A theoretical computational model of a plate in hypersonic flow |
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| Institution: | 1. Department of Aerospace Engineering, Center for Advanced Vehicular Systems (CAVS), Mississippi State University, Mississippi State 39762, United States;2. Air Force Research Laboratory, Wright Patterson Air Force Base Dayton OH 45433, United States;1. Faculty of Mechanical Engineering, Federal University of Uberlândia, Uberlândia, Brazil;2. São Carlos School of Engineering, University of São Paulo, São Carlos, Brazil;3. Faculty of Engineering, University of Porto, Porto, Portugal;1. College of Astronautics, Northwestern Polytechnical University, Xi?an 710072, China;2. Duke University, Durham, NC 27708-0300, United States |
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| Abstract: | A theoretical model of an elastic panel in hypersonic flow is derived to be used for design and analysis. The nonlinear von Kármán plate equations are coupled with 1st order Piston Theory and linearized at the nonlinear steady-state deformation due to static pressure differential and thermal loads. Eigenvalue analysis is applied to determine the system’s stability, natural frequencies and mode shapes. Numerically time marching the equations provides transient response prediction which can be used to estimate limit cycle oscillation amplitude, frequency and time to onset. The model’s predictive capability is assessed by comparison to an experiment conducted at a free stream flow of Mach 6. Good agreement is shown between the theoretical and experimental natural frequencies and mode shapes of the fluid–structure system. Stability analysis is performed using linear and nonlinear methods to plot stability, flutter and buckling zones on a free stream static pressure vs temperature differential plane. |
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| Keywords: | Structural dynamics Fluid–structure interaction Panel flutter Hypersonic Piston theory |
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