Abstract
Composite-walled hexagonal honeycomb core is considered for stiffness-based design. It is shown that the torsional and flexural stiffnesses of its all-composite sandwich may be 3- and 8-times higher, respectively, compared to structural foam core sandwich panel. This increase is attributed to an order of magnitude higher transverse shear resistance of composite-HC core. All-composite design can also outperform traditional aluminum core sandwich by about 25% and 60% increase in stiffness values under torsional and flexural loading. The results also reveal that stiffness of sandwich panel configurations of an arbitrarly fixed total structural weight can be mapped into unified “master design curves”. They suggest skin-to-core weight ratio for optimal flexural and torsional stiffnesses. The ratios herein are 1.3 and 2.6 respectively. The penalty of one on the other is about 8–10%. The ratio of 1.85 is the best compromise between the flexural and torsional stiffnesses reducing the trade-off to 2–3%.
Sign-in/Register to access full text options 
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.
