Equivalent bulging factors of internally pressurized cracked laminated composite cylindrical shell structures

Bulging factor expressions developed and available in the literature so far, are useful for damage tolerance design and characterization of internally pressurized cracked isotropic shell structures. They are not applicable to laminated composite shell structures. On the other hand, modern aircrafts and many aerospace systems are made of or partially made of laminated composite materials. Consequently, simple formulas have been developed and are presented as possibly viable means for tolerance design and characterization of cracked laminated composite shell structures under internal pressure. These simple formulas give the so-called equivalent bulging factors. Several cases of laminated composite cylindrical shells under suddenly applied internal pressures are studied. Their corresponding equivalent bulging factors are determined and presented to demonstrate the simplicity of use and their potential in damage tolerance design and characterization of internally pressurized cracked laminated composite shell structures.