Response of Segmented-Stiffness Composite Cylinders to Axial End Shortening

摘要

Composite fuselage structures that feature different laminates in the crown, sides, and keel may be part of future aircraft designs. Here exact and approximate solutions for the response to axial end shortening of cylinders made in this fashion are investigated. It is concluded that circumferential displacements are what distinguish these designs from more conventional single-laminate designs.