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A Computational Method for Predicting the Damage and Failure Due to Impact of Double Hat Stiffened Aircraft Skin Panels
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DOI：10.1007/s42496-025-00301-4.png)
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Abstract
En 中文
We present a computational method to predict the extent of damage and disbond failure of stiffened carbon fiber reinforced polymer (CFRP) structural panels which are core structures used in modern aircraft. Low-velocity impacts (LVI) can occur during maintenance, transport, or service. Precisely predicting the extent of LVI damage to accurately assess the residual compressive load carrying capacity of the panel is needed. We present results for the extent and amount of impact damage in a CFRP structural panel due to LVI impact using a novel high fidelity computational method developed by the authors. Different damage modes, such as delamination, matrix failure and fiber failure are predicted and compared for different impact locations. Additionally, the results from a 105J impact simulation were used to develop a field function that links element size, cohesive strength, and disbond area, enabling computational efficiency while maintaining prediction accuracy.
Keywords:
Composite
Hat stiffener
Impact
Delamination
Damage
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