Open Access
Volume 37, Number 4, August 2019
Page(s) 737 - 743
Published online 23 September 2019
  1. Federal Aviation Administration. Damage Tolerance and Fatigue Evaluation of Structure[S]. AC 25.571-1D, 2011 [Google Scholar]
  2. Belytschko T, Black T. Elastic Crack Growth in Finite Elements with Minimal Remeshing[J]. International Journal for Numerical Methods in Engineering, 1999, 86: 1141–1151 [Google Scholar]
  3. Moes N, Dolbow J, Belytschko T. A Finite Element Method for Crack Growth without Remeshing[J]. International Journal for Numerical Methods in Engineering, 2015, 46: 131–150[Article] [NASA ADS] [CrossRef] [Google Scholar]
  4. Bergara A, Dorado J I, Martin-Meizoro A, et al. Fatigue Crack Propagation in Complex Stress Fields:Experiments and Numerical Simulations Using the Extended Finite Element Method(XFEM)[J]. International Journal of Fatigue, 2017, 103: 112–121 [Article] [Google Scholar]
  5. Dirik H, Yalcinkaya T. Crack Path and Life Prediction under Mixed Mode Cycle Variable Amplitude Loading through XFEM[J]. International Journal of Fatigue, 2018, 114: 34–50 [Article] [CrossRef] [Google Scholar]
  6. Menk A B, Ttephane Pierre Alain. Crack Growth Calculations in Solder Joints Based on Microstructural Phenomena with X-FEM[J]. Computational Material Science, 2011, 50(3): 1145–1156 [Article] [CrossRef] [Google Scholar]
  7. Wang Chong, Lu Tongli. Analysis of Crack Growth at Countersink Hole of Airplane Skinbased on FEM[J]. Journal of Shanghai University of Engineering Science, 2011, 25(2): 117–120 [Article] (In chinese) [Google Scholar]
  8. Su Yi, Wang Shengnan. Analysis of Fatigue and Damage Tolerance of Joint Region of Aircraft Certain Part[J]. Aeronautical Computing Technique, 2013, 43(3): 45–47 [Article] (In chinese) [NASA ADS] [Google Scholar]
  9. Lu Yongjun, Zhang Huanqing, Wang Fenghui, et al. Applicaton of Extended Finite Element Method in Fatigue Life Estimation of Structural Components[J]. Chinese Journal of Applied Mechanics Echanics, 2016, 33(3): 441–446 [Article] (In chinese) [Google Scholar]
  10. Forth S C, Wright C W, Johnston W M. 7075-T6 and 2024-T351 Aluminum Alloy Fatigue Crack Growth Rate Data[R]. NASA/TM-2005-213907, 2005 [Google Scholar]

Current usage metrics show cumulative count of Article Views (full-text article views including HTML views, PDF and ePub downloads, according to the available data) and Abstracts Views on Vision4Press platform.

Data correspond to usage on the plateform after 2015. The current usage metrics is available 48-96 hours after online publication and is updated daily on week days.

Initial download of the metrics may take a while.