Composite material structure, aircraft wing and aircraft fuselage provided with same, and method for manufacturing composite material structure

A method of manufacturing a composite material structure, the composite material structure comprising a fiber-reinforced plastic composite material extending in one direction, wherein the one direction is 0°, and having a plurality of holes defined at intervals in a row in the one direction, that is subjected to a tensile load or a compressive load in the one direction, the method comprising:

• bending a composite material reinforced using continuous fibers made even in a longitudinal direction in a peripheral region around the holes so that a center line of a width of the composite material weaves between adjacent holes and zigzags in the one direction, thereby obtaining a first area,
• wherein:
• a tensile rigidity and/or compressive rigidity in the one direction of the peripheral region is lower than a tensile rigidity and/or compressive rigidity in the one direction of another region that surrounds the peripheral region;
• the first area includes at least two parallel parts, wherein a first parallel part is positioned on a side and in contact with a hole of the plurality and is connected to a second parallel part on a side and in contact with an adjacent hole of the plurality by a slanted part disposed between the hole and adjacent hole, such that first parallel part on the side of the hole and the second parallel part on the side of the adjacent hole are on opposite sides;
• and
• wherein the parallel part comprises the continuous fibers oriented in a 0° direction, is parallel to a first diameter of its corresponding hole, and includes an extension line of a second diameter of its corresponding hole oriented in a ±90° direction, wherein a portion of the parallel part has a length equal to or greater than the first diameter of its corresponding hole.