the instructions issued by the ground or on-board management system. The on-board management system or the ground module that needs to be reconstructed reconstructs all modules that need to be reconstructed according to the preset requirements.

3. The bus design method for stacked satellites according to claim 1, characterized in that: The process of uploading the reconstruction file in the reconstruction step includes: Sending steps: The ground sends file data frames to the satellite. If the satellite detects frame loss, it sends a file packet loss request to the ground; Packet loss processing steps: After receiving the file packet loss application, the ground will put the packet loss frame back into the sending queue until the data frame is sent. The satellite will then start to detect the integrity of the received data. If it is complete, it will send a reception error-free frame to the ground. If it is incomplete, it will continue to send the file packet loss application. Steps to form a reconstruction file: After the ground confirms that there are no error frames in the received verification, the confirmed file is uploaded as the reconstruction file.

4. The bus design method for stacked satellites according to claim 1, characterized in that: Also includes: Self-test steps: The solution for automatic detection of bus access by onboard equipment includes two aspects: functional test and communication test; Among them, the functional test uses ground software to analyze and test various parameter indicators after the single machine is connected to the power bus, control bus and information bus to confirm whether the function of the single machine connecting to the three types of buses is normal. If it is normal, the test passes; if it is not normal, troubleshooting is carried out; The communication test runs preset test cases through the ground software. If the expected control bus data and expected information bus data are received, the communication test passes, otherwise troubleshooting is performed.

5. The bus design method for stacked satellites according to claim 1, characterized in that: include: The onboard single machine draws power directly from the middle of the power bus through the bus cable, a preset number of transfer terminals and protectors on the bus, and can be controlled through digital instructions on the digital bus.

6. A bus design system for stacked satellites, characterized in that: include: Control bus module: according to the path and transmission protocol of control information transmission to each execution unit, the control bus is set to complete the control information transmission on the satellite; Information bus module: according to the business data interaction, the information bus is set up so that all business data are collected to the network switch of the switching system through the information bus, and then stored or distributed by the network switch; Power bus module: Lead out the power bus at the output end of the power controller and form a power supply loop, so that the single machine on the satellite can obtain voltage from the power bus through the transfer terminal; Reconstruction module: When the transmission data is abnormal, upload the reconstruction file, and the onboard management system will reconstruct all modules that need to be reconstructed according to the reconstruction file; or reconstruct through instructions, and the onboard management system or the ground will reconstruct the modules that need to be reconstructed according to the reconstruction instructions; Bus design module: Integrate the control bus, information bus, power bus and reconstruction module to form a bus.

7. The bus design system for stacked satellites according to claim 6, characterized in that: The reconstruction module includes: Platform software reconstruction module: Through high-speed uplink and downlink transmission, the satellite stores the received platform reconstruction file in the onboard small fixed memory of the onboard management system, and then sends the platform reconstruction file to the intelligent processing system for processing through the network switch, and then sends the reconstruction file to all single machines that need to be reconstructed; Payload software reconstruction module: Through high-speed uplink and downlink transmission, the satellite stores the received payload reconstruction file in the onboard small fixed memory of the onboard management system, and then sends the payload reconstruction file directly to all payload units that need to be reconstructed through the network switch; if the sending of the payload unit fails, it will be sent to the intelligent processing system by the network switch, and finally sent to the payload unit that needs to be reconstructed by the intelligent processing system; On-board local file reconstruction module: reads its own local files according to the instructions issued by the ground or on-board management system. The on-board management system or the ground module that needs to be reconstructed reconstructs all modules that need to be reconstructed according to the preset requirements.

8. The bus design system for stacked satellites according to claim 6, characterized in that: The process of uploading the reconstruction file in the reconstruction module includes: Sending module: The ground sends file data frames to the satellite. If the satellite detects frame loss, it sends a file packet loss request to the ground. Packet loss processing module: After receiving the file packet loss application, the ground will put the packet loss frame back into the sending queue until the data frame is sent. The satellite will then start to detect the integrity of the received data. If it is complete, it will send a reception error-free frame to the ground. If it is incomplete, it will continue to send the file packet loss application. Forming a reconstruction file module: After the ground confirms that there are no error frames in the reception verification, the confirmed file is uploaded as the reconstructed file.

9. The bus design system for stacked satellites according to claim 6, characterized in that: Also includes: Self-test module: The solution for automatic detection of bus access by onboard equipment includes functional testing and communication testing; Among them, the functional test uses ground software to analyze and test various parameter indicators after the single machine is connected to the power bus, control bus and information bus to confirm whether the function of the single machine connecting to the three types of buses is normal. If it is normal, the test passes; if it is not normal, troubleshooting is carried out; The communication test runs preset test cases through the ground software. If the expected control bus data and expected information bus data are received, the communication test passes, otherwise troubleshooting is performed.

10. The bus design system for stacked satellites according to claim 6, characterized in that: include: The onboard single machine draws power directly from the middle of the power bus through the bus cable, a preset number of transfer terminals and protectors on the bus, and can be controlled through digital instructions on the digital bus.

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