NONPERIODIC FLUTTER OF A BUCKLED COMPOSITE PANEL

被引：8

作者：

CHANDIRAMANI, NK

PLAUT, RH

LIBRESCU, LI

机构：

[1] Department of Engineering Science and Mechanics, Virginia Polytechnic Institute and State University, Blacksburg, 24061, VA

[2] Department of Civil Engineering, Virginia Polytechnic Institute and State University, Blacksburg, 24061, VA

来源：

SADHANA-ACADEMY PROCEEDINGS IN ENGINEERING SCIENCES | 1995年 / 20卷

关键词：

PANEL FLUTTER; NONPERIODIC MOTION; CHAOS; SHEAR DEFORMATION; LAMINATED COMPOSITE PLATES;

D O I：

10.1007/BF02823212

中图分类号：

T [工业技术];

学科分类号：

08 ;

摘要：

The nonlinear vibrations of a composite panel subjected to uniform edge compression and a high-supersonic coplanar flow is analysed. Third-order piston theory aerodynamics is used and the. effects of in-plane edge restraints, small initial geometric imperfections, transverse shear deformation, and transverse normal stress are considered in the structural model. Periodic solutions and their bifurcations are determined using a predictor-corrector type Shooting Technique, in conjunction with the Arclength Continuation Method for the static state. It is demonstrated that third-order aerodynamic nonlinearities are destabilizing, and hard flutter oscillations (both periodic and quasiperiodic) of the buckled panel are obtained. Furthermore, chaotic motions of an uncompressed panel, as well as a buckled-chaotic transition, and chaos via period-doubling are possible, and the associated Lyapunov exponents are computed. A coexistence of the buckled state with flutter motion may also occur. Results indicate that edge restraints parallel to the flow do not significantly affect the immediate postcritical response, and that a higher-order shear deformation theory is required for a moderately thick/flexible-in-transverse-shear composite panel.

引用

页码：671 / 689

页数：19

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