To reduce the part count by implementation of flexible beams in an aircraft rotor.SOLUTION: An example flexible beam 102 for coupling a rotor blade 104 to a rotor hub 106 includes a first composite laminate, a second composite laminate, a third composite laminate, first resilient core members, and second resilient core members. The first composite laminate forms a first skin of the flexible beam. The second composite laminate is located opposite the first composite laminate, and forms a second skin of the flexible beam. The third composite laminate is located between the first composite laminate and the second composite laminate. The first resilient core members extend between the first composite laminate and the third composite laminate. The second resilient core members extend between the second composite laminate and the third composite laminate.SELECTED DRAWING: Figure 1

    【課題】航空機のローターに可撓性ビームを実装することにより、部品点数の低減を図る。【解決手段】ローターブレード104をローターハブ106に連結するための例示的な可撓性ビーム102が、第1の複合材積層板、第2の複合材積層板、第3の複合材積層板、第1の弾性コア部材、及び第2の弾性コア部材を含む。第1の複合材積層板が、可撓性ビームの第1の外板を形成する。第2の複合材積層板が、第1の複合材積層板の反対側に位置付けられ、可撓性ビームの第2の外板を形成する。第3の複合材積層板が、第1の複合材積層板と第2の複合材積層板の間に位置付けられる。第1の弾性コア部材が、第1の複合材積層板と第3の複合材積層板の間で延在する。第2の弾性コア部材が、第2の複合材積層板と第3の複合材積層板の間で延在する。【選択図】図1


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    Title :

    STRUCTURALLY TUNABLE CORES


    Additional title:

    構造的に調整可能なコア


    Contributors:

    Publication date :

    2020-10-22


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Japanese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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