On-orbit update method for satellite-borne integrated electronic system program

Abstract

The invention discloses an on-orbit update method for a satellite-borne integrated electronic system program. The on-orbit update method comprises the steps as follows: dividing the satellite-borne integrated electronic system program into a monitoring program and a service logic program, receiving an update data block of a target program block in the service logic program to be updated from the ground through the monitoring program, detecting if the target program block runs, updating after the target program block is executed if the target program block runs, and otherwise, updating immediately; and when updating, obtaining a program execution right from the service logic program to be updated through the monitoring program, storing the current version and the version number of the target program block to an external memory, importing a new-version program block carried by the update data block into a memory, giving the program execution right to the service logic program to be updated, and updating the original version number of the target program block into a new version number through the service logic program to be updated. Compared with the prior art, the on-orbit update method is strong in commonality, updates the granularity into a function, and can execute the rollback and delete operations.

Description

technical field [0001] The invention relates to a program updating method of a tiny satellite, in particular to an on-orbit updating method of a satellite-borne integrated electronic system program. Background technique [0002] As a scientific experiment platform with strong versatility and high reliability, microsatellites need to adapt to different mission requirements in various situations and deal with various sudden failures. update capability. [0003] At present, satellite-ground communication generally adopts PCM measurement and control system, and its remote control code rate is up to 4000bps, while the demodulation capability of existing measurement and control transponders is generally 2000bps. Without considering space-based relay and multi-station relay, the length of a single TT&C arc of a low-Earth orbit satellite generally does not exceed 10 minutes (with an elevation angle above 5 degrees), that is, the maximum size of data blocks injected into a single TT...

AI Technical Summary

Problems solved by technology

[0007] (1) It is necessary to add control flags to variable program blocks, so its update granularity is determined by the control flags; in practical applications, if too many control flags are inserted, the code volume of variable program blocks will expand and affect The execution efficiency of the program on the star; and if too few control flags are inserted, the update granularity will be too coarse, and the amount of data on the note will be too large, which will put pressure on the measurement and control circle;

[0008] (2) It is necessary to design the on-orbit update program block in the on-board business logic program, which increases the complexity of the business logic program design and reduces the program versatility;

[0009] (3) After the update, the new version of the program block will overwrite the original version of the program block. If the update does not meet the requirements, it cannot be restored to the original version

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