Predicting Snap-through of a Thin-walled Panel due to Thermal and Acoustic Loads
Abstract
Under contract from Wright-Patterson AFB (WPAFB), ATA Engineering, Inc., (ATA) has performed a study of "snap-through buckling" of a panel on a hypersonic vehicle under the influence of fluctuating pressures. Snap-through occurs when the elastic stiffness of the structure is cancelled by the effects of compressive stress within the structure. If this effect causes the structure to suddenly displace a large amount in a direction normal to the load direction then it is classical bifurcation buckling. If there is a sudden large movement in the direction of the loading it is snap-through buckling. The analysis was performed by applying aerothermal loads and fluctuating pressure loads on a thin-walled panel. Representative metallic (Inconel X-750) panel structures have been defined. Uncoupled nonlinear computational structural dynamics (NLCSD) using Abaqus/Explicit simulations performed on these panels include their quasi-static deformation under the vehicle?s aerothermal loads and their vibratory response to aerodynamic fluctuating pressure loads. The latter analysis has captured the phenomenon of snap-through response between two stable buckling equilibrium positions. The presenters will show the methods used and the results of this study, especially as it relates to the use of Abaqus.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 2010
- Accession Number
- ADA552457
Entities
People
- Parthiv Shah
- R. S. Miskovish
- Stephen M. Spottswood