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10 条记录 (耗时 0.012 秒)

    Wing flap deflection control removal
    2.
    发明授权
    Wing flap deflection control removal 有权

    公开(公告)号：US11981431B2

    公开(公告)日：2024-05-14

    申请号：US16712901

    申请日：2019-12-12

    申请人： The Boeing Company

    发明人： Jan A. Kordel ,  Jacob Daniel Virnig ,  Michael Albert Balzer ,  Bruce Detert ,  Emanuel Rizal Setiawan

    IPC分类号： B64C9/18 ,  B64C9/02 ,  B64F5/00 ,  B64C3/44

    CPC分类号： B64C9/18 ,  B64C9/02 ,  B64F5/00 ,  B64C2003/445 ,  Y02T50/30

    摘要： A high-lift device surface and associated method of designing the high-lift device surface is described. Methods include entering one or more flight conditions, and receiving aerodynamic forces at a wing, the wing comprising a fixed portion, a seal coupled to and extending from the fixed portion of the wing, and a high-lift device surface having an as-built shape determined based on an anticipated deformation during flight. Methods also include deforming the high-lift device surface based, at least in part, on the received aerodynamic forces, contacting, based on the deforming, the high-lift device surface with the seal, wherein the deforming causes the high-lift device to deform from the as-built shape to a second shape, and wherein the contacting causes the high-lift device to fully contact the seal to prevent air flow between the seal and the high-lift device surface due to the received aerodynamic forces.

    Assemblies and methods for deploying a trailing edge flap of an aircraft
    3.
    发明授权
    Assemblies and methods for deploying a trailing edge flap of an aircraft 有权

    公开(公告)号：US11964766B2

    公开(公告)日：2024-04-23

    申请号：US17681061

    申请日：2022-02-25

    申请人： BOMBARDIER INC.

    发明人： Dmitry Budnitsky ,  Howard Ian Smith ,  Thomas Hanson

    IPC分类号： B64C9/16 ,  B64C9/02

    CPC分类号： B64C9/16 ,  B64C9/02 ,  Y02T50/30

    摘要： Trailing edge assemblies, couplers and methods for deploying a trailing edge flap of an aircraft wing are disclosed. An exemplary method disclosed herein comprises guiding an aft portion of the trailing edge flap along an elongated track member as the trailing edge flap moves toward the deployed position; guiding a forward portion of the trailing edge flap along the elongated track member as the trailing edge flap moves toward the deployed position; and accommodating transverse movement of the forward portion of the trailing edge flap relative to the elongated track member.

    ASSEMBLIES AND METHODS FOR DEPLOYING A TRAILING EDGE FLAP OF AN AIRCRAFT
    8.
    发明公开
    ASSEMBLIES AND METHODS FOR DEPLOYING A TRAILING EDGE FLAP OF AN AIRCRAFT 审中-公开

    公开(公告)号：US20240228016A1

    公开(公告)日：2024-07-11

    申请号：US18615260

    申请日：2024-03-25

    申请人： BOMBARDIER INC.

    发明人： Dmitry BUDNITSKY ,  Howard Ian SMITH ,  Thomas HANSON

    IPC分类号： B64C9/16 ,  B64C9/02

    CPC分类号： B64C9/16 ,  B64C9/02 ,  Y02T50/30

    摘要： Trailing edge assemblies, couplers and methods for deploying a trailing edge flap of an aircraft wing are disclosed. An exemplary method disclosed herein comprises guiding an aft portion of the trailing edge flap along an elongated track member as the trailing edge flap moves toward the deployed position; guiding a forward portion of the trailing edge flap along the elongated track member as the trailing edge flap moves toward the deployed position; and accommodating transverse movement of the forward portion of the trailing edge flap relative to the elongated track member.

    Propelling system with variable aerodynamic controls
    9.
    发明授权
    Propelling system with variable aerodynamic controls 有权

    公开(公告)号：US11738861B2

    公开(公告)日：2023-08-29

    申请号：US16449173

    申请日：2019-06-21

    申请人： Thomas Norman Hesse

    发明人： Thomas Norman Hesse

    IPC分类号： B64C27/68 ,  B64C9/00 ,  B64C27/72

    CPC分类号： B64C27/68 ,  B64C9/00 ,  B64C27/72 ,  B64C2009/005 ,  Y02T50/30

    摘要： A propelling system with variable aerodynamic controls is a system used to generate and control the flight forces of an aircraft. The system includes a stator, a rotor, a plurality of propelling units, and a control system. The stator serves as the stationary connection to the aircraft. The rotor revolves the propelling units about a central rotation axis. The control system enables the control of the propelling units. The propelling units generate the flight forces for the aircraft in the desired direction. In addition, each of the propelling units include a blade body, a shaft channel, a spar shaft, and at least one aileron assembly. The shaft channel receives the spar shaft within the blade body. The spar shaft connects the blade body to the rotor. The blade body passively corrects its angle of attack and supports the aileron assembly. The aileron assembly adjusts the pitch of the blade body.