Laminate Stiffness Tailoring for Improved Buckling Performance

Published: 31-07-2020| Version 1 | DOI: 10.17632/v2h5h5vdcc.1
Contributor:
Christopher York

Description

This data item provides supplementary information to an article entitled: Laminate Stiffness Tailoring for Improved Buckling Performance. The article presents a stiffness tailoring approach for improved buckling performance using double angle-ply laminates. These special configurations are either stiffness matched to the extensional stiffness of equivalent balanced and symmetric laminate designs, or standard-ply designs, representing typical aircraft components, such as a spar, skin or stiffener, to identify configurations with improved buckling performance, or matched to specific bending stiffness properties, in order to achieve a buckling performance threshold. Tailored designs with matched isotropic properties in bending are used to demonstrate the influence of variation in axial stiffness on the stability of thin walled sections. Many of the designs can be tapered in thickness, through ply terminations, which permit tailoring of the bending stiffness properties between compression and shear dominant regions. The following electronic appendices are listed below: Appendix 1 - Balanced and Symmetric Standard-Ply Designs Appendix 2 - Double Angle-Ply Designs Derived from Standard-Ply Designs Appendix 3 - Double Angle-Ply Designs Appendix 4 - Tapered Double Angle-Ply Designs