Progressive Damage Analysis of Laminated Composite (PDALC)--a computational model implemented in the NASA COMET finite element code
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Progressive Damage Analysis of Laminated Composite (PDALC)--a computational model implemented in the NASA COMET finite element code

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Published by National Aeronautics and Space Administration, Langley Research Center, National Technical Information Service, distributor in Hampton, Va, [Springfield, Va .
Written in English

Subjects:

  • Residual strength.,
  • Constitutive equations.,
  • Structural analysis.,
  • Finite element method.,
  • Stress distribution.,
  • Laminates.,
  • Composite materials.,
  • Matrix materials.,
  • Cracking (Fracturing)

Book details:

Edition Notes

Other titlesComputational model implemented in the NASA COMET finite element code.
StatementDavid C. Lo ... [et al.].
SeriesNASA technical memorandum -- 4724.
ContributionsLo, David C., Langley Research Center.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL15504614M

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Progressive Damage Analysis of Laminated Composite (PDALC)—A Computational Model Implemented in the NASA COMET Finite Element Code.   Failure or damage mode of composite material is complex compared with homogeneous material, for example, metal or alloy, attributing their multiphase microstructures. The failure mode of composite laminate is usually classified into three types: fiber failure, matrix failure, and : Zhaotian Wu, Chuwei Zhou.   2. Progressive damage analysis. To perform progressive damage analysis of composite materials, the user needs to provide linear elastic orthotropic material properties and two material models: damage initiation and damage evolution law. Damage initiation criteriaCited by: Progressive multi-damage analysis of composite laminate using higher order zig-zag plate theory Article (PDF Available) in Advances in Mechanical Engineering 12(4) April

A method for analysis of progressive failure in the Computational Structural Mechanics Testbed is presented in this report. The relationship employed in this analysis describes the matrix crack damage and fiber fracture via kinematics-based volume-averaged variables. notched laminated plate. A parametric study of progressive damage have also been presented to study the effect due to change in lamination scheme. Progressive failure analysis of laminated plate Progressive damage analysis have been performed on IM7/ composite laminates. Hierarchical material models with microstructure for nonlinear analysis of progressive damage in laminated composite structures: Author(s): Haj-Ali, Rami M. Doctoral Committee Chair(s): Pecknold, David A. Department / Program: Civil and Environmental Engineering: Discipline: Civil and Environmental Engineering: Degree Granting Institution. xComposites is a powerful tool for various analyses of composites: failure analysis, progressive damage analysis, fatigue analysis, & etc. Using the micromechanics-based multiscale approach, you can unveil the micro mechanisms of composites, design your novel combinations, and test new parts.

2. Composite Material Damage Model MAT_ Damage model MAT_ linked with LS-DYNA code is used for the progressive damage analysis of UD or PW composite laminates, and the behaviors of fiber failure, matrix damage and delamination can effectively be simulated under diverse loading conditions. In addition to the criteria for these.   Progressive failure analysis of carbon-fiber reinforced polymer (CFRP) laminates using combined material nonlinear elasticity and continuum damage mechanics based on treatment of coupon test 24 June | Journal of Composite Materials, Vol. 50, No. The subject of the presented research was a thin-walled composite column made of CFRP (carbon-epoxy laminate). The test sample had a top-hat cross-section with a symmetrical arrangement of laminate layers [90/−45/45/0]s. The composite structure was subjected to the process of axial compression. Experimental and numerical tests for the loss of stability and load-carrying capacity of . A novel progressive damage and failure model for fiber reinforced laminated composites is presented in this work. The model uses the thermodynamically based Schapery Theory (ST) to model progressive microdamage in the matrix phase. Matrix failure is not governed with a matrix failure criterion, but rather matrix failure occurs naturally through the evolution of microdamage.