PROBLEM TO BE SOLVED: To reduce weight of wing skin without compromising bending strength, bending stiffness, and damage tolerance.SOLUTION: A composite laminated plate comprises a first plurality of plies of reinforcing fibers for lengthwise strength with respect to a dominant load direction, and a second plurality of plies of reinforcing fibers oriented at angles ± β with respect to the dominant load direction, where β is included in the range from 15 degrees to 35 degrees inclusive.

    【課題】曲げ強度、曲げ剛性、及び損傷許容性を犠牲にすることなしに、ウイングスキンの重さを減少させる。【解決手段】主要な荷重方向に関して縦方向の強度の強化用繊維の第1の複数のプライ、及び主要な荷重方向に関してプラスマイナスβの角度に方向付けられる強化用繊維の第2の複数のプライを備え、前記βは15度以上かつ35度以下の範囲内に含まれる、複合材の積層板を提供する。【選択図】なし


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    Title :

    COMPOSITE LAMINATED PLATE HAVING REDUCED CROSSPLY ANGLE


    Additional title:

    縮小されたクロスプライ角度を有する複合材の積層板


    Contributors:

    Publication date :

    2015-12-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Japanese


    Classification :

    IPC:    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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