Abstract
This study addresses the effect of thickness variation on the stability of the composite cylindrical shells under axial compression. Various lamination configurations and three commonly used composite materials are considered. Numerical results show that certain types of thickness variation patterns can greatly reduce the classical buckling load. Results indicate that the most detrimental effect of the thickness variation occurs when the wave number of the thickness variation is twice that of the classical buckling mode. For this case, an asymptotic formula is established by use of a computer algebra, which relates the buckling load reduction rate to the thickness variation parameter.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
