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    <copyright>Copyright © 2026. National Academy of Sciences. All rights reserved.</copyright>
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    <managingEditor>tris-trb@nas.edu (Bill McLeod)</managingEditor>
    <webMaster>tris-trb@nas.edu (Bill McLeod)</webMaster>
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      <title>Finite element modelling of bi-material interface for crack growth evaluation: Technical note</title>
      <link>https://trid.trb.org/View/1508262</link>
      <description><![CDATA[Finite element (FE) method is commonly used to study cracks in structures. In this paper, J-integral method is applied over FE model of a cracked body to determine stress intensity factor (SIF) in the domain of linear elastic fracture mechanics (LEFM). This paper formulates the J-integral methodology for 2D FE model using a coarse mesh with less degrees of freedom. Two cases, a finite plate with edge cracks and a normal crack growth in fiber metal laminated plate, are demonstrated. Numerical implementation and mesh refinement issues to maintain path independent J-integral values are explored.]]></description>
      <pubDate>Tue, 29 May 2018 16:03:50 GMT</pubDate>
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      <title>Modelling Bird Impacts on an Aircraft Wing - Part 1: Material Modeling of the Fibre Metal Laminate Leading Edge Material With Continuum Damage Mechanics</title>
      <link>https://trid.trb.org/View/756861</link>
      <description><![CDATA[Glass-based FML may be a suitable material for aircraft parts likely to be subjected to high velocity impacts from objects such as runway debris or birds.  This article reports on a research study undertaken to examine the performance of a glass-based fiber metal laminates (FML) leading edge structure, and to develop analytical tools capable of predicting the structural response of such as structure to a bird strike.  This article is the first in a two-part series reporting on this research.  In this part, the authors describe the development of a material model for the FML, based on a recently implemented continuum damage mechanics (CDM) model and capturing its strain rate dependency.  Results from the model are compared with experimental results on FML at variable strain rates and the model is shown to be capable of capturing most of the complex strain rate dependent behavior exhibited by these materials.  The authors conclude that, considering the incomplete data available for the individual constituents of the FML (particularly the glass layers), the agreement between the simulations and experiments is very good.  They note particularly the capturing of the complex failure process in the quasi-static 0 degree FML tests.]]></description>
      <pubDate>Thu, 23 Jun 2005 12:40:28 GMT</pubDate>
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      <title>Modelling Bird Impacts on an Aircraft Wing - Part 2: Modelling the Impact With an SPH Bird Model</title>
      <link>https://trid.trb.org/View/756862</link>
      <description><![CDATA[Glass-based FML may be a suitable material for aircraft parts likely to be subjected to high velocity impacts from objects such as runway debris or birds.  This article reports on a research study undertaken to examine the performance of a glass-based fiber metal laminates (FML) leading edge structure, and to develop analytical tools capable of predicting the structural response of such as structure to a bird strike.  This article is the second in a two-part series reporting on this research.  In this part, the authors report on the development of a finite element model, used to simulate the bird strike tests.  The model uses smooth particle hydrodynamics (SPH) for modeling the bird and the material model developed in Part 1 of the paper for modeling the leading edge skin.  The authors conclude that the pre-test models were successful in providing predictive capability, with the strain-rate dependent continuum damage mechanics model used for the FML skin successfully predicting the behavior of the skins, despite the amount of input data that was not available (and thus had to be estimated).  However, the models incorrectly predicted that rivet failures occurred in the two outer ribs and also underestimated the amount of skin deformation.  The two FML leading edge structures performed well, successfully absorbing the energy of the bird impact without penetration of the skin.  In addition, the SPH method was very effective for modeling bird strikes on these structures.]]></description>
      <pubDate>Thu, 23 Jun 2005 12:40:28 GMT</pubDate>
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