Hypersonic aircraft structures must operate in a complex loading environment, where the coupling of the aircraft structural response with the aerodynamics will lead to conditions involving rich nonlinear dynamics. The modeling of these fluid-thermal-structural interactions is complex and prohibitively expensive when high fidelity models are used (i.e., CFD and FEA). This aspect, and the lack of relevant flight-test and experimental data, have resulted in knowledge gaps, which have led to the design of overly-conservative structures in the past. Work at the Structural Sciences Center (SSC) of the USAF Research Laboratory has focused on addressing these knowledge gaps from a structures perspective. As discussed in Part I of this paper, 3 years ago the SSC began a series of wind-tunnel experiments to provide full-field experimental data for a clamped nominally flat panel exposed to supersonic flow. The present work will focus on numerical predictions of the panel dynamic response using a reduced order model (ROM) for the structural response and full-field measurement data to represent the loads on the panel.
CITATION STYLE
Perez, R. A., Spottswood, S. M., Beberniss, T. J., Bartram, G. W., & Eason, T. G. (2016). Nonlinear dynamic response prediction of a thin panel in a multi-discipline environment: Part II—numerical predictions. In Conference Proceedings of the Society for Experimental Mechanics Series (Vol. 1, pp. 249–257). Springer New York LLC. https://doi.org/10.1007/978-3-319-29739-2_23
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