COMPOSITE-MATERIAL STRUCTURE AND AIRCRAFT MAIN WING AND AIRCRAFT FUSELAGE PROVIDED WITH THE SAME

摘要

A composite-material structure used for an aircraft, comprises a holed structural member and an adjacent structural member that are a composite material made of fiber reinforced plastic. Both extend in a longitudinal direction of a main wing of the aircraft. The adjacent structural member is connected to a side portion of the holed structural member. The holed structural member and the adjacent structural member are configured to have applied thereto a tensile compressive load. The holed structural member is configured to have a total tensile/compressive rigidity in the longitudinal direction lower than a total tensile/compressive rigidity of the adjacent structural member. A bottom-surface skin of a main wing is formed of the holed structural member and the adjacent structural member that connects the holed structural member with the adjacent structural member. The hole is an access hole used for inspecting a fuel tank provided inside the main wing.