COMPOSITE MATERIAL STRUCTURE, AIRCRAFT WING AND AIRCRAFT FUSELAGE PROVIDED WITH SAME, AND METHOD FOR MANUFACTURING COMPOSITE MATERIAL STRUCTURE

摘要

The purpose of the present invention is to provide a lightweightcomposite material structure while suppressing a drop in strength. In acomposite material structure, which is configured as a fiber-reinforcedplasticcomposite material extending in one direction and having a plurality of holes(5) formed at intervals in a row in the one direction and which is subjectedto atensile load and/or a compressive load in the one direction, a peripheralregion(3a) around the holes (5) comprises a first area (10) obtained by bendingcomposite material, which is reinforced using continuous fibers that have beenmade even in the longitudinal direction, so that the center line of the width(W)of the composite material weaves between adjacent holes (5) and zigzags in theone direction. The tensile rigidity and/or compressive rigidity in the onedirection of the peripheral region (3a) around the holes (5) is lower than thetensile rigidity and/or the compressive rigidity in the one direction of theotherregions (3b) that surround the peripheral regions (3a).