To optimize a lamination order of an anisotropic composite laminate structure while utilizing characteristics of an anisotropic material.SOLUTION: A designing method of an anisotropic composite laminate structure, which structures a predetermined portion of an airframe structure of an aircraft, and is structured by laminating a plurality of kinds of composite layers of which orientation directions of reinforced fibers are different from each other, includes an area setting process (S410) in which the anisotropic composite laminate structure of the predetermined portion is sectioned into a plurality of areas in a thickness direction, and a laminate structure determining process (S420) in which at least a lamination order of the plurality of kinds of composite layers is determined for each area according to a stress direction acting on the predetermined portion.SELECTED DRAWING: Figure 11
【課題】異方性材料の特性を活かしながら、異方性複合材積層構造の積層順を最適化する。【解決手段】航空機の機体構造の所定部位を構成し、強化繊維の配向方向が相互に異なる複数種類の複合材層を積層して構成される異方性複合材積層構造の設計方法は、所定部位における異方性複合材積層構造を、厚さ方向に複数の領域に区分する領域設定工程(S410)と、所定部位に作用する応力方向に応じて、複数種類の複合材層の少なくとも積層順を、領域ごとに決定する積層構造決定工程(S420)と、を含む。【選択図】図11
DESIGNING METHOD OF ANISOTROPIC COMPOSITE LAMINATE STRUCTURE
異方性複合材積層構造の設計方法
2022-10-07
Patent
Electronic Resource
Japanese
IPC: | B64C AEROPLANES , Flugzeuge |