In-orbit reorganization method for satellite-borne load unit software

Abstract

The invention discloses an in-orbit reorganization method for satellite-borne load unit software. By utilizing the method, in-orbit switching, in-orbit updating and in-orbit error correction of software versions can be realized, so that the application flexibility and maintenance efficiency of the software versions are remarkably improved. The method is realized through the following steps of: ina load unit, two field-programmable gate arrays FPGA1 and FPGA2 are connected with a digital signal processor DSP via a common end, wherein the FPGA1, the FPGA2 and the DSP have software program versions with n independent and complete functions; after electrification, sending a software program version switching instruction and information to the FPGA1, the FPGA2 and the DSP by a load managementcomputer in sequence, so as to realize an in-orbit switching function among multiple versions of software programs of the FPGA1, the FPGA2 and the DSP; and moreover, sending a software program versionmaintenance instruction and information to the DSP by the load management computer, configuring a corresponding control signal by the DSP according to the received command so as to realize in-orbit updating and in-orbit error correction functions of software program versions of the FPGA1, the FPGA2 and the DSP in Flash, and managing states of software versions through an information list manner so as to complete in-orbit reorganization.

Description

technical field [0001] The invention relates to an on-orbit recombination method for software of satellite-borne load units such as communication satellites, remote sensing satellites, reconnaissance satellites, and navigation satellites. It adopts the method of rapid switching and updating of software versions to realize the function of software reorganization of the load unit, making the load unit more versatile, expandable, flexible and maintainable. Background technique [0002] With the increase of satellite platform load capacity and the expansion of functions, higher requirements are put forward for the satellite payload. The satellite load is the most important part of the satellite, which determines the size of the satellite, the orbital requirements and the resulting capabilities. Designing for reliability in a space environment is a difficult problem for payload cells that employ field-programmable gate array (FPGA) and digital signal processor (DSP) architecture...

AI Technical Summary

Problems solved by technology

[0004] The above-mentioned method of updating and upgrading software on orbit still has some defects, mainly including: (1) the functions of the fixed part of the program cannot be updated and upgraded; Application function; (3) When the program code or data is affected by the space environment and needs to be maintained, the software can only be re-injected from the ground; (4) It cannot meet the application of multi-task and multi-functional satellite platforms, because in the software update process In the middle, due to the limitation of transit time and remote control arc, it will greatly affect the timeliness of satellite work

Images