Abstract Many thin walled structures experience a combination of static thermal stress and large amplitude dynamic loads. From a dynamic perspective, the heating can change both the linear and nonlinear properties of the system so that completely different responses may be obtained (e.g. they may snap through rather than exhibiting a simple hardening nonlinearity). This work uses the “cold modes” approach to create various reduced order models of one panel from a concept hypersonic vehicle; heating is assumed to change only the linear natural frequencies of the panel, but not the mode shapes or geometrically nonlinear effects. The resulting reduced order models are studied by computing their nonlinear normal modes and their response subject to a random dynamic pressure. The comparisons reveal that much can be inferred about the response from the nonlinear modes.
Nonlinear Dynamic Analysis of a Thermally Buckled Aircraft Panel Using NNMs
2017-01-01
11 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
Nonlinear Dynamic Analysis of a Thermally Buckled Aircraft Panel Using NNMs
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