An inter-satellite cross-platform laser communication link error tracing and cooperative error control method

Abstract

The application discloses an inter-satellite cross-platform laser communication link error tracing and cooperative error control method, which firstly deploys multiple types of sensors in an inter-satellite laser communication terminal device to collect various types of state data in real time. An error characteristic database is constructed, and a machine learning algorithm is used to analyze the real-time state data. By comparing and matching the database data, an error tracing model is established to realize the identification and positioning of the error source. Then, according to the error tracing result, the corresponding cooperative error control strategy is started. Finally, a closed-loop feedback mechanism is established. If the error does not reach the expected effect, the cooperative error control strategy is adjusted again until the error is effectively suppressed. Through accurate tracing, cooperative control and closed-loop feedback, the method can improve the stability, reliability and data transmission quality of the inter-satellite laser communication link, and provides technical support for the efficient operation of the satellite internet.

Description

Technical Field

[0001] This invention relates to the field of inter-satellite laser communication technology, and in particular to a method for tracing the source of errors and coordinating error control in inter-satellite cross-platform laser communication links. Background Technology

[0002] In the cutting-edge field of inter-satellite laser communication, with the rapid development and large-scale deployment of satellite internet, the stability and accuracy of inter-satellite cross-platform laser communication links, as the core channel for data interaction between satellite nodes, have become crucial pillars determining the performance of the entire satellite network. Whether it's cross-orbit communication between low-Earth orbit and high-Earth orbit satellites, or constellation links composed of multiple satellites within the same orbit, extremely high demands are placed on the continuous and stable transmission of laser signals—millisecond-level link interruptions or minute signal deviations can lead to the failure of massive data transmission or unacceptable bit error rates, directly impacting the application efficiency of satellite internet in core scenarios such as remote sensing data backhaul and global communication coverage.

[0003] However, the operating environment of inter-satellite laser communication links is extremely complex: at the space environment level, random interference from the cosmic background radiation, electromagnetic radiation fluctuations caused by solar flares, and thermal deformation of optical components due to extreme temperature differences (-270℃ to +150℃) all directly affect the propagation path of the laser signal and the terminal equipment; at the satellite platform level, micro-vibrations generated by the satellite attitude and orbit control system adjustments and mechanical disturbances during thruster operation can cause drift in the pointing accuracy of the laser transmitting and receiving antennas, even a 0.1 arcsecond shift can cause the laser beam to deviate from the receiving field of view; at the equipment level, long-term operation of the laser can lead to performance degradation problems such as power attenuation, sensitivity drift of photodetectors, and response delay of servo drive systems, further exacerbating link errors. These factors do not exist in isolation, but rather overlap and couple with each other—for example, satellite vibration may exacerbate the thermal stress distribution of optical components, while increased temperature may amplify the noise of the equipment circuitry, forming a chain error effect of "vibration-temperature-noise," making the causes of link errors exceptionally complex.

[0004] Existing technologies generally employ a singular, passive correction approach when addressing the aforementioned errors: some solutions reduce inherent optical system errors by using ultra-precision optical lenses (such as mirrors with surface roughness below 0.1 nm), but cannot address dynamic errors caused by changes in the external environment; another approach improves noise immunity by optimizing signal demodulation algorithms (such as using coherent reception technology), but is powerless against physical errors such as antenna pointing deviation. This approach has two major limitations: First, it lacks a systematic error tracing mechanism. When an anomaly occurs in the link (such as a sudden drop in received power), technicians find it difficult to quickly distinguish whether the error originates from space radiation interference, satellite attitude jitter, or equipment aging using existing data, often requiring hours or even days to troubleshoot one by one, severely impacting fault response efficiency; Second, it cannot achieve coordinated control of multiple factors. When facing coupled errors such as "vibration + high temperature," simply activating vibration isolation devices or reducing laser power may result in poor error suppression due to the one-sidedness of control measures, or even cause new parameter imbalances.

[0005] The aforementioned problems directly lead to a bottleneck in the reliability of inter-satellite laser communication links, which is far from meeting the requirements of "seamless coverage and real-time response" of satellite internet, and have become key obstacles restricting the large-scale and industrialized development of inter-satellite laser communication technology. Summary of the Invention

[0006] This invention aims to solve the technical problems in existing inter-satellite cross-platform laser communication links, such as the difficulty in accurately tracing the source of errors and the inability to coordinate the control of multiple error factors. It enables rapid location and effective suppression of communication link errors, thereby improving the stability, reliability and data transmission quality of inter-satellite laser communication links.

[0007] This invention provides a method for tracing the source of errors and coordinating error control in inter-satellite cross-platform laser communication links, including:

[0008] The status data during the operation of the communication link is collected by sensors deployed in the inter-satellite laser communication terminal equipment. The status data includes first status data and second status data collected after the first status data.

[0009] The first-state data will be classified and stored according to the error type to construct an error feature database;

[0010] The second-state data is analyzed and processed, and an error source tracing model is established by comparing and matching it with data in the error feature database.

[0011] When a communication link error occurs, the source of the error is identified and located using an error tracing model to generate error tracing results; and

[0012] Based on the error source tracing results, the corresponding collaborative error control strategy is activated.

[0013] In one embodiment of the present invention, it further includes:

[0014] After detecting the status of the communication link after error control, the newly collected status data is input into the error tracing model for verification. If the error does not achieve the expected control effect, the collaborative error control strategy is readjusted until the error is suppressed.

[0015] In one embodiment of the present invention, the sensor includes one or more of the following:

[0016] An inertial measurement unit, configured to detect the attitude of optical elements;

[0017] A photodetector configured to detect laser emission and reception power;

[0018] A temperature sensor, configured to detect the temperature of the device; and

[0019] A radiation sensor configured to detect space radiation dose.

[0020] In one embodiment of the present invention, when a communication link error occurs, the identification and location of the source of the communication link error through the error tracing model includes determining whether the error is caused by one or more of the following: space environment factors, satellite platform factors, or factors of the communication terminal itself.

[0021] In one embodiment of the present invention, the activation of a corresponding collaborative error control strategy based on the error source tracing results includes:

[0022] If the error is caused by insufficient accuracy of the optical tracking system, then the parameters of the drive motor of the optical antenna should be adjusted in a coordinated manner and the tracking control algorithm should be optimized.

[0023] If the error is caused by satellite vibration, the vibration isolation device of the satellite platform and the active vibration suppression system inside the communication terminal will be activated simultaneously.

[0024] If the error involves the coupling of multiple factors, then a variety of control methods should be used in combination.

[0025] This invention also provides an inter-satellite cross-platform laser communication link error tracing and cooperative error control system, characterized in that it includes:

[0026] The multi-type sensor data acquisition module is configured to collect various status data in real time during the operation of the communication link;

[0027] The error feature database is configured to store state data features corresponding to different error types, providing a basis for comparison for the error source tracing model;

[0028] The error tracing model is configured to compare and match real-time data with data in the error feature database to identify and locate the source of communication link errors.

[0029] The collaborative error control strategy execution module is configured to activate the corresponding collaborative error control strategy based on the error source results obtained from the error tracing model.

[0030] The closed-loop feedback mechanism module is configured to continuously monitor the communication link status after error control, ensuring the continuity and effectiveness of error control and keeping the communication link in a stable operating state.

[0031] In one embodiment of the present invention, the multi-type sensor data acquisition module includes:

[0032] An inertial measurement unit is configured to detect the attitude of optical elements;

[0033] A photodetector is configured to detect laser emission and reception power;

[0034] A temperature sensor is configured to detect the temperature of the device.

[0035] A radiation sensor is configured to detect space radiation dose.

[0036] In one embodiment of the present invention, the error feature database includes:

[0037] The data classification unit is configured to classify the historical operational data of the laser communication terminal;

[0038] The feature extraction unit is configured to extract error features from the classified historical data;

[0039] The database maintenance unit is configured to periodically update the database content, incorporating new error types and characteristic data.

[0040] In one embodiment of the present invention, the error tracing model includes:

[0041] The data preprocessing unit is configured to receive real-time data transmitted from the sensor and perform filtering, noise reduction, and standardization processing.

[0042] The algorithm processing unit is configured to carry out machine learning algorithms based on vector machines and random forests to perform operations on the feature vectors of preprocessed real-time data.

[0043] The error localization unit is configured to compare the algorithm results with the error feature database to determine the specific source of the error.

[0044] In one embodiment of the present invention, the cooperative error control strategy execution module includes:

[0045] The strategy selection unit is configured to select a corresponding scheme from a preset control strategy library based on the error tracing results;

[0046] The multi-dimensional control unit is configured to perform specific control operations for different error sources;

[0047] The coupled error processing unit is configured to comprehensively call multiple control units and coordinate the operating parameters of each unit when the error is caused by the coupling of multiple factors.

[0048] The present invention has the following beneficial effects:

[0049] (1) By deploying multiple types of sensors (such as high-precision inertial measurement units, photoelectric detectors, temperature sensors, etc.) to collect real-time status data such as attitude, power, and temperature of the communication link, and combining machine learning algorithms with a pre-built error feature database, an error tracing model can be constructed to quickly and accurately locate the source of error. This process breaks through the limitations of traditional single troubleshooting methods and can quickly determine whether the error is caused by space environment factors (such as background radiation, extreme temperature), satellite platform factors (such as vibration, attitude control deviation) or communication terminal factors (such as insufficient optical tracking accuracy, equipment performance degradation), greatly shortening the problem troubleshooting time and significantly improving the efficiency of fault handling.

[0050] (2) The collaborative error control strategy initiated based on the error source tracing results can take comprehensive measures to address different error sources and multi-factor coupling scenarios. For example, for errors caused by the coupling of satellite vibration and high temperature, vibration isolation devices (such as rubber vibration isolation pads and spring vibration isolators) can be activated simultaneously, optical tracking system parameters can be adjusted, and equipment heat dissipation schemes can be optimized, thus avoiding the limitations of a single control method on coupled errors. This multi-dimensional collaborative control method effectively solves the problem of different error factors influencing each other and being difficult to suppress individually, significantly improving the overall effect of error control.

[0051] (3) The closed-loop feedback mechanism continuously inputs newly collected data into the error tracing model for verification by real-time monitoring of the link status after error control. If the error does not meet expectations, the control strategy is dynamically adjusted (such as optimizing the damping coefficient of the vibration isolation device and improving the tracking algorithm), forming a continuous optimization cycle of "detection-evaluation-adjustment". This mechanism ensures the continuity and effectiveness of error control, enabling the communication link to maintain a stable operating state in the complex and ever-changing space environment, thereby improving the data transmission quality, reliability and stability of inter-satellite laser communication, and providing strong technical support for the efficient and continuous operation of satellite internet. Attached Figure Description

[0052] Figure 1A flowchart of an inter-satellite cross-platform laser communication link error tracing and cooperative error control method according to an embodiment of the present invention is shown; and

[0053] Figure 2 A block diagram of an inter-satellite cross-platform laser communication link error tracing and collaborative error control system is shown in one embodiment of the present invention. Detailed Implementation

[0054] In the following description, the invention is described with reference to various embodiments. However, those skilled in the art will recognize that the embodiments may be practiced without one or more specific details or with other alternatives and / or additional methods, materials, or components. In other instances, well-known structures, materials, or operations are not shown or described in detail so as not to obscure the inventive points of the invention. Similarly, for illustrative purposes, specific quantities, materials, and configurations are set forth to provide a comprehensive understanding of embodiments of the invention. However, the invention is not limited to these specific details.

[0055] In this invention, the various embodiments are merely intended to illustrate the solutions of the invention and should not be construed as limiting.

[0056] In this specification, references to "an embodiment" or "this embodiment" mean that a particular feature, structure, or characteristic described in connection with that embodiment is included in at least one embodiment of the invention. The phrase "in one embodiment" appearing throughout this specification does not necessarily refer to the same embodiment in all instances.

[0057] Furthermore, the numbering of the steps in the methods of the present invention does not limit the execution order of the method steps. Unless otherwise specified, the method steps may be executed in different orders.

[0058] The present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0059] Figure 1 A flowchart of an inter-satellite cross-platform laser communication link error tracing and collaborative error control method according to an embodiment of the present invention is shown.

[0060] like Figure 1 As shown, in one embodiment of the present invention, taking an inter-satellite laser communication system of a satellite constellation as an example in practical applications, the method flow for inter-satellite cross-platform laser communication link error tracing and cooperative error control includes:

[0061] The S100 status data acquisition system employs multiple types of sensors installed on the laser communication terminal of each satellite, including a high-precision inertial measurement unit (with a measurement accuracy of 0.01 arcseconds), a high-sensitivity photodetector (with a power measurement accuracy of 0.1μW), and a temperature sensor (accuracy ±0.5℃). These sensors transmit data such as optical antenna attitude, laser power, and equipment temperature to the satellite's data processing module at a frequency of 10 times per second.

[0062] The S200 constructs an error feature database, which is obtained by analyzing and organizing the operating data of this model of laser communication terminal under various simulated environments (such as different temperatures, vibration intensities, and radiation dose conditions). The database contains hundreds of error types and their corresponding feature data.

[0063] The S300 establishes an error tracing model, uses machine learning algorithms to analyze and process the collected real-time status data, and compares and matches it with data in the error feature database to establish an error tracing model, enabling rapid identification and accurate location of communication link error sources.

[0064] In one communication instance, the S400 positioning error was detected when the system detected an abnormal drop in laser receiving power. Analysis using an error tracing model revealed both an optical antenna pointing angle shift (up to 0.5 arcseconds) and an increase in equipment temperature (exceeding normal operating temperature by 10°C). Based on the error characteristic database, the error was determined to be caused by a combination of satellite vibration leading to optical antenna shift and high temperature causing a performance degradation in the laser transmitting unit.

[0065] The S500 employs a cooperative error control strategy. The cooperative error control strategy execution module activates the satellite platform's vibration isolation device, using rubber vibration isolation pads and spring vibration isolators to reduce the impact of satellite vibration on the communication terminal. Simultaneously, it adjusts the drive motor parameters of the optical tracking system to re-align the optical antenna. Furthermore, it sends commands through the ground control center to reduce the operating current of the laser emission unit and cool it down.

[0066] The S600 closed-loop feedback detection module continuously monitors the communication link status, inputting newly collected data back into the error tracing model for verification every 5 minutes. If the error is still not effectively controlled, the control strategy is readjusted, such as further increasing the damping coefficient of the vibration isolation device and optimizing the tracking control algorithm, until the laser receiving power returns to normal and the communication link error is controlled within the allowable range.

[0067] Figure 2 A block diagram of an inter-satellite cross-platform laser communication link error tracing and collaborative error control system is shown in one embodiment of the present invention.

[0068] In one embodiment of the present invention, the inter-satellite cross-platform laser communication link error tracing and collaborative error control system includes:

[0069] The multi-sensor data acquisition module 100 is responsible for collecting various status data during the operation of the communication link in real time, such as the pointing angle of the optical antenna, the intensity change of the laser beam, and the operating temperature of the equipment. It transmits the data to the satellite's data processing module at a frequency of 10 times per second, providing a data foundation for subsequent error analysis.

[0070] The inertial measurement unit 110 is installed at the optical antenna base to capture antenna attitude changes in real time.

[0071] The photodetector 120 is integrated into the laser receiving port to directly detect the intensity of the laser signal.

[0072] Temperature sensors 130 are evenly distributed on the surface of core heat-generating components (such as lasers and drive circuits) of terminal devices to comprehensively sense the temperature distribution of the device.

[0073] Radiation sensor 140 is a radiation sensor that detects spatial radiation dose, enabling more comprehensive collection of environmental data.

[0074] The Error Feature Database 200 was constructed by analyzing and organizing the operational data of this laser communication terminal model under various simulated environments (such as different temperatures, vibration intensities, and radiation dose conditions). The database stores the state data characteristics corresponding to different error types, including hundreds of error types and their characteristic data, providing a comparison basis for error tracing models and helping to determine the source of errors.

[0075] Data classification unit 210 classifies historical operating data of laser communication terminals under simulated environments (such as different temperatures, vibrations, and radiation conditions). Based on the source of error (space environment, satellite platform, terminal itself) and the form of error manifestation (angle shift, power fluctuation, signal attenuation, etc.), the data is divided into different categories, laying the foundation for subsequent feature extraction.

[0076] The feature extraction unit 220 extracts error features from the classified historical data. For example, for errors caused by temperature, it extracts the correlation features between the rate of temperature change and the laser beam drift; for errors caused by satellite vibration, it extracts the corresponding features of vibration frequency, amplitude and antenna pointing error, and stores these features in a quantized manner.

[0077] Database maintenance unit 230 regularly updates the database content, incorporating new error types and characteristic data. Simultaneously, it cleans historical data, removing outliers and redundant information to ensure the accuracy and validity of the characteristic data in the database, providing a reliable comparison benchmark for error tracing.

[0078] Error source tracing model 300 utilizes machine learning algorithms (such as those based on Support Vector Machines (SVM)) to analyze and process the collected real-time status data. By comparing and matching real-time data with data in an error feature database, it achieves rapid identification and precise location of communication link error sources. This model can determine whether the error is caused by space environment factors (such as background radiation interference and extreme temperature changes), satellite platform factors (such as satellite vibration and attitude control errors), or factors within the communication terminal itself (such as insufficient accuracy of the optical tracking system and performance degradation of the laser emitting unit).

[0079] The data preprocessing unit 310 receives real-time data transmitted from the sensor and performs filtering, noise reduction, and standardization. It removes random noise from the data (such as sudden anomalies caused by electromagnetic interference) and converts parameters of different physical quantities (such as angle, power, and temperature) into feature vectors of a unified dimension, facilitating subsequent algorithm analysis.

[0080] The algorithm processing unit 320 is equipped with machine learning algorithms such as Support Vector Machine (SVM) and Random Forest to perform calculations on the preprocessed real-time data feature vectors. By comparing the similarity with feature vectors in the error feature database, the matching probability of different error types is calculated.

[0081] The error localization unit 330 determines the specific source of the error based on the algorithm's calculation results. If the matching probability of a certain type of error exceeds a preset threshold (e.g., 90%), it determines that the error is caused by that source, specifying whether it is due to space environment factors (e.g., cosmic radiation interference), satellite platform factors (e.g., attitude control system jitter), or communication terminal factors (e.g., optical lens aging).

[0082] The collaborative error control strategy execution module 400 initiates corresponding collaborative error control strategies based on the error source results obtained from the error tracing model. If the error is caused by insufficient accuracy of the optical tracking system, the drive motor parameters of the optical antenna are adjusted collaboratively, and the tracking control algorithm is optimized. If the error is caused by satellite vibration, the vibration isolation device of the satellite platform and the active vibration suppression system inside the communication terminal are activated simultaneously. If the error involves multiple coupled factors, multiple control methods are used comprehensively, such as adjusting the optical system while optimizing the signal processing algorithm and enhancing the noise suppression capability, to achieve comprehensive processing of multiple error factors.

[0083] The strategy selection unit 410 selects a corresponding scheme from a preset control strategy library based on the error source tracing results. For example, if the error originates from satellite platform vibration, a vibration suppression strategy is invoked; if the error is caused by excessive terminal temperature, a temperature regulation strategy is activated.

[0084] The multi-dimensional control unit 420 performs specific control operations for different error sources. These include: an optical antenna drive unit (adjusting motor speed and direction to correct pointing angle), a laser power adjustment unit (changing operating current to stabilize laser output power), a temperature control unit (starting cooling fans or heating elements to control equipment temperature within a suitable range), and a satellite platform coordination unit (sending commands to the satellite attitude control system to adjust platform stability).

[0085] The coupling error processing unit 430, when errors are caused by the coupling of multiple factors (such as vibration + high temperature), comprehensively calls multiple control units and coordinates the operating parameters of each unit. For example, while activating the vibration isolation device, it increases heat dissipation and optimizes the antenna tracking frequency to avoid interference between different control methods.

[0086] The closed-loop feedback mechanism module 500 continuously monitors the communication link status after error control, and inputs newly collected data back into the error tracing model for verification every 5 minutes. If the error is still found to be not under control as expected, the collaborative error control strategy is readjusted, such as further increasing the damping coefficient of the vibration isolation device and optimizing the tracking control algorithm, until the laser receiving power returns to normal and the communication link error is controlled within the allowable range, ensuring the continuity and effectiveness of error control and keeping the communication link in a stable operating state.

[0087] Although various embodiments of the invention have been described above, it should be understood that they are presented by way of example only and not as limitations. It will be apparent to those skilled in the art that various combinations, modifications, and alterations can be made without departing from the spirit and scope of the invention. Therefore, the breadth and scope of the invention disclosed herein should not be limited by the exemplary embodiments disclosed above, but should be defined solely by the appended claims and their equivalents.

Claims

1. A method for tracing the source of errors and coordinating error control in inter-satellite cross-platform laser communication links, characterized in that, include: The status data during the operation of the communication link is collected by sensors deployed in the inter-satellite laser communication terminal equipment. The status data includes first status data and second status data collected after the first status data. The first-state data will be classified and stored according to the error type to construct an error feature database; The second-state data is analyzed and processed, and an error source tracing model is established by comparing and matching it with data in the error feature database. When a communication link error occurs, the source of the communication link error is identified and located through an error tracing model to generate an error tracing result; Based on the error source tracing results, activate the corresponding collaborative error control strategy; as well as After detecting the status of the communication link after error control, the newly collected status data is input into the error tracing model again for verification. If the error does not achieve the expected control effect, the collaborative error control strategy is readjusted until the error is suppressed. The sensor mentioned above includes: An inertial measurement unit, configured to detect the attitude of optical elements; A photodetector configured to detect laser emission and reception power; A temperature sensor, configured to detect the temperature of the device; and A radiation sensor configured to detect space radiation dose.

2. The method according to claim 1, characterized in that, When communication link errors occur, the source of the error is identified and located through the error tracing model, including determining whether the error is caused by one or more of the following factors: space environment factors, satellite platform factors, or factors of the communication terminal itself.

3. The method according to claim 2, characterized in that, Based on the error source tracing results, the corresponding collaborative error control strategies include: If the error is caused by insufficient accuracy of the optical tracking system, then the parameters of the drive motor of the optical antenna should be adjusted in a coordinated manner and the tracking control algorithm should be optimized. If the error is caused by satellite vibration, the vibration isolation device of the satellite platform and the active vibration suppression system inside the communication terminal will be activated simultaneously. If the error involves the coupling of multiple factors, then a variety of control methods should be used in combination.

4. A cross-platform inter-satellite laser communication link error tracing and collaborative error control system, characterized in that, include: The multi-type sensor data acquisition module is configured to collect various status data in real time during the operation of the communication link; The error feature database is configured to store state data features corresponding to different error types, providing a basis for comparison for the error source tracing model; The error tracing model is configured to compare and match real-time data with data in the error feature database to identify and locate the source of communication link errors. The collaborative error control strategy execution module is configured to activate the corresponding collaborative error control strategy based on the error source results obtained from the error tracing model. The closed-loop feedback mechanism module is configured to continuously monitor the communication link status after error control, ensuring the continuity and effectiveness of error control, and keeping the communication link in a stable operating state at all times. The multi-type sensor data acquisition module includes: An inertial measurement unit is configured to detect the attitude of optical elements; A photodetector is configured to detect laser emission and reception power; A temperature sensor is configured to detect the temperature of the device. A radiation sensor is configured to detect space radiation dose.

5. The inter-satellite cross-platform laser communication link error tracing and collaborative error control system according to claim 4, characterized in that, The error feature database includes: The data classification unit is configured to classify the historical operational data of the laser communication terminal; The feature extraction unit is configured to extract error features from the classified historical data; The database maintenance unit is configured to periodically update the database content, incorporating new error types and characteristic data.

6. The inter-satellite cross-platform laser communication link error tracing and collaborative error control system according to claim 4, characterized in that, The error tracing model includes: The data preprocessing unit is configured to receive real-time data transmitted from the sensor and perform filtering, noise reduction, and standardization processing. The algorithm processing unit is configured to carry out machine learning algorithms based on vector machines and random forests to perform operations on the feature vectors of preprocessed real-time data. The error localization unit is configured to compare the algorithm results with the error feature database to determine the specific source of the error.

7. The inter-satellite cross-platform laser communication link error tracing and cooperative error control system according to claim 4, characterized in that, The collaborative error control strategy execution module includes: The strategy selection unit is configured to select a corresponding scheme from a preset control strategy library based on the error tracing results; The multi-dimensional control unit is configured to perform specific control operations for different error sources; The coupled error processing unit is configured to comprehensively call multiple control units and coordinate the operating parameters of each unit when the error is caused by the coupling of multiple factors.

Images