Satellite communication system and method based on afdx bus architecture

Abstract

The application relates to a satellite communication system and method based on an AFDX bus architecture. The system comprises a plurality of satellite integrated electronic subsystems, each satellite integrated electronic subsystem comprising at least one terminal device configured to implement network connection, traffic shaping and virtual link management; and an AFDX switch network connected to the plurality of terminal devices using a star topology, configured to provide deterministic data transmission and redundant communication; wherein the AFDX switch network comprises a plurality of interconnected AFDX switches, each AFDX switch supporting a dual-redundant network structure and a virtual link configuration. The satellite communication system based on the AFDX bus architecture significantly improves the transmission rate, reliability and flexibility of the satellite communication system, and is suitable for satellite constellation networking and inter-satellite communication.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of space electronic communication technology, in particular to a satellite communication system and method based on AFDX bus architecture, which is suitable for low-orbit satellite, spacecraft integrated electronic system and satellite constellation networking communication. BACKGROUND

[0002] With the vigorous development of low-orbit satellite industry, the complexity of satellite equipment and the number of satellites are increasing, and the space satellite electronic systems and satellite network work together more and more, so the frequency and bandwidth demand of data exchange are increasing. The traditional space bus unidirectional transmission form such as RS422, MIL-1553B, CAN, etc. has been difficult to meet the system requirements because of too small bandwidth. Although IEEE802.3 Ethernet widely used in Internet has the characteristics of high speed and low cost, and has a wide range of commercial use. However, it cannot provide the robustness required by space electronic systems and networks, and cannot guarantee bandwidth, quality of service and security, so it cannot be used as a new generation of space bus that requires high real-time, high reliability, good security and large bandwidth.

[0003] AFDX (Avionics Full-Duplex Switched Ethernet, Avionics Full-Duplex Switched Ethernet) is a data bus protocol widely used in the field of aviation, which has the advantages of high reliability, real-time and bandwidth guarantee. However, AFDX is mainly used in avionics systems at present, and there is no mature application of satellite communication system. Especially for satellites, they are faced with harsh environments such as space radiation, extreme temperature, single particle effect, etc. Direct application of aviation AFDX system cannot meet the reliability requirements.

[0004] Therefore, there is an urgent need for a satellite communication bus architecture that can adapt to space environment, has high bandwidth, high reliability and low weight. SUMMARY

[0005] The task of the present application is to provide a satellite communication system and method based on AFDX bus architecture, which solves the problems of low bandwidth, high weight and high cost of space bus through the system and / or method, and greatly reduces the wiring complexity and system weight through star topology and virtual link technology.

[0006] In the first aspect of the present application, the above-mentioned task is solved by a satellite communication system based on AFDX bus architecture, which comprises:

[0007] a plurality of satellite integrated electronic subsystems, each satellite integrated electronic subsystem comprising at least one terminal device, the terminal device being configured to perform traffic shaping on on-board service data according to virtual link parameters; and

[0008] an AFDX switch network connecting the plurality of terminal devices using a star topology and configured to provide deterministic data transmission and redundant communication, wherein the AFDX switch network comprises a plurality of interconnected AFDX switches, each AFDX switch supporting a dual-redundant network structure and a virtual link configuration, wherein the AFDX switches are configured to receive traffic-shaped data and perform deterministic forwarding.

[0009] Further, the virtual link parameters comprise one or more of: a minimum packet gap, a maximum frame length, and a jitter value; and / or

[0010] The AFDX switches are connected by high-speed backplane buses or optical fibers to support network expansion and satellite constellation networking.

[0011] Further, the terminal devices are connected to the AFDX switches by twisted pairs or optical fibers.

[0012] Further, the satellite communication system based on the AFDX bus architecture further comprises:

[0013] a protocol adaptation layer configured to perform conversion between the AFDX protocol and a satellite space-ground communication protocol or an inter-satellite link protocol.

[0014] Further, the AFDX switches and terminal devices use a radiation-hardened design, which comprises selecting radiation-hardened components and / or adding a metal shielding layer.

[0015] Further, the redundant communication is configured to adjust a maximum reception time interval of redundant frames to adapt to long delays and single event effects in space environment.

[0016] Further, the AFDX switches comprise:

[0017] a filtering and policing module configured to filter data frames and limit bandwidth usage; and / or

[0018] a switching module configured to configure bandwidth and forward data frames according to the virtual link; and / or

[0019] an embedded terminal module configured to manage and control the AFDX switch body.

[0020] Further, the AFDX switches further comprise:

[0021] a monitoring module configured to monitor network status and count operation information; and / or

[0022] a configuration management module configured to load a network configuration table and support remote management.

[0023] Further, the star topology is a dual-redundant star topology, each terminal device is connected to a redundant switch in the AFDX switch network through two independent physical links.

[0024] In a second aspect of the application, the aforementioned task is also solved by an AFDX bus architecture based satellite communication method applied to the AFDX bus architecture based satellite communication system, comprising the following steps:

[0025] Performing traffic shaping on the on-board service data by the terminal device integrated in the satellite integrated electronic subsystem to obtain virtual link parameters;

[0026] Receiving the shaped data by using the AFDX switch network of the star topology and performing deterministic forwarding; and

[0027] During the communication process, anti-radiation reinforcement design and redundancy management suitable for space environment are performed, the anti-radiation reinforcement design includes selecting anti-radiation devices and / or adding a metal shielding layer, and the redundancy management includes adjusting the maximum receiving time interval of the redundant frame.

[0028] The technical solution provided by the application has the following advantages:

[0029] 1. The AFDX bus architecture currently only used in aviation systems (such as Airbus A380, Boeing 787 and A400M military transport aircraft, etc.) is applied to the field of space (such as satellite communication) in a novel way, and an AFDX bus architecture based satellite communication system is proposed, which realizes significant technical progress: the transmission rate is significantly improved, and the transmission rate can reach 100 Mbps or even higher, and the transmission rate is improved by about 50-100 times (hundred megabit network) or 250-600 times (gigabit network). The way is, according to the characteristics of on-board communication, the AFDX bus architecture is uniquely adapted to be suitable for on-board communication environment. For example, the adaptation includes: such as due to the special requirements of satellite communication environment (interference, transmission delay, signal attenuation, etc.), traffic shaping and deterministic forwarding according to virtual link parameters, and selecting anti-radiation devices and / or adding a metal shielding layer for core components such as communication terminal and AFDX switch, allowing inter-satellite communication protocol conversion, etc. The above adaptation is based on the following insights of the inventor:

[0030] In inter-satellite communication, traffic shaping is crucial because satellite links have long delay, high error rate and dynamic topology change, and the real-time performance and reliability of critical data (such as telemetry, command, etc.) must be guaranteed by shaping; while in aviation environment, the link is stable and the delay is low, and shaping is mainly used for priority scheduling, not fault tolerance.

[0031] Deterministic forwarding is particularly crucial in space, because satellite missions (such as imaging, control, etc.) have strict requirements on timing, while single-particle effects and signal attenuation in the space environment can cause transmission uncertainty, which needs to be guaranteed by hardware and protocol level; while in aviation, there are also deterministic requirements, but the environment is relatively mild.

[0032] Inter-satellite communication often uses space protocols such as CCSDS, and the compatibility of AFDX needs to be realized through a protocol adaptation layer to support integrated space-ground communication; while in aviation, standardized AFDX is generally used, and there is no need for frequent protocol conversion.

[0033] In addition, adaptation measures such as anti-radiation reinforcement, thermal management, and optimization of redundancy mechanisms are necessary in the space environment, while in aviation, they are only optional or simplified implementation.

[0034] 2. Since the AFDX bus architecture is adopted, the satellite communication system based on the AFDX bus architecture according to the present application can also realize the following advantages:

[0035] Through double-redundancy design and environmental adaptability optimization, the reliability of the system in the space environment is greatly improved;

[0036] Using COTS technology and open standards, the cost is greatly reduced and the flexibility of technology update is improved;

[0037] Through the star topology structure, the weight of the cable can be greatly reduced.

[0038] In summary, through the present application, the inter-satellite communication capability of the satellite is greatly improved. BRIEF DESCRIPTION OF DRAWINGS

[0039] To further illustrate the above and other advantages and features of the embodiments of the present application, more specific descriptions of the embodiments of the present application will be presented with reference to the accompanying drawings. It can be understood that these drawings only depict typical embodiments of the present application, and therefore should not be considered as limiting the scope thereof. In the drawings, for the sake of clarity and conciseness, the same or corresponding parts will be denoted by the same or similar reference numerals.

[0040] Figure 1 Fig. 1 shows a network architecture schematic diagram of a satellite communication system based on an AFDX bus architecture according to an embodiment of the present application;

[0041] Figure 2 Fig. 2 shows a module schematic diagram of an AFDX switch according to an embodiment of the present application; and

[0042] Figure 3 Fig. 3 shows a flowchart of a satellite communication method based on an AFDX bus architecture according to an embodiment of the present application. DETAILED DESCRIPTION

[0043] In the following description, reference is made to the accompanying drawings which form a part hereof, and which are shown by way of illustration of the embodiments of the present application. However, it is understood that embodiments of the present application can be practiced without many of the specific details that are set forth in the following description. In other instances, well-known structures and operational aspects of the systems have not been shown or described in order to avoid obscuring the subject matter of the present application. Similarly, for purposes of explanation, specific numbers and configurations are set forth in order to provide a thorough understanding of the embodiments of the present application. However, the present application can be practiced without the specific details (i.e., modifications, omissions, and the like) that are set forth in the following description. Furthermore, the terminology and phraseology used herein is solely used for descriptive purposes and should not be construed as limiting of the present application.

[0044] 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.

[0045] It should be noted that the embodiments of the present application are described in a specific order of method steps, however this is only for the purpose of illustrating the specific embodiment and does not limit the order of the steps. On the contrary, in different embodiments of the present application, the order of the steps can be adjusted according to the actual needs of the adjustment.

[0046] In the present application, each module of the system according to the present application can be implemented using software, hardware, firmware or a combination thereof. When a module is implemented using software, the function of the module can be implemented by a computer program flow, for example, the module can be implemented by a code segment (such as a code segment in C, C++, etc.) stored in a storage device (such as a hard disk, a memory, etc.), wherein when the code segment is executed by a processor, the corresponding function of the module can be implemented. When a module is implemented using hardware, the function of the module can be implemented by setting a corresponding hardware structure, for example, the function of the module can be implemented by hardware programming on a programmable device such as a field programmable logic gate array (FPGA), or the function of the module can be implemented by designing an application specific integrated circuit (ASIC) including a plurality of transistors, resistors and capacitors, etc. electronic devices. When a module is implemented using firmware, the function of the module can be written in the form of program code in the read-only memory such as EPROM or EEPROM of the device, and when the program code is executed by the processor, the corresponding function of the module can be implemented. In addition, some functions of the module can need to be implemented by a separate hardware or cooperated with the hardware, for example, the detection function is implemented by a corresponding sensor (such as a proximity sensor, an acceleration sensor, a gyroscope, etc.), the signal transmitting function is implemented by a corresponding communication device (such as a Bluetooth device, an infrared communication device, a baseband communication device, a Wi-Fi communication device, etc.), the output function is implemented by a corresponding output device (such as a display, a speaker, etc.), and so on.

[0047] The application solves the problems of low bandwidth, large weight and high cost of traditional aerospace buses such as MIL-STD-1553B and RS422 by applying AFDX bus technology to a satellite environment. In view of the requirements of space radiation, extreme temperature and long-period reliable transmission, the system adopts anti-radiation reinforcement design, thermal management optimization, protocol adaptation layer and redundant mechanism optimization for adapting to single particle effect, thereby significantly improving the transmission rate, reliability and flexibility of the satellite communication system, and being suitable for low-orbit satellite constellation networking and inter-satellite communication.

[0048] Figure 1 A network architecture diagram of a satellite communication system based on an AFDX bus architecture according to an embodiment of the application is shown. The satellite communication system based on the AFDX bus architecture will be described below in combination with Figure 1 The satellite communication system based on the AFDX bus architecture is described. The satellite communication system based on the AFDX bus architecture includes a plurality of satellite integrated electronic subsystems and an AFDX switch network. As shown in Figure 1 each satellite integrated electronic subsystem includes at least one terminal device, i.e., a terminal system, including Figure 1 the mechanism system 102, the thermal control system 103, the power supply system 104, the data management system 105, the TT&C communication system 106, the GNC system 107, the power system 108 and other satellite systems 109 in

[0049] The AFDX switch network uses a star topology to connect a plurality of terminal devices, and the AFDX switch network is used to provide deterministic data transmission and redundant communication. The AFDX switch network includes a plurality of interconnected AFDX switches, i.e., the switches 101 in Figure 1 each AFDX switch supports a dual-redundant network structure and a virtual link configuration. The AFDX switch is configured to receive traffic-shaped data and perform deterministic forwarding.

[0050] The satellite communication system of the embodiment includes 12 AFDX switches interconnected by high-speed backplane buses or optical fibers to form an extensible backbone switching network supporting constellation networking and inter-satellite link communication. Each AFDX switch is connected to a plurality of terminal devices (e.g., 24 terminal devices), each of which is integrated into a satellite integrated electronic subsystem, and the AFDX switch is responsible for accessing different satellite integrated subsystem devices to a data transmission network, which adopts a distributed system. In an embodiment of the application, the satellite integrated electronic subsystems can be an attitude and orbit control system, a payload data management system, a satellite service host, etc. Physically, each terminal device is connected to the AFDX switch through a pair of twisted pairs or optical fibers to achieve redundancy of the physical link. The terminal device is used to perform traffic shaping on the on-board service data according to virtual link parameters. In an embodiment of the application, the virtual link parameters include one or more of the following: minimum packet gap, maximum frame length, and jitter value. The terminal device is responsible for data acquisition, traffic shaping, and virtual link management. Data acquisition is based on hot backup redundancy of data packets to improve the reliability of the entire system. Each device of the satellite integrated subsystem needs to implant a terminal module that implements network connection to complete the traffic shaping function of the AFDX system data. The terminal device shapes the service flow into the parameters (such as minimum packet gap, maximum frame length, and jitter value) defined in each virtual link according to a predefined configuration table, and sends it to the switch after scheduling and superposition. The application programming interface exported by the terminal device enables each device to communicate through a simple message interface. Data streams are transmitted through virtual links (VL). A virtual link is a logical one-way communication channel, and its bandwidth and transmission characteristics are pre-configured and guaranteed.

[0051] The AFDX switch network fundamentally solves the problem of explosive growth of the number of cables (O(n) vs O(n²)) caused by point-to-point full connection in traditional avionics systems (especially systems requiring arbitrary interconnection) by adopting a physical star topology. In combination with the virtual link technology, a large number of logical communication channels are efficiently multiplexed on the physical link, further reducing the necessity of laying additional physical cables to meet different communication needs. The standardized Ethernet medium and optimized wiring path also contribute. These factors work together to significantly reduce the physical complexity of internal wiring (fewer cables, clearer paths) and effectively reduce the weight burden caused by a large number of long cables, which is crucial for aircrafts that are extremely sensitive to weight.

[0052] Star topology is a network structure in which all terminal devices are directly connected to a central node (i.e. AFDX switch) through independent, point-to-point links. The AFDX switch is the central node and communication hub of the entire network. Each terminal device is connected to a port of the switch using a dedicated physical link (twisted pair or optical fiber), usually two redundant links. There is no direct physical connection between terminal devices. Communication between any two terminal devices must be relayed through the central AFDX switch.

[0053] The AFDX switch network adopts a star network topology with an Ethernet switch as the core device to connect terminal devices of various subsystems. The AFDX switch network has the following characteristics: (1) full duplex: the physical connection medium is a twisted pair, and two independent data lines are used for transmission and reception respectively; (2) switched network: the network adopts a star topology with a central node as a switch; (3) configurable: supports communication configuration of switches and end systems; (4) deterministic transmission of virtual links: the network ensures the determinism of point-to-point data communication delay by establishing virtual links and allocating time slot bandwidth of 1ms-128ms; (5) redundancy: dual switches provide higher reliability for the system; (6) high transmission rate: the network supports two transmission rates of 10Mb / s and 100Mb / s; (7) physical layer complies with PART2 standard of ARINC664, compatible with traditional Ethernet; (8) supports mapping of high-level protocols such as ARINC429; (9) error analysis and statistical information, records statistics of network information; (10) supports IP, UDP and ICMP communication protocols; (11) meets the ARINC653 avionics communication software design standard, supports SAP software communication interface.

[0054] In an embodiment of the present application, the satellite communication system based on the AFDX bus architecture further comprises a protocol adaptation layer configured to perform conversion between the AFDX protocol and a satellite space-ground communication protocol or an inter-satellite link protocol. If only a single environment (such as pure LEO satellite) is involved, it is more efficient to directly use the CCSDS standard. If the project needs to be quickly deployed and is mainly for aviation (such as suborbital vehicles), it is a practical choice to modify the existing AFDX protocol stack (enhance radiation protection). If it is for deep space missions or new aerospace platforms, developing a hybrid architecture (such as AFDX+CCSDS hybrid protocol) is more sustainable.

[0055] In an embodiment of the present application, the AFDX switch and the terminal device use a radiation-hardened design, which includes selecting radiation-hardened devices and / or adding a metal shielding layer, such as adding a tantalum skin protection, etc.

[0056] In an embodiment of the present application, the redundant communication is configured to adjust the redundant frame maximum receiving time interval to adapt to the long delay and single particle effect in the space environment. The AFDX redundancy mechanism is optimized to adapt to the satellite single particle effect, which can be designed in a collaborative manner from three aspects of hardware reinforcement, protocol improvement, and system fault tolerance, and dynamically adjust the redundancy strategy in combination with the space environment characteristics. The ultimate goal of the design is to achieve sub-millisecond fault recovery and near-zero uncorrectable error rate to meet the high reliability requirements of space missions. In an embodiment of the present application, the power consumption and heat dissipation of the AFDX switch and terminal device need special design. High-heat devices can use high-thermal-conductivity materials (such as diamond copper), heat pipes, and other measures for heat dissipation treatment, thereby optimizing thermal management.

[0057] AFDX can become an efficient solution for satellite constellation networking through enhanced dynamic topology support, long-distance latency optimization, and space environment adaptation, and is particularly suitable for military or scientific missions with high requirements for determinism and reliability. In the future, it needs to be combined with software-defined network (SDN) and on-board AI scheduling to further optimize its space application performance.

[0058] In an embodiment of the present application, the star topology can be a double-redundant star topology, and each terminal device is connected to a redundant switch in the AFDX switch network through two independent physical links. It is worth noting that each AFDX switch is connected to at most 24 terminals, supports cascading expansion, has lower wiring cost than the bus type, and is more convenient to manage.

[0059] Figure 2 A module schematic diagram of the AFDX switch in an embodiment of the present application is shown. As shown in Figure 2 The filtering and control module, the switching module, the embedded terminal module, the monitoring module, and the configuration management module of the AFDX switch.

[0060] The filtering and control module is responsible for preliminary checking of the data frames entering the switch. The filtering and control module is configured to filter the data frames and discard abnormal frames (such as length abnormality, alignment error, destination MAC error, etc.), and only allow 64-1518 byte frames. The filtering and control module also limits bandwidth usage based on byte or frame rate to prevent network congestion.

[0061] The switching module is responsible for scheduling and forwarding data frames to the correct output port according to the destination address of the data frame and the virtual link configuration table. The switching module is configured to forward data frames according to the virtual link configuration bandwidth. The switching module supports full-duplex switching and handles the priority of the virtual link, uses physically separated transmit / receive channels, supports 128 transmit virtual links and 4096 receive virtual links, and accesses the electronic device through the PCI bus. The switching module pre-allocates bandwidth through the virtual link to guarantee the real-time performance of point-to-point communication and supports a rate of 100 Mbps.

[0062] The embedded end module is configured to manage and control the AFDX switch body. The core function of the terminal device (especially the communication protocol stack processing, traffic shaping, VL management, and redundancy processing) is directly integrated into the hardware or firmware of the AFDX switch, and the embedded end module itself is an end system for managing and controlling the switch body, which is a switch (responsible for connecting and forwarding network traffic) and a host (running an application or service requiring network communication) at the same time.

[0063] The monitoring module monitors the running state of the switch, the traffic statistics of each port, error information, and the like in real time, and sends the state information to an external network management terminal for system health management and fault diagnosis. The monitoring module is used for fault control, and a single point fault does not affect the whole, and a terminal fault only affects self communication; the monitoring module is used for timeout processing, and a frame that is not sent within a timeout period is discarded.

[0064] The configuration management module is configured to load a network configuration table and support remote management. The terminal parameter configuration table (including a VL list, bandwidth allocation, port mapping, and the like) is loaded at system startup to realize network initialization; the configuration management module supports network management functions, and the switch parameters can be configured remotely.

[0065] The processing flow of the data frame is as follows: the data frame is first subjected to filtering and regulation by the filtering and regulation module, the compliant data frame is sent to the switching module for forwarding, and finally the physical port is sent out. The monitoring module, the configuration management module, and the embedded end module interact with the whole process to perform data acquisition and management.

[0066] The application provides a satellite communication system based on an AFDX bus architecture, and provides a new bus communication system scheme for a satellite of China, in particular, a future geosynchronous satellite network system. At present, most of the launch vehicles and satellites of China adopt MILSTD-1553 buses or RS422 buses, but with the rapid development of the performance and functions of a spacecraft, the launch vehicles, satellites, and other spacecraft have higher requirements for the buses, in particular, in terms of data rate performance. The use of the AFDX technology can greatly improve the communication performance of the aerospace electronic integrated system, reduce wiring on the spacecraft, reduce weight, and the like. The AFDX has the characteristics of high speed, openness, high maturity of commercial components, and relatively low development cost. With the continuous improvement of the AFDX technology, the AFDX bus is expected to become the best choice for a high-performance spacecraft.

[0067] The satellite communication system based on the AFDX bus architecture provided by the application has a significantly improved transmission rate, and the transmission rate can reach 100 Mbps or even higher, and the transmission rate improvement ratio is about 50-100 times (hundred megabit network) or 250-600 times (gigabit network), depending on the anti-radiation design level and task requirements; through double redundancy design and environmental adaptability optimization, the reliability of the system in the space environment is greatly improved; by using COTS technology and open standards, the cost is greatly reduced and the technical update flexibility is improved; through the star topology structure, the weight of the cable can be greatly reduced.

[0068] In one embodiment of the application, the application also provides a satellite communication method based on the AFDX bus architecture, as shown in the accompanying drawings, the method comprises the following steps: Figure 3

[0069] Step 301: performing traffic shaping on the on-board service data through the terminal equipment integrated in the satellite integrated electronic subsystem to obtain virtual link parameters. In one embodiment of the application, the virtual link parameters can include bandwidth allocation interval, maximum frame length and jitter value.

[0070] Step 302: receiving the shaped data through the AFDX switch network using the star topology and performing deterministic forwarding.

[0071] Step 303: during the communication process, performing anti-radiation reinforcement design and redundancy management suitable for the space environment; the anti-radiation reinforcement design includes selecting anti-radiation devices and / or adding a metal shielding layer; the redundancy management includes adjusting the maximum receiving time interval of the redundant frame to adapt to the long delay and single particle effect in the space environment.

[0072] Although the embodiments of the application are described above, it should be understood that they are only presented as examples and 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 application. Therefore, the width and scope of the application disclosed herein should not be limited by the above disclosed exemplary embodiments, but should be defined according to the technical solutions of the application and their equivalent replacements.​

Claims

1. A satellite communication system based on AFDX bus architecture, characterized in that, Comprising: a plurality of satellite integrated electronic subsystems, each satellite integrated electronic subsystem comprising at least one terminal device configured to perform traffic shaping on on-board traffic data according to virtual link parameters; an AFDX switch network connecting the plurality of terminal devices using a star topology and configured to provide deterministic data transmission and redundant communication, wherein the AFDX switch network comprises a plurality of interconnected AFDX switches, each AFDX switch supporting a dual-redundant network structure and virtual link configuration, wherein the AFDX switches are configured to receive traffic shaped data and perform deterministic forwarding; and a protocol adaptation layer configured to perform conversion between AFDX protocol and satellite space-ground communication protocol or inter-satellite link protocol; wherein the AFDX switches and terminal devices use radiation-hardened design, which comprises selection of radiation-hardened components and / or addition of metal shielding layer; wherein the redundant communication is configured to adjust the maximum receive interval of redundant frames to accommodate long delays and single event effects in space environment; wherein the AFDX switches comprise: a filtering and policing module configured to filter data frames and limit bandwidth usage; and / or a switching module configured to configure bandwidth and forward data frames according to virtual link; and / or an embedded end module configured to manage and control the AFDX switch body.

2. The satellite communication system based on AFDX bus architecture according to claim 1, wherein: the virtual link parameters comprise one or more of the following: minimum packet gap, maximum frame length and jitter value; and / or the AFDX switches are connected through high-speed backplane bus or optical fiber to support network expansion and satellite constellation networking.

3. The satellite communication system based on AFDX bus architecture according to claim 1, characterized in that, the terminal devices are connected to the AFDX switches through twisted pair or optical fiber.

4. The satellite communication system based on AFDX bus architecture according to claim 1, characterized in that, the AFDX switches further comprise: a monitoring module configured to monitor network status and count operation information; and / or a configuration management module configured to load network configuration table and support remote management.

5. The satellite communication system based on AFDX bus architecture according to claim 1, characterized in that, the star topology is a dual-redundant star topology, each terminal device is connected to redundant switches in the AFDX switch network through two independent physical links.

6. A satellite communication method based on AFDX bus architecture, applied to the system of any one of claims 1-5, characterized in that, the method comprises the following steps: performing traffic shaping on on-board traffic data through terminal devices integrated in satellite integrated electronic subsystems to obtain virtual link parameters; receiving shaped data through AFDX switch network using star topology and performing deterministic forwarding; and performing radiation-hardened design and redundant management adapted to space environment during communication, the radiation-hardened design comprises selection of radiation-hardened components and / or addition of metal shielding layer, the redundant management comprises adjusting the maximum receive interval of redundant frames.

Images