To provide a landing gear which can avoid ground resonance while absorbing a large landing energy.SOLUTION: A landing gear 10 comprises: a pair of skids 20 which are located in parallel on a longitudinal axis of an airframe 12 of a rotary wing aircraft 11; a cross tube 30 which is installed onto the airframe, connects the pair of skids, and has an internal space; and a stiffening part 40 which suppresses flattening of the cross tube. The cross tube has a bent tube portion 37 on an end part 31 side with respect to an installation part 35 to the airframe, and a midship part 32 on a side opposite to the bent tube portion 37 side with respect to the installation part. The stiffening part is located in an internal space of at least any one tube portion of the bent tube portion 37 and between the pair of bent tube portions 37.SELECTED DRAWING: Figure 3

    【課題】大きな着陸エネルギを吸収しつつ、地上共振を回避することができる降着装置を提供する。【解決手段】降着装置10は、回転翼航空機11の機体12の前後軸に平行に配置される一対のスキッド20と、前記機体に装着され、一対の前記スキッドを連結し、且つ、内部空間を有するクロスチューブ30と、前記クロスチューブの扁平化を抑制する補剛部40と、を備え、前記クロスチューブは、前記機体との装着部35よりも端部31側に湾曲管部分37、及び、前記装着部よりも前記湾曲管部分37側と反対側の中央部32を有し、前記補剛部は、前記湾曲管部分37及び一対の前記湾曲管部分37の間のうちの少なくともいずれかの管部分の内部空間に配置されている。【選択図】図3


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    Titel :

    LANDING GEAR AND STIFFENING MEMBER


    Weitere Titelangaben:

    降着装置及び補剛部材


    Beteiligte:
    UEKI YOICHI (Autor:in)

    Erscheinungsdatum :

    24.10.2019


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Japanisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / F16F SPRINGS , Federn



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