Satellite-borne laser communication on-orbit reliability error code fault test method and device

Abstract

This invention relates to the field of communication data processing technology, and provides a method and apparatus for testing the on-orbit reliability bit error rate (BER) faults in spaceborne laser communication. The method includes: determining the communication stage of the spaceborne laser communication terminal; selecting a corresponding BER test mode based on the determined communication stage, performing BER testing on the received data, and obtaining the test results; wherein the communication stage includes an initial link establishment stage, a link stabilization stage, and a service transmission stage, and the corresponding BER test modes are a pseudo-random binary sequence test mode, a blank frame test mode, and a service data test mode, respectively; based on the test results, determining whether to switch to the next communication stage or to issue a fault warning. This invention can effectively overcome the deficiencies of existing static testing of ground equipment, ensure the pertinence of link evaluation at each stage and the security of state transition, and improve the accuracy of on-orbit reliability BER fault testing for spaceborne laser communication.

Description

Technical Field

[0001] This invention relates to the field of communication data processing technology, and in particular to a method and apparatus for testing on-orbit reliability bit error faults in spaceborne laser communication. Background Technology

[0002] Bit Error Rate (BER) is a core performance indicator for digital communication systems, directly reflecting the probability of errors occurring during signal transmission due to factors such as channel noise, interference, and fading. Accurate and efficient calculation or estimation of BER is crucial for performance evaluation, link quality monitoring, power control, channel switching, and resource scheduling of communication systems. As communication technologies evolve from traditional wireless communication to more complex systems such as high-speed serial communication and fiber optic communication, the accurate calculation of BER faces increasing challenges. Forward error correction (FEC) is widely used to reduce the bit error rate (BER). FEC adds redundant checksum information at the transmitting end, allowing the receiving end to detect and correct some errors, thereby reducing the original high BER to the level required by the system. When evaluating FEC performance, it is necessary to calculate the pre-FEC BER and the post-FEC BER. Ultimately, the system focuses on whether the post-FEC BER meets the required standard.

[0003] Taking a traditional 10G terrestrial optical communication system as an example, bit error rate (BER) testing relies heavily on key equipment such as a Bit Error Rate Tester (BERT), a high-speed oscilloscope, an OSA spectrometer, an optical attenuator, and an Integrated Bit Error Rate Test IP Core (IBERT). The BERT is the core equipment for standard BER testing. The high-speed oscilloscope is used to observe eye diagrams and measure signal integrity parameters such as jitter. The OSA spectrometer is used to measure parameters such as the optical wavelength and optical signal-to-noise ratio (OSNR) of the DWDM optical module. The optical attenuator is used to control the optical power at the receiver to test the receiver's sensitivity and dynamic range. The IBERT is used in FPGA development, employing IBERT IP cores provided by companies such as Xilinx to achieve self-transmit and receive testing within the chip, eliminating the need for external instruments.

[0004] In traditional terrestrial communication systems, the above-mentioned equipment can basically achieve accurate bit error rate testing and obtain reliable results. However, when testing the bit error rate of spaceborne laser communication equipment in orbit, the communication bit error rate will change according to the tracking status of the laser communication terminal. The bit error rate is no longer a fixed indicator parameter, but changes in real time and needs to be measured in real time. Therefore, it is not possible to use terrestrial equipment to test the bit error rate in orbit. Summary of the Invention

[0005] This invention provides a method and apparatus for testing the on-orbit reliability bit error rate of spaceborne laser communication, which solves the shortcomings of existing on-orbit testing of bit error rate of ground equipment that cannot cope with the changes in bit error rate of spaceborne laser communication equipment tracking status. It can effectively make up for the deficiencies of existing static testing of ground equipment, ensure the pertinence of link evaluation at each stage and the security of state transition, and improve the accuracy of on-orbit reliability bit error rate testing of spaceborne laser communication.

[0006] This invention provides a method for testing the on-orbit reliability of spaceborne laser communication using bit error rate (BER) faults, comprising: determining the communication stage of the spaceborne laser communication terminal; selecting a corresponding BER test mode based on the determined communication stage, performing BER testing on the received data, and obtaining test results; wherein the communication stage includes an initial link establishment stage, a link stabilization stage, and a service transmission stage, and the corresponding BER test modes are a pseudo-random binary sequence test mode, a blank frame test mode, and a service data test mode, respectively; and based on the test results, determining whether to switch to the next communication stage or to issue a fault warning.

[0007] According to the present invention, an on-orbit reliability bit error rate (BER) fault testing method for spaceborne laser communication is provided. The method selects a corresponding BER test mode based on a determined communication stage, performs BER testing on the received data, and obtains the test results. The method includes: selecting a pseudo-random binary sequence test mode based on the initial link establishment stage of the communication stage; generating and sending pseudo-random binary sequence data; and receiving pseudo-random binary sequence data sent by the peer. Based on the locally generated pseudo-random binary sequence data and the pseudo-random binary sequence data sent by the peer, the number of erroneous bits and the total number of bits are determined, and the pseudo-random binary sequence BER is obtained as the test result.

[0008] According to the present invention, a method for testing on-orbit reliability bit error rate faults in spaceborne laser communication is provided. Based on the communication phase as the initial link establishment phase, a pseudo-random binary sequence test mode is selected, and pseudo-random binary sequence data is generated and sent. The method includes: based on the communication phase as the initial link establishment phase, in response to the control command of the ground monitoring system, switching to the pseudo-random binary sequence test mode, generating pseudo-random binary sequence data of the corresponding order, and sending the generated pseudo-random binary sequence data to the optical port. Based on the locally generated pseudo-random binary sequence data and the pseudo-random binary sequence data sent by the peer, the number of erroneous bits and the total number of bits are determined to obtain the pseudo-random binary sequence bit error rate. This includes: performing high-speed serial-to-parallel processing on the received pseudo-random binary sequence data sent by the peer; comparing the processed data bit by bit with the locally generated pseudo-random binary sequence data; and calculating the ratio of the number of erroneous bits to the total number of bits within a fixed time interval to obtain the pseudo-random binary sequence bit error rate.

[0009] According to the present invention, a method for testing on-orbit reliability bit error rate faults in spaceborne laser communication is provided. Based on the test results, it is determined whether to switch to the next communication stage or to issue a fault warning. The method includes: determining whether the frequency of change of the bit error rate of the pseudo-random binary sequence within the target duration meets the preset communication bit error rate standard range; if it is determined that the bit error rate meets the preset communication bit error rate standard range and is maintained for a preset time, it is determined that the acquisition and tracking is stable and the method switches to the link stability stage; or, if it is determined that the bit error rate does not meet the preset communication bit error rate standard range and is greater than the upper limit of the preset communication bit error rate standard range, it is determined that the acquisition and tracking system module is not aligned and the physical link is not established.

[0010] According to the present invention, a method for testing the on-orbit reliability of spaceborne laser communication based on bit error rate (BER) faults includes: selecting a corresponding BER testing mode based on a determined communication phase; performing BER testing on received data to obtain test results; and further comprising: selecting an empty frame test mode when the communication phase is a stable link phase and there is no client service data transmission; generating and sending an empty frame containing a fixed code pattern, and receiving an empty frame sent by the peer; comparing the corresponding fixed code pattern between the locally generated empty frame and the empty frame sent by the peer to determine the number of error bits that have not undergone forward error correction decoding, thus obtaining the pre-correction BER of the empty frame; performing forward error correction decoding on the empty frame sent by the peer, and combining it with the locally generated empty frame to compare the corresponding fixed code pattern to determine the number of error bits after forward error correction decoding, thus obtaining the post-correction BER of the empty frame; and obtaining the test results based on the pre-correction BER and post-correction BER of the empty frame.

[0011] According to the present invention, a method for testing on-orbit reliability bit error rate faults in spaceborne laser communication generates and transmits empty frames containing known fixed code patterns, including: automatically generating an empty frame structure according to the frame structure specified by the air interface link protocol frame; filling the empty frame structure with preset data; and sending the filled empty frame structure to the other end. Based on the test results, determine whether to switch to the next communication stage or issue a fault warning, including: when the bit error rate after empty frame correction is zero, determine that the link quality meets the data transmission requirements and switch to the service transmission stage; or, when the bit error rate before empty frame correction is not zero and the bit error rate after empty frame correction is not zero, report an alarm signal that exceeds the error correction capability.

[0012] According to the present invention, a method for testing on-orbit reliability bit error rate faults in spaceborne laser communication is provided. When the bit error rate after empty frame correction is zero, the link quality is determined to meet the data transmission requirements, and the system switches to the service transmission stage. The method includes: when the bit error rate before empty frame correction is not zero and the bit error rate after empty frame correction is zero, the link fluctuation or slight attenuation is determined to be normal, and the link quality is determined to meet the data transmission requirements, and the system switches to the service transmission stage; or, when the bit error rate before empty frame correction is zero and the bit error rate after empty frame correction is zero, the link condition is determined to be excellent, and the link quality is determined to meet the data transmission requirements, with no errors to correct in forward error correction and unimpeded service.

[0013] According to the present invention, an on-orbit reliability bit error rate (BER) fault testing method for spaceborne laser communication is provided. The method selects a corresponding BER testing mode based on a determined communication phase, performs BER testing on received data, and obtains test results. The method further includes: selecting a service data testing mode based on the communication phase being a service transmission phase; encoding and sending the service data; and receiving the encoded service data sent by the peer; decoding the received encoded service data using forward error correction (FEC) and obtaining the number of erroneous bits corrected during decoding to determine the pre-correction BER; and obtaining the test results based on the pre-correction BER and monitored alarm signals. The alarm signals are reported by the forward error correction system when the number of erroneous bits exceeds the error correction threshold.

[0014] According to the present invention, a method for testing on-orbit reliability bit error rate faults in spaceborne laser communication is provided. Based on the test results, it is determined whether to switch to the next communication stage or to issue a fault warning. The method further includes: when an alarm signal is received, determining that an abnormal situation of a large number of bit errors has occurred in the service transmission, suspending the transmission of service data, and switching back to pseudo-random binary sequence data or empty frames for testing.

[0015] This invention also provides an on-orbit reliability bit error rate (BER) fault testing device for spaceborne laser communication, comprising: a stage determination module for determining the communication stage of the spaceborne laser communication terminal; a testing module for selecting a corresponding BER test mode according to the determined communication stage, performing BER testing on the received data, and obtaining test results; wherein the communication stage includes an initial link establishment stage, a link stabilization stage, and a service transmission stage, and the corresponding BER test modes are a pseudo-random binary sequence test mode, a blank frame test mode, and a service data test mode, respectively; and a processing module for determining, based on the test results, whether to switch to the next communication stage or to issue a fault warning.

[0016] The present invention also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the on-orbit reliability bit error fault testing method for spaceborne laser communication as described above.

[0017] The present invention also provides a non-transitory computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the on-orbit reliability bit error fault testing method for spaceborne laser communication as described above.

[0018] The present invention also provides a computer program product, including a computer program that, when executed by a processor, implements the on-orbit reliability bit error fault testing method for spaceborne laser communication as described above.

[0019] The present invention provides a method and apparatus for on-orbit reliability bit error rate (BER) testing of spaceborne laser communication. By determining the communication stage of the spaceborne laser communication terminal, the exact position of the terminal in the workflow is clarified, providing a foundation for subsequent targeted testing strategies. Based on the determined communication stage, a corresponding BER test mode is selected. This one-to-one correspondence between stage and test mode ensures that the BER testing method strictly matches the link status and data characteristics of different communication stages, achieving precise adaptation of the testing method. Subsequently, the selected corresponding test mode is used to perform BER testing on the received data to obtain the test results. The test results show that, due to the adoption of a dedicated mode that matches the current stage, the obtained test results can objectively reflect the actual transmission quality of the link under this specific stage. By directly using the test results as the decision-making basis for state control and risk management, it can ensure that the link can smoothly transition to the next stage when it meets the standards, and can also provide timely fault warnings when it fails to meet the standards. This has built a closed-loop testing and control mechanism covering the entire communication process, which can effectively make up for the deficiencies of existing static testing of ground equipment, ensure the pertinence of link evaluation at each stage and the security of state transition, and improve the accuracy of on-orbit reliability error fault testing for spaceborne laser communication. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in this invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0021] Figure 1 This is a flowchart illustrating the on-orbit reliability bit error fault testing method for spaceborne laser communication provided by the present invention. Figure 2 This is a schematic diagram of the architecture of the on-orbit reliability bit error fault testing method for spaceborne laser communication provided by the present invention; Figure 3 This is a functional block diagram of the spaceborne laser communication terminal provided by the present invention; Figure 4This is a block diagram of the transmission direction processing of the communication control box of the spaceborne laser communication terminal provided by the present invention; Figure 5 This is a block diagram of the receiving direction processing of the communication control box of the spaceborne laser communication terminal provided by the present invention; Figure 6 This is a schematic diagram of the structure of the on-orbit reliability bit error fault testing device for spaceborne laser communication provided by the present invention; Figure 7 This is a schematic diagram of the structure of the electronic device provided by the present invention. Detailed Implementation

[0022] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of this invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this invention. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0023] Figure 1 This is one of the flowcharts illustrating the on-orbit reliability bit error rate fault testing method for spaceborne laser communication provided by the present invention, such as... Figure 1 As shown, the method includes the following: S11, determine the communication stage of the spaceborne laser communication terminal; S12, select the corresponding bit error rate test mode according to the determined communication stage, perform bit error rate test on the received data, and obtain the test result; wherein, the communication stage includes the initial link establishment stage, the link stabilization stage and the service transmission stage, and the corresponding bit error rate test modes are pseudo-random binary sequence test mode, empty frame test mode and service data test mode, respectively. S13, based on the test results, determine whether to switch to the next communication stage or issue a fault warning.

[0024] It should be noted that the following specific combinations Figures 2-5 This invention describes the on-orbit reliability error test method for spaceborne laser communication.

[0025] Step S11: Determine the communication stage of the spaceborne laser communication terminal.

[0026] It should be added that the spaceborne laser communication terminal is installed on the satellite and uses laser as an information carrier to transmit data between satellites and between satellites and ground stations. In the transmitting direction, the spaceborne laser communication terminal is responsible for packaging the on-board data into frame format data suitable for transmission in the space optical link, and in the receiving direction, it is responsible for restoring the data transmitted on the optical path into customer service data.

[0027] Step S12: Select the corresponding bit error rate test mode according to the determined communication stage, perform bit error rate test on the received data, and obtain the test result; wherein, the communication stage includes the initial link establishment stage, the link stabilization stage and the service transmission stage, and the corresponding bit error rate test modes are pseudo-random binary sequence test mode, empty frame test mode and service data test mode, respectively.

[0028] In one optional embodiment, a corresponding bit error rate (BER) test mode is selected based on the determined communication stage, and the received data is subjected to a BER test to obtain the test result. This includes: selecting a pseudo-random binary sequence test mode based on the initial link establishment stage of the communication stage, generating and sending pseudo-random binary sequence data, and receiving pseudo-random binary sequence data sent by the peer; determining the number of erroneous bits and the total number of bits based on the locally generated pseudo-random binary sequence data and the pseudo-random binary sequence data sent by the peer, and obtaining the pseudo-random binary sequence BER as the test result.

[0029] It should be noted that, based on the initial link establishment phase of the communication stage, a pseudo-random binary sequence test mode is selected to match the test method with the specific early link establishment phase, providing a targeted testing method for this phase. By generating and sending pseudo-random binary sequence data and receiving pseudo-random binary sequence data sent by the peer, actual data transmission and reception are realized in a real communication link, allowing the test process to reflect the actual transmission status of the link. Subsequently, based on the locally generated pseudo-random binary sequence data and the received pseudo-random binary sequence data sent by the peer, the number of error bits and the total number of bits are determined, converting the transmission quality into specific bit-level statistical data, and thus obtaining the pseudo-random binary sequence bit error rate as the test result. Therefore, through the above steps from mode selection, data transmission and reception, benchmark comparison to quantification calculation, a quantitative bit error rate test result can be accurately obtained in the initial link establishment phase, providing objective data support for evaluating the current link's transmission quality.

[0030] Specifically, based on the communication phase as the initial link establishment phase, a pseudo-random binary sequence test mode is selected to generate and send pseudo-random binary sequence data. This includes: based on the communication phase as the initial link establishment phase, in response to the control command of the ground monitoring system, switching to the pseudo-random binary sequence test mode, generating pseudo-random binary sequence data of the corresponding order, and sending the generated pseudo-random binary sequence data to the optical port.

[0031] It should be noted that by basing the initial link establishment phase on the communication phase, the specific timing of the operation is clearly defined, ensuring that the test actions match the initial link establishment scenario. This responds to control commands from the ground monitoring system, switching to a pseudo-random binary sequence test mode. The activation of the test mode is directly linked to the commands from the ground monitoring system, achieving remote controllability of the test mode switching. Subsequently, pseudo-random binary sequence data of the corresponding order is generated, giving the generated test data a specific order attribute to adapt to specific test configuration requirements. Finally, the generated pseudo-random binary sequence data is sent to the optical port, directly outputting the test data to the physical optical path. Thus, through the step-by-step operation of the above-mentioned phase triggering, command response, data generation, and optical port output, the process of being controlled by ground commands during the initial link establishment phase, generating specific order test data, and injecting it into the physical optical path is achieved, ensuring the controllability and adaptability of the test data source.

[0032] In addition, based on the locally generated pseudo-random binary sequence data and the pseudo-random binary sequence data sent by the other end, the number of erroneous bits and the total number of bits are determined to obtain the pseudo-random binary sequence bit error rate. This includes: performing high-speed serial-to-parallel processing on the received pseudo-random binary sequence data sent by the other end; comparing the data after high-speed serial-to-parallel processing with the locally generated pseudo-random binary sequence data bit by bit, and calculating the ratio of the number of erroneous bits to the total number of bits within a fixed time interval to obtain the pseudo-random binary sequence bit error rate.

[0033] It should be noted that high-speed serial-to-parallel conversion refers to the process by which the receiving end converts a high-speed serial bit stream into low-bit-width parallel data. By performing high-speed serial-to-parallel conversion on the pseudo-random binary sequence data sent by the receiving end, and then combining it with locally generated pseudo-random binary sequence data, the data after high-speed serial-to-parallel conversion is cyclically checked to continuously identify bit errors that occur during data transmission. The discrete error bit statistics are transformed into a proportional value within a fixed time dimension, thereby eliminating the impact of instantaneous fluctuations and accurately obtaining the pseudo-random binary sequence bit error rate that reflects the link transmission quality within that time period.

[0034] In an optional embodiment, the method of selecting a corresponding bit error rate (BER) test mode based on the determined communication stage, performing BER testing on the received data, and obtaining the test result further includes: selecting an empty frame test mode when the communication stage is a stable link stage and there is no customer service data transmission, generating and sending an empty frame containing a fixed code pattern, and receiving an empty frame sent by the peer; comparing the corresponding fixed code pattern between the locally generated empty frame and the empty frame sent by the peer to determine the number of error bits that have not undergone forward error correction decoding, and obtaining the BER before BER correction; performing forward error correction decoding on the empty frame sent by the peer, and combining it with the locally generated empty frame to compare the corresponding fixed code pattern to determine the number of error bits after forward error correction decoding, and obtaining the BER after BER correction; and obtaining the test result based on the BER before BER correction and the BER after BER correction.

[0035] It should be noted that, based on the premise that the communication phase is a stable link phase and there is no customer service data transmission, the empty frame test mode is selected to clarify the specific timing of the test execution and ensure that the test process does not interfere with normal customer services. Simultaneously, by generating and sending empty frames containing a fixed code pattern, and receiving empty frames sent by the peer, a known and definite reference benchmark is established for subsequent error comparison using the fixed code pattern. Based on the locally generated empty frames and the empty frames sent by the peer, the number of error bits is determined by directly comparing the corresponding fixed code patterns before forward error correction decoding, thus objectively reflecting the physical link's stability without error correction. The original transmission quality during error processing is used to obtain the pre-correction bit error rate (BER). After forward error correction decoding of the empty frames sent by the peer, the number of error bits is determined by comparing the corresponding fixed code pattern with the locally generated empty frames. This allows for the evaluation of the forward error correction processing's ability to correct original transmission errors, thus obtaining the post-correction BER. The test results are obtained by combining the pre-correction and post-correction BERs, ensuring that the final result includes both the original link quality dimension without error correction and the actual usable quality dimension after error correction. This ensures that a comprehensive and accurate multi-dimensional bit error performance index of the link under no-service transmission conditions can be obtained.

[0036] Specifically, generating and sending empty frames containing known fixed code patterns includes: automatically generating an empty frame structure according to the frame structure specified by the air interface link protocol frame; filling the empty frame structure with preset data; and sending the filled empty frame structure to the other end.

[0037] It should be noted that the empty frame structure is automatically generated according to the frame structure specified by the air interface link protocol frame. This ensures that the generated empty frames strictly adhere to the format requirements specified by the communication protocol, guaranteeing the standardization and legality of the empty frames transmitted in the physical link. At the same time, automatic generation eliminates the need for external manual intervention. The empty frame structure is filled with preset data. Since the preset data is fixed content known to both parties, it can provide a clear and definite reference benchmark for subsequent error comparison at the receiving end. Thus, the filled empty frame structure is sent to the other end, completing the actual injection of test data into the physical link. This allows the other end to receive the signal used for testing, providing a reliable data source for subsequent link quality assessment.

[0038] In one optional embodiment, the method of selecting a corresponding bit error rate (BER) test mode based on the determined communication stage, performing BER testing on the received data, and obtaining test results further includes: selecting a service data test mode based on the communication stage being a service transmission stage, encoding and sending the service data, and receiving the encoded service data sent by the peer; decoding the received encoded service data using forward error correction (FEC) and obtaining the number of error bits corrected during the decoding process to determine the BER before service error correction; obtaining the test results based on the BER before service error correction and the monitored alarm signals; the alarm signals are reported by FEC when the number of error bits exceeds the error correction threshold.

[0039] It should be noted that, based on the communication phase being the service transmission phase, the service data test mode is selected. The service data is encoded and sent, and the encoded service data sent by the other end is received. Because the actual service data is directly used as the processing object, the test process can be carried out synchronously with the real service transmission, enabling direct monitoring of the actual service transmission status. Based on the received encoded service data, forward error correction is used for decoding, and the number of erroneous bits corrected during decoding is obtained to determine the pre-correction bit error rate. The bit error rate is calculated by directly extracting the actual number of bits corrected by forward error correction during decoding, without relying on additional known test sequences for comparison, thus providing an objective reflection. This reflects the initial error level of service data during transmission in the physical link. Based on the pre-correction bit error rate and monitored alarm signals, test results are obtained. The alarm signals are reported when the number of error bits exceeds the correction threshold. When the number of error bits exceeds the correction threshold, it indicates that the current link error rate has reached or exceeded the processing limit of forward correction, and continued transmission will result in service data corruption. Combining this alarm signal with the pre-correction bit error rate accurately indicates whether the current link's error correction capability is approaching the safety boundary. Therefore, without interfering with normal service transmission, it accurately obtains the transmission error status of service data and keenly detects risk signals exceeding the error correction capability. Furthermore, the service data includes Ethernet data or image / video data.

[0040] It should be added that, in the transmitting direction, the spaceborne laser communication terminal performs framing, encoding, scrambling, high-speed parallel-to-serial conversion, and electro-optical conversion on-board data before transmitting it through the optical path; in the receiving direction, it performs photoelectric conversion, serial-to-parallel conversion, frame synchronization, descrambling, and decoding to extract the original data.

[0041] Pseudo-random binary sequence data, empty frames, and service data are all processed and tested through the transmission and reception directions of the spaceborne laser communication terminal. For details, please refer to the previous text, which will not be repeated here.

[0042] Step S13: Based on the test results, determine whether to switch to the next communication stage or issue a fault warning.

[0043] In one optional embodiment, the communication phase is the initial link establishment phase. When the pseudo-random binary sequence test mode is selected, based on the test results, it is determined whether to switch to the next communication phase or to issue a fault warning. This includes: determining whether the frequency of change of the pseudo-random binary sequence bit error rate within the target duration meets the preset communication bit error rate standard range; if it is determined that it meets the preset communication bit error rate standard range and is maintained for a preset time, it is determined that the acquisition and tracking is stable and the system switches to the link stability phase; or, if it is determined that it does not meet the preset communication bit error rate standard range and is greater than the upper limit of the preset communication bit error rate standard range, it is determined that the acquisition and tracking system module has not been aligned and the physical link has not been established.

[0044] It should be noted that by judging whether the frequency of change of the pseudo-random binary sequence bit error rate within the target duration meets the preset communication bit error rate standard range, the one-sidedness of relying solely on the instantaneous bit error rate for evaluation is avoided. Instead, the fluctuation of the bit error rate is examined from a time dimension, making the evaluation results more continuous and objective. After determining that the frequency of change meets the standard range, it is also required to maintain it for a preset time. This double confirmation mechanism eliminates the possibility of short-term accidental compliance and ensures that the acquisition and tracking state truly reaches stability. This provides a reliable basis for a safe switch to the link stable stage and avoids link instability caused by premature switching. When it is determined that the value does not meet the standard range and exceeds the upper limit, it is clearly determined that the acquisition and tracking system module has not been aligned and the physical link has not been established. By using this bit error rate exceeding the limit judgment method, the test data is directly correlated with the specific physical alignment state, providing a clear direction for locating the cause of the fault, thereby reasonably controlling the timing of the switching and fault warning actions in the communication stage.

[0045] In an optional embodiment, when the communication phase is a stable link phase and there is no customer service data transmission, when selecting the empty frame test mode, based on the test results, it is determined whether to switch to the next communication phase or to issue a fault warning, including: when the bit error rate after empty frame correction is zero, it is determined that the link quality meets the data transmission requirements and the system switches to the service transmission phase; or, when it is determined that the bit error rate before empty frame correction is not zero and the bit error rate after empty frame correction is not zero, it is determined that the link quality has seriously deteriorated and exceeded the upper limit of the forward error correction capability, an alarm signal exceeding the error correction capability is reported, and the ongoing service transmission is suspended, and the system returns to the initial link establishment phase to re-investigate the fault.

[0046] It should be noted that when the post-correction error rate of the empty frame is determined to be zero, the link quality is deemed to meet the data transmission requirements, and the system switches to the service transmission stage. Using zero post-correction errors as the release criterion ensures that subsequent service data transmitted to customers will not be damaged by residual errors, thus providing a reliable basis for securely switching to the service transmission stage. Conversely, when both the pre-correction and post-correction error rates of the empty frame are not zero, the link quality is determined to have severely deteriorated and exceeded the upper limit of the forward error correction capability. By combining the characteristic that both pre- and post-correction error rates are not zero, it is possible to effectively identify… In extreme cases where physical layer errors cannot be corrected by the module, the system avoids misclassifying abnormal links as usable links. After determining that the limit has been exceeded, it reports an alarm signal that exceeds the error correction capability, suspends the service being transmitted, returns to the initial link establishment stage to re-investigate the fault, issues anomaly alarms in a timely manner, actively blocks the continued transmission of damaged service data, and provides specific downgrade investigation paths to prevent the fault from further escalating. Thus, based on the actual error correction and recovery capability of the link, it accurately controls the timing of service access and promptly implements service protection and fault recovery mechanisms in the event of severe deterioration.

[0047] Furthermore, when the bit error rate after empty frame correction is determined to be zero, the link quality is deemed to meet the data transmission requirements, and the process switches to the service transmission stage. This includes: when the bit error rate before empty frame correction is not zero, and the bit error rate after empty frame correction is zero, it is determined to be normal link fluctuation or slight attenuation, and the link quality is deemed to meet the data transmission requirements, thus switching to the service transmission stage; or, when the bit error rate before empty frame correction is zero, and the bit error rate after empty frame correction is zero, the link status is determined to be excellent, and the link quality is deemed to meet the data transmission requirements, with no errors to correct in forward error correction and unimpeded service.

[0048] It should be noted that by determining that the bit error rate before empty frame correction is not zero and the bit error rate after empty frame correction is zero, it is accurately diagnosed as normal link fluctuation or slight attenuation. This effectively distinguishes the relationship between minor physical layer defects and the actual availability of the link, avoiding blindly abandoning the link due to minor physical fluctuations. Based on the above diagnosis of normal fluctuation or slight attenuation, it is further confirmed that the link quality meets the data transmission requirements and switches to the service transmission stage. Thus, by utilizing the characteristic that forward error correction has completely eliminated the original error, the link with normal fluctuations can also be effectively utilized, improving the overall availability of the communication link. By determining that the bit error rate before and after empty frame correction is zero, the link is accurately diagnosed as being in excellent condition. This clearly indicates that the current physical layer transmission is completely error-free and of excellent quality. Based on this excellent condition, the link quality is confirmed to meet the data transmission requirements. It is also clearly indicated that there are no errors to correct in the forward error correction and that the service is unimpeded. This allows the system to accurately determine that the error correction module is in a healthy state where it does not need to perform error correction when entering the service phase. This enables the system to make precise state classifications for different physical link performances and, under the premise of ensuring that the final delivered data is error-free, to reasonably allow links of different quality to enter the service transmission phase.

[0049] In an optional embodiment, the communication phase is the service transmission phase. When selecting the service data test mode, based on the test results, it is determined whether to switch to the next communication phase or to issue a fault warning. This also includes: when an alarm signal is received, it is determined that an abnormal situation of a large number of bit errors has occurred in the service transmission, the transmission of service data is suspended, and the test is switched back to pseudo-random binary sequence data or empty frames.

[0050] It should be noted that by establishing the judgment criteria based on the frequency statistics of alarm occurrences when alarm signals are received, misjudgments caused by occasional single alarms are avoided, providing objective quantitative triggering conditions for assessing link status. Based on alarm frequency exceeding limits, an abnormal situation of a large number of bit errors in service transmission is judged, so as to accurately define that the current link is in a continuously deteriorating and unusable state that cannot be effectively corrected. After the anomaly is judged, the transmission of service data is suspended in time to stop the loss in time and prevent a large amount of damaged service data from continuing to be transmitted downstream, thereby protecting the integrity of service data. The test is then switched back to pseudo-random binary sequence data or empty frames to actively eliminate the interference of complex content in the actual service data. The test mode is then returned to the basic test mode to re-examine and investigate the quality of the underlying link. This allows for the timely detection of continuously deteriorating link faults during the service transmission stage, effectively preventing the spread of damaged services, and providing a clear means of investigation for relocating underlying link problems.

[0051] In addition, based on the test results, determining whether to switch to the next communication stage or issue a fault warning also includes: if no alarm signal is received, the service is considered normal; if an alarm message is received, it indicates that the forward error correction has collapsed. At this time, the post-correction bit error rate will inevitably exist and is uncontrollable. Based on this, the system roughly estimates the abnormal state with a large number of bit errors and issues a fault warning.

[0052] It should be noted that by using the presence or absence of alarm signals as a direct criterion, a simple and effective confirmation method is provided for the continuous and normal operation of services. When an alarm message is confirmed to be received, it indicates that the forward error correction has collapsed. The occurrence of the alarm message is directly related to the failure of the error correction mechanism, which clarifies that the current link's error correction capability can no longer guarantee data integrity. Based on the collapse of forward error correction, it is pointed out that the post-correction bit error rate will inevitably exist and is uncontrollable. It is objectively deduced that the downstream received data will face unpredictable and uneliminable error risks. Based on this, the system roughly estimates the abnormal state with a large number of bit errors and issues a fault warning. In order to quickly identify serious faults and issue warning signals in a timely manner when it is impossible to accurately count the specific bit error value.

[0053] It should be added that, based on the communication phase being the service transmission phase, the service data test mode is selected, and the service data is encoded and sent, including: acquiring the service data and encoding the service data; encapsulating the encoded service data into a normal frame data structure and sending it to the other end.

[0054] In one alternative embodiment, in the 10G OOK spaceborne laser communication system, a system block diagram can be found... Figure 2 As shown, one or more satellites carry one or more onboard laser communication terminal payloads. Communication between satellites requires the onboard laser communication terminals to capture and track each other's optical layers. To verify the capture and tracking effect between the two onboard laser communication terminals and whether the communication conditions are met, it is necessary to observe the telemetry information of the onboard laser communication terminals in real time at the telemetry station. The communication bit error rate information contained in this telemetry information is particularly important for confirming whether the onboard communication environment meets the communication conditions. Therefore, this paper designs a method and device for calculating the communication bit error rate in multiple scenarios and using different methods.

[0055] The calculation and testing of the communication bit error rate are both implemented within the communication equipment of the laser communication terminal product. The specific location within the product is as follows: Figure 3 The communication control box shown includes a communication device with two directions: a transmitting direction and a receiving direction. The transmitting direction is responsible for packaging the client data into frame format data suitable for transmission in the space optical link, while the receiving direction is responsible for restoring the data transmitted on the optical path back into the client data.

[0056] like Figure 4As shown, this mainly describes the implementation of relevant functional modules in the communication control box in the transmission direction to realize the calculation of the bit error rate at the other end. First, during the initial link establishment phase, a pseudo-random binary sequence (PRBS) data generation module is required. This module can generate PRBS data of different orders via command control. The generated pseudo-random data is directly sent to the optical port through the high-speed interface, providing a data source for the PRBS bit error rate test at the receiving end. During the link stabilization phase, an empty frame structure is generated according to the frame structure specified by the air interface link protocol, i.e., an empty frame test mode. This frame structure is automatically generated when a frame is generated to maintain the link communication state in the absence of customer service transmission. Its characteristic is that the content within its frame structure is filled with known data, allowing the peer communication device to easily verify based on the corresponding known data and generate bit error rate information. During the service transmission phase, the normal frame data structure generated by the sending end carries customer data within its frame structure. In this case, the peer communication device cannot perform data analysis in the same way as with empty frames, as it cannot predict the data content within the frame. Therefore, we use a forward error correction module to encode the data, allowing the peer communication device to decode the encoded data and ultimately calculate the bit error rate.

[0057] like Figure 5 As shown, this paper focuses on describing the functional modules in the communication control box, where each module in the receiving direction corresponds to the functional module in the transmitting direction, and implements the corresponding bit error rate calculation function. In the air interface data frame receiving direction, the received data passes through the frame synchronization module, extracts the corresponding data frame based on the frame header data, and then passes through the descrambling module to descramble the data after removing the frame header, restoring the original frame structure data. After the data frame is restored, the bit error rate test function described in this paper can be performed on the restored frame structure data to calculate the corresponding bit error rate. This is mainly divided into three parts, which are described in detail below.

[0058] When the transmitting end switches to PRBS data mode, the corresponding receiving end data also enters the PRBS bit error rate test function module. This module performs cyclic verification on the PRBS data, counts the number of error bits and the total number of bits respectively, calculates their ratio value within a fixed time interval, and obtains the bit error rate value. At this time, the bit error rate can characterize the signal-to-noise ratio status of the entire spatial link and whether it can meet the communication indicators.

[0059] When the entire link is tested in PRBS mode and meets the current device's communication bit error rate standard (e.g., greater than e-7), it can be switched to empty frame bit error rate testing. At this time, the bit error rate before and after error correction is calculated by verifying the known data in the empty frame. Even if there are stable bit errors in PRBS mode, the bit error rate after error correction can still be 0 based on the performance of the forward error correction module. By observing the empty frame bit error rate, the bit error rates before and after correction can be observed more clearly and compared. When the bit error rate after correction is 0, the next working state and test can be started.

[0060] Under the condition that the post-correction bit error rate measured by the empty frame bit error rate is stable at 0, normal transmission of customer services can be carried out. At the same time, during the normal service transmission process, the information reported by the forward error correction module can still be used to calculate the pre-correction bit error rate. At the same time, alarm information of the forward error correction module exceeding the error correction capability can also be observed. If there is an alarm, the customer service may be interrupted. At this time, other abnormal phenomena can be triggered based on this alarm information, so as to quickly locate the relevant fault problems remotely on orbit.

[0061] In summary, the implementation of the three-level bit error fault monitoring function provides a reliable method for locating on-orbit communication link faults during spaceborne laser terminal communication testing, thereby improving the reliability of the test.

[0062] In summary, this invention determines the communication stage of the spaceborne laser communication terminal to clarify its exact position in the workflow, providing a foundation for subsequent targeted testing strategies. Based on the determined communication stage, a corresponding bit error rate (BER) test mode is selected. This one-to-one correspondence between stage and test mode ensures that the BER testing method strictly matches the link status and data characteristics of different communication stages, achieving precise adaptation of the testing method. Subsequently, the received data is tested using the selected test mode to obtain the test results. Because a dedicated mode matching the current stage is adopted, the obtained test results objectively reflect the actual transmission quality of the link in that specific stage. By directly using the test results as the basis for state control and risk management decisions, it ensures that the link smoothly transitions to the next stage when it meets the standards, and provides timely fault warnings when it fails to meet the standards. This constructs a closed-loop testing and control mechanism covering the entire communication process, effectively compensating for the deficiencies of existing static testing of ground equipment, ensuring the relevance of link evaluation at each stage and the safety of state transitions, and improving the accuracy of on-orbit reliability BER fault testing for spaceborne laser communication.

[0063] The following describes the on-orbit reliability error test device for spaceborne laser communication provided by the present invention. The on-orbit reliability error test device for spaceborne laser communication described below can be referred to in correspondence with the on-orbit reliability error test method for spaceborne laser communication described above.

[0064] Figure 6 A schematic diagram of an on-orbit reliability bit error fault testing device for spaceborne laser communication is shown. The device includes: Phase determination module 61 determines the communication phase of the spaceborne laser communication terminal. Test module 62 selects the corresponding bit error rate test mode according to the determined communication stage, performs bit error rate test on the received data, and obtains the test results; wherein, the communication stage includes the initial link establishment stage, the link stabilization stage and the service transmission stage, and the corresponding bit error rate test modes are pseudo-random binary sequence test mode, empty frame test mode and service data test mode, respectively. Processing module 63 determines, based on the test results, whether to switch to the next communication stage or issue a fault warning.

[0065] It should be noted that the specific principles of the embodiments of the present invention are the same as those of the method embodiments described above. For details, please refer to the method embodiments above. More detailed explanations will not be repeated here.

[0066] Figure 7 An example is a schematic diagram of the physical structure of an electronic device, such as... Figure 7 As shown, the electronic device may include a processor 710, a communications interface 720, a memory 730, and a communication bus 740. The processor 710, communications interface 720, and memory 730 communicate with each other via the communication bus 740. The processor 710 can call logical instructions in the memory 730 to execute a method for testing the on-orbit reliability of spaceborne laser communication using bit error rate (BER) faults. This method includes: determining the communication stage of the spaceborne laser communication terminal; selecting the corresponding BER test mode based on the determined communication stage; performing BER testing on the received data; and obtaining the test results. The communication stages include an initial link establishment stage, a link stabilization stage, and a service transmission stage, with corresponding BER test modes of pseudo-random binary sequence test mode, empty frame test mode, and service data test mode, respectively. Based on the test results, it is determined whether to switch to the next communication stage or to issue a fault warning.

[0067] Furthermore, the logical instructions in the aforementioned memory 730 can be implemented as software functional units and, when sold or used as independent products, can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention, essentially, or the part that contributes to the prior art, or a part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of the present invention. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0068] On the other hand, the present invention also provides a computer program product, which includes a computer program that can be stored on a non-transitory computer-readable storage medium. When the computer program is executed by a processor, the computer can execute the on-orbit reliability bit error rate fault testing method for spaceborne laser communication provided by the above methods. The method includes: determining the communication stage of the spaceborne laser communication terminal; selecting the corresponding bit error rate test mode according to the determined communication stage, performing a bit error rate test on the received data, and obtaining the test result; wherein the communication stage includes an initial link establishment stage, a link stabilization stage, and a service transmission stage, and the corresponding bit error rate test modes are a pseudo-random binary sequence test mode, a blank frame test mode, and a service data test mode, respectively; and determining whether to switch to the next communication stage or to issue a fault warning based on the test result.

[0069] In another aspect, the present invention also provides a non-transitory computer-readable storage medium storing a computer program thereon. When executed by a processor, the computer program is implemented to perform the on-orbit reliability bit error rate fault testing method for spaceborne laser communication provided by the above methods. The method includes: determining the communication stage of the spaceborne laser communication terminal; selecting a corresponding bit error rate test mode according to the determined communication stage, performing a bit error rate test on the received data, and obtaining the test result; wherein the communication stage includes an initial link establishment stage, a link stabilization stage, and a service transmission stage, and the corresponding bit error rate test modes are a pseudo-random binary sequence test mode, a blank frame test mode, and a service data test mode, respectively; and based on the test result, determining whether to switch to the next communication stage or to issue a fault warning.

[0070] The device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the modules can be selected to achieve the purpose of this embodiment according to actual needs. Those skilled in the art can understand and implement this without any creative effort.

[0071] Through the above description of the embodiments, those skilled in the art can clearly understand that each embodiment can be implemented by means of software plus necessary general-purpose hardware platforms, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solutions, in essence or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, magnetic disk, optical disk, etc., and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute the methods described in the various embodiments or some parts of the embodiments.

[0072] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for testing on-orbit reliability bit error rate faults in spaceborne laser communication, characterized in that, include: Determine the communication phase of the spaceborne laser communication terminal; Select the corresponding bit error rate test mode according to the determined communication stage, perform bit error rate test on the received data, and obtain the test results; wherein, the communication stage includes the initial link establishment stage, the link stabilization stage and the service transmission stage, and the corresponding bit error rate test modes are pseudo-random binary sequence test mode, empty frame test mode and service data test mode, respectively. Based on the test results, determine whether to switch to the next communication stage or issue a fault warning.

2. The on-orbit reliability bit error rate test method for spaceborne laser communication according to claim 1, characterized in that, Select the corresponding bit error rate (BER) test mode based on the determined communication stage, perform BER testing on the received data, and obtain the test results, including: Based on the fact that the communication phase is the initial link establishment phase, a pseudo-random binary sequence test mode is selected, pseudo-random binary sequence data is generated and sent, and pseudo-random binary sequence data sent by the other end is received. Based on the locally generated pseudo-random binary sequence data and the pseudo-random binary sequence data sent by the other end, the number of erroneous bits and the total number of bits are determined, and the pseudo-random binary sequence bit error rate is obtained as the test result.

3. The on-orbit reliability bit error rate test method for spaceborne laser communication according to claim 2, characterized in that, Based on the fact that the communication phase is the initial link establishment phase, a pseudo-random binary sequence test mode is selected, and pseudo-random binary sequence data is generated and sent, including: Based on the fact that the communication phase is the initial link establishment phase, in response to the control command of the ground monitoring system, the system switches to the pseudo-random binary sequence test mode, generates pseudo-random binary sequence data of the corresponding order, and sends the generated pseudo-random binary sequence data to the optical port. Based on the locally generated pseudo-random binary sequence data and the pseudo-random binary sequence data sent by the peer, the number of erroneous bits and the total number of bits are determined, and the pseudo-random binary sequence bit error rate is obtained, including: The pseudo-random binary sequence data received from the peer is processed by high-speed serialization and parallelization; based on the data after high-speed serialization and parallelization, it is compared bit by bit with the locally generated pseudo-random binary sequence data, and the ratio of the number of erroneous bits to the total number of bits is counted within a fixed time interval to obtain the bit error rate of the pseudo-random binary sequence.

4. The on-orbit reliability bit error rate test method for spaceborne laser communication according to claim 2, characterized in that, Based on the test results, determine whether to switch to the next communication stage or issue a fault warning, including: Determine whether the frequency of change in the pseudo-random binary sequence bit error rate within the target duration meets the preset communication bit error rate standard range; Once the preset communication bit error rate standard range is met and maintained for a preset time, the acquisition and tracking are determined to be stable, and the process switches to the link stability phase; or, If the error rate does not meet the preset communication error rate standard range and is greater than the upper limit of the preset communication error rate standard range, it is determined that the capture and tracking system module is not aligned and the physical link is not established.

5. The on-orbit reliability bit error rate test method for spaceborne laser communication according to claim 1, characterized in that, Select the appropriate bit error rate (BER) testing method based on the determined communication stage, perform BER testing on the received data, and obtain the test results, which also include: Based on the fact that the communication phase is a stable link phase and there is no customer business data transmission, select the empty frame test mode, generate and send an empty frame containing a fixed code pattern, and receive an empty frame sent by the other end. Based on the locally generated empty frame and the empty frame sent by the peer, the corresponding fixed code pattern is compared to determine the number of error bits that have not undergone forward error correction decoding, and the pre-correction error rate of the empty frame is obtained. Forward error correction decoding is performed on the empty frame sent by the peer, and the corresponding fixed code pattern is compared with the locally generated empty frame to determine the number of error bits after forward error correction decoding, and the bit error rate after empty frame correction is obtained. The test results are obtained based on the bit error rate before and after the empty frame correction.

6. The on-orbit reliability bit error rate test method for spaceborne laser communication according to claim 5, characterized in that, Generate and send empty frames containing a known fixed code pattern, including: Based on the frame structure specified in the air interface link protocol frame, an empty frame structure is automatically generated; The empty frame structure is filled with preset data, and the filled empty frame structure is sent to the other end; The process of determining whether to switch to the next communication phase or issue a fault warning based on the test results includes: When the post-correction bit error rate of the empty frame is determined to be zero, the link quality is deemed to meet the data transmission requirements, and the system switches to the service transmission phase; or, When it is determined that the bit error rate before the empty frame correction is not zero, and the bit error rate after the empty frame correction is not zero, an alarm signal exceeding the error correction capability is reported.

7. The on-orbit reliability bit error rate test method for spaceborne laser communication according to claim 6, characterized in that, When the post-correction bit error rate of the empty frame is determined to be zero, the link quality is deemed to meet the data transmission requirements, and the process switches to the service transmission stage, including: If the pre-correction bit error rate of the empty frame is determined to be non-zero, and the post-correction bit error rate is zero, it is determined to be normal link fluctuation or slight attenuation, the link quality is deemed to meet the data transmission requirements, and the system switches to the service transmission stage; or, When the bit error rate before the empty frame correction is zero and the bit error rate after the empty frame correction is zero, the link status is determined to be excellent, the link quality is determined to meet the data transmission requirements, there are no errors to correct in the forward error correction, and the service is unimpeded.

8. The on-orbit reliability bit error rate test method for spaceborne laser communication according to claim 1, characterized in that, Select the appropriate bit error rate (BER) testing method based on the determined communication stage, perform BER testing on the received data, and obtain the test results, which also include: Based on the fact that the communication stage is the service transmission stage, the service data test mode is selected, the service data is encoded and sent, and the encoded service data sent by the other end is received. Based on the received encoded service data, forward error correction is used for decoding, and the number of error bits corrected during the decoding process is obtained to determine the service error rate before correction. The test results are obtained based on the forward error rate and the monitored alarm signals; the alarm signals are reported when the number of error bits exceeds the error correction threshold.

9. The on-orbit reliability bit error rate test method for spaceborne laser communication according to claim 8, characterized in that, Based on the test results, determining whether to switch to the next communication stage or issue a fault warning also includes: Upon receiving an alarm signal, it is determined that an abnormal situation has occurred in the service transmission, resulting in a large number of bit errors. The transmission of service data is then suspended, and the system switches back to pseudo-random binary sequence data or empty frames for testing.

10. A spaceborne laser communication on-orbit reliability bit error rate fault testing device, characterized in that, include: The phase determination module determines the communication phase in which the spaceborne laser communication terminal is located. The testing module selects the corresponding bit error rate test mode according to the determined communication stage, performs bit error rate testing on the received data, and obtains the test results; wherein, the communication stage includes the initial link establishment stage, the link stabilization stage, and the service transmission stage, and the corresponding bit error rate test modes are pseudo-random binary sequence test mode, empty frame test mode, and service data test mode, respectively. Based on the test results, the processing module determines whether to switch to the next communication stage or issue a fault warning.

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