International Journal of Aerospace System Engineering

The Society for Aerospace System Engineering (항공우주시스템공학회)
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Strength and Crack Growth Computation for Various types of Stringers for Stiffened Panels using XFEM Techniques

  • Krishna, Lok S (SID, CSIR-National Aerospace Laboratories) ;
  • Reshma, G (Department of Aerospace Engineering, IIAEM-Jain University) ;
  • Dattaguru, B (Department of Aerospace Engineering, IIAEM-Jain University)
  • Received : 2018.10.13
  • Accepted : 2019.12.28
  • Published : 2020.06.30
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Abstract

In this paper the crack growth, modeling, and simulation of the stiffened and un-stiffened cracked panels presented using commercially available finite element software packages. Computation of stresses and convergence of stress intensity factor for single edge notch (SEN) specimens carried out using the finite element method (FEM) and extended finite element method (XFEM) and compared with an analytical solution. XFEM techniques like cohesive segment method and LEFM using virtual crack closure technique (VCCT), used for crack growth analysis and presented results for un-stiffened and stiffened panels considering various crack domain. The non-linear analysis considering both geometric and material non-linearity on stiffened panels with various stringers like a blade, L, inverted T and Z sections the results were presented. Arrived at the optimum stringer section type for the considered panel under axial loading from the numerical analysis.

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References

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