TY - GEN
T1 - Fatigue damage prognosis of aircraft wing structure using time-based subcycle formulation and hybrid learning
AU - Yu, Yang
AU - Venkatesan, Karthik Rajan
AU - Liu, Yongming
N1 - Funding Information:
The research reported in this paper was supported by funds from NASA University Leadership Initiative program (Contract No. NNX17AJ86A, PI: Yongming Liu, Project Officer: Kai Goebel). The support is gratefully acknowledged.
Publisher Copyright:
© 2019 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
PY - 2019
Y1 - 2019
N2 - The aircraft wing structures are prone to fatigue during flight operations as they undergo complex loading conditions. The classical cycle-based formulation for fatigue crack growth has intrinsic difficulties in dealing with these complex loadings since they often cannot be described as cyclic. In this study, a time-based subcycle formulation for fatigue crack growth is adopted to address this difficulty. Meanwhile, real-time fatigue damage prognosis requires efficient prediction of aircraft dynamical responses. In order to reduce the computational costs, this study proposes a hybrid learning method to simulate the aircraft dynamics. The hybrid learning method integrates the underlying physics of the dynamical system into learning models such as neural networks to reduce the training and computational costs. For demonstration, the aircraft wing structure is modeled as a cantilever beam and the proposed method is adopted to conduct the fatigue damage prognosis.
AB - The aircraft wing structures are prone to fatigue during flight operations as they undergo complex loading conditions. The classical cycle-based formulation for fatigue crack growth has intrinsic difficulties in dealing with these complex loadings since they often cannot be described as cyclic. In this study, a time-based subcycle formulation for fatigue crack growth is adopted to address this difficulty. Meanwhile, real-time fatigue damage prognosis requires efficient prediction of aircraft dynamical responses. In order to reduce the computational costs, this study proposes a hybrid learning method to simulate the aircraft dynamics. The hybrid learning method integrates the underlying physics of the dynamical system into learning models such as neural networks to reduce the training and computational costs. For demonstration, the aircraft wing structure is modeled as a cantilever beam and the proposed method is adopted to conduct the fatigue damage prognosis.
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U2 - 10.2514/6.2019-2384
DO - 10.2514/6.2019-2384
M3 - Conference contribution
AN - SCOPUS:85083942823
SN - 9781624105784
T3 - AIAA Scitech 2019 Forum
BT - AIAA Scitech 2019 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Scitech Forum, 2019
Y2 - 7 January 2019 through 11 January 2019
ER -