Solid finite element-based techniques that have been successfully used for simulation of the matrix-dominated failure modes in carbon-fiber and glass-fiber reinforced polymer-matrix composites are presented in this work. Such techniques do not require initial flaw assumptions for the damage prediction. The main objective of this work is to show the ability of solid finite element-based techniques to accurately predict the onset and progression of damage under quasi-static and fatigue loading. The specific objectives are: (a) to develop failure simulation models of multidirectional carbon/epoxy laminate articles in a finite element code; and (b) to correlate the failure predictions with test data. The test articles include 16-ply IM7/8552 tape open-hole tensile coupons, a hybrid Ti, carbon/epoxy and glass/epoxy laminate, and a hybrid carbon/epoxy and glass/epoxy lug laminate. Available stress-strain relations and failure criteria are built in ABAQUS models, and material fatigue curves are used to predict the number of cycles to fatigue damage onset and progression. Model predictions and subsequent test correlations are presented: Three-dimensional solid element finite element simulation and fracture-based failure criteria show the ability to capture the multi-stage matrix-ply cracking and delaminations in composite laminates, including the hybrid laminates. The fatigue progression algorithm presented in this work is able to accurately capture ply cracking sequence and fatigue crack growth in the open hole tensile specimen.


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    Title :

    Finite element-based damage tolerance methods for aircraft composites


    Additional title:

    Auf FE-Verfahren basierende Schadenstoleranzmethoden für Verbundwerkstoffe in der Luftfahrt


    Contributors:


    Publication date :

    2011


    Size :

    10 Seiten, 22 Bilder, 4 Tabellen, 11 Quellen



    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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