Multiphysics based progressive failure analysis for cryogenic composite fuel tank design
Additional Document Info
Thermal residual stresses, internal fuel pressure and acceleration stresses during launch stage were evaluated and quantified for cryogenic composite fuel tank design. Fuel leakage induced temperature variation through laminate thickness after initial cracking was applied to a progressive failure analysis. Comparison of the results with conventional failure analyses was performed. Critical temperature and pressure conditions for failure initiation and whole laminate cracking were found based on the failure analysis.