SBOK085 April   2024 SN54SC2T74-SEP

PRODUCTION DATA  

  1.   1
  2.   Abstract
  3.   Trademarks
  4. 1Overview
  5. 2Single-Event Effects (SEE)
  6. 3Test Device and Test Board Information
  7. 4Irradiation Facility and Setup
  8. 5Results
    1. 5.1 SEL Results
    2. 5.2 Single-Event Transients (SET)
    3. 5.3 Event Rate Calculations
  9. 6Summary
  10. 7References

5.3 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 shown in Heavy Ion Orbital Environment Single-Event Effects Estimations. A minimum shielding configuration of 100mils (2.54mm) of aluminum, and worst-week solar activity is assumed. (This is similar to a 99% upper bound for the environment.) Using the 95% upper-bounds for the SEL and the SET, the event rate calculation for the SEL and the SET is listed in Table 5-3 and Table 5-4, respectively. Note that this number is for reference since no SEL or SET events were observed.

Table 5-3 SEL Event Rate Calculations for Worst-Week LEO and GEO Orbits
Orbit Type Onset LETEFF (MeV-cm2 / mg) CREME96 Integral FLUX ( per day / cm2) σSAT (cm2) Event Rate (per day) Event Rate (FIT) MTBE (Years)
LEO (ISS) 48 6.40 × 10-4 1.23 × 10-7 7.87 × 10-11 3.28 × 10-3 3.48 × 107
GEO 2.17 × 10-3 2.67 × 10-10 1.11 × 10-2 1.03 × 107
Table 5-4 SET Event Rate Calculations for Worst-Week LEO and GEO Orbits
Orbit Type Onset LETEFF (MeV-cm2 / mg) CREME96 Integral FLUX (per day / cm2) σSAT (cm2) Event Rate (per day) Event Rate (FIT) MTBE (Years)
LEO (ISS) 48 6.40 × 10-4 1.94 × 10–8 1.24 × 10–11 5.16 × 10–4 2.21 × 108
GEO 2.17 × 10-3 4.20 × 10–11 1.75 × 10–3 6.52 × 107

MTBE is the mean-time-between-events in years at the given event rates. These rates clearly demonstrate the SEE robustness of the SN54SC2T74-SEP in two harshly conservative space environments. Customers using the SN54SC2T74-SEP must only use the above estimations as a rough guide and TI recommends performing event rate calculations based on specific mission orbital and shielding parameters to determine if the product satisfies the reliability requirements for the specific mission.