SBAK043 April   2026 DAC39RF10-SP , DAC39RFS10-SP

 

  1.   1
  2.   2
  3.   Trademarks
  4. 1Introduction
  5. 2Single-Event Effects
  6. 3Device and Test Board Information
  7. 4Irradiation Facility and Setup
  8. 5Test Setup and Procedures
  9. 6Single-Event Latch-Up (SEL) Results
  10. 7Single-Event Functional Interrupt (SEFI) Results
    1. 7.1 Converter Performance and Digital (DUC + JESD204C Link) Hardness
    2. 7.2 Configuration Register Hardness
    3. 7.3 SPI Programming During Irradiation
  11. 8SEU Results
    1. 8.1 JESD204C Link Monitoring Results
    2. 8.2 Digital Up-Converter and NCO Upset Recovery
    3. 8.3 Estimating Upset Rates in Unprotected Data Paths
    4. 8.4 Event Rate Calculations
    5. 8.5 Summary of Radiation Hardness
  12. 9References
  13.   A Appendix: Recommendations for Hi-Rel Systems
    1.     A.1 Summary of Rad-Hard Design Features
    2.     A.2 SPI Programming
    3.     A.3 JESD204C Reliability
    4.     A.4 Equalizer Usage in Radiation Environments
    5.     A.5 NCO Reliability
    6.     A.6 NCO Frequency and Phase Correction (Strategy #1)
    7.     A.7 NCO Frequency Correction (Strategy #2)
    8.     A.8 NCO Self-Sync/Self-Coherent Mode (Strategy #3)

8.4 Event Rate Calculations

Event rates were calculated for LEO (ISS) and GEO environments by combining CREME96 orbital integral flux estimations and simplified SEE cross sections according to methods described in Heavy Ion Orbital Environment Single-Event Effects Estimations. A minimum shielding configuration of 100mils (2.54mm) of aluminum, and worst-week solar activity (this is similar to a 99% upper bound for the environment) is assumed. Using the 95% upper bounds, the event rates for SEUs are shown in Table 8-2.

Table 8-2 SEU Event Rate Calculations for Worst-Week LEO and GEO Orbits
Orbit Type Onset LET (MeV·cm2/mg) σ SAT (cm2) Event Rate (/day) Event Rate (FIT) MTBE (YEARS)
LEO (ISS) 1.0000 5.00E-05 1.28E-06 5.33E+01 2.14E+03
GEO 1.05E-05 4.36E+02 2.62E+02