Single event effect vulnerability analysis and on-orbit error rate prediction

摘要

On-orbit single event effect error rate is predicted combining accelerated radiation test and space radiation environment model for a FPGA-based signal processing platform. With partial TMR and reconfiguration mitigation method, there is no single event latch is observed when the surface linear energy transfer of heavy ion is 99.8 MeV.cm2/mg, and the error/SEU ratio is 4.7431e-004. Error rate of four different orbits (400 km, 800 km, 1200 km, 35784 km) is calculated, the most vulnerability orbit is the 1200 km orbit, and the average first error time is 521.8 days.