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

Conference paper (2021)

Authors

Lucas Kootte Aerospace Structures & Computational Mechanics - Aerospace Engineering
C. Bisagni Aerospace Structures & Computational Mechanics - Aerospace Engineering
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
Research Group
Aerospace Structures & Computational Mechanics (Aerospace Engineering) (TU Delft)
Copyright: © 2021 Lucas Kootte, C. Bisagni, Vipul Ranatunga, Stephen B. Clay, Carlos G. Dávila, Cheryl Rose
DOI: https://doi.org/10.2514/6.2021-0441
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Published Date

2021

Language

English

Reuse Rights

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Faculty

Aerospace Engineering

Department

Aerospace Structures & Materials

Research Group

Aerospace Structures & Computational Mechanics

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.

Files

6.2021_0441.pdf
(.pdf | 0.864 Mb)