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    SHORT TAKEOFF AND LANDING VEHICLE WITH FORWARD SWEPT WINGS
    22.
    发明申请
    SHORT TAKEOFF AND LANDING VEHICLE WITH FORWARD SWEPT WINGS 有权

    公开(公告)号：US20220073200A1

    公开(公告)日：2022-03-10

    申请号：US17345493

    申请日：2021-06-11

    Applicant: Kitty Hawk Corporation

    Inventor： Pranay Sinha ,  Damon Vander Lind

    IPC: B64C29/00 ,  G05D1/10 ,  B64C13/48 ,  B64C39/12 ,  B64D27/24 ,  B64D27/26 ,  B60L53/00 ,  B60L50/64 ,  B64C27/82 ,  B64D27/02 ,  B64D31/06

    Abstract: A vehicle includes a tilt rotor that is aft of a wing and that is attached to the wing via a pylon. The tilt rotor has an adjustable maximum downward angle from horizontal that is less than or equal to 60° and that is set via a setting associated with a flight computer. The vehicle takes off and lands using at least some lift from the wing and from the tilt rotor. In response to a change to the adjustable maximum downward angle, via the setting associated with the flight computer, which produces a new maximum downward angle: the flight computer updates an actuator authority database associated with the flight computer to reflect the new maximum downward angle. Using the updated actuator authority database that reflects the new maximum downward angle, the flight computer generates a rotor control signal for the tilt rotor.

    PYLON MOUNTED TILT ROTOR
    23.
    发明申请
    PYLON MOUNTED TILT ROTOR 有权

    公开(公告)号：US20210387724A1

    公开(公告)日：2021-12-16

    申请号：US16899991

    申请日：2020-06-12

    Applicant: Kitty Hawk Corporation

    Inventor： Campbell McLaren ,  Pranay Sinha

    IPC: B64C29/00 ,  B64D33/08 ,  B64D27/24 ,  B64D29/02

    Abstract: A tilt rotor system, comprising: a pylon portion that includes: an upper protrusion that is configured to be in contact with an upper surface of a wing when the tilt rotor system and the wing are coupled; and a lower protrusion that is configured to be in contact with a lower surface of the wing when the tilt rotor system and the wing are coupled; and a rotor portion that includes a rotor, wherein the rotor portion is moveably coupled to the pylon portion such that the rotor portion is able to move between: (1) a first position that is associated with a vertical flight mode of a vehicle that includes the tilt rotor system and the wing and (2) a second position that is associated with a forward flight mode of the vehicle that includes the tilt rotor system and the wing.

    Fixed wing aircraft with trailing rotors
    24.
    发明授权
    Fixed wing aircraft with trailing rotors 有权

    公开(公告)号：US11180248B2

    公开(公告)日：2021-11-23

    申请号：US16168461

    申请日：2018-10-23

    Applicant: Kitty Hawk Corporation

    Inventor： Damon Vander Lind ,  Pranay Sinha

    IPC: B64C29/00 ,  B64C39/12 ,  B64C1/00

    Abstract: A plurality of port-side tilt rotors and a plurality of starboard-side tilt rotors are configured to rotate between a first rotor position and a second rotor position. The port-side tilt rotors are coupled to a trailing edge of the fixed and forward-swept wing on the port side and the starboard-side tilt rotors are coupled to the trailing edge of the fixed and forward-swept wing on the starboard side. The aircraft also includes a fuselage. When the port-side and starboard-side tilt rotors are in the first rotor position, at least some of a lift to keep the aircraft airborne comes from thrust output by the rotors at least some of the time. When in the second rotor position, at least some of the lift to keep the aircraft airborne comes from aerodynamic lift on the fixed and forward-swept wing at least some of the time.

    TILTING MECHANISM WITH TELESCOPING ACTUATOR
    27.
    发明申请
    TILTING MECHANISM WITH TELESCOPING ACTUATOR 有权

    公开(公告)号：US20210107642A1

    公开(公告)日：2021-04-15

    申请号：US17066956

    申请日：2020-10-09

    Applicant: Kitty Hawk Corporation

    Inventor： Pranay Sinha ,  Damon Vander Lind

    IPC: B64C29/00 ,  B64C13/48

    Abstract: A tiltrotor has a range of motion between a forward flight position and a hovering position, where a pylon and the tiltrotor are coupled via a telescoping actuator, a rigid bottom bar, and a fixed hinge that is attached between the rigid bottom bar and the tiltrotor. The tiltrotor moves from the forward flight position to the hovering position includes extending the telescoping actuator so that the tilt rotor rotates about the fixed hinge.

    Fixed wing aircraft with trailing rotors and T-tail
    28.
    发明授权
    Fixed wing aircraft with trailing rotors and T-tail 有权

    公开(公告)号：US12263942B2

    公开(公告)日：2025-04-01

    申请号：US18211510

    申请日：2023-06-19

    Applicant: Kitty Hawk Corporation

    Inventor： Pranay Sinha ,  Damon Vander Lind

    IPC: B64C29/00 ,  B64C5/02 ,  B64C11/46 ,  B64C39/12

    Abstract: An aircraft that includes a canard having a leading edge and a trailing edge, a forward swept and fixed wing having a trailing edge, and a plurality of tilt rotor submodules. The plurality of tilt rotor submodules includes a first tilt rotor submodule where the leading edge of the canard contacts the first tilt rotor submodule at position that is within a range of 40% to 60%, inclusive, of the length of the first tilt rotor submodule where 0% corresponds to a forward tip of the first tilt rotor submodule and 100% corresponds to an aft tip of the first tilt rotor submodule. The trailing edge of the canard contacts the first tilt rotor submodule at position that is within a range of 55% to 80%, inclusive, of the length of the first tilt rotor submodule. The plurality of tilt rotor submodules also includes a second tilt rotor submodule that is coupled to the trailing edge of the forward swept and fixed wing.

    FIXED WING AIRCRAFT WITH TRAILING ROTORS AND T-TAIL
    29.
    发明公开
    FIXED WING AIRCRAFT WITH TRAILING ROTORS AND T-TAIL 审中-公开

    公开(公告)号：US20240190564A1

    公开(公告)日：2024-06-13

    申请号：US18211510

    申请日：2023-06-19

    Applicant: Kitty Hawk Corporation

    Inventor： Pranay Sinha ,  Damon Vander Lind

    IPC: B64C29/00 ,  B64C5/02 ,  B64C11/46 ,  B64C39/12

    CPC classification number: B64C29/0033 ,  B64C5/02 ,  B64C11/46 ,  B64C39/12

    Abstract: An aircraft that includes a canard having a leading edge and a trailing edge, a forward swept and fixed wing having a trailing edge, and a plurality of tilt rotor submodules. The plurality of tilt rotor submodules includes a first tilt rotor submodule where the leading edge of the canard contacts the first tilt rotor submodule at position that is within a range of 40% to 60%, inclusive, of the length of the first tilt rotor submodule where 0% corresponds to a forward tip of the first tilt rotor submodule and 100% corresponds to an aft tip of the first tilt rotor submodule. The trailing edge of the canard contacts the first tilt rotor submodule at position that is within a range of 55% to 80%, inclusive, of the length of the first tilt rotor submodule. The plurality of tilt rotor submodules also includes a second tilt rotor submodule that is coupled to the trailing edge of the forward swept and fixed wing.

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