A Refresh Adaptive Continuous High Reliable On-orbit FPGA Reconfiguration System and Method

Abstract

The present application relates to a refresh self-adaptive continuous high-reliability on-orbit FPGA reconfiguration system and method. The system includes: a SRAM type FPGA unit for receiving ground control instructions and reconstructing configuration data. The read-only storage unit is used to store the original configuration data corresponding to the SRAM type FPGA unit. A programmable storage unit for storing reconfiguration configuration data. The high-reliability control unit is used to automatically select the boot source for SRAM-type FPGA booting when powered on, and refresh it; when receiving ground control instructions, select the corresponding configuration data for FPGA booting, or according to the data obtained from the SRAM-type FPGA The reconstructed configuration data for FPGA reconstruction. The above system provides a reliable hardware architecture for FPGA on-orbit reconfiguration, supports program updates to fix bugs and add functions, and also avoids system problems caused by successful FPGA reconfiguration but bugs in the updated software itself, and can improve satellite and other systems. Reliability, effectiveness and flexibility.

Description

technical field [0001] The present application relates to the field of spaceflight on-orbit system reconfiguration and reliability technology, in particular to a refresh-adaptive continuous high-reliability on-orbit FPGA reconfiguration system and method. Background technique [0002] With the rapid construction of space-based application systems such as satellite communications, satellite earth observation, and global satellite navigation and positioning in my country, as well as the vigorous development of commercial aerospace, various large-scale constellation plans have been proposed one after another, and the functions and complexity of satellite projects have increased significantly. In order to improve the reliability, effectiveness and flexibility of the satellite system, the satellite platform and its payload software are developing towards the trend of on-orbit reusability, portability, dynamic loading and maintainability. [0003] At present, many in-orbit satelli...

AI Technical Summary

Problems solved by technology

However, when single event effects occur on its FPGA or configured memory chips, mainly including single event upset SEU, single event function interruption SEFI, single event transient pulse SET, etc., its software on-orbit reconfiguration process is prone to failure, which in turn causes system failures. task interruption

In addition, these in-orbit satellites cannot repair the loopholes in the software itself, so FPGA reconfiguration cannot solve the system problems caused by the successful reconfiguration of the software but the loopholes in the software itself

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