Composite material structure, and aircraft wing and aircraft fuselage provided therewith

A composite material structure for an aircraft comprising:

• a structure member with holes consisting of metal, the structure member with holes extending in one direction and having holes formed therein;
• an adjacent structure member formed as a composite material consisting of fiber reinforced plastics, the adjacent structure member extending in the one direction and being connected to a side portion of the structure member with holes and to a portion avoiding positions of the holes formed in the structure member with holes;
• and
• a plurality of stringers provided so as to extend in the one direction,
• wherein the structure member with holes includes:
• a fixed thickness region;
• and
• peripheral edge regions reinforcing peripheral edge portions of the holes, each of the peripheral edge regions being further increased in thickness compared to the fixed thickness region, and
• wherein regions other than the peripheral edge regions are not increased in thickness,
• wherein the side portion of the structure member with holes is connected to the side portion of the adjacent structure member at division surfaces extending in the one direction, or the division surfaces are provided so as to incline with respect to a plate thickness direction and are connected to each other,
• wherein one of the stringers extends in the one direction along the division surfaces, and
• wherein the one stringer is placed on the division surfaces, and is fixed to an inner surface of the structure member with holes and the adjacent structure member by fasteners configured by a bolt, a nut, and/or bonding.