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Progressive Damage Analysis of Laminated Composite (PDALC)-A Computational Model Implemented in the NASA COMET Finite Element CodeA 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.
Document ID
19970002981
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Lo, David C. (Texas A&M Univ. College Station, TX United States)
Coats, Timothy W. (Old Dominion Univ. Norfolk, VA United States)
Harris, Charles E. (NASA Langley Research Center Hampton,VA United States)
Allen, David H. (Texas A&M Univ. College Station, TX United States)
Date Acquired
September 6, 2013
Publication Date
November 1, 1996
Subject Category
Structural Mechanics
Report/Patent Number
NAS 1.15:4724
NASA-TM-4724
L-17545
Accession Number
97N11760
Funding Number(s)
PROJECT: RTOP 538-02-10-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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