Satellite-borne terminal equipment on-orbit fault autonomous identification processing method

Abstract

The invention discloses a satellite-borne terminal equipment on-orbit fault autonomous identification processing method. The method comprises the following steps: S1, acquiring working conditions of an online board card and an offline board card of satellite-borne terminal equipment and a telemetering function operation state; s2, according to the current working condition and the operation state of the telemetering function, performing telemetering terminal alarm early warning identification, if an alarm early warning result appears, performing fault autonomous disposal, and if the alarm early warning result does not appear, performing telemetering terminal fault early warning identification; s3, board card switching is carried out according to the fault early warning identification result of the telemetry terminal; if the fault early warning is reached, automatically switching the board cards, and if the fault early warning is not reached, returning to the step S2. According to the invention, the autonomous handling of the terminal identification on-orbit fault is realized, and the requirements of accuracy and real-time performance of on-orbit fault handling are met.

Description

Technical Field

[0001] The present invention relates to the technical field of onboard equipment fault identification and processing, and in particular to a method for autonomously identifying and processing on-orbit faults of onboard terminal equipment. Background Art

[0002] As a device for collecting the main digital parameters and engineering parameters of spacecraft, the onboard terminal equipment is used to collect digital parameters and engineering parameters within the system and provide data services to the outside world. Its data services require data continuity without data service interruption or incomplete data reception. In particular, the health status of astronauts on orbit and the key operating parameters of key equipment must be ensured to be foolproof.

[0003] The fault management of traditional satellite-borne terminal equipment is limited by the limited satellite measurement and control resources. Only when the satellite enters the station and is in the measurement and control range of the ground measurement and control station, can it establish a communication link with the ground station to receive the satellite's downlink data. The downlink data is then analyzed by the ground station, and the measurement and control personnel work with the design personnel to carry out fault troubleshooting and recovery. Finally, the remote control commands such as restart, switch, and reset are generally used to reconstruct the mission scenario to complete the fault recovery. However, due to the limited measurement and control resources and the long information transmission and response cycle of the large closed-loop link between the sky and the earth, it is difficult to respond quickly to faults that occur outside the station. The entire fault troubleshooting and recovery operation takes at least several minutes or even longer, which poses a certain risk to the on-orbit operation of the equipment and affects the normal execution of on-orbit missions.

[0004] Therefore, how to automatically detect faults and execute fault handling procedures on-orbit, quickly resolve faults and restore to normal status, and improve the real-time response capabilities of fault location and autonomous handling on-orbit are issues that need to be addressed urgently. Summary of the invention

[0005] To solve the above problems, the present invention provides a method for autonomously identifying and processing on-orbit faults of satellite-borne terminal equipment. The method identifies the alarm and warning results of the terminal equipment by collecting the working conditions and functional operation status of online boards and offline boards, triggers the activation of offline boards according to the alarm and warning results of the terminal equipment, and realizes the parallel operation of online boards and offline boards. The switching between offline boards and online boards is triggered by the fault warning results of the terminal equipment, and the terminal identifies and autonomously handles on-orbit faults, which meets the requirements of accuracy and real-time performance of on-orbit fault handling, while ensuring the uninterrupted data service and the integrity of data reception, and improving the on-orbit fault handling effect.

[0006] The present invention provides a method for autonomously identifying and processing on-orbit faults of satellite-borne terminal equipment, and the specific technical solution is as follows:

[0007] S1: Acquire the working conditions of the online and offline boards of the satellite terminal equipment and the operating status of the telemetry function;

[0008] S2: According to the current working conditions and the operation status of the telemetry function, the telemetry terminal alarm warning identification is performed. If an alarm warning result occurs, the fault is handled autonomously. If no alarm warning result occurs, the telemetry terminal fault warning identification is performed;

[0009] S3: Switch boards based on the fault warning identification result of the telemetry terminal;

[0010] If the fault warning is reached, the board is switched automatically. If the fault warning is not reached, the process returns to step S2.

[0011] Furthermore, the fault is handled autonomously, as follows:

[0012] The online board task scenario is dynamically configured to the designated offline board, and the normal operation of the offline board is restored. The online board provides data services to the outside.

[0013] Furthermore, the mission scenario includes telemetry function programs, configuration files and working parameters;

[0014] The specific process of the dynamic configuration is as follows:

[0015] The telemetry function program is deployed and configured to the offline board through dynamic burning; it is initialized according to the configuration file; and the telemetry collection function is restored according to the code rate and code type.

[0016] Furthermore, the specific process of board switching is as follows:

[0017] Switching the offline board to provide external data services, while terminating the online board from providing external data services;

[0018] The online board is de-networked and offline.

[0019] Furthermore, the data buffer sizes of the online board and the offline board are set respectively, and data packets are received at the same time. When switching boards, the data packets of the online board and the offline board are compared according to the timestamp of each data packet.

[0020] Furthermore, the board operating conditions include voltage, current, and temperature;

[0021] The telemetry function operation status includes telemetry subcarrier lock status, bit synchronization lock status, frame synchronization lock status, telemetry bit error rate, frame loss rate and frame error rate.

[0022] Further, according to the voltage parameters of the board working condition, a standard voltage and a voltage threshold ratio are provided, the voltage threshold ratio includes a first voltage threshold ratio and a second voltage threshold ratio, the second voltage threshold ratio is greater than the first voltage threshold ratio; if the difference between the collected voltage parameter and the standard voltage exceeds the first voltage threshold ratio, an alarm is issued, and if the difference between the collected voltage parameter and the standard voltage exceeds the second voltage threshold ratio, a fault warning is issued;

[0023] According to the current parameters of the board working condition, a first current threshold and a second current threshold are set, and the second current threshold is greater than the first current threshold; if the collected current parameter exceeds the first current threshold, an alarm is issued, and if the collected current parameter exceeds the second current threshold, a fault warning is issued;

[0024] According to the temperature parameters of the board working condition, a first temperature threshold interval and a second temperature threshold interval are set, and the lowest temperature of the second temperature threshold interval is greater than the highest temperature of the first temperature threshold interval; if the collected temperature parameter is within the first temperature threshold interval or the second temperature threshold interval, an alarm is issued; if the collected temperature parameter is lower than the lowest temperature of the first temperature threshold interval or higher than the highest temperature of the second temperature threshold interval, a fault warning is issued.

[0025] Furthermore, the telemetry bit error rate, telemetry frame error rate and missed frame rate are respectively provided with alarm thresholds and fault thresholds. If any parameter reaches the corresponding alarm threshold, an alarm warning is issued; if any parameter reaches the corresponding fault threshold, or any state item corresponding to the telemetry subcarrier lock state, bit synchronization lock state and frame synchronization lock state is lost, a fault warning is issued.

[0026] Furthermore, the alarm threshold and fault threshold corresponding to the telemetry frame error rate and frame leakage rate are the same.

[0027] Furthermore, before step S2, it also includes: according to the current working conditions and the operating status of the telemetry function, the telemetry terminal fault warning is identified, if the fault warning is reached, the board is switched autonomously, if the fault warning is not reached, step S2 is executed.

[0028] The beneficial effects of the present invention are as follows:

[0029] The present invention identifies the alarm and warning results of the terminal equipment by collecting the working conditions and functional operation status of the online board and the offline board, triggers the activation of the offline board according to the alarm and warning results of the terminal equipment, and realizes the parallel operation of the online board and the offline board, at which time only the online board provides data services to the outside; then, the monitoring and judgment are continued on the basis of the alarm and warning results of the terminal equipment, and the fault warning results of the terminal equipment are identified, and the offline board is switched online according to the fault warning results of the terminal equipment, and only the offline board provides data services to the outside, while the online board is offline, and the terminal identifies the autonomous handling of the on-orbit fault, realizes that the fault handling will be moved from the ground system to the on-orbit autonomous handling, quickly solves the fault and recovers to the normal state, improves the real-time response capability of fault location and on-orbit autonomous handling, meets the requirements of accuracy and real-time performance of on-orbit fault handling, and at the same time ensures that the data service is not interrupted and the integrity of data reception is improved, and the on-orbit fault handling effect is improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 It is a schematic diagram of the method flow of Example 1 of the present invention.

[0031] Figure 2 It is a schematic diagram of the method flow of Example 2 of the present invention. DETAILED DESCRIPTION

[0032] The following description clearly and completely describes the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0033] In the description of the embodiments of the present invention, it should be noted that the indicated orientation or positional relationship is based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship in which the invention product is usually placed when in use, or the orientation or positional relationship commonly understood by those skilled in the art, or the orientation or positional relationship in which the invention product is usually placed when in use, which is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In addition, the terms "first" and "second" are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0034] In the description of the embodiments of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a direct connection, or an indirect connection through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0035] Example 1

[0036] Embodiment 1 of the present invention discloses a method for autonomously identifying and processing on-orbit faults of a satellite-borne terminal device, such as Figure 1 As shown, the specific steps are as follows:

[0037] S1: Acquire the working conditions of the online and offline boards of the satellite terminal equipment and the operating status of the telemetry function;

[0038] As a preferred embodiment, the board operating conditions include voltage, current, and temperature;

[0039] The telemetry function operation status includes telemetry subcarrier lock status, bit synchronization lock status, frame synchronization lock status, telemetry bit error rate, frame loss rate and frame error rate.

[0040] According to the voltage parameters of the board working condition, a standard voltage and a voltage threshold ratio are provided, wherein the voltage threshold ratio includes a first voltage threshold ratio and a second voltage threshold ratio;

[0041] Specifically, the standard voltage is 5V; the first voltage threshold ratio is 5%, and the second voltage threshold ratio is 10%;

[0042] If the difference between the collected voltage parameter and the standard voltage exceeds the first voltage threshold ratio, that is, the error between the collected voltage parameter and the standard voltage is within ±5%, an alarm warning is issued; if the difference between the collected voltage parameter and the standard voltage exceeds the second voltage threshold ratio, that is, the error between the collected voltage parameter and the standard voltage is within ±10%, a fault warning is issued;

[0043] According to the current parameters of the board working condition, a first current threshold and a second current threshold are set;

[0044] Specifically, the first current threshold and the second current threshold are 10A and 16A respectively;

[0045] If the collected current parameter exceeds the first current threshold of 10A, an alarm warning is issued; if the collected current parameter exceeds the second current threshold of 16A, a fault warning is issued;

[0046] According to the temperature parameter of the board working condition, a first temperature threshold interval and a second temperature threshold interval are set; the lowest temperature of the second temperature threshold interval is greater than the highest temperature of the first temperature threshold interval;

[0047] Specifically, the lowest temperature of the first temperature threshold interval is -45°C and the highest temperature is -30°C, the lowest temperature of the second temperature threshold interval is 70°C and the highest temperature is 85°C; the accuracy of the temperature parameter is 0.1°C;

[0048] If the collected temperature parameter is within the first temperature threshold interval or the second temperature threshold interval, that is, lower than -30℃ and higher than -45℃ or greater than 70℃ and less than 85℃, an alarm warning will be issued; if the collected temperature parameter is lower than the lowest temperature of the first temperature threshold interval or higher than the highest temperature of the second temperature threshold interval, that is, lower than -45℃ or higher than 85℃, a fault warning will be issued.

[0049] As a preferred embodiment, the telemetry bit error rate, telemetry frame error rate and missed frame rate are respectively provided with an alarm threshold and a fault threshold. If any parameter reaches the corresponding alarm threshold, an alarm warning is issued; if any parameter reaches the corresponding fault threshold, or any state item corresponding to the telemetry subcarrier lock state, bit synchronization lock state and frame synchronization lock state is lost, a fault warning is issued.

[0050] Specifically, the telemetry bit error rate alarm warning threshold is 1×E-6, the telemetry bit error rate fault warning threshold is 1×E-5, the telemetry frame error rate and missed frame rate alarm warning threshold is 1×E-4, and the fault warning threshold is 1×E-3.

[0051] Through the working condition of the board and the operating status of the telemetry function, it is possible to determine whether equipment failure has occurred, and when a failure occurs, autonomous on-orbit fault handling can be carried out.

[0052] Among them, the onboard terminal equipment refers to the telemetry terminal, which is used to collect telemetry data from spacecraft and astronauts and provide data services to the outside world.

[0053] S2: According to the current working conditions and the operating status of the telemetry function, the telemetry terminal alarm warning is identified. If an alarm warning result occurs, the fault is handled autonomously;

[0054] As a preferred embodiment, the autonomous fault handling is as follows:

[0055] Dynamically configure the online board task scenario to the specified offline board, and restore the normal operation of the offline board, so that the online board and the offline board can work in parallel, and only the online board provides data services to the outside world;

[0056] Specifically, the designated offline board is to select offline boards with good current working conditions as designated offline boards;

[0057] The mission scenario includes telemetry function procedures, configuration files and working parameters;

[0058] The specific process of the dynamic configuration is as follows:

[0059] The telemetry function program is deployed and configured to the offline board through dynamic burning; initialization processes such as link establishment are performed according to the configuration file; and the telemetry collection function is restored according to working parameters such as bit rate and code type.

[0060] If no alarm warning result appears, the telemetry terminal fault warning identification is carried out.

[0061] S3: Switch boards based on the fault warning identification result of the telemetry terminal;

[0062] If a fault warning is reached, the board will be switched automatically.

[0063] The specific process of board switching is as follows:

[0064] The data buffer sizes of the online board and the offline board are respectively set, and data packets are received at the same time. When switching boards, the data packets of the online board and the offline board are compared according to the timestamp of each data packet, and the offline board is switched to provide data services externally, and the online board is stopped from providing data services externally;

[0065] The online board is de-networked and offline.

[0066] The continuity of the data packet timestamp is utilized to ensure that the data packets received by the offline board are continuous with the data packets received by the online board, thus ensuring that there is no data loss during the switching process.

[0067] If the fault warning is not reached, return to step S2.

[0068] Example 2

[0069] Embodiment 2 of the present invention discloses a method for autonomously identifying and processing on-orbit faults of a satellite-borne terminal device, such as Figure 2 As shown, the specific steps are as follows:

[0070] S1: Acquire the working conditions of the online and offline boards of the satellite terminal equipment and the operating status of the telemetry function;

[0071] As a preferred embodiment, the board operating conditions include voltage, current, and temperature;

[0072] The telemetry function operation status includes telemetry subcarrier lock status, bit synchronization lock status, frame synchronization lock status, telemetry bit error rate, frame loss rate and frame error rate.

[0073] According to the voltage parameters of the board working condition, a standard voltage and a voltage threshold ratio are provided, wherein the voltage threshold ratio includes a first voltage threshold ratio and a second voltage threshold ratio;

[0074] Specifically, the standard voltage is 5V; the first voltage threshold ratio is 5%, and the second voltage threshold ratio is 10%;

[0075] If the difference between the collected voltage parameter and the standard voltage exceeds the first voltage threshold ratio, that is, the error between the collected voltage parameter and the standard voltage is within ±5%, an alarm warning is issued; if the difference between the collected voltage parameter and the standard voltage exceeds the second voltage threshold ratio, that is, the error between the collected voltage parameter and the standard voltage is within ±10%, a fault warning is issued;

[0076] According to the current parameters of the board working condition, a first current threshold and a second current threshold are set;

[0077] Specifically, the first current threshold and the second current threshold are 10A and 16A respectively;

[0078] If the collected current parameter exceeds the first current threshold of 10A, an alarm warning is issued; if the collected current parameter exceeds the second current threshold of 16A, a fault warning is issued;

[0079] According to the temperature parameter of the board working condition, a first temperature threshold interval and a second temperature threshold interval are set; the lowest temperature of the second temperature threshold interval is greater than the highest temperature of the first temperature threshold interval;

[0080] Specifically, the lowest temperature of the first temperature threshold interval is -45°C and the highest temperature is -30°C, the lowest temperature of the second temperature threshold interval is 70°C and the highest temperature is 85°C; the accuracy of the temperature parameter is 0.1°C;

[0081] If the collected temperature parameter is within the first temperature threshold interval or the second temperature threshold interval, that is, lower than -30℃ and higher than -45℃ or greater than 70℃ and less than 85℃, an alarm warning will be issued; if the collected temperature parameter is lower than the lowest temperature of the first temperature threshold interval or higher than the highest temperature of the second temperature threshold interval, that is, lower than -45℃ or higher than 85℃, a fault warning will be issued.

[0082] As a preferred embodiment, the telemetry bit error rate, telemetry frame error rate and missed frame rate are respectively provided with an alarm threshold and a fault threshold. If any parameter reaches the corresponding alarm threshold, an alarm warning is issued; if any parameter reaches the corresponding fault threshold, or any state item corresponding to the telemetry subcarrier lock state, bit synchronization lock state and frame synchronization lock state is lost, a fault warning is issued.

[0083] Specifically, the telemetry bit error rate alarm warning threshold is 1×E-6, the telemetry bit error rate fault warning threshold is 1×E-5, the telemetry frame error rate and missed frame rate alarm warning threshold is 1×E-4, and the fault warning threshold is 1×E-3.

[0084] Through the working condition of the board and the operating status of the telemetry function, it is possible to determine whether equipment failure has occurred, and when a failure occurs, autonomous on-orbit fault handling can be carried out.

[0085] Among them, the onboard terminal equipment refers to the telemetry terminal, which is used to collect telemetry data from spacecraft and astronauts and provide data services to the outside world.

[0086] As a preferred embodiment, in this embodiment, the telemetry terminal fault warning identification is performed according to the current working conditions and the operating status of the telemetry function. If the fault warning is reached, the board is switched autonomously and step S3 is executed. If the fault warning is not reached, step S2 is executed.

[0087] S2: According to the current working conditions and the operating status of the telemetry function, the telemetry terminal alarm warning is identified. If an alarm warning result occurs, the fault is handled autonomously;

[0088] As a preferred embodiment, the autonomous fault handling is as follows:

[0089] Dynamically configure the online board task scenario to the specified offline board, and restore the normal operation of the offline board, so that the online board and the offline board can work in parallel, and only the online board provides data services to the outside world;

[0090] Specifically, the designated offline board is to select offline boards with good current working conditions as designated offline boards;

[0091] The mission scenario includes telemetry function procedures, configuration files and working parameters;

[0092] The specific process of the dynamic configuration is as follows:

[0093] The telemetry function program is deployed and configured to the offline board through dynamic burning; initialization processes such as link establishment are performed according to the configuration file; and the telemetry collection function is restored according to working parameters such as bit rate and code type.

[0094] If no alarm warning result appears, the telemetry terminal fault warning identification is carried out.

[0095] S3: Switch boards based on the fault warning identification result of the telemetry terminal;

[0096] If a fault warning is reached, the board will be switched automatically.

[0097] The specific process of board switching is as follows:

[0098] The data buffer sizes of the online board and the offline board are respectively set, and data packets are received at the same time. When switching boards, the data packets of the online board and the offline board are compared according to the timestamp of each data packet, and the offline board is switched to provide data services externally, and the online board is stopped from providing data services externally;

[0099] The online board is de-networked and offline.

[0100] The continuity of the data packet timestamp is utilized to ensure that the data packets received by the offline board are continuous with the data packets received by the online board, thus ensuring that there is no data loss during the switching process.

[0101] If the fault warning is not reached, return to step S2.

[0102] The present invention is not limited to the above-mentioned specific embodiments, but extends to any new features or any new combination disclosed in this specification, as well as any new method or process steps or any new combination disclosed.

Claims

1. A method for autonomously identifying and processing on-orbit faults of satellite-borne terminal equipment, characterized in that: include: S1: Acquire the working conditions of the online and offline boards of the satellite terminal equipment and the operating status of the telemetry function; S2: According to the current working conditions and the operation status of the telemetry function, the telemetry terminal alarm warning identification is performed. If an alarm warning result occurs, the fault is handled autonomously. If no alarm warning result occurs, the telemetry terminal fault warning identification is performed; S3: Switch boards based on the fault warning identification result of the telemetry terminal; If the fault warning is reached, the board is switched automatically. If the fault warning is not reached, the process returns to step S2.

2. The method for autonomously identifying and processing on-orbit faults of satellite-borne terminal equipment according to claim 1, characterized in that: The autonomous handling of the fault is as follows: The online board task scenario is dynamically configured to the designated offline board, and the normal operation of the offline board is restored. The online board provides data services to the outside.

3. The method for autonomously identifying and processing on-orbit faults of satellite-borne terminal equipment according to claim 2, characterized in that: The mission scenario includes telemetry function procedures, configuration files and working parameters; The specific process of the dynamic configuration is as follows: The telemetry function program is deployed and configured to the offline board through dynamic burning; it is initialized according to the configuration file; and the telemetry collection function is restored according to the code rate and code type.

4. The method for autonomously identifying and processing on-orbit faults of satellite-borne terminal equipment according to claim 1, characterized in that: The specific process of board switching is as follows: Switching the offline board to provide external data services, while terminating the online board from providing external data services; The online board is de-networked and offline.

5. The method for autonomously identifying and processing on-orbit faults of satellite-borne terminal equipment according to claim 4, characterized in that: The data buffer sizes of the online board and offline board are set respectively, and data packets are received at the same time. When switching boards, the data packets of the online board and offline board are compared according to the timestamp of each data packet.

6. The method for autonomously identifying and processing on-orbit faults of satellite-borne terminal equipment according to claim 1, characterized in that: Board operating conditions include voltage, current, and temperature; The telemetry function operation status includes telemetry subcarrier lock status, bit synchronization lock status, frame synchronization lock status, telemetry bit error rate, frame loss rate and frame error rate.

7. The method for autonomously identifying and processing on-orbit faults of satellite-borne terminal equipment according to claim 6 is characterized in that: According to the voltage parameters of the board working condition, a standard voltage and a voltage threshold ratio are provided, wherein the voltage threshold ratio includes a first voltage threshold ratio and a second voltage threshold ratio, wherein the second voltage threshold ratio is greater than the first voltage threshold ratio; if the difference between the collected voltage parameter and the standard voltage exceeds the first voltage threshold ratio, an alarm is issued, and if the difference between the collected voltage parameter and the standard voltage exceeds the second voltage threshold ratio, a fault is issued; According to the current parameter of the board working condition, a first current threshold and a second current threshold are set, and the second current threshold is greater than the first current threshold; If the collected current parameter exceeds the first current threshold, an alarm warning is issued; if the collected current parameter exceeds the second current threshold, a fault warning is issued; According to the temperature parameters of the board working condition, a first temperature threshold interval and a second temperature threshold interval are set, and the lowest temperature of the second temperature threshold interval is greater than the highest temperature of the first temperature threshold interval; if the collected temperature parameter is within the first temperature threshold interval or the second temperature threshold interval, an alarm is issued; if the collected temperature parameter is lower than the lowest temperature of the first temperature threshold interval or higher than the highest temperature of the second temperature threshold interval, a fault warning is issued.

8. The method for autonomously identifying and processing on-orbit faults of satellite-borne terminal equipment according to claim 6, characterized in that: The telemetry bit error rate, telemetry frame error rate and missed frame rate are respectively provided with an alarm threshold and a fault threshold. If any parameter reaches the corresponding alarm threshold, an alarm warning is issued. If any parameter reaches the corresponding fault threshold, or any state item corresponding to the telemetry subcarrier lock state, bit synchronization lock state and frame synchronization lock state is lost, a fault warning is issued.

9. The method for autonomously identifying and processing on-orbit faults of satellite-borne terminal equipment according to claim 8, characterized in that: The alarm threshold and fault threshold corresponding to the telemetry frame error rate and frame leakage rate are the same.

10. The method for autonomously identifying and processing on-orbit faults of a satellite-borne terminal device according to any one of claims 1 to 9, characterized in that: Before step S2, it also includes: according to the current working condition and the operating status of the telemetry function, the telemetry terminal fault warning identification is performed, if the fault warning is reached, the board is switched autonomously, if the fault warning is not reached, step S2 is executed.

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