Satellite load measurement and control communication circuit

Abstract

The invention provides a measurement and control communication circuit suitable for a satellite load and a satellite platform, the circuit forms CAN bus communication through SPI protocol transmission, and the circuit comprises a processor module, two bus control modules, two data transceiver modules, two protection modules and a bus interface module. The processor module is respectively connected with the two bus control modules, the two bus control modules are respectively connected with the two data receiving and transmitting modules, the two data receiving and transmitting modules are respectively connected with the two protection modules, and the two protection modules are respectively connected with the bus interface module. The two measurement and control communication circuits are in hot backup. According to the measurement and control communication circuit provided by the invention, the reliable performance is ensured in a severe space environment, meanwhile, fewer components are used, the circuit layout area is smaller, the development efficiency is higher, and the requirement of rapid development of commercial spaceflight is met.

Description

Technical Field

[0001] The invention belongs to the field of satellite payload electronic technology, and in particular relates to a satellite payload measurement, control and communication circuit. Background Art

[0002] Currently in the space satellite payload system, the satellite payload measurement and control communication circuit refers to the electronic circuit system that is responsible for implementing the measurement and control communication tasks of the satellite payload. It exchanges data with the satellite platform integrated electronics through specific communication protocols and interfaces. The design and application of satellite payload measurement and control communication circuits is an important part of modern aerospace technology. Its main functions include data transmission, command reception and execution, status monitoring, etc. These are key technologies to ensure that the satellite payload can operate normally and ensure that the satellite completes its established tasks. The specific functions are as follows:

[0003] Data communication function: This is the basic responsibility of the measurement and control communication circuit, including transmitting telemetry data from the payload to the satellite platform, and receiving remote control commands and data sent by the satellite platform. These data and commands are crucial for monitoring and managing the operating status of the satellite payload.

[0004] Command response function: The performance of a satellite in orbit depends largely on its control and operation of the payload. The telemetry and control communication circuits need to reliably receive and process commands from the platform to ensure that each command can be accurately executed to adjust the operation of the payload.

[0005] Status monitoring function: This function involves monitoring the working conditions of each satellite payload subsystem, including power supply, attitude control, propulsion system, imaging system, etc. Through real-time monitoring, possible problems can be discovered and solved in time to ensure the safe and stable operation of the satellite platform and related payloads.

[0006] SPI protocol, which refers to Serial Perripheral Interface protocol, is a high-speed, full-duplex, synchronous communication bus protocol that works in master-slave mode. It only occupies four wires on the chip's transmission pins, saving the chip's pins and saving space on the PCB layout. It is precisely because of this simple and easy-to-use feature that more and more chips are now integrating this communication protocol. CAN communication, which refers to Controller Area Network communication, is an ISO internationally standardized serial communication protocol network that was first born in the automotive industry. With the increasing maturity of technology, CAN's high performance and reliability have been recognized and widely used in industrial automation, ships, medical equipment, etc. The CAN bus consists of CAN_H and CAN_L twisted pairs. It transmits signals through differential voltage, improves anti-interference ability, and ensures data transmission reliability. CAN communication is a multi-node communication protocol with low data transmission delay between terminals. Under the current standard, the maximum data transmission rate of variable-rate CAN reaches 8Mbps. With the development of commercial aerospace, lightweight, highly reliable satellite payload measurement and control communication systems based on CAN bus interface and high-speed protocol design will be more and more used in satellite payload design.

[0007] The existing satellite payload measurement and control communication circuits basically use the traditional MIL-STD-1553B standard serial data bus interface to achieve communication with the satellite integrated electronic unit. Its main functions include: communicating with the satellite integrated electronic unit through the bus, receiving data injection, bus internal instructions, broadcast information, system synchronization and other communication data. Based on the consideration of inheritance and stability in the traditional aerospace field, subsequent models basically follow this method. However, facing the needs of the rapid development of the current aerospace industry, the circuits of the traditional MIL-STD-1553B protocol interface have become increasingly difficult to meet the needs, and have the following disadvantages: Since MIL-STD-1553B is a relatively old standard, it will encounter difficulties when upgrading modern systems and being compatible with new technologies, and there are compatibility issues; the implementation of this interface requires dedicated hardware and software support, including dedicated isolation transformers, coupling transformers, transceivers and protocol processors, which not only have many components and occupy a large space, but also are more difficult and time-consuming during system integration, debugging and testing, increasing the complexity of system development and maintenance; the maximum data transmission rate of MIL-STD-1553B is only 1Mbps, which seems to be insufficient bandwidth under the needs of modern high-speed communication and is difficult to meet the needs of large data transmission; the process of remote terminal (RT) message transmission on the MIL-STD-1553B bus needs to be transferred through the bus controller (BC). This master-slave architecture limits direct point-to-point communication and increases communication delays.

[0008] The general CAN communication circuit is very sensitive to electromagnetic interference EMI and noise, especially in harsh environments. If the bus is not well shielded and grounded, noise may cause data transmission errors. In this environment, the signal attenuation and noise problems of the CAN bus are more obvious when transmitting data at a high rate over long distances. In the space environment, satellites and their payloads are subject to extreme temperature fluctuations, radiation, various electromagnetic waves, solar wind, plasma and other environmental factors, which affect the reliability of the CAN bus system. Therefore, how to ensure the stable operation of the system in such an environment is a major challenge. Any communication failure in satellite applications may have a serious impact on the entire mission. Therefore, it is very important to design a system that can detect and recover from faults in a timely manner. Although the CAN bus has a fault detection mechanism, fault recovery under such extreme conditions is still a challenge. In the complex space electronic environment, high-frequency noise and transient voltages can cause unstable power supply voltage, causing latch-up, and seriously causing the risk of circuit burnout; space particle radiation can affect the integrity of the CAN bus signal. How to reduce the risk of latch-up and minimize electromagnetic interference to avoid signal attenuation and incompleteness requires careful design of electrical interfaces and appropriate measures to solve these problems.

[0009] Therefore, in modern aerospace systems, as payloads and satellites are developing towards lightweight and miniaturization, how to solve the signal latching and interference problems caused by the harsh environment of satellite payload measurement and control communication systems under limited resources, and provide a measurement and control circuit for CAN bus communication that can operate stably in the space environment are technical problems that need to be urgently solved by technical personnel in this field. Summary of the invention

[0010] The purpose of the present invention is to provide a satellite payload measurement and control communication circuit in view of the problems in the prior art.

[0011] To this end, the above-mentioned purpose of the present invention is achieved through the following technical solutions:

[0012] A measurement and control communication circuit suitable for use between a satellite payload and a satellite platform, characterized in that: the measurement and control communication circuit comprises a processor module, a first bus control module, a first data transceiver module, a first protection module, a second bus control module, a second data transceiver module, a second protection module and a bus interface module; the processor module is connected to the first bus control module and the second bus control module, the first bus control module is connected to the first data transceiver module, the second bus control module is connected to the second data transceiver module, the first data transceiver module is connected to the first protection module, the second data transceiver module is connected to the second protection module The first protection module and the second protection module are connected to the CAN bus interface of the satellite platform through the bus interface module; the first and second measurement and control communication circuits are hot-backed up; the first and second are two CAN communication circuits that can exchange data through the SPI protocol, one is in the main state and the other is in the standby state. The circuit states of the two are the same, and the two states are hot-backed up. Data is exchanged in real time through the SPI protocol, and the states of the two CAN communication circuits are kept synchronized in real time. The SPI protocol is used to perform data transmission with the processor module to realize the satellite payload CAN bus measurement and control communication circuit, and the measurement and control communication between the payload and the satellite platform is managed through the processor module.

[0013] While adopting the above technical solutions, the present invention may also adopt or combine the following technical solutions:

[0014] As a preferred technical solution of the present invention: the measurement and control circuit processor module is selected from a single-chip microcomputer, FPGA or DSP.

[0015] As the preferred technical solution of the present invention: the first bus control module and the second bus control module include four standard interface leads and an interrupt pin, namely, a chip select CS, a clock SCLK, a master input slave output MISO, and a master output slave input MOSI. They are connected to the processor module through a standard serial peripheral interface SPI to realize data sending, data receiving, error handling, speed control, frame filtering, and interrupt control.

[0016] As a preferred technical solution of the present invention: the first data transceiver module, the first protection module and the second data transceiver module, the second protection module are interfaces between the bus control module and the physical bus, realizing signal conversion and data transmission functions.

[0017] As a preferred technical solution of the present invention: in signal conversion, the first data transceiver module and the second data transceiver module convert the digital signal output by the CAN bus control module into a bus differential level signal when sending data, and convert the differential level signal received on the bus into a digital signal when receiving data, and pass it to the two protection modules.

[0018] As a preferred technical solution of the present invention: during signal transmission, the first protection module and the second protection module

[0019] Transmit data to the bus control module for processing. During signal transmission, it supports high-speed and low-speed transmission of the bus to maintain efficient and stable communication. It suppresses electromagnetic interference to reduce noise on the bus and achieve stable data communication.

[0020] Compared with the prior art, a satellite payload measurement and control communication circuit of the present invention has the following beneficial effects: the present invention sets up two independent CAN controllers, each of which has an SPI protocol transmission function. The circuit states of the two bus control modules are the same and are synchronized in real time to ensure that when one of the two fails, the other can immediately take over, thereby ensuring the continuity and reliability of data transmission. The dual-channel hot backup cooperates with the fast switching mechanism to effectively avoid system interruptions caused by single point failures and improve the stability and reliability of the system in harsh environments.

[0021] The present invention combines the high bandwidth and low latency characteristics of the SPI protocol with the high reliability and long-distance communication capability of the CAN bus technology. By using the widely supported SPI protocol and CAN bus, the circuit of the present invention is compatible with more electronic components, which is beneficial to maintenance and upgrading, and also reduces the complexity of development and integration. The present invention fully utilizes the mature characteristics of the SPI protocol and CAN bus technical solutions, and can provide a wide selection of electronic components with better versatility and compatibility. The structure is simple, and the total circuit design components are fewer, making the space layout smaller. The development efficiency is high, and the circuit system test is convenient and fast. The CAN bus measurement and control communication circuit formed by SPI protocol transmission has the characteristics of high bandwidth and low latency, which is more in line with the development trend of high-throughput data transmission in the future.

[0022] The present invention provides additional electrical isolation for sensitive electronic components through the cooperation of the protection module and the bus interface module, reduces the impact of electromagnetic interference on the signal, and protects the signal integrity: signal integrity protection measures are added to the circuit design, including impedance matching, signal filtering, etc., to ensure the stability and integrity of the signal during transmission.

[0023] The present invention effectively solves the signal latching and interference problems caused by the harsh environment of the satellite payload measurement and control communication system under limited resources through comprehensive measures such as dual-channel hot backup, application of mature technology, simplified circuit design, anti-interference design and special design adapted to harsh environment, and provides a measurement and control circuit for CAN bus communication that can operate stably in the space environment, which not only improves the performance and reliability of the system, but also provides strong technical support for the development trend of high-throughput data transmission in the future. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1It is a schematic diagram of a circuit module of an embodiment of a satellite payload measurement and control communication circuit of the present invention;

[0025] Figure 2 It is a CAN measurement and control communication principle diagram of a satellite payload measurement and control communication circuit of the present invention;

[0026] Figure 3 It is a data transmission waveform diagram of an embodiment of the present invention. DETAILED DESCRIPTION

[0027] The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.

[0028] A satellite payload measurement and control communication circuit of the present invention discloses a measurement and control circuit suitable for CAN bus communication between a satellite payload and a satellite platform through SPI protocol transmission. Compared with traditional satellite payload measurement and control circuits, the circuit is not easily affected and disturbed by the harsh space environment, can operate stably, uses fewer components and has a smaller circuit layout area, so as to meet the needs of the rapid development of commercial aerospace.

[0029] The above technical purpose of the present invention is achieved through the following technical solutions: a measurement and control circuit suitable for CAN communication between satellite payload and satellite platform, further, CAN bus data is transmitted through SPI protocol. The circuit of the present invention includes a processor module, a 2-way CAN bus control module with SPI interface, a 2-way CAN bus data transceiver module, a 2-way protection module and a CAN bus interface module.

[0030] The processor module of the present invention is an FPGA, and the first bus control module and the second bus control module are connected to the processor module via a standard 4-wire SPI interface.

[0031] The SPI interface protocol can realize full-duplex transmission of data, with simple communication and fast data transmission rate, and can support data transmission of up to 10Mbps. The CAN bus control module uses high-speed mode for data transmission, in which the baud rate ranges from a maximum of 8Mbps. The transmission rate of the SPI protocol is higher than the maximum transmission rate of the CAN bus, so as a data exchange interface with the processor, it fully meets the requirements of CAN bus high-speed mode data transmission.

[0032] The first bus control module and the second bus control module are independent CAN controllers. They both have SPI protocol transmission function and are connected to the processor module through the standard serial peripheral interface SPI, making full use of the high-speed, full-duplex, synchronous communication characteristics of the SPI interface to ensure the efficiency and stability of data transmission.

[0033] The first CAN bus control module and the second CAN bus control module use a 16MHz active crystal oscillator as an external frequency input, and a 22Ω resistor is connected in series to the output end of the crystal oscillator. The matching capacitor is selected as a 22pF polar capacitor according to the calculation result of the formula.

[0034] The formula for the crystal matching capacitance is:

[0035] CL=CS+(CD*CG) / (CD+CG)

[0036] Among them, CL (load capacitance) is the load capacitance, CS (shunt capacitance) is the parasitic capacitance between transistor pins, CD is the total capacitance from the output pin of the crystal oscillator circuit to the ground, and CG is the total capacitance from the input pin of the crystal oscillator circuit to the ground. The parasitic capacitance CS is generally 0.5pF to 1pF, and CD and CG are generally 10 to 50pF, including the PCB trace capacitance and the parasitic capacitance of the transistor pin.

[0037] The data exchange pins TXCAN and RXCAN of the first bus control module and the second bus control module are respectively connected to the corresponding pins CANTx and CANRx of the first data transceiver module and the second data transceiver module.

[0038] The two-way data transceiver module converts the CAN bus logic level into a differential level for transmitting data on two bus cables with differential voltages.

[0039] The buses of the first data transceiver module and the second data transceiver module are connected to the bus interface module through the first protection circuit and the second protection circuit respectively. This output port protection circuit can effectively improve the anti-interference ability of the system, reduce system EMI, enhance system ESD protection and surge protection, and meet the radiation standard. Finally, the bus interface module (CAN Bus Port) is connected to the bus interface at the platform to achieve the purpose of measurement and control communication between the satellite payload and the satellite platform.

[0040] The first CAN measurement and control communication circuit and the second CAN measurement and control communication circuit constitute a measurement and control communication hot backup circuit of the satellite payload subsystem, which enhances the convenience of design and improves the reliability of telemetry and remote control functions.

[0041] The processor module FPGA is programmed to configure the peripheral SPI unit through a dedicated 32-bit RISC processor soft core MicroBlaze, and after internal layout and wiring, it is connected to other logic units and IO pins on the FPGA, and is integrated into a configuration data stream. Its configuration CAN baud rate is 500Kbps, and the master and standby are consistent. The software functions include an initialization module, a state machine module, a read data cache module, and a write data cache module. The workflow is that after the processor module is powered on and started, the configuration data stream is loaded, and the initialization module in the software is entered. After the initialization is successful, according to the judgment condition of the state machine module, the read data cache module or the write data cache module is scheduled to enter, thereby realizing the function of SPI protocol transmission to constitute CAN bus communication.

[0042] In summary, the present invention has the following beneficial effects: using the SPI protocol and the processor module for data transmission, realizing the satellite payload CAN bus measurement and control communication circuit, through the above-mentioned processor module software, it can meet the measurement and control communication requirements between the payload and the satellite platform, and can receive the broadcast time code, satellite parameters, internal instructions, injection data, orbit calculation parameters and other instructions issued by the platform and send its own telemetry data. The present invention makes circuit design and program development simple and fast, data transmission is stable and reliable, not easily affected and disturbed by the harsh space environment, uses fewer components, has a smaller circuit layout area, and has a simple structure, which is suitable for wide application in the design of commercial space satellite payload electronics.

[0043] Example 1

[0044] like Figure 1-Figure 3 As shown, the present invention is a CAN bus communication measurement and control circuit suitable for transmission between a satellite payload and a satellite platform through the SPI protocol. Figure 1 As shown, it includes a processor module, a first bus control module, a second bus control module, a first data transceiver module, a second data transceiver module, a first protection module, a second protection module and a bus interface module connected to the platform.

[0045] For details, see Figure 2As shown, FPGA is selected as the core processor module U1, model XC7K325T-FFG900I, and 12 pins are bound as the SPI interfaces of the first and second CAN bus control modules respectively. When operating the bidirectional port, the IO state is set to high impedance Z as input. The first SPI interface is: CAN_A_SPI_CS#, CAN_A_SPI_MISO, CAN_A_SPI_MOSI, CAN_A_SPI_SCK, CAN_A_INT#, and the second SPI interface is: CAN_B_SPI_CS#, CAN_B_SPI_MISO, CAN_B_SPI_MOSI, CAN_B_SPI_SCK, CAN_B_INT#. The pins are connected to the SPI standard interfaces corresponding to the first bus control module U2 and the second bus control module U4 respectively, where the interrupt pins CAN_A_INT# and CAN_B_INT# are effective at low level, and are pulled up to high level state by R2 and R9 respectively in normal working state, and the resistance value is 10KΩ.

[0046] Specifically, the model of the first CAN bus control module U2 is MCP2517FD, and its reference operating frequency is supplied by an external 16MHz active crystal oscillator XTAL_A. The model of the second CAN bus control module U4 is MCP2517FD, and its reference operating frequency is supplied by an external 16MHz active crystal oscillator XTAL_B. The active crystal oscillator is more stable than the passive crystal oscillator. A 22Ω resistor is connected in series to the output end of the crystal oscillator. The series resistor is used to reduce the reflected wave and avoid harmonic interference caused by overshoot caused by the superposition of reflected waves, thereby ensuring the integrity of the signal.

[0047] Specifically, the matching capacitors C4, C5, C9, and C10 of the active crystal oscillators of the first and second bus control modules are 22pF, and their main function is to match the crystal oscillator and the oscillation circuit so that the circuit can be easily started and in a reasonable excitation state.

[0048] The formula for the crystal matching capacitance is:

[0049] CL=CS+(CD*CG) / (CD+CG)

[0050] Among them, CL (load capacitance) is the load capacitance, CS (shunt capacitance) is the parasitic capacitance between transistor pins, CD is the total capacitance from the output pin of the crystal oscillator circuit to the ground, and CG is the total capacitance from the input pin of the crystal oscillator circuit to the ground. The parasitic capacitance CS is generally 0.5Pf~1pF, and CD and CG are generally 10~50pF, including the PCB trace capacitance and the parasitic capacitance of the transistor pin.

[0051] Specifically, the data exchange pins TXCAN and RXCAN of the first bus control module U2 and the second bus control module U4 are respectively connected to the corresponding data exchange pins CANTx and CANRx of the first data transceiver module U3 and the second data transceiver module U5. The model of the first data transceiver module U3 and the second data transceiver module U5 is TCAN1042G. The CAN bus data transceiver module converts the CAN bus logic level into a differential level to transmit data on two bus cables with differential voltages.

[0052] Furthermore, the first data transceiver module U3 and the second data transceiver module U5 are connected to the bus interface module via the first protection module and the second protection module, respectively. Based on the common-mode high resistance and differential-mode low resistance characteristics of the common-mode inductor, the common-mode inductors L1 and L2 with an inductance of 100uH are placed near the first protection module and the second protection module bus, which can effectively filter out the high-frequency noise outside the bus and the common-mode noise generated by the asymmetric signal of the data transceiver module, and do not affect the differential signal transmission quality of the CAN bus, which has the effect of improving the anti-interference ability of the system and reducing the EMI of the system. Capacitors C1, C3 and C6, C8 with a capacitance of 33pF are selected and placed on the bus respectively to the ground, which can effectively filter out the transient overshoot of the CAN bus. The 120Ω terminal matching resistor of the bus consists of two 1% precision resistors with a resistance value of 60.4Ω connected in series. The positions in the first bus and the second bus are R1, R4 and R12, R13 respectively, and the 4.7nF capacitors C2 and C7 are grounded at the middle connection point, which helps to improve the signal consistency between the buses and reduce EMI. At the same time, the common mode interference here can be led to the ground to reduce interference to the bus. The dedicated ESD protection device PESD2CAN with small parasitic capacitors is placed near the bus interface D1, D2 and D3, D4, which can effectively enhance the ESD protection capability of the chip.

[0053] Specifically, the protected first CAN bus and the second CAN bus are both in hot backup state and are connected to the bus interface module, and the bus interface module CAN Bus Port is connected to the bus interface module of the platform to realize the measurement and control communication data transmission function between the satellite payload and the satellite platform.

[0054] Further, according to the telemetry and remote control communication circuit of the present invention, a communication lower computer program based on FPGA is written, and the peripheral SPI unit is configured through the dedicated 32-bit RISC processor soft core MicroBlaze programming, and after the internal layout and wiring are connected to other logic units and IO pins on the FPGA, it is integrated into a configuration data stream. The software function includes an initialization module, a state machine module, a read data cache module, and a write data cache module. The workflow is that after the processor module is powered on and started, the configuration data stream is loaded, and the initialization module in the software is entered. After the initialization is successful, according to the judgment condition of the state machine module, the read data cache module or the write data cache module is scheduled to enter, thereby realizing the function of SPI protocol transmission constituting CAN bus communication.

[0055] According to the matching capacitor and crystal oscillator characteristics, the corresponding register parameters are designed and configured, and the baud rate of the CAN bus is set to 500Kbps for communication testing. Figure 3 The figure shows the normal communication data transmission and reception waveform.

[0056] A satellite payload measurement and control communication circuit of the present invention is a measurement and control circuit suitable for CAN bus communication between a satellite payload and a satellite platform through SPI protocol transmission. Compared with traditional satellite payload measurement and control circuits, it is not easily affected and disturbed by the harsh space environment, can operate stably, uses fewer components and has a smaller circuit layout area, so as to meet the needs of the rapid development of commercial aerospace.

[0057] The above-mentioned specific implementation methods are used to explain the present invention and are only preferred embodiments of the present invention, rather than limiting the present invention. Any modifications, equivalent substitutions, improvements, etc. made to the present invention within the spirit of the present invention and the protection scope of the claims shall fall within the protection scope of the present invention.

Claims

1. A measurement and control communication circuit suitable for use between a satellite payload and a satellite platform, characterized in that: The measurement and control communication circuit comprises a processor module, a first bus control module, a first data transceiver module, a first protection module, a second bus control module, a second data transceiver module, a second protection module and a bus interface module; the processor module is connected to the first bus control module and the second bus control module, the first bus control module is connected to the first data transceiver module, the second bus control module is connected to the second data transceiver module, the first data transceiver module is connected to the first protection module, the second data transceiver module is connected to the second protection module, the first protection module and the second protection module are connected to the satellite platform CAN bus interface through the bus interface module to form two measurement and control communication circuits; the first and second paths are two CAN communication circuits that can exchange data through the SPI protocol, one is in the main state, the other is in the standby state, the circuit states of the two are the same, the two states are hot-backed up, data is exchanged in real time through the SPI protocol, the states of the two CAN communication circuits are kept synchronized in real time, the SPI protocol is used to transmit data with the processor module, the hot backup of the two satellite payload CAN bus measurement and control communication circuits is realized, and the measurement and control communication between the payload and the satellite platform is managed through the processor module.

2. The measurement and control communication circuit suitable for use between a satellite payload and a satellite platform according to claim 1, characterized in that: The measurement and control circuit processor module uses a single-chip microcomputer, FPGA or DSP.

3. The measurement and control communication circuit suitable for use between a satellite payload and a satellite platform according to claim 1, characterized in that: The first bus control module and the second bus control module include four standard interface leads and an interrupt pin: chip select CS, clock SCLK, master input slave output MISO, master output slave input MOSI. They are connected to the processor module through a standard serial peripheral interface SPI to realize data sending, data receiving, error handling, speed control, frame filtering, and interrupt control.

4. The measurement and control communication circuit suitable for use between a satellite payload and a satellite platform according to claim 1, characterized in that: The first data transceiver module, the first protection module, the second data transceiver module, and the second protection module are interfaces between the bus control module and the physical bus, realizing signal conversion, transmission guarantee, and noise management functions.

5. The measurement and control communication circuit suitable for use between a satellite payload and a satellite platform according to claim 4, characterized in that: In the signal conversion, the first data transceiver module and the second data transceiver module convert the digital signal output by the CAN bus control module into a bus differential level signal when sending data, and convert the differential level signal received on the bus into a digital signal when receiving data, and pass it to the bus control module for processing; The signal transmission supports high-speed and low-speed bus transmission to maintain efficient and stable communication.

6. The measurement and control communication circuit suitable for use between a satellite payload and a satellite platform according to claim 4, characterized in that: The first protection module and the second protection module are connected to the bus interface module through an electromagnetic compatibility protection circuit, and achieve stable data communication by suppressing electromagnetic interference and reducing noise on the bus.

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