Abstract
Fatigue failure analysis of pristine composite laminates and composite laminates with circular cut-outs made of CFRP T300/5208 with stacking sequence {0}5s , {90}5s , {0/90/0/90/0} s and {+45/−45/0/90/0} s are carried out. Fatigue damage model using physics-based approach based on multicontinuum theory and kinetic theory of fracture considering matrix cracking failure criterion is developed to calculate the fatigue life of above-mentioned composite laminates. Following the above model, S-N curves are derived for different stress ratios for the pristine composite laminates and laminates with circular cut-outs. The proposed fatigue model has been validated by comparing the predicted results with experimental results available in the literature. The results show that the fatigue life to failure of pristine composite laminates is more as compared to the laminates with circular cut-outs. For different stress ratio values, the stress-life (S-N) curves move upward indicating that fatigue life is more as the stress ratio decreases for all the laminates. The physics-based approach can be used as an alternative approach for predicting fatigue life of composites. This analytical approach minimizes expensive testing activities significantly. The studies are important and essential to evaluate the structural integrity of composite airframe structures.
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Acknowledgements
The authors kindly acknowledge the financial support of council of Scientific and Industrial Research (CSIR) under ASTA grant ESC-02-12-03. They would like to thank the Director, CSIR-National Aerospace Laboratories, Bangalore and Dr. Satish Chandra, Head, STTD, CSIR-NAL, Bangalore for encouragement and permitting them to present and publish the work.
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Sahoo, P.K., Gujar, S., Manjuprasad, M. (2018). Fatigue Life Prediction of Composite Airframe Panel. In: Prakash, R., Jayaram, V., Saxena, A. (eds) Advances in Structural Integrity. Springer, Singapore. https://doi.org/10.1007/978-981-10-7197-3_7
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DOI: https://doi.org/10.1007/978-981-10-7197-3_7
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