Buckling of Stiffened Laminated Composite Circular Cylindrical Shells with Different Moduli in Tension and Compression: Preliminary Results.
Final rept. 1 Apr 73-31 Jul 74,
SOUTHERN METHODIST UNIV DALLAS TEX DEPT OF CIVIL AND MECHANICAL ENGINEERING
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An exact buckling criterion, within the framework of classical buckling theory, is derived for eccentrically stiffened multilayered circular cylindrical shells made of materials that have different orthotropic moduli in tension and compression. Such behavior is typical of many current composite materials. The buckling criterion is valid for arbitrary combinations of axial and circumferential loading, including axial compression and internal pressure as well as axial tension and lateral pressure. The material model stress-strain relationship is based on a bilinear stress-strain curve with a discontinuity in slope modulus at the origin. Numerical results are used to illustrate application of the buckling criterion. In particular, results are given for single-layered shells with noticeable differences in tensile and compressive moduli. Moreover, preliminary results are shown for shells laminated of advanced composite materials. Finally, the effects of eccentric stiffeners are displayed.
- Laminates and Composite Materials