Abstract
Abstract A mesomechanical approach for simulating the mechanical performance of non-crimp fabric (NCF) composite structural parts is presented. The approach is based upon the use of representative volume elements (RVEs) fully characterized using homogenized progressive failure analysis previously verified for NCF materials through comparison with experimental results. NCF material is treated as a stitched laminated composite material system. Both characterization of the RVEs and modeling of the structural part are performed using the FE method. The derived behavior of the RVEs is assigned to the elements of a global FE model of the structural part. Implementation of the proposed multi-scale approach is made for a novel NCF ‘pi’ (Π) joint used to adhesively join aircraft structural parts. The assembled structure is subjected to T-tension loading. Debonding is an additional failure mode considered in the global analysis. Predicted results are in the form of failure initiation and progression within the structural part. The proposed approach is expandable to any type of fabric material, as long as the corresponding RVE is appropriately defined and characterized.
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