To provide a steering blade capable of preventing the surface from becoming depressed by an acting fluid force in addition to light weight in comparison with the solid steering blade by cutting out.SOLUTION: A steering blade 20 of the invention takes charge of the attitude control of a missile 1 and comprises: an outer cover 21 covering the interior space; and a lattice structure 23 supporting the outer cover in the interior space. The lattice structure 23 can change the mechanical strength in one or both of a blade length direction h and a blade width direction w. For example, the mechanical strength in a part of a bottom 20A of the blade length direction h in the steering blade 20 is increased larger than the other region in the blade length direction h; and the mechanical strength in a forward edge 20C and a rear edge 20D in the blade width direction w can increase larger than the other region in the blade width direction w.SELECTED DRAWING: Figure 3

    【課題】削り出しによる中実な操舵翼に比べて軽量であるのに加えて、作用する流体力により表面がへこむのを防ぐことのできる操舵翼を提供すること。【解決手段】本発明の操舵翼20は、飛翔体1の姿勢制御を担い、内部空間を覆う外皮21と、内部空間において前記外皮を支持するラティス構造23と、を備える。ラティス構造23は、機械的強度を、翼長方向h及び翼幅方向wの一方又は双方で変化させることができる。例えば、操舵翼20にける翼長方向hの根元20Aの部分における機械的強度を翼長方向hの他の領域よりも大きくしたり、翼幅方向wの前縁20C及び後縁20Dにおける機械的強度を翼幅方向wの他の領域よりも大きくしたりすることができる。【選択図】図3


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    Titel :

    STEERING BLADE OF MISSILE, AND MISSILE


    Weitere Titelangaben:

    飛翔体の操舵翼、及び、飛翔体


    Beteiligte:
    HIMENO HIROMITSU (Autor:in) / KYUNO HIROAKI (Autor:in)

    Erscheinungsdatum :

    14.03.2019


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Japanisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / F42B EXPLOSIVE CHARGES, e.g. FOR BLASTING , Explosive Ladungen, z.B. für Sprengungen



    COMPARTMENT OF CONTROLLED MISSILE STEERING DRIVE

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