Effect of Composite Stiffened Panel Design on Skin-Stringer Separation in Postbuckling
Luc Kootte (TU Delft - Aerospace Structures & Computational Mechanics)
Chiara Bisagni (TU Delft - Aerospace Structures & Computational Mechanics)
Vipul Ranatunga (Air Force Institute of Technology)
Stephen B. Clay (Air Force Research Laboratory Sensors Directorate Wright-Patterson AFB)
Carlos G. Dávila (NASA Langley Research Center)
Cheryl Rose (NASA Langley Research Center)
More Info
expand_more
Other than for strictly personal use, it is not permitted to download, forward or distribute the text or part of it, without the consent of the author(s) and/or copyright holder(s), unless the work is under an open content license such as Creative Commons.
Abstract
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 postbuckling deformation using the building block approach and single-stringer specimens. In particular, the methodology can identify whether the skin-stringer separation occurs due to bending or twisting, so that these two possible modes can be studied separately. For bending, a simple criterion that can predict the location of initiation is presented. This procedure has the potential to reduce the overall development cost and allows the investigation of the design parameters that influence the skin-stringer separation.