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    Rotor assembly having collective pitch control
    51.
    发明授权
    Rotor assembly having collective pitch control 有权

    公开(公告)号：US10351232B2

    公开(公告)日：2019-07-16

    申请号：US15606257

    申请日：2017-05-26

    Applicant: Bell Helicopter Textron Inc.

    Inventor： John Richard McCullough ,  Paul K. Oldroyd

    IPC: B64C27/605 ,  B64C27/54 ,  B64C29/00

    Abstract: A rotor assembly for an aircraft operable to generate a variable thrust output at a constant rotational speed. The rotor assembly includes a mast rotatable at the constant speed about a mast axis. A rotor hub is coupled to and rotatable with the mast. The rotor hub includes a plurality of spindle grips extending generally radially outwardly. Each of the spindle grips is coupled to one of a plurality of rotor blades and is operable to rotate therewith about a pitch change axis. A collective pitch control mechanism is coupled to and rotatable with the rotor hub. The collective pitch control mechanism is operably associated with each spindle grip such that actuation of the collective pitch control mechanism rotates each spindle grip about the respective pitch change axis to collectively control the pitch of the rotor blades, thereby generating the variable thrust output.

    Aircraft having pod assembly jettison capabilities
    52.
    发明授权
    Aircraft having pod assembly jettison capabilities 有权

    公开(公告)号：US10343773B1

    公开(公告)日：2019-07-09

    申请号：US16246474

    申请日：2019-01-12

    Applicant: Bell Helicopter Textron Inc.

    Inventor： John Richard McCullough ,  Paul K. Oldroyd

    IPC: B64C29/02 ,  B29C39/02 ,  B64C39/02 ,  B64D1/08 ,  B64C39/06 ,  G05D1/00 ,  B64D25/12

    Abstract: An aircraft includes a flying frame and a pod assembly that is selectively attached to the flying frame. The pod assembly has an aerodynamic outer shape. The flying frame includes an airframe having first and second wings, a propulsion system attached to the airframe and a flight control system operably associated with the propulsion system. The flying frame has a vertical takeoff and landing mode in which the first wing is forward of the pod assembly and the second wing is aft of the pod assembly. The flying frame has a forward flight mode in which the first wing is below the pod assembly and the second wing is above the pod assembly. The flying frame is operable for flight both with the pod assembly and without the pod assembly attached thereto. The flying frame is operable to jettison the pod assembly during flight.

    Prioritizing Use of Flight Attitude Controls of Aircraft
    53.
    发明申请
    Prioritizing Use of Flight Attitude Controls of Aircraft 审中-公开

    公开(公告)号：US20190031338A1

    公开(公告)日：2019-01-31

    申请号：US16154282

    申请日：2018-10-08

    Applicant: Bell Helicopter Textron Inc.

    Inventor： John Richard McCullough ,  Paul K. Oldroyd

    IPC: B64C29/02 ,  G05D1/08 ,  G05D1/00 ,  B64C13/16 ,  B64C11/46

    Abstract: Systems and methods of prioritizing the use of flight attitude controls of aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. A method includes determining an optimal flight attitude state for the aircraft during flight, the aircraft including first and second wings with first and second pylons coupled therebetween forming an airframe with a two-dimensional distributed thrust array and a plurality of aerosurfaces coupled to the airframe; monitoring the current flight attitude state of the aircraft; identifying deviations between the current flight attitude state and the optimal flight attitude state; ordering the flight attitude controls of the aircraft based upon the flight attitude control authority of each in the current flight attitude state; and implementing the highest order flight attitude control to bias the aircraft from the current flight attitude state toward the optimal flight attitude state.

    Man Portable Aircraft System for Rapid In-situ Assembly
    54.
    发明申请
    Man Portable Aircraft System for Rapid In-situ Assembly 审中-公开

    公开(公告)号：US20190031335A1

    公开(公告)日：2019-01-31

    申请号：US16154188

    申请日：2018-10-08

    Applicant: Bell Helicopter Textron Inc.

    Inventor： John Richard McCullough ,  Paul K. Oldroyd

    IPC: B64C29/00 ,  B64C1/06 ,  B64C3/56 ,  B64C27/26 ,  B64C27/28 ,  B64C27/30 ,  B64C29/02 ,  B64C39/02 ,  B64C39/08 ,  B64D27/24 ,  B64D27/26

    Abstract: A man portable aircraft system includes first and second wings with first and second pylons couplable between pylon stations thereof to form an airframe. Each of a plurality of propulsion assemblies is couplable to one of a plurality of nacelle stations of the wings to form a two-dimensional distributed thrust array. A flight control system is couplable to the airframe and is operable to independently control each of the propulsion assemblies. A payload is couplable between payload stations of the first and second pylons. A man portable container is operable to receive the wings, pylons, propulsion assemblies, flight control system and payload in a disassembled configuration. The connections between the wings, pylons, propulsion assemblies and payload are operable for rapid in-situ assembly. In an assembled configuration, the aircraft is operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation.

    Aircraft having Multiple Independent Yaw Authority Mechanisms
    56.
    发明申请
    Aircraft having Multiple Independent Yaw Authority Mechanisms 审中-公开

    公开(公告)号：US20180297711A1

    公开(公告)日：2018-10-18

    申请号：US15972481

    申请日：2018-05-07

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Paul K. Oldroyd ,  John Richard McCullough

    IPC: B64D31/06 ,  B64C29/02 ,  B64D27/24 ,  B64C27/52 ,  B64C39/02 ,  G05D1/08

    Abstract: An aircraft has multiple independent yaw authority mechanisms. The aircraft includes an airframe having first and second wings with at least first and second pylons extending therebetween and with a plurality of tail members extending therefrom each having an active control surface. A two-dimensional distributed thrust array is coupled to the airframe that includes a plurality of propulsion assemblies each having a rotor assembly and each operable for thrust vectoring. A flight control system is operable to independently control each of the propulsion assemblies. A first yaw authority mechanism includes differential speed control of rotor assemblies rotating clockwise compared to rotor assemblies rotating counterclockwise. A second yaw authority mechanism includes differential longitudinal control surface maneuvers of control surfaces of two symmetrically disposed tail members. A third yaw authority mechanism includes differential thrust vectoring of propulsion assemblies.

    Wing Pivot Structures for Tiltrotor Aircraft
    58.
    发明申请
    Wing Pivot Structures for Tiltrotor Aircraft 审中-公开

    公开(公告)号：US20180079486A1

    公开(公告)日：2018-03-22

    申请号：US15271717

    申请日：2016-09-21

    Applicant: Bell Helicopter Textron Inc.

    Inventor： James Everett Kooiman ,  John Richard McCullough ,  Brian Dale Obert

    IPC: B64C3/56 ,  B64C29/00 ,  B64C11/28 ,  B64C5/10 ,  B64C5/02

    CPC classification number: B64C3/56 ,  B64C5/02 ,  B64C5/10 ,  B64C11/28 ,  B64C29/0033

    Abstract: A wing pivot apparatus for rotating a wing between a flight orientation and a stowed orientation relative to a fuselage of a tiltrotor aircraft. The apparatus includes a guide ring that is fixably coupled to the fuselage. Forward and aft wing attach assemblies are coupled respectively to forward and aft spars of the wing and are moveably supported by the guide ring. Forward and aft wing support fittings are coupled respectively to the forward and aft spars of the wing and are selectively securable respectively to first and second fore-aft beams of the fuselage. A plurality of lock assemblies selectively secures the wing support fittings to the fore-aft beams of the fuselage when the wing is in the flight orientation. An actuator coupled to the fuselage is operable to reversibly rotate the wing between the flight orientation and the stowed orientation.

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