Abstract
A variationaly consistent mathematical model based on the refined higher order theory is used to develop a finite element procedure for analyzing the dynamic instability under biaxial buckling loads of rectangular composite plates. Laminates with various thicknesses and stacking sequence under various biaxial loads and boundary conditions are considered. The natural frequencies and mode shapes as well as the buckling loads and deformed shapes are computed for different values of transverse compressive load and the shift between the primary and secondary buckling modes is analyzed. The second order approximation of the instability regions corresponding to the first two natural frequencies are determined and the effects of static transverse and longitudinal compressive loads are investigated.
| Original language | English (US) |
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| Title of host publication | 19th AIAA Applied Aerodynamics Conference |
| State | Published - 2001 |
| Event | 19th AIAA Applied Aerodynamics Conference 2001 - Anaheim, CA, United States Duration: Jun 11 2001 → Jun 14 2001 |
Other
| Other | 19th AIAA Applied Aerodynamics Conference 2001 |
|---|---|
| Country/Territory | United States |
| City | Anaheim, CA |
| Period | 6/11/01 → 6/14/01 |
ASJC Scopus subject areas
- Aerospace Engineering
- Mechanical Engineering