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Progressive Damage Analysis of Laminated Composite (Pdalc)-A Computational Model Implemented in the NASA Comet Finite Element Code

National Aeronautics and Space Adm Nasa
Progressive Damage Analysis of Laminated Composite (Pdalc)-A Computational Model Implemented in the NASA Comet Finite Element Code by National Aeronautics and Space Adm Nasa PDF

Author : National Aeronautics and Space Adm Nasa
Publisher : Independently Published
Page : 48 pages
File Size : 16,90 MB
Release : 2018-10-25
Category : Science
ISBN : 9781729236956

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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. Damage accumulation during monotonic and cyclic loads is predicted by damage evolution laws for tensile load conditions. The implementation of this damage model required the development of two testbed processors. While this report concentrates on the theory and usage of these processors, a complete list of all testbed processors and inputs that are required for this analysis are included. Sample calculations for laminates subjected to monotonic and cyclic loads were performed to illustrate the damage accumulation, stress redistribution, and changes to the global response that occur during the load history. Residual strength predictions made with this information compared favorably with experimental measurements. Lo, David C. and Coats, Timothy W. and Harris, Charles E. and Allen, David H. Langley Research Center RTOP 538-02-10-01

Progressive Damage Analysis of Laminated Composite (Pdalc) (a Computational Model Implemented in the NASA Comet Finite Element Code). 2.0

National Aeronautics and Space Adm Nasa
Progressive Damage Analysis of Laminated Composite (Pdalc) (a Computational Model Implemented in the NASA Comet Finite Element Code). 2.0 by National Aeronautics and Space Adm Nasa PDF

Author : National Aeronautics and Space Adm Nasa
Publisher : Independently Published
Page : 42 pages
File Size : 28,22 MB
Release : 2018-10-17
Category : Science
ISBN : 9781728889474

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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 damage variables. Damage accumulation during monotonic and cyclic loads is predicted by damage evolution laws for tensile load conditions. The implementation of this damage model required the development of two testbed processors. While this report concentrates on the theory and usage of these processors, a complete listing of all testbed processors and inputs that are required for this analysis are included. Sample calculations for laminates subjected to monotonic and cyclic loads were performed to illustrate the damage accumulation, stress redistribution, and changes to the global response that occurs during the loading history. Residual strength predictions made with this information compared favorably with experimental measurements. Coats, Timothy W. and Harris, Charles E. and Lo, David C. and Allen, David H. Langley Research Center RTOP 538-13-11-05