Configuration method and system used for satellite-bone SRAM (Static Random Access Memory) type FPGA (Field Programmable Gate Array) working on track for long time

Abstract

The invention relates to a configuration method and system used for a satellite-bone SRAM (Static Random Access Memory) type FPGA (Field Programmable Gate Array) working on track for a long time. The method comprises the following steps: electrification: a delay configuration strategy is adopted for the FPGA to avoid configuration errors caused by power supply fluctuation generated at the moment of the boot; configuration process monitoring: the configuration condition of the FPGA is monitored by a DSP (Digital Signal Processor), and when the configuration of the FPGA is monitored to be normally completed, the FPGA is informed of entering a normal measurement state by the DSP, and an on-line reconfiguration step is started if the configuration of the FPGA is monitored to be not completed in time; reconfiguration: a low-level pulse larger than 300ns is controlled to be applied to a configuration reset pin of the FPGA by the DSP under the condition of uninterruptible power supply, and then the configuration process is automatically completed by the FPGA; normal working process monitoring: whether the configuration of the FPGA is correct or not is monitored regularly by the DSP in a normal working process, and FPGA on-line reconfiguration is started by the DSP if the configuration of the FPGA is wrong; and regular reconfiguration: a triple modular redundancy design is adopted for the FPGA, and is matched with the regular reconfiguration to improve the reliability of the FPGA.

Description

technical field [0001] The present invention relates to the configuration and monitoring design of FPGA in anti-single particle reinforcement design when SRAM-type FPGA is used in space-borne equipment and working in space high-irradiation environment, and specifically relates to a configuration of space-borne SRAM-type FPGA for long-term on-orbit work methods and systems. Background technique [0002] Spaceborne radar altimeter is an active microwave remote sensor, which can realize effective measurement of sea surface height, sea surface effective wave height, sea surface backscatter coefficient and sea surface wind speed. Further inversion of these data can be applied to studies in marine geophysics, ocean dynamics, ocean climatology, and polar ice detection. [0003] The HY-2 radar altimeter is a dual-frequency radar with two bands of Ku and C. The numerical control unit adopts the SRAM FPGA of Virtex II series 2V3000 of Xilinx Company to realize the control of the tran...

AI Technical Summary

Problems solved by technology

The design idea of ​​triple-mode redundancy is to copy the same functional small module into three copies, and then output it from the voting device. As long as two of them are normal, the entire logic function is correct; and the periodic reconfiguration solves the problem of error accumulation; currently FPGAs working in the space environment more or less include triple-mode redundancy design; for FPGAs that are short-term and intermittent during the orbit, triple-mode redundancy design should be done to prevent single event effects, but no design is required. Regular reconfiguration; this is because for short-term intermittent start-up FPGAs, due to the short start-up time, it is unlikely that the single-event flips of three identical logic units in one working cycle will accumulate to two copies, resulting in output errors

However, the existing reconfiguration technology is generally realized by sending program-controlled instructions, and some designs do not have the reconfiguration function. If a single event effect is found, it can only be eliminated by turning off and on the device.

This will greatly reduce the automation level of the equipment containing this kind of SRAM FPGA that has been working on the rail for a long time, and at the same time repeatedly switch on and off to increase the frequency of use of the relay

The resource overhead of triple-mode redundant design is high, but for spaceborne equipment working in the space environment, reliability is the first consideration, and it is necessary to exchange more resources for reliability.

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