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Reliability modelling for rotorcraft component fatigue life prediction with assumed usage

Published online by Cambridge University Press:  08 July 2016

S. Dekker ,
G. Wurzel  and
R. Alderliesten
S. Dekker*
Affiliation:
Airbus Helicopters Germany, Delft University of Technology, Donauwörth Germany, Marenco Swisshelicopter, Pfäffikon, Zurich, Switzerland
G. Wurzel
Affiliation:
Airbus Helicopters Germany, Donauwörth, Germany
R. Alderliesten
Affiliation:
Delft University of Technology, Delft, The Netherlands
*
[email protected]
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Abstract

Fatigue life is a random variable. Thus, the reliability of a conservative fatigue life prediction for a component in the helicopter dynamic system needs to be substantiated. A standard analytical substantiation method uses averaged manoeuvre loads instead of seeing manoeuvre loads as a random variable whose distribution is estimated with limited precision. This simplification may lead to inaccuracies. A new simulation-based method is developed to conservatively predict fatigue life, while also accounting for the full random distribution and uncertainty of manoeuvre loads. Both methods fully account for uncertain fatigue strength but assume that the mission profile is known or can at least be conservatively estimated. Simulations under synthetic but realistic engineering conditions demonstrate that both methods may be used for accurate substantiation of conservative fatigue life predictions. The simulations also demonstrate that, under the tested conditions, uncertainties from manoeuvre loads may be neglected in fatigue life substantiations as the resulting error is not significant with respect to uncertainties in component fatigue strength.

Keywords

Fatigue life predictionservice life limitreliability substantiationhelicopter
Type
Research Article
Information
The Aeronautical Journal , Volume 120 , Issue 1232 , October 2016 , pp. 1658 - 1692
Copyright
Copyright © Royal Aeronautical Society 2016 

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