The purpose of the present invention is to provide a lightweight composite material structure while suppressing a drop in strength. In a composite material structure, which is configured as a fiber-reinforced plastic composite 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 subjected to a tensile load and/or a compressive load in the one direction, a peripheral region (3a) around the holes (5) comprises a first area (10) obtained by bending composite material, which is reinforced using continuous fibers that have been made 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 the one direction. The tensile rigidity and/or compressive rigidity in the one direction of the peripheral region (3a) around the holes (5) is lower than the tensile rigidity and/or the compressive rigidity in the one direction of the other regions (3b) that surround the peripheral regions (3a).
COMPOSITE MATERIAL STRUCTURE, AIRCRAFT WING AND AIRCRAFT FUSELAGE PROVIDED WITH SAME, AND METHOD FOR MANUFACTURING COMPOSITE MATERIAL STRUCTURE
2017-01-12
Patent
Elektronische Ressource
Englisch
IPC: | B29C Formen oder Verbinden von Kunststoffen , SHAPING OR JOINING OF PLASTICS / B32B LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM , Schichtkörper, d.h. aus Ebenen oder gewölbten Schichten, z.B. mit zell- oder wabenförmiger Form, aufgebaute Erzeugnisse / B64C AEROPLANES , Flugzeuge |
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