Autonomous operation system for low-orbit satellite payload

Abstract

The application discloses a low-orbit satellite load autonomous operation system and relates to the technical field of satellite communication. The application adopts a three-layer modular architecture of a resource allocation layer, a load control layer and an application service layer, constructs a three-dimensional function system of "task autonomous decomposition-resource dynamic scheduling-fault prediction fault-tolerant processing", and realizes an "resource-control-application" end-to-end autonomous closed loop. The resource allocation layer optimizes resource scheduling through link management and route management, the load control layer realizes load independent control and fault self-recovery, and the application service layer completes task autonomous planning and whole-process execution. The application can improve communication capacity and link stability, significantly reduce ground operation and maintenance pressure, enhance system reliability and task flexibility, provide on-orbit verification data for load component selection and redundancy design, and is suitable for large-scale low-orbit constellation engineering practice.

Description

Technical Field

[0001] This invention relates to the field of satellite communication technology, specifically to an autonomous operation system for low-Earth orbit satellite payloads, applicable to the autonomous management and control of payloads in large-scale low-Earth orbit satellite constellations. Background Technology

[0002] With the large-scale deployment of low-Earth orbit satellite constellations, satellite payload autonomous operation technology still has significant shortcomings: when executing mission instructions, it is impossible to fully consider the current working mode and health status of the satellite, which can easily lead to loss of control over the working status; at the same time, the formulation of mission instructions and status monitoring rely too much on the ground operation and maintenance center, resulting in poor flexibility in mission adjustment, weak fault response capability, and high pressure on ground operation and maintenance; and this technology has not yet achieved efficient integration with payload system configuration, reliability design and satellite application scenarios, making it difficult to fully improve payload utilization efficiency and system cost-effectiveness. Summary of the Invention

[0003] This invention aims to provide an autonomous operation system for low-Earth orbit (LEO) satellite payloads to address the problems of insufficient autonomous operation capability and high ground maintenance pressure in existing technologies. It constructs a three-dimensional functional system of "autonomous task decomposition - dynamic resource scheduling - fault prediction and fault-tolerant processing" to achieve an end-to-end autonomous closed loop of "resources-control-application" and ensure the efficiency of autonomous execution throughout the entire process.

[0004] To achieve the above-mentioned technical effects, the technical solution adopted by the present invention is as follows:

[0005] An autonomous operation system for low-Earth orbit satellite payloads includes a resource allocation layer, a payload control layer, and an application service layer;

[0006] The resource allocation layer is used to implement physical layer resource and protocol resource scheduling, including an autonomous transmission link management module and an autonomous routing and network management module;

[0007] The load control layer is used to realize load hierarchical management and fault prediction and fault tolerance, shorten the load invalid start-up time, and perform rapid on-orbit fault handling to avoid affecting the upgrade.

[0008] The application service layer is used to realize autonomous operation planning and execution, complete the autonomous decomposition of satellite payload tasks and command generation, and reduce the pressure of ground operation and maintenance.

[0009] Furthermore, the link prediction model in the autonomous transmission link management module adds an active control mode, which dynamically introduces additional attenuation values ​​from the environment. and the deviation adjustment value between the theoretical estimate and the measured value in orbit A link budget quantitative analysis model is introduced to construct an active early warning and forward-looking control mechanism.

[0010] Furthermore, the implementation process of the active control method is as follows:

[0011] The satellite's position vector in the Earth-fixed coordinate system acquired by the satellite platform Velocity vector Subtracting the coordinates of the satellite and the ground station yields the pointing vectors of the satellite and the ground station, respectively. Let this vector be in the Earth-fixed coordinate system. Based on the above parameters, the theoretical values ​​of communication distance, link loss, and received signal-to-noise ratio are calculated respectively. The calculation formulas are as follows: ; ; ; in: Communication distance, in km; Operating frequency, in MHz; Link attenuation, measured in dB; Additional attenuation values ​​are introduced dynamically for the environment and are retrieved in real time from the distributed ledger environment parameter library, in dB. This is the adjustment value for the deviation between the theoretical value of the signal-to-noise ratio budget and the measured value in orbit. It is dynamically updated through in-orbit closed-loop calibration and is expressed in dB.

[0012] The satellite uses the transmit power, link budget L, and satellite payload reception capability reported by the terminal during the network access process. The value completes the theoretical estimate of the signal-to-noise ratio budget. And combined with real-time signal-to-noise ratio estimates After completing the adjustment, the uplink error was calculated. The calculation formula is: ; ; in, This represents the beam transmit power, measured in dBW. The value is the antenna gain of the receiving system. With noise temperature The value is expressed in dB / K. It is the signal power of the receiving system. With noise power spectral density The ratio, in dBHz; The downlink then calculates the signal-to-noise ratio (SNR) budget based on the terminal's receiving capability, link budget, and agreed-upon transmit power for the satellite payload. This estimate is then adjusted in conjunction with the real-time SNR estimate to determine the downlink error. .

[0013] Furthermore, the autonomous transmission link management module implements a rate adaptive adjustment function, supporting both passive response control and active early warning control modes.

[0014] Passive response control is achieved by adjusting the link rate in real time based on the link parameters returned from the peer; proactive early warning control is used to predict and warn of link status in the future, specifically by integrating pre-stored spatial environment parameters, theoretical estimates of link budget, and measured values ​​to conduct a multi-dimensional comprehensive analysis, and when the prediction... When the fluctuation exceeds the preset threshold, a rate reduction process is triggered. Before the fluctuation occurs, the transmission rate is dynamically adjusted to the optimal level to ensure the stability and reliability of the communication link.

[0015] Furthermore, the load classification and control module, while supporting both on-demand and on-path telemetry and control, adopts a load monitoring method based on the power supply link to achieve beam resource scheduling, service mode switching, service status monitoring, and working mode switching. The telemetry status is fully covered and updated at the millisecond level.

[0016] Furthermore, the fault prediction and fault tolerance process is as follows: First, key status information is extracted at three levels: individual load unit, load subsystem, and whole satellite; then, corresponding processing is carried out according to the fault level, including resetting the software module level for individual unit anomalies, reloading or backing up the program for subsystem anomalies, and cutting off the power supply bus of the individual unit and reporting for whole satellite anomalies.

[0017] Compared with the prior art, the present invention has the following advantages:

[0018] 1. The communication capacity can be greatly improved by the autonomous power supply link establishment and flexible switching function module.

[0019] 2. Reduce ground maintenance pressure: Achieve frequency interference avoidance and unplanned interruption recovery between high and low orbit constellations, reducing the amount of ground command uploading and maintenance personnel requirements.

[0020] 3. Enhance system reliability and flexibility: effectively shorten the invalid power-on time of satellite payloads, improve system reliability through fault prediction and fault-tolerant processing, and enhance mission flexibility through autonomous planning and execution.

[0021] 4. Optimize construction costs: Provide important on-orbit verification data for the selection of low-Earth orbit satellite payload components and the design of primary and backup redundancy, which can be extended to large-scale low-Earth orbit constellation engineering practices. Attached Figure Description

[0022] Figure 1 This is a design architecture diagram of the autonomous operation system for low-Earth orbit satellite payloads, including the autonomous operation system and method.

[0023] Figure 2This is a flowchart and connection diagram illustrating the adaptive adjustment of the autonomous operation system and method for low-Earth orbit satellite payloads.

[0024] Figure 3 This is a flowchart of the fault prediction and fault-tolerant processing functions of the autonomous operation system and method for low-orbit satellite payloads. Detailed Implementation

[0025] The following is in conjunction with the appendix Figure 1 The present invention will be further described with reference to specific embodiments.

[0026] An autonomous operation system for low-orbit satellite payloads includes a three-layer modular architecture consisting of a resource allocation layer, a payload control layer, and an application service layer. This architecture constructs a three-dimensional functional system encompassing "autonomous task decomposition, dynamic resource scheduling, and fault prediction and tolerance." The three-layer architecture works in synergy to achieve full-process autonomy from resource scheduling to payload control and application execution.

[0027] The specific functional modules of each layer are as follows:

[0028] 1) Resource Allocation Layer: This layer is primarily used for the dynamic optimization and scheduling of physical and protocol resources, addressing issues such as frequent changes in low-Earth orbit satellite constellation topology, near-far effects in satellite-to-ground links, and uncertainties in the wireless channel environment. It improves satellite communication capacity and link stability, and includes two core functional modules:

[0029] ① Autonomous Transmission Link Management Module: Based on multi-dimensional data such as real-time satellite position, distribution of network terminals, reception status assessment, and peer parameter feedback, it integrates a satellite-to-ground link prediction model and an adaptive adjustment algorithm to achieve dual-dimensional optimization of communication rate in both prediction and real-time mode. The satellite-to-ground link prediction model incorporates a space environment parameter library and link estimation error values, retrieves dynamic environmental attenuation values ​​in real time, and combines the deviation adjustment values ​​from on-orbit closed-loop calibration to complete precise link adjustment. When the link loses synchronization, it automatically switches to the lowest speed level to ensure communication continuity.

[0030] ② Autonomous Routing and Network Management Module: Employs Layer 2 autonomous routing technology, nodes complete link-layer routing synchronization and path calculation by sending routing frames without IP information, adapting to dynamic changes in the topology of the low-Earth orbit satellite network; based on Link State Advertisement (LSA), it senses the connection status between constellation satellites and the availability of satellite-to-ground feeder links, and uses the path state-based shortest path algorithm (LS-Dijkstra) to select the best communication path, reducing control layer complexity and onboard routing pressure.

[0031] 2) Payload Control Layer: This layer is crucial for enabling independent management and self-healing of payloads, reducing ineffective payload startup time, decreasing dependence on the satellite platform, and improving on-orbit service quality and service life. It includes two core functional modules:

[0032] ① Payload hierarchical management module: In addition to supporting on-demand telemetry and control and on-path telemetry and control, a new payload monitoring method based on the feeder link is added. The payload monitoring unit is independently responsible for execution and monitoring, without relying on the satellite platform. It reuses high-speed service interface transmission with a transmission rate of Gbps, supports the execution of all remote control commands of the payload, and the telemetry content covers all payload information and is updated frequently. It realizes functions such as beam resource scheduling, service mode switching, and working mode switching, avoiding the limitations of satellite platform processing capabilities.

[0033]

[0034] ② Fault Prediction and Fault Tolerance Module: This module uses factors such as load fault level detection, fault location, and fault recovery as inputs to the digital model. It extracts key status information at three levels: "individual load," "subsystem load," and "whole satellite," enabling autonomous fault identification and hierarchical processing. In the event of an individual load failure, a software module-level reset is performed first; if failure persists, the subsystem is reported. In the event of a subsystem failure, program reloading, neighboring satellite resource coordination, or backup startup are executed; if failure still occurs, the whole satellite is reported. In the event of a whole satellite failure, the primary power bus of the individual load is directly de-energized and reported to the health management module, extending the load's operational lifespan.

[0035] 3) Application Service Layer: This layer is primarily used to enable autonomous planning and full-process execution of payload missions, reducing interaction with ground operations and maintenance centers and improving the flexibility of constellation missions. It includes four core functional modules:

[0036] ① Autonomous Operation Planning and Execution Module: Based on the mission plan, business usage strategy, constraints and other prerequisites formulated by the ground, combined with satellite position, attitude and orbit control data and autonomously acquired working status, it autonomously completes mission scheduling and parsing, instruction generation and decomposition execution, realizing flexible payload application and energy optimization management;

[0037] ② Payload Autonomous Power-On / Off Module: Supports storage of multiple working models and autonomously completes the entire process of payload power-on, parameter configuration, service establishment, service exit and power-off based on satellite time, orbital parameters, energy status, etc., without relying on the satellite power distribution box (except for the payload control module), reducing the demand on satellite storage resources;

[0038] ③ Autonomous Interference Avoidance Module: The low-orbit satellite analyzes the pointing angle based on the frequency avoidance table and real-time satellite parameters to determine if it meets the avoidance angle requirements. If not, it combines the current Ka band usage and resource allocation status to select strategies such as cross-satellite or local frequency points and bandwidth adjustments to achieve interference avoidance against GEO satellites, which complies with the relevant regulations of the International Telecommunication Union.

[0039] ④ Autonomous power supply link establishment and flexible switching module: By configuring two power supply link payloads, a single satellite can achieve uninterrupted relay communication between multiple gateway stations; the satellite calculates the reliability of the current path and the gateway station it is about to enter in real time. While communicating with the current gateway station, it schedules another power supply link to point to the target gateway station to update the routing table. Then, it autonomously switches the routing table to ensure that the communication service is uninterrupted, without loss, and without out-of-order, and avoids latency jitter.

[0040] Reference Figure 2 The basic working principle of this invention is as follows:

[0041] Autonomous transmission link management module: Based on communication distance, spatial environment, received signal level and signal-to-noise ratio estimation, and peer parameter feedback, it generates real-time operating parameter adjustment commands to adjust parameters such as symbol rate, modulation method, and coding method, thereby improving link communication quality and efficiency. Specifically, it includes:

[0042] Channel estimation and quality feedback: The receiver completes level estimation and signal-to-noise ratio estimation, and feeds back the quality parameters to the local link prediction model and the transmitter.

[0043] Link prediction model: Based on channel quality feedback parameters, satellite ephemeris parameters, a pre-stored environmental parameter database for a certain period, and adjustment values ​​for deviations between theoretical values ​​and on-orbit measured values ​​of other beam budgets, a satellite-to-ground link prediction model is established. An active early warning and passive adjustment mechanism is constructed, and relevant parameter configurations are completed. The detailed implementation process is as follows:

[0044] The position vector of the satellite in the Earth-fixed coordinate system obtained by the satellite platform is denoted as... The velocity vector is Subtracting the coordinates of the satellite and the ground station yields the pointing vectors of the satellite and the ground station, respectively. Let this vector be expressed in Earth-fixed coordinates as... Based on the above parameters, the theoretical values ​​of communication distance, link loss, and received signal-to-noise ratio are calculated respectively. The calculation formulas are as follows:

[0045]

[0046]

[0047]

[0048] in: Communication distance, in km; Operating frequency, in MHz; Link attenuation, measured in dB; Additional attenuation values ​​are introduced dynamically for the environment and are retrieved in real time from the distributed ledger environment parameter library, in dB. The deviation adjustment value between the theoretical value of the signal-to-noise ratio budget and the measured value in orbit is dynamically updated through in-orbit closed-loop calibration, and the unit is dB; Xg, Yg, and Zg are satellite vectors.

[0049] The satellite uses the transmit power, link budget L, and satellite payload receiving capability reported by the terminal during the network access process. The value is equal to the theoretical estimate of the signal-to-noise ratio budget. And combined with real-time signal-to-noise ratio estimates After completing the adjustment, the uplink error was calculated. The calculation formula is:

[0050]

[0051]

[0052] in, This represents the beam transmit power, measured in dBW. The value is the antenna gain of the receiving system. With noise temperature The value is expressed in dB / K. It is the signal power of the receiving system. With noise power spectral density Ratio, in dBHz.

[0053] The downlink then calculates the signal-to-noise ratio (SNR) budget based on factors such as terminal receiving capability, link budget, and agreed-upon satellite payload transmit power. This estimate is then adjusted in conjunction with the real-time SNR estimate to calculate the downlink error. ;

[0054] Adaptive adjustment algorithm: Based on the channel quality parameters fed back from the receiver, the communication rate of the transmitter is passively adjusted. During the adjustment process, the error between the predicted and actual values ​​is monitored in real time. The modulation strategy is as follows:

[0055] ① The demodulation unit of the ground equipment estimates the downlink received signal-to-noise ratio and periodically reports it to the satellite;

[0056] ② The satellite demodulation unit parses the ground-reported link information and adjusts the downlink signal-to-noise ratio (SNR). The system compares the data with the modulation and coding pattern table stored on the satellite and reports the results to the payload monitoring unit; it can be updated in orbit.

[0057] ③ If the parsed downlink reception Access above the next level The load monitoring unit generates a command to jump the downlink modulation and coding mode to the next level; if the parsed downlink received... Below the current modulation and coding mode's cutoff The load monitoring unit generates a command to jump the downlink modulation and coding mode to the next level;

[0058] ④ If the parsed downlink reception Not greater than the next level of admission And not less than the current mode's criterion. If so, the downlink modulation and coding mode remains unchanged.

[0059] ⑤ If, during the adaptive adjustment process, the link prediction model identifies fluctuations that exceed the fluctuation threshold, a mode adjustment is triggered, and the corresponding rate adjustment is completed before that moment to ensure link reliability.

[0060] The uplink rate adaptive strategy is basically the same as described above.

[0061] The following is combined with Figure 3 The present invention will be further described with reference to specific embodiments.

[0062] This functional module stores payload health status data in real time through a configured non-volatile storage area and extracts key status information hierarchically according to a three-level architecture of "payload unit - payload subsystem - satellite as a whole". Relevant log files can be downloaded to the ground operation and maintenance center as needed according to mission requirements. Among them, the key information of the payload unit includes core parameters such as telemetry polling frame count, software version loading status, and watchdog operation status. When an anomaly occurs, the software module-level reset operation is performed first. If the status is not restored after the reset, the anomaly information is reported to the higher-level payload subsystem. The key information of the payload subsystem, based on the information of the unit, adds parameters such as communication port packet loss rate, level of each interface, and module coordination status. When an anomaly occurs, the system sequentially performs handling measures such as program reloading, other beam scheduling, neighboring satellite resource coordination, or backup unit restart. If the handling is ineffective, the system is reported to the satellite control level. The key information of the satellite as a whole, based on the information of the subsystem, further incorporates core operating parameters such as unit operating temperature, power supply voltage, and operating current. When an anomaly occurs, the system directly performs a power outage of the unit's primary power bus and reports it to the satellite health management module simultaneously. This graded fault identification and fault-tolerant handling mechanism significantly improves the reliability and safety of the payload's on-orbit operation, provides key on-orbit verification data support for the selection of payload components and the design of main backup redundancy for sub-components, and thus effectively optimizes the overall construction cost of the satellite.

Claims

1. An autonomous operation system for low-Earth orbit satellite payloads, characterized in that, It includes a resource allocation layer, a load control layer, and an application service layer; The resource allocation layer is used to implement physical layer resource and protocol resource scheduling, including an autonomous transmission link management module and an autonomous routing and network management module; The load control layer is used to realize load hierarchical management and fault prediction and fault tolerance, shorten the load invalid start-up time, and perform rapid on-orbit fault handling to avoid affecting the upgrade. The application service layer is used to realize autonomous operation planning and execution, complete the autonomous decomposition of satellite payload tasks and command generation, and reduce the pressure of ground operation and maintenance.

2. The autonomous operation system for low-Earth orbit satellite payloads according to claim 1, characterized in that, The link prediction model in the autonomous transmission link management module adds an active control mode, which dynamically introduces additional attenuation values ​​from the environment. and the deviation adjustment value between the theoretical estimate and the measured value in orbit A link budget quantitative analysis model is introduced to construct an active early warning and forward-looking control mechanism.

3. The autonomous operation system for low-Earth orbit satellite payloads according to claim 2, characterized in that, The implementation process of the active control method is as follows: The satellite's position vector in the Earth-fixed coordinate system acquired by the satellite platform Velocity vector Subtracting the coordinates of the satellite and the ground station yields the pointing vectors of the satellite and the ground station, respectively. Let this vector be expressed in Earth-fixed coordinates as... Based on the above parameters, the theoretical values ​​of communication distance, link loss, and received signal-to-noise ratio are calculated respectively. The calculation formulas are as follows: ； ； ； in: Communication distance, in km; Operating frequency, in MHz; Link attenuation, measured in dB; Additional attenuation values ​​are introduced dynamically for the environment and are retrieved in real time from the distributed ledger environment parameter library, in dB. This is the adjustment value for the deviation between the theoretical value of the signal-to-noise ratio budget and the measured value in orbit. It is dynamically updated through in-orbit closed-loop calibration and is expressed in dB. The satellite uses the transmit power, link budget L, and satellite payload reception capability reported by the terminal during the network access process. The value completes the theoretical estimate of the signal-to-noise ratio budget. And combined with real-time signal-to-noise ratio estimates After completing the adjustment, the uplink error was calculated. The calculation formula is: ； ； in, This represents the beam transmit power, measured in dBW. The value is the antenna gain of the receiving system. With noise temperature The value is expressed in dB / K. It is the signal power of the receiving system. With noise power spectral density The ratio, in dBHz; The downlink then calculates the signal-to-noise ratio (SNR) budget based on the terminal's receiving capability, link budget, and agreed-upon transmit power for the satellite payload. This estimate is then adjusted in conjunction with the real-time SNR estimate to determine the downlink error. .

4. The autonomous operation system for low-Earth orbit satellite payloads according to claim 2, characterized in that, The autonomous transmission link management module implements adaptive rate adjustment and supports both passive response control and active early warning control modes. Passive response control is achieved by adjusting the link rate in real time based on the link parameters returned from the peer; proactive early warning control is used to predict and warn of link status in the future, specifically by integrating pre-stored spatial environment parameters, theoretical estimates of link budget, and measured values ​​to conduct a multi-dimensional comprehensive analysis, and when the prediction... When the fluctuation exceeds the preset threshold, a step-by-step rate reduction process is triggered to dynamically adjust the transmission rate to the optimal level before the fluctuation occurs, ensuring the stability and reliability of the communication link.

5. The autonomous operation system for low-Earth orbit satellite payloads according to claim 1, characterized in that, The load classification and control module supports both on-demand and on-path telemetry and control, and adopts a load monitoring method based on the power supply link to achieve beam resource scheduling, service mode switching, service status monitoring and working mode switching. The telemetry status is fully covered and updated at the millisecond level.

6. The autonomous operation system for low-Earth orbit satellite payloads according to claim 1, characterized in that, The fault prediction and fault tolerance process is as follows: First, key status information is extracted at three levels: individual load, load subsystem, and whole satellite. Then, corresponding processing is carried out according to the fault level, including software module-level reset for individual load abnormalities, program reloading or backup startup for subsystem abnormalities, and power outage of the individual load power bus and reporting for whole satellite abnormalities.

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