Effect of Composite Stiffened Panel Design on Skin-Stringer Separation in Postbuckling

To design aeronautical composite multi-stringer panels that can safely operate in a postbuckled state, it is important to identify the parameters that can influence the different modes in which skin-stringer separation might occur. A methodology is under development to study the interaction between the skin-stringer separation and the...

A Methodology to Investigate Skin-Stringer Separation in Postbuckled Composite Stiffened Panels

A methodology is presented to investigate and improve the strength and damage tolerance of stiffened composite panels used in aerospace structures subjected to postbuckling deformation. These structural panels have the capability to operate in the postbuckling field, but the possible interaction between the postbuckling deformation and the...

Study of Skin-Stringer Separation in Postbuckled Composite Aeronautical Structures

Aeronautical composite stiffened structures have the capability to carry loads deep into postbuckling, yet they are typically designed to operate below the buckling load to avoid potential issues with durability and structural integrity. Large out-of-plane postbuckling deformation of the skin can result in the opening of the skin-stringer...