Integration of composite materials in aviation applications undeniably offer multiple important benefits, and more modelling techniques and failure analysis tools are increasingly being developed in evaluated to reduce the high costs associated with investigating the mechanical characteristics and prediction of failure of fiber reinforced composites. This article evaluates and compares between some of the most common failure criteria, Hashin, Puck and maximum stress criteria. The conclusion of this article shows that the interactive failure criteria are more adequate to use in the prediction of failure although they are inherently more complex to describe.
In this study, a damaged three-stringer PRSEUS panel simulating a midbay-to-midbay damage scenario was modelled in Abaqus and analyzed under tension. Moreover, employing the Abaqus built-in Hashin failure criteria verified the reliability of the criteria in predicting damage initiation with great accuracy. Further, these criteria were implemented via UMAT to investigate the effect of shear stress on the analysis, indicating that manipulating the coefficient of shear stress contribution led to a significant enhancement in analysis accuracy. Lastly, the same procedure was followed in the analysis of a repaired three-stringer panel, validating once again the adequacy of the adopted approach and simultaneously highlighting the efficiency of the repair technique in restoring load carrying of the PRSEUS panel. This study may provide a dependable reference presenting a simplified and significantly less computationally demanding approach for damage analysis composite structures and their repair, in addition to further applying these techniques to access the damage-arresting capabilities of these structures.
In this study, a finite element approach was used to analyze the PRSEUS-based undamaged wing structure of a civil aircraft with a blended-wing-body configuration. The displacement, stress, and strain distribution of the PRSEUS wing structure were studied under an aerodynamic load with three different values of the factor of safety. This was used as a reference to study the response of the same wing configuration, first with a single stringer, where failure was initiated at the fourth loading value, while the second loading condition was sufficient to initiate failure in the triple-stringer damage wing. In addition, damage to rib components was investigated, and it was shown that damage to a single rib and double rib did not impose significant risks to the structural integrity of the wing structure, and the results have shown that the values of displacement, stress, and strain do not differ much from those of the undamaged wing, even as the length of the rib damage is increased.
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