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• W2197766105 abstract "Carbon Fibres Reinforced Plastics composites have been demonstrated particularly suitable for aerospace structural applications due to their high specific strength and stiffness. Nevertheless, the relevant costs related to composites manufacturing and the difficulties in predicting their failure mechanisms have considerably slowed down their integration in the aerospace industry. Furthermore, the lack of robust numerical tools, able to take into account the damage tolerance of composite structures, especially in the preliminary design phases, has led to an over-conservative design, not fully realising the promised economic benefits. Among their several and complex failure mechanisms, composite structures have been demonstrated to be highly sensitive to delaminations arising after impact with foreign objects or caused by manufacturing defects. Hence, in order to design less conservative aerospace composite structures, it is mandatory to account for the effects of delaminations and their evolution even in the earlier stages of the design process. In order to achieve this goal, newer and faster numerical procedures representing the main phenomenological features governing the structural behaviour of damage tolerant composite structures, such as the delamination growth, needs to be developed.Thus, the study presented in this chapter has been aimed at developing a linear approach useful to improve the preliminary design and optimisation of stiffened composite panels tolerant to low velocity impacts induced damage." @default.
• W2197766105 created "2016-06-24" @default.
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• W2197766105 date "2015-01-01" @default.
• W2197766105 modified "2023-09-27" @default.
• W2197766105 title "A Fast Numerical Methodology for Delamination Growth Initiation Simulation" @default.
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• W2197766105 doi "https://doi.org/10.1007/978-3-319-04004-2_9" @default.
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