Static and Fatigue Post-Buckled Behavior of Composite Shear Panels in the ACAP Design

Laminated composites offer high strength with significant weight savings compared to metallic structures. When used as typical stiffened skin in aircraft design, laminated composites weigh approximately 1.5 Ib/ft² as compared to 2 Ib/ft² for comparable metallic skins; approximately a 25%, savings. In metallic structures, it is common practice to design skins to buckle when integrity and durability is maintained and loading is below design allowables. The behavior of metallic skins in the post-buckling range is well known and design information (empirical in nature) readily available. However, laminated composites are being utilized as typical skin structure in modern aircraft with little data available describing their behavior in the postbuckled range.