Instability of Short Circular Cylindrical Laminated Composite Shells under Pure Bending.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
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Short cylindrical shells made from symmetrical laminated advanced composites were analyzed with the intent of examining the effects of certain shell properties on shell instability. Four laminates were considered over a range of length to radius ratio of 12 to 10. Reinforcing fiber stiffness was also varied so that the effects of stiffening the laminates could be observed. Shell bending bifurcation analysis was performed using the STAGS-C computer code with a kinematic end rotation applied to the shell to produce the desired shell bending. Axial compression bifurcation comparison runs were also made using the STAGS-C program.
- Laminates and Composite Materials