A materials science and aerospace structural analysis of carbon-fiber matrix degradation under cyclic thermal and pressure loads.
Carbon-fiber composite layers are bonded by epoxy matrices that can micro-crack when exposed to cyclic cabin pressurization, freeze-thaw moisture cycles (-55°C at cruise to +45°C on tropical runways), and high-G turbulence.
AirplaneTwin models interlaminar shear stress using cohesive zone elements, predicting the onset and propagation of delamination blisters between composite plies before structural stiffness degrades.
Predicting exact crack growth rates allows airline engineering teams to schedule targeted non-destructive testing (NDT) during routine overnight layovers rather than grounding aircraft unexpectedly.