Damping effects in nonlinear panel flutter

被引：10

作者：

Bismarck-Nasr, MN ^{[1
]}

Bones, CA ^{[1
]}

机构：

[1] Inst Tecnol Aeronaut, Div Aeronaut Engn, BR-12228900 Sao Jose Dos Campos, Brazil

来源：

AIAA JOURNAL | 2000年 / 38卷 / 04期

关键词：

D O I：

10.2514/2.1014

中图分类号：

V [航空、航天];

学科分类号：

08 [工学]; 0825 [航空宇航科学与技术];

摘要：

An attempt was made to assess and discuss the effect of damping in nonlinear panel flutter analysis. Structural, viscoelastic, and aerodynamic dampings were included in the formulation, and their effect on the stability boundary of the shell was presented. A finite element formulation was used for the problem formulation, and the nonlinear aeroelastic solution was made using perturbation method.

引用

页码：711 / 713

页数：3

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