PROBLEM TO BE SOLVED: To provide a highly efficient structural design of a composite tail boom that is based on a semi-monocoque design with a stressed skin and a stiffening framework.SOLUTION: The invention relates to an aircraft with a composite tail boom (3) that comprises at least partly a tubular tail boom cone with an outer skin (8) and an inner skin (9). The inner skin (9) delimits a hollow interior (3c) of the composite tail boom (3). A plurality of rod-shaped stiffening elements (10) and a plurality of ring-shaped stiffening elements (11) are arranged between the outer skin (8) and the inner skin (9). The plurality of rod-shaped stiffening elements (10) are oriented in the longitudinal direction of the composite tail boom (3), and the plurality of ring-shaped stiffening elements (11) are distributed along the longitudinal direction in the tubular tail boom cone.SELECTED DRAWING: Figure 2

    【課題】応力表皮及び補剛枠組みを伴うセミモノコック設計に基づく複合テールブームの高効率の構造設計を提供する。【解決手段】本発明は、外側表皮(8)及び内側表皮(9)を伴う管状テールブームコーンを少なくとも部分的に備える複合テールブーム(3)を伴う航空機に関し、内側表皮(9)は、複合テールブーム(3)の中空内部(3c)を区切り、複数の棒状剛化要素(10)及び複数の環状剛化要素(11)は、外側表皮(8)と内側表皮(9)との間に配置され、複数の棒状剛化要素(10)は、複合テールブーム(3)の縦方向に配向され、複数の環状剛化要素(11)は、管状テールブームコーン内に縦方向に沿って分散される。【選択図】図2


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    Titel :

    AIRCRAFT WITH FUSELAGE AND COMPOSITE TAIL BOOM


    Weitere Titelangaben:

    胴体及び複合テールブームを伴う航空機


    Beteiligte:
    AXEL FINK (Autor:in)

    Erscheinungsdatum :

    25.01.2018


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Japanisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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