Because metallic aircraft components are subject to a variety of in-service loading conditions, predicting their fatigue life has become a critical challenge. To address the failure mode mitigation of aircraft components and at the same time reduce the life-cycle costs of aerospace systems, a reliable prognostics framework is essential. In this paper, a hybrid prognosis model that accurately predicts the crack growth regime and the residual-useful-life estimate of aluminum components is developed. The methodology integrates physics-based modeling with a data-driven approach. Different types of loading conditions such as constant amplitude, random, and overload are investigated. The developed methodology is validated on an Al 2024-T351 lug joint under fatigue loading conditions. The results indicate that fusing the measured data and physics-based models improves the accuracy of prediction compared to a purely data-driven or physics-based approach.
Fatigue Life Prediction Using Hybrid Prognosis for Structural Health Monitoring
Journal of Aerospace Information Systems ; 11 , 4 ; 211-232
2014-04-25
22 pages
Article (Journal)
Electronic Resource
English
2012-2448 Fatigue Life Prediction Using Hybrid Prognosis for Structural Health Monitoring
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