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    AIRCRAFT VERTICAL STABILIZER DESIGN
    1.
    发明申请
    AIRCRAFT VERTICAL STABILIZER DESIGN 审中-公开

    公开(公告)号：US20180327079A1

    公开(公告)日：2018-11-15

    申请号：US15593304

    申请日：2017-05-11

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Brendan P. Lanigan ,  Joshua R. O'Neil

    IPC: B64C5/06 ,  B64C27/82 ,  B64C5/02

    CPC classification number: B64C5/06 ,  B64C27/82 ,  B64C2027/8272 ,  B64C2027/8281

    Abstract: In one embodiment, a vertical stabilizer comprises an airfoil structure configured to be mounted to an aircraft at a vertical orientation. The airfoil structure comprises a leading edge and a trailing edge, wherein the trailing edge is configured to form a blunt shaped edge. The airfoil structure further comprises a root end and a tip end, wherein the airfoil structure is tapered from the root end to the tip end. The airfoil structure is also cambered. Finally, the airfoil structure is further configured to be mounted with a rotor, and is also further configured to house one or more internal components associated with the aircraft.

    Aircraft horizontal stabilizer design
    3.
    发明授权
    Aircraft horizontal stabilizer design 有权

    公开(公告)号：US10518865B2

    公开(公告)日：2019-12-31

    申请号：US15593241

    申请日：2017-05-11

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Brendan P. Lanigan ,  Joshua R. O'Neil

    IPC: B64C5/02 ,  B64C27/82 ,  B64C27/06

    Abstract: In one embodiment, a horizontal stabilizer comprises an airfoil structure configured to be mounted to an aircraft at a horizontal orientation. The airfoil structure comprises a leading edge, a trailing edge, a top surface, and a bottom surface. Moreover, the airfoil structure is cambered, wherein a camber of the airfoil structure forms a concave slope on the top surface and a convex slope on the bottom surface.

    METHOD AND APPARATUS TO IMPROVE LIFT TO DRAG RATIO OF A ROTOR BLADE
    4.
    发明申请
    METHOD AND APPARATUS TO IMPROVE LIFT TO DRAG RATIO OF A ROTOR BLADE 审中-公开

    公开(公告)号：US20180362145A1

    公开(公告)日：2018-12-20

    申请号：US15843039

    申请日：2017-12-15

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Christopher E. Foskey ,  Brendan P. Lanigan

    IPC: B64C11/18 ,  B64C11/24

    Abstract: In a first aspect, there is a method for improving a lift to drag ratio of a rotor blade, including providing a blade member having a leading edge and a trailing edge; providing a leading edge extension member; and coupling the leading edge extension member to a portion of the leading edge of the blade member to form the rotor blade. In a second aspect, there is a rotor blade including a blade member having a leading edge, and a trailing edge; and a leading edge extension member disposed on the leading edge of the blade member, wherein the leading edge extension member is configured to extend the chord length of at least a portion of the rotor blade. In a third aspect, there is a leading edge extension member for a rotor blade including a convex exterior surface configured to extend at least a portion of the chord length of the rotor blade.

    Method and apparatus to improve lift to drag ratio of a rotor blade
    6.
    发明授权
    Method and apparatus to improve lift to drag ratio of a rotor blade 有权

    公开(公告)号：US10604234B2

    公开(公告)日：2020-03-31

    申请号：US15843039

    申请日：2017-12-15

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Christopher E. Foskey ,  Brendan P. Lanigan

    IPC: B64C11/18 ,  B64C11/24 ,  B64C27/473 ,  F03D1/06 ,  B64C29/00

    Abstract: In a first aspect, there is a method for improving a lift to drag ratio of a rotor blade, including providing a blade member having a leading edge and a trailing edge; providing a leading edge extension member; and coupling the leading edge extension member to a portion of the leading edge of the blade member to form the rotor blade. In a second aspect, there is a rotor blade including a blade member having a leading edge, and a trailing edge; and a leading edge extension member disposed on the leading edge of the blade member, wherein the leading edge extension member is configured to extend the chord length of at least a portion of the rotor blade. In a third aspect, there is a leading edge extension member for a rotor blade including a convex exterior surface configured to extend at least a portion of the chord length of the rotor blade.

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