COMPOSITE MATERIAL STRUCTURE, AND AIRCRAFT WING AND FUSELAGE PROVIDED THEREWITH

摘要

Provided is a composite material structure that enables weight reduction, with consideration given to stress concentrations in areas around holes. A wing (1), which is the composite material structure, is a composite material made of fiber reinforced plastic extending in one direction and in which access holes (5) are formed. A lower outer plate (3) on the wing (1) is subjected to a tensile load in the longitudinal direction. The longitudinal tensile stiffness of peripheral regions (3a) of the access holes (5) is smaller than the longitudinal tensile stiffness of other regions (3b) surrounding the peripheral regions (3a).