A fuselage configured for a stable in-flight transition between forward flight and vertical takeoff and landing is described. In one embodiment, an aircraft may include an airframe, opposing wings extending from opposing sides of the airframe, and a plurality of engines. At least one engine may be mounted to each of the opposing wings, and at least a portion of each of the opposing wings including at least one of the plurality of engines may rotate relative to the airframe about a rotational axis that is non-perpendicular and transverse to the longitudinal axis of the airframe. A rotating portion of a wing including at least one of a plurality of engines in the described manner may provide a stable and smooth transition between vertical flight and forward flight.

    本发明描述了被配置成用于在向前飞行与竖向起飞和降落之间的稳定的飞行中过渡的机身。在一个实施例中,飞机可以包括机体、从机体的相对的侧延伸的相对的机翼以及多个发动机。至少一个发动机可以被安装到相对的机翼中的每个,并且包括多个发动机中的至少一个的每个相对的机翼的至少一部分可以相对于机体围绕与机体的纵向轴线不垂直且成横向的旋转轴线旋转。以所描述的方式包括多个发动机中的至少一个的机翼的旋转部分可以在竖向飞行和向前飞行之间提供稳定且平滑的过渡。


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    Titel :

    Vertical take-off and landing fuselage


    Weitere Titelangaben:

    竖向起降的机身


    Beteiligte:

    Erscheinungsdatum :

    12.07.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64U



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