Fault recognition and processing method based on satellite-bone bus

Abstract

The invention relates to a fault recognition and processing method based on a satellite-bone bus. The method of the invention comprises the following steps: firstly, determining the fault type of a satellite, telemetry parameters related to various fault types and a range of normal values of the parameters; then setting the maximum times that the telemetry parameters related to the various fault types exceed the range of the normal values, and storing security instruction groups for removing faults corresponding to the various fault types in an instruction library; collecting the telemetry parameters of each device of the satellite by the satellite-bone bus at a set time, and when the telemetry parameters related to a fault type are abnormal and the abnormal times exceed the set maximum times, judging and entering the fault type; obtaining the corresponding security instruction group from the instruction library, and judging whether the security instruction group is executed; if the security instruction group is executed, clearing the corresponding abnormal count values of the telemetry parameters until the execution of the security instruction group is finished; and if the security instruction group is not executed, sequentially executing every security instruction in the security instruction group until the execution of the security instruction group is finished. The invention has the characteristics of good real-time performance and strong versatility.

Description

technical field [0001] The invention relates to a method for identifying and processing faults of a satellite system by using a satellite-borne bus. Background technique [0002] At present, as the design of fault identification and safety management in the satellite safety design method, there are mainly the following two types: the first is the method of safety management of satellites through real-time telemetry, manual interpretation of abnormal states, and real-time injection of remote control commands. This method can greatly save on-board resources; the second method is a method in which a stand-alone device independently monitors the abnormal state and conducts safety management through internal instructions. This method of operation can be carried out autonomously on the orbit. Exception handling and restoring the settings to their normal state. [0003] Although the above two methods have their own advantages, there are also some shortcomings. The application ran...

AI Technical Summary

Problems solved by technology

The application range of the first method has great limitations. It is only suitable for the situation where the satellite is within the visible range of the ground measurement and control station. If the satellite fails in the uncontrollable arc, the fault will remain until it enters the controllable arc. It can only be ruled out, and keeping working in the failure mode for a long time may cause fatal harm to the satellite; the second remote operation method makes it possible for the satellite to be safely managed outside the visual range of the measurement and control station, but because the on-board equipment is independent of each other , the safety management operation can only be performed on a single device. If the failure of this device causes other stand-alone devices to be affected and related safety operations need to be performed, it will not be able to handle it. Therefore, there are also situations where the danger cannot be eliminated after a long time working in the fault mode. In addition, the The method cannot make an accurate judgment on the fault phenomenon that occurs jointly by multiple devices

[0004] It can be seen that although the above two processing methods can play a certain role in satellite fault identification and safety management, they still cannot meet the autonomous and real-time requirements of satellite fault identification and elimination.

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