Abstract
A 54 degree-of-freedom, high-order triangular plate finite element extended for geometrically nonlinear static and dynamic analysis is used to formulate and analyze the supersonic nonlinear panel flutter problems. The finite element formulation is based on Kirchhoffs theory of thin plates. The quasisteady aerodynamic theory is used. Numerical solution procedures are presented. The limit cycle oscillation analyses are performed for twodimensional and square panels with all edges simply supported and clamped, respectively. The effects of in-plane compressive force, mass ratio, and in-plane edge stress free condition are considered. Stress distributions for the limit cycle oscillation of a two-dimensional panel are plotted. For the case of panels under static pressure differential, the results for the steady mean amplitude and flutter dynamic pressure are obtained for the twodimensional and square panels, respectively. The effect of biaxial in-plane compressive stress for a simply supported square panel is studied and boundaries among the flat and stable region, dynamically stable buckled region, and the limit cycle oscillation region are found. Alternative analytical and numerical solutions are available for most of the examples for comparison and all are in excellent agreement.
Published Version
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