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  • Verification of a Hypersonic Test Panel through modal analysis of two finite element solvers, and various element types and formulations

    Paper number



    Ms. Erika Lieberknecht, United States



    Panels on hypersonic vehicles are subjected to complex aero-thermal loading, resulting in large in-plane stresses. There is a concern that these loads can lead to thermo-mechanical buckling. Since thermo-mechanical buckling can be analyzed by studying the decrease in natural frequencies of the panels as the in-plane compression and shear loads increase,   investigating the panel's natural frequencies using various finite element formulations is a first step in modeling this phenomenon. Selection of appropriate shell or 3-D solid finite element, to be used for discretizing the panel  is very important  as the unique curvature of these panels  decreases the validity of both the thin-shell as well as shallow shell  assumptions. Finite element type and formulation selections for the modal analysis were investigated and comparisons were made using LS-Dyna\textsuperscript{\textcopyright} and Abaqus\textsuperscript{\textcopyright}, two well-established finite element solvers. The variation in eigenvalues and natural frequencies, obtained  from various finite element formulations, of an example hypersonic panel are quantified in this study. The thermo-mechanical buckling load will next be obtained by studying natural frequencies of these panels under increased compression and shear loads.
    Abstract document


    Manuscript document