Please use this identifier to cite or link to this item: http://nopr.niscair.res.in/handle/123456789/29417
Title: Crack growth simulation of stiffened fuselage panels using XFEM techniques
Authors: Singh, Krishna Lok
Keswani, Kamal
Vaggar, Mallikarjun
Keywords: SIF;XFEM;Crack growth;VCCT;Cohesive segment method
Issue Date: Aug-2014
Publisher: NISCAIR-CSIR, India
Abstract: In this paper, crack growth modelling and simulation of stiffened and un-stiffened fuselage panels has been presented using commercially available finite element software package. Computation of stress intensity factor for a single edge notch specimen has been computed using extended finite element method (XFEM), FEM and compared with the analytical solution. The geometric nonlinear and elastic-plastic (material nonlinear) analysis has been performed on a specimen, stiffened and un-stiffened fuselage panels. XFEM techniques like cohesive segment and XFEM based LEFM using virtual crack closure technique (VCCT) are used for crack growth analysis. Various crack domain selection and parametric studies of stiffener thickness are presented. It is observed from the numerical analyses that the stiffened panels have about 20% higher yield strength compared to the un-stiffened panel.
Page(s): 418-428
URI: http://hdl.handle.net/123456789/29417
ISSN: 0975-1017 (Online); 0971-4588 (Print)
Appears in Collections:IJEMS Vol.21(4) [August 2014]

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