4.6 Article

Face/core disbond fatigue growth in honeycomb cored aircraft sandwich elements under mixed mode flatwise tension loading

Journal

JOURNAL OF SANDWICH STRUCTURES & MATERIALS
Volume 25, Issue 1, Pages 23-43

Publisher

SAGE PUBLICATIONS LTD
DOI: 10.1177/10996362221115420

Keywords

Sandwich disbond/debond; honeycomb core; aircraft element; mixed-mode characterization; sandwich tearing test; crack growth rate; mode-mixity; fracture toughness

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This study investigates the disbond damage growth in honeycomb cored sandwich structures under static and fatigue mixed mode loading through numerical and experimental methods. A two-dimensional finite element model and the Crack Surface Displacement Extrapolation mode separation method were used to predict face/core interface fatigue crack propagation based on a fracture mechanics analysis sub-routine. The Cycle Jump technique was employed to accelerate the fatigue analysis. Mixed mode fatigue characterization testing was performed, which generated a relationship between crack propagation rates and energy release rate amplitudes as a modified Paris Law. The numerical model was validated against experimental measurements, showing good agreement.
Disbond damage growth in honeycomb cored sandwich structures due to static and fatigue mixed mode loading is investigated numerically and experimentally. A two dimensional finite element model was generated using core homogenization and the Crack Surface Displacement Extrapolation mode separation method, integrated into a fracture mechanics based analysis sub-routine to predict face/core interface fatigue crack propagation. The Cycle Jump technique was furthermore applied to accelerate fatigue analysis. Mixed mode fatigue characterization testing was conducted using Double Cantilever Beam specimens loaded with Uneven Bending Moments, generating a relationship between crack propagation rates and energy release rate amplitudes as a modified Paris Law, measured at three mode-mixity phase angles. The measured Paris laws were subsequently used as input data for the numerical fatigue model. The numerical model was validated against CFRP/Nomex (R) Sandwich Tearing Test specimen tests with a propagating face/core interface crack yielding varying mode-mixities. The results from the validation showed good agreement between numerical predictions and experimental measurements.

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