TY - GEN

T1 - Aerospace electronics reliability

T2 - 2015 IEEE Aerospace Conference, AERO 2015

AU - Bernstein, Joseph B.

N1 - Publisher Copyright:
© 2015 IEEE.

PY - 2015/6/5

Y1 - 2015/6/5

N2 - We present a method for predicting the failure rate, and thus the reliability of an electronic system by summing the failure rate of each known failure mechanism. We use a competing acceleration factor methodology by combining the physics of failure for each mechanism with their effects as observed by High/Low temperature and High/Low voltage stresses. Our method assumes that lifetime of each of its failure mechanisms follows constant rate distribution and each mechanism is independently accelerated by the stress factors, which include also frequency, current, and other factors that can be entered into a reliability model. The overall failure rate is thus, also follows an exponential distribution and is described in the standard FIT (Failure unIT or Failure in Time). The method combines mathematical models for known failure mechanism and solves them simultaneously at a multiplicity of accelerated life tests to find a consistent set of weighting factors for each mechanism. The result of solving the system of equations is a more accurate and a unique combination for each system model by proportional summation of each of the contributing failure mechanisms.

AB - We present a method for predicting the failure rate, and thus the reliability of an electronic system by summing the failure rate of each known failure mechanism. We use a competing acceleration factor methodology by combining the physics of failure for each mechanism with their effects as observed by High/Low temperature and High/Low voltage stresses. Our method assumes that lifetime of each of its failure mechanisms follows constant rate distribution and each mechanism is independently accelerated by the stress factors, which include also frequency, current, and other factors that can be entered into a reliability model. The overall failure rate is thus, also follows an exponential distribution and is described in the standard FIT (Failure unIT or Failure in Time). The method combines mathematical models for known failure mechanism and solves them simultaneously at a multiplicity of accelerated life tests to find a consistent set of weighting factors for each mechanism. The result of solving the system of equations is a more accurate and a unique combination for each system model by proportional summation of each of the contributing failure mechanisms.

UR - http://www.scopus.com/inward/record.url?scp=84940676657&partnerID=8YFLogxK

U2 - 10.1109/AERO.2015.7118899

DO - 10.1109/AERO.2015.7118899

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AN - SCOPUS:84940676657

T3 - IEEE Aerospace Conference Proceedings

BT - 2015 IEEE Aerospace Conference, AERO 2015

PB - IEEE Computer Society

Y2 - 7 March 2015 through 14 March 2015

ER -