Scientific experiment payload and satellite platform docking data interface test method and system

Abstract

The present application relates to scientific experiment load test technical field, especially to a kind of scientific experiment load and satellite platform interfacing data interface test method and system, method includes: before the power-on of scientific experiment load, the electrical connector characteristics of scientific experiment load is tested, the connector characteristics of scientific experiment load is detected, scientific experiment load is powered on, and surge current test is carried out, and power consumption and power pull bias test are carried out, and the CAN bus performance and function of scientific experiment load are tested, scientific experiment load is accessed to satellite platform, the remote control telemetry function between scientific experiment load and satellite platform is tested, and the network port data transmission between scientific experiment load and satellite platform is tested, can be all-around test to scientific experiment load, and can be all-around test to the scientific experiment load accessed to satellite platform, greatly reduce risk.

Description

Technical Field

[0001] This invention relates to the field of scientific experimental payload testing technology, and in particular to a method and system for testing the data interface between a scientific experimental payload and a satellite platform. Background Technology

[0002] Most scientific experimental payloads possess functions such as space environment detection and space magnetic and gravitational field measurement. The effective data collected and measured needs to be transmitted to the ground via the satellite platform's data transmission subsystem. Currently, most scientific experimental payloads carried by microsatellites and nanosatellites are novel payloads, meaning they have no flight experience. This makes it impossible to accurately verify the functionality and program stability of these payloads, potentially leading to functional deficiencies and mission failures in space. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to provide a method and system for testing the data interface between scientific experimental payloads and satellite platforms, addressing the shortcomings of the existing technology.

[0004] The technical solution of the present invention for a data interface testing method for docking scientific experimental payloads with satellite platforms is as follows:

[0005] Before powering on the scientific experimental payload, the characteristics of the electrical connectors of the scientific experimental payload are tested to obtain the first test result. The characteristics of the connectors of the scientific experimental payload are then tested to obtain the second test result.

[0006] When the first test result and the second test result are both normal, the scientific experimental payload is powered on and a surge current test is performed to obtain the third test result. The power consumption and power supply bias test of the scientific experimental payload is performed to obtain the fourth test result. The CAN bus performance and function of the scientific experimental payload are tested to obtain the fifth test result.

[0007] When the first test result, the second test result, the third test result, the fourth test result, and the fifth test result are all normal, the scientific experimental payload is connected to the satellite platform, and the remote control and telemetry function between the scientific experimental payload and the satellite platform is tested to obtain the sixth test result. The network port data transmission between the scientific experimental payload and the satellite platform is tested to obtain the seventh test result.

[0008] The beneficial effects of the scientific experimental payload and satellite platform docking data interface testing method of the present invention are as follows:

[0009] It can conduct comprehensive testing of scientific experimental payloads, as well as scientific experimental payloads connected to satellite platforms, to verify the functionality and program stability of scientific experimental payloads to the greatest extent possible, greatly reducing the risk that scientific experimental payloads may have functional deficiencies in space, thus failing to complete their missions.

[0010] Based on the above scheme, the scientific experimental payload and satellite platform docking data interface testing method of the present invention can be further improved as follows.

[0011] Furthermore, the process of connecting the scientific experimental payload to the satellite platform includes:

[0012] The scientific experimental payload is connected to the satellite platform according to the pre-defined connection lines specified by the satellite platform.

[0013] Furthermore, the scientific experimental payload is a scientific experimental payload based on the UDP protocol.

[0014] Furthermore, it also includes:

[0015] If the first test result, the second test result, the third test result, the fourth test result, the fifth test result, the sixth test result, and the seventh test result are all normal, then an alert will be issued indicating that the scientific experimental payload is normal, and an alert will be issued indicating that the scientific experimental payload and the satellite platform are docking normally.

[0016] The technical solution of the scientific experimental payload and satellite platform docking data interface testing system of the present invention is as follows:

[0017] Includes a test module, a power-on module, and an access module;

[0018] Before the power-on module powers on the scientific experimental payload, the test module is used to: test the electrical connector characteristics of the scientific experimental payload to obtain a first test result, and test the connector characteristics of the scientific experimental payload to obtain a second test result;

[0019] The power-on module is used to: power on the scientific experimental payload when both the first test result and the second test result are normal; the test module is also used to: perform surge current test on the scientific experimental payload to obtain a third test result; perform power consumption and power supply bias test on the scientific experimental payload to obtain a fourth test result; and test the CAN bus performance and function of the scientific experimental payload to obtain a fifth test result.

[0020] The access module is used to: connect the scientific experimental payload to the satellite platform when the first test result, the second test result, the third test result, the fourth test result, and the fifth test result are all normal. The test module is also used to: test the remote control and telemetry function between the scientific experimental payload and the satellite platform to obtain a sixth test result, and test the network port data transmission between the scientific experimental payload and the satellite platform to obtain a seventh test result.

[0021] The beneficial effects of the scientific experimental payload and satellite platform docking data interface testing system of the present invention are as follows:

[0022] It can conduct comprehensive testing of scientific experimental payloads, as well as scientific experimental payloads connected to satellite platforms, to verify the functionality and program stability of scientific experimental payloads to the greatest extent possible, greatly reducing the risk that scientific experimental payloads may have functional deficiencies in space, thus failing to complete their missions.

[0023] Based on the above scheme, the scientific experimental payload and satellite platform docking data interface testing system of the present invention can be further improved as follows.

[0024] Furthermore, the access module is specifically used for:

[0025] The scientific experimental payload is connected to the satellite platform according to the pre-defined connection lines specified by the satellite platform.

[0026] Furthermore, the scientific experimental payload is a scientific experimental payload based on the UDP protocol.

[0027] Furthermore, it also includes a reminder module, which is used to: issue a reminder that the scientific experimental payload is normal when the first test result, the second test result, the third test result, the fourth test result, the fifth test result, the sixth test result, and the seventh test result are all normal; and issue a reminder that the scientific experimental payload and the satellite platform are docking normally. Attached Figure Description

[0028] Figure 1 This is a flowchart illustrating a method for testing the data interface between a scientific experimental payload and a satellite platform, according to an embodiment of the present invention.

[0029] Figure 2 A schematic diagram of a single-machine test of a scientific experimental payload;

[0030] Figure 3 A schematic diagram illustrating the testing of a scientific experimental payload after it has been connected to a satellite platform;

[0031] Figure 4This is a schematic diagram of a data interface testing system for docking scientific experimental payloads with a satellite platform, according to an embodiment of the present invention. Detailed Implementation

[0032] like Figure 1 As shown in the figure, a method for testing the data interface between a scientific experimental payload and a satellite platform according to an embodiment of the present invention includes the following steps:

[0033] S1. Before powering on the scientific experimental payload, the characteristics of its electrical connectors are tested to obtain the first test result. The characteristics of the connectors on the scientific experimental payload are then tested to obtain the second test result, such as... Figure 2 As shown, specifically:

[0034] 1) Check and test the electrical connector characteristics of the scientific experimental load:

[0035] Before powering on a scientific experimental payload, its electrical connector characteristics must be checked. First, verify that the markings and model numbers of all connectors on the payload match the data interface sheet. This prevents subsequent operators from making incorrect connections when connecting the payload to the platform, which could cause irreversible damage to the payload and other individual units on the satellite, potentially leading to a major accident.

[0036] 2) Testing the connector characteristics of scientific experimental payloads:

[0037] The characteristics of the scientific experimental payload connectors were checked to ensure that each node of each connector strictly conforms to the interface data sheet. Specifically:

[0038] First, use a multimeter to measure the continuity between the power supply positive line and the power supply return line of the equipment. This step is crucial to prevent product accidents caused by power supply short circuits during equipment development. Next, measure the impedance to ground of each data bus node to ensure that the bus node is not connected to GND, guaranteeing no internal short circuits and stable operation under normal conditions. Finally, measure the CAN bus matching resistor for remote control and telemetry data transmission. It should correspond to the resistance value agreed upon on the data interface sheet to ensure normal CAN bus data interaction of the entire satellite system after the scientific experimental payload is connected to the platform.

[0039] S2. When both the first and second test results are normal, power on the scientific experiment payload and perform a surge current test to obtain the third test result. Then, perform power consumption and power supply bias tests on the scientific experiment payload to obtain the fourth test result. Finally, test the CAN bus performance and functionality of the scientific experiment payload to obtain the fifth test result. Specifically:

[0040] 1) Power on the scientific experimental payload and perform surge current testing:

[0041] After all interfaces of the scientific payload have been checked, the payload unit can now be powered on for surge current testing. The purpose of this test is to ensure that the instantaneous current generated when the payload unit's relays are powered on is within the range required by the satellite platform. Otherwise, an excessively large surge current could damage the payload equipment or, in severe cases, cause irreparable damage to the entire satellite's power supply system. If the instantaneous current during payload startup is too high, the payload provider needs to design measures to reduce the instantaneous current and ensure it remains within the specified range.

[0042] 2) Perform power consumption and power supply bias tests on scientific experimental payloads:

[0043] Once the satellite is in orbit, all payloads and equipment are powered by its built-in power module. Due to limited resources, it is crucial to verify that the actual power consumption of the scientific experiment payload at its nominal voltage conforms to the protocol specifications. The scientific experiment payload is connected to a DC power supply, and the output voltage of the DC power supply is set to the payload's nominal voltage. A CAN bus testing device is used to observe the payload's normal operation after power-on, and the device power consumption is calculated using the formula W = U × I.

[0044] Because the satellite's orbital environment after it enters Earth's orbit includes both the Earth's shadow and the sunlit zone, the satellite experiences several challenges. Firstly, in the Earth's shadow, the satellite receives no sunlight, and all equipment is powered by its internal batteries. Therefore, if the payload is operating extensively during this period, the overall satellite power supply voltage may be low. Secondly, in the sunlit zone, the solar panels receive ample sunlight, resulting in abundant energy for the satellite. The satellite platform's power supply voltage to the payload will exceed the payload's power supply voltage. The satellite's operational parameters will assess the platform's power supply range for the payload, and the payload should operate normally within this voltage range. To verify that the payload operates normally within the power supply range provided by the satellite platform, we need to perform a power supply bias test on the payload.

[0045] Set the DC power supply thresholds for the satellite platform to the payload. Power on the scientific experiment payload and use the CAN bus testing equipment to send rapid and gradual change request commands. Observe the telemetry parameters returned by the payload and determine that the payload is operating normally based on the telemetry parameters. Calculate the power consumption of the payload at this time.

[0046] 3) Test the CAN bus performance and functionality of the scientific experimental payload:

[0047] CAN bus performance and functional testing. The interface between the scientific experimental payload and the satellite platform's onboard computer is the CAN bus interface. Therefore, verifying the CAN bus performance indicators provides a strong guarantee for stable on-orbit communication between the scientific experimental payload and the onboard computer, as detailed below:

[0048] ① CAN bus performance testing generally includes fast / slow change request response time, response frame interval, indirect command response time, CAN bus differential level, and CAN bus baud rate. Use an oscilloscope connected to the CAN bus test ground, with the oscilloscope probes touching the H and L terminals of the CAN bus ground, respectively. Set the oscilloscope trigger level and send fast / slow change requests and indirect commands to the CAN ground control terminal. The oscilloscope should capture the corresponding waveforms. Record the CAN bus performance indicators. The CAN bus response time and frame interval should be within the range specified by the satellite platform; otherwise, it may affect the satellite administrator's misinterpretation of payload response information.

[0049] ②CAN bus functional testing generally includes communication function testing. This involves sending rapid and slow telemetry polling requests and indirect commands through the CAN bus ground testing equipment, and checking whether the scientific payload response information returned by the CAN bus is consistent with the format specified in the CAN bus protocol.

[0050] S3. When the first, second, third, fourth, and fifth test results are all normal, connect the scientific experiment payload to the satellite platform and test the remote control and telemetry functions between the scientific experiment payload and the satellite platform to obtain the sixth test result. Then, test the network interface data transmission between the scientific experiment payload and the satellite platform to obtain the seventh test result. Figure 3 As shown, specifically:

[0051] 1) Test the remote control and telemetry capabilities between the scientific experimental payload and the satellite platform:

[0052] By sending status acquisition commands to the scientific experiment payload via a test laptop, the spacecraft sends rapid-change and slow-change acquisition request commands to the scientific experiment payload at pre-defined time intervals. The test laptop then interprets the status telemetry of the scientific experiment payload's response. This step confirms that the internal program of the scientific experiment payload is consistent with the pre-agreed CAN bus protocol. Indirect commands are then sent to the scientific experiment payload to observe its response and actions, fully verifying the functionality of the payload equipment.

[0053] 2) Test the data transmission via the network interface between the scientific experimental payload and the satellite platform:

[0054] Scientific experimental payloads should have the ability to automatically generate test data (including fixed or incremental data) and be able to control the output of test data through indirect commands. Specifically:

[0055] ① Set the data transmission subsystem to the scientific experiment payload partition recording state through indirect commands, send indirect commands to control the scientific experiment payload to send test data to the data transmission all-in-one machine through the network port, and stop the data recording of the data transmission all-in-one machine after the data is sent.

[0056] ② Connect the data transmission all-in-one machine to the data transmission ground inspection equipment, and send the data recorded by the scientific experimental payload in the data transmission zone to the ground.

[0057] ③ Analyze the raw data received by the data transmission ground inspection equipment, check that the internal scientific experiment payload data frame structure conforms to the pre-defined UDP frame protocol, and check the continuity of frame count in the scientific experiment payload data frame structure, and check that there are no frame drops.

[0058] The testing processes S1 to S2 described above can be collectively referred to as the stand-alone testing process of the scientific experimental payload, and the testing process S3 described above can be collectively referred to as the testing process of connecting the scientific experimental payload to the satellite platform.

[0059] This invention enables comprehensive testing of scientific experimental payloads, as well as comprehensive testing of scientific experimental payloads connected to satellite platforms. It verifies the functionality and program stability of scientific experimental payloads to the greatest extent possible, greatly reducing the risk that scientific experimental payloads may have functional deficiencies in space, thus failing to complete their missions.

[0060] Optionally, in the above technical solution, in step S3, the scientific experiment payload is connected to the satellite platform, including:

[0061] S30. Connect the scientific experimental payload to the satellite platform according to the pre-defined connection lines specified by the satellite platform.

[0062] Optionally, in the above technical solution, the scientific experiment payload is a scientific experiment payload based on the UDP protocol.

[0063] Optionally, the above technical solution also includes:

[0064] S4. If the first, second, third, fourth, fifth, sixth, and seventh test results are all normal, then a reminder that the scientific experimental payload is normal and a reminder that the docking between the scientific experimental payload and the satellite platform is normal will be issued.

[0065] This invention describes a testing method for the data interface between a scientific experimental payload and a satellite platform based on the UDP protocol. This includes checking the electrical interface, CAN bus interface, payload remote control and telemetry functions, and verifying the correctness of payload data transmission to the ground via data transmission equipment. The purpose of this invention is to provide a testing method for the data interface between a scientific experimental payload and a satellite platform based on the UDP protocol. This proposed method for interfacing with the entire satellite platform accelerates the compatibility of the entire satellite platform with the scientific experimental payload, speeds up the satellite development cycle, and possesses high versatility.

[0066] In the above embodiments, although the steps are numbered S1, S2, etc., they are only specific embodiments given in this application. Those skilled in the art can adjust the execution order of S1, S2, etc. according to the actual situation, which is also within the protection scope of this invention. It can be understood that in some embodiments, some or all of the above embodiments may be included.

[0067] like Figure 2 As shown, a scientific experimental payload and satellite platform docking data interface test system 200 according to an embodiment of the present invention includes a test module 210, a power-on module 220 and an access module 230.

[0068] Before the power-on module 220 powers on the scientific experiment payload, the test module 210 is used to: test the electrical connector characteristics of the scientific experiment payload to obtain a first test result, and test the connector characteristics of the scientific experiment payload to obtain a second test result.

[0069] The power-on module 220 is used to: power on the scientific experiment payload when there are no abnormalities in the first test result and the second test result. The test module 210 is also used to: perform surge current test on the scientific experiment payload to obtain the third test result, perform power consumption and power supply bias test on the scientific experiment payload to obtain the fourth test result, and test the CAN bus performance and function of the scientific experiment payload to obtain the fifth test result.

[0070] The access module 230 is used to connect the scientific experiment payload to the satellite platform when the first test result, the second test result, the third test result, the fourth test result, and the fifth test result are all normal. The test module 210 is also used to test the remote control and telemetry function between the scientific experiment payload and the satellite platform to obtain the sixth test result, and to test the network port data transmission between the scientific experiment payload and the satellite platform to obtain the seventh test result.

[0071] This invention enables comprehensive testing of scientific experimental payloads, as well as comprehensive testing of scientific experimental payloads connected to satellite platforms. It verifies the functionality and program stability of scientific experimental payloads to the greatest extent possible, greatly reducing the risk that scientific experimental payloads may have functional deficiencies in space, thus failing to complete their missions.

[0072] Optionally, in the above technical solution, the access module 230 is specifically used for:

[0073] Connect the scientific experimental payloads to the satellite platform according to the pre-defined connection lines specified by the satellite platform.

[0074] Optionally, in the above technical solution, the scientific experiment payload is a scientific experiment payload based on the UDP protocol.

[0075] Optionally, the above technical solution also includes a reminder module, which is used to: issue a reminder that the scientific experimental payload is normal when the first test result, the second test result, the third test result, the fourth test result, the fifth test result, the sixth test result, and the seventh test result are all normal, and to issue a reminder that the scientific experimental payload and the satellite platform are docked normally.

[0076] The parameters and steps for each unit module to achieve their respective functions in the above-described scientific experimental payload and satellite platform docking data interface testing system 200 of the present invention can be referred to the parameters and steps in the embodiments of the method for testing a scientific experimental payload and satellite platform docking data interface described above, and will not be repeated here.

[0077] Those skilled in the art will know that this invention can be implemented as a system, method, or computer program product.

[0078] Therefore, this disclosure can be implemented in the following forms: it can be entirely hardware, entirely software (including firmware, resident software, microcode, etc.), or a combination of hardware and software, generally referred to herein as a "circuit," "module," or "system." Furthermore, in some embodiments, the invention can also be implemented as a computer program product in one or more computer-readable media, the computer-readable medium containing computer-readable program code.

[0079] Any combination of one or more computer-readable media may be used. A computer-readable medium can be a computer-readable signal medium or a computer-readable storage medium. A computer-readable storage medium can be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination thereof. More specific examples (a non-exhaustive list) of computer-readable storage media include: an electrical connection having one or more wires, a portable computer disk, a hard disk, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fiber, portable compact disk read-only memory (CD-ROM), optical storage device, magnetic storage device, or any suitable combination thereof. In this document, a computer-readable storage medium can be any tangible medium that contains or stores a program that can be used by or in connection with an instruction execution system, apparatus, or device.

[0080] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A method for testing the data interface between a scientific experimental payload and a satellite platform, characterized in that, include: Before powering on the scientific experimental payload, the characteristics of the electrical connector of the scientific experimental payload are tested to obtain the first test result, and the characteristics of the connector of the scientific experimental payload are tested to obtain the second test result. When the first test result and the second test result are both normal, the scientific experimental payload is powered on and a surge current test is performed to obtain the third test result. The power consumption and power supply bias test of the scientific experimental payload is performed to obtain the fourth test result. The CAN bus performance and function of the scientific experimental payload are tested to obtain the fifth test result. When the first test result, the second test result, the third test result, the fourth test result, and the fifth test result are all normal, the scientific experimental payload is connected to the satellite platform, and the remote control and telemetry function between the scientific experimental payload and the satellite platform is tested to obtain the sixth test result. The network port data transmission between the scientific experimental payload and the satellite platform is tested to obtain the seventh test result. The testing included verifying data transmission over the network interface between the scientific experimental payload and the satellite platform, including: The data transmission subsystem is set to the scientific experiment payload partition recording state by indirect command. Indirect command is sent to control the scientific experiment payload to send test data to the data transmission all-in-one machine through the network port. After the data is sent, the data recording of the data transmission all-in-one machine is stopped. Connect the data transmission all-in-one machine to the data transmission ground inspection equipment to send the data recorded by the scientific experimental payloads in the data transmission partition to the ground; Analyze the raw data received by the data transmission ground inspection equipment, check whether the internal scientific experiment payload data frame structure conforms to the pre-defined UDP frame protocol, and check the continuity of frame counts in the scientific experiment payload data frame structure. The performance and functionality of the CAN bus for scientific experimental payloads were tested, including: CAN bus performance testing includes fast / slow change request response time, response frame interval, indirect command response time, CAN bus differential level, and CAN bus baud rate. An oscilloscope is connected to the CAN bus test ground, with the oscilloscope probes touching the H and L terminals of the CAN bus test ground respectively. The oscilloscope trigger level is set, and fast / slow change requests and indirect commands are sent to the CAN test ground control terminal. The oscilloscope captures the corresponding waveforms, and the CAN bus performance indicators are recorded. The CAN bus response time and frame interval should be within the range specified by the satellite platform. CAN bus functional testing includes communication function testing. The test involves sending rapid and slow telemetry polling requests and indirect commands to the ground inspection equipment via the CAN bus, and checking whether the scientific payload response information returned by the CAN bus is consistent with the format specified in the CAN bus protocol.

2. The method for testing the data interface between a scientific experimental payload and a satellite platform according to claim 1, characterized in that, The process of connecting the scientific experimental payload to the satellite platform includes: The scientific experimental payload is connected to the satellite platform according to the pre-defined connection lines specified by the satellite platform.

3. The method for testing the data interface between a scientific experimental payload and a satellite platform according to claim 1, characterized in that, The scientific experiment payload is a scientific experiment payload based on the UDP protocol.

4. The method for testing the data interface between a scientific experimental payload and a satellite platform according to claim 1, characterized in that, Also includes: If the first test result, the second test result, the third test result, the fourth test result, the fifth test result, the sixth test result, and the seventh test result are all normal, then an alert will be issued indicating that the scientific experimental payload is normal, and an alert will be issued indicating that the scientific experimental payload and the satellite platform are docking normally.

5. A data interface testing system for docking scientific experimental payloads with a satellite platform, characterized in that, Includes a test module, a power-on module, and an access module; Before the power-on module powers on the scientific experiment payload, the test module is used to: test the characteristics of the electrical connector of the scientific experiment payload to obtain a first test result, and test the characteristics of the connector of the scientific experiment payload to obtain a second test result; The power-on module is used to: power on the scientific experimental payload when both the first test result and the second test result are normal; the test module is also used to: perform surge current test on the scientific experimental payload to obtain a third test result; perform power consumption and power supply bias test on the scientific experimental payload to obtain a fourth test result; and test the CAN bus performance and function of the scientific experimental payload to obtain a fifth test result. The access module is used to: connect the scientific experimental payload to the satellite platform when the first test result, the second test result, the third test result, the fourth test result, and the fifth test result are all normal; the test module is also used to: test the remote control and telemetry function between the scientific experimental payload and the satellite platform to obtain a sixth test result; and test the network port data transmission between the scientific experimental payload and the satellite platform to obtain a seventh test result. The testing included verifying data transmission over the network interface between the scientific experimental payload and the satellite platform, including: The data transmission subsystem is set to the scientific experiment payload partition recording state by indirect command. Indirect command is sent to control the scientific experiment payload to send test data to the data transmission all-in-one machine through the network port. After the data is sent, the data recording of the data transmission all-in-one machine is stopped. Connect the data transmission all-in-one machine to the data transmission ground inspection equipment to send the data recorded by the scientific experimental payloads in the data transmission partition to the ground; Analyze the raw data received by the data transmission ground inspection equipment, check whether the internal scientific experiment payload data frame structure conforms to the pre-defined UDP frame protocol, and check the continuity of frame counts in the scientific experiment payload data frame structure. CAN bus performance testing includes fast / slow change request response time, response frame interval, indirect command response time, CAN bus differential level, and CAN bus baud rate. An oscilloscope is connected to the CAN bus test ground, with the oscilloscope probes touching the H and L terminals of the CAN bus test ground respectively. The oscilloscope trigger level is set, and fast / slow change requests and indirect commands are sent to the CAN test ground control terminal. The oscilloscope captures the corresponding waveforms, and the CAN bus performance indicators are recorded. The CAN bus response time and frame interval should be within the range specified by the satellite platform. CAN bus functional testing includes communication function testing. The test involves sending rapid and slow telemetry polling requests and indirect commands to the ground inspection equipment via the CAN bus, and checking whether the scientific payload response information returned by the CAN bus is consistent with the format specified in the CAN bus protocol.

6. The scientific experimental payload and satellite platform docking data interface testing system according to claim 5, characterized in that, The access module is specifically used for: The scientific experimental payload is connected to the satellite platform according to the pre-defined connection lines specified by the satellite platform.

7. The scientific experimental payload and satellite platform docking data interface testing system according to claim 5, characterized in that, The scientific experiment payload is a scientific experiment payload based on the UDP protocol.

8. The scientific experimental payload and satellite platform docking data interface testing system according to claim 5, characterized in that, It also includes a reminder module, which is used to: issue a reminder that the scientific experimental payload is normal when the first test result, the second test result, the third test result, the fourth test result, the fifth test result, the sixth test result, and the seventh test result are all normal; and issue a reminder that the scientific experimental payload and the satellite platform are docking normally.

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