Correlation of Fuselage and Subcomponent Panel Responses Using ABAQUS Explicit Progressive Damage Analysis Tools

摘要

Analysis performed in this study substantiates the need for high fidelity vehiclelevel progressive damage analyses (PDA) structural models for use in theverification and validation of proposed sub-scale structural models and to supportrequired full-scale vehicle level testing. PDA results are presented that capture andcorrelate the responses of sub-scale 3-stringer and 7-stringer panel models and anidealized 8-ft diameter fuselage model, which provides a vehicle level environmentfor the 7-stringer sub-scale panel model. Two unique skin-stringer attachmentassumptions are considered and correlated in the models analyzed: the TIEconstraint interface versus the cohesive element (COH3D8) interface. Evaluatingdifferent interfaces allows for assessing a range of predicted damage modes,including delamination and crack propagation responses. Damage modelsconsidered in this study are the ABAQUS built-in Hashin procedure and theCOmplete STress Reduction (COSTR) damage procedure implemented through aVUMAT user subroutine using the ABAQUS/Explicit code.