Structural skin panels on high-speed aircraft are susceptible to buckling under mechanical and thermal loading. While many studies have explored the large deformations observed during dynamic snap-through, and often these deformations are taken to be a proxy for increased stresses, few have directly explored the internal stresses its potential impact on fatigue. This presentation will introduce recent results on the internal stress histories in post-buckled thin structural panels. The work relies on commercial finite element software; however, experimental results will also be introduced.

In this presentation, the potential effect of dynamic snap-through on fatigue life will be discussed, and the effect of panel thickness, in-plane (thermal and mechanical) loads, and transverse (aerodynamic) loads will be shown. The results are organized in terms of characteristic types of behavior observed in bistable structures under harmonic forcing (e.g., periodic, and chaotic snap-through). This work is a part of a larger effort toward a challenge-problem based framework for the characterization of structural dynamics and life cycle in extreme environments.


Nonlinear Structural Dynamics and Stress Analysis of Composite Aerostructural Skin Panels

Division / Sponsors: 
Design Engineering Division and Computers & Information In Engineering Division


Paper Proceedings: https://asmedigitalcollection.asme.org/IDETC-CIE/IDETC-CIE2020/volume/83907

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