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    Aircraft having omnidirectional ground maneuver capabilities
    21.
    发明授权
    Aircraft having omnidirectional ground maneuver capabilities 有权

    公开(公告)号：US10661892B2

    公开(公告)日：2020-05-26

    申请号：US15606197

    申请日：2017-05-26

    Applicant: Textron Innovations Inc.

    Inventor： John Richard McCullough ,  Paul K. Oldroyd

    IPC: B64C29/00 ,  B64C39/04 ,  B64C39/08 ,  B64C25/36 ,  B64C25/04

    Abstract: An aircraft having omnidirectional ground maneuver capabilities. The aircraft includes an airframe and a plurality of propulsion assemblies attached to the airframe. Each of the propulsion assemblies includes a nacelle having a mast axis, a rotor assembly having a tilting degree of freedom relative to the mast axis and a tail assembly rotatable about the mast axis. The tail assembly includes at least one wheel having a rotational axis. A flight control system is operable to independently control each of the propulsion assemblies including tilting each rotor assembly and rotating each tail assembly. For each propulsion assembly, the rotor assembly and the tail assembly have complementary configurations in which a thrust vector generated by the rotor assembly has a horizontal component that is generally perpendicular to the rotational axis of the wheel, thereby enabling omnidirectional ground maneuvers.

    Aircraft generating thrust in multiple directions
    22.
    发明授权
    Aircraft generating thrust in multiple directions 有权

    公开(公告)号：US10583921B1

    公开(公告)日：2020-03-10

    申请号：US16526860

    申请日：2019-07-30

    Applicant: Textron Innovations Inc.

    Inventor： John Richard McCullough ,  Paul K. Oldroyd

    IPC: B64C29/02 ,  B64C29/00 ,  B64C11/28 ,  B64C27/50 ,  B64C39/02 ,  B64D35/00 ,  B64D25/12

    Abstract: An aircraft has an airframe with first and second wings having first and second pylons extending therebetween. A distributed propulsion system attached to the airframe includes a plurality of propulsion assemblies that are independently controlled by a flight control system. A pod assembly is coupled to the airframe. In a VTOL flight mode, the first wing is forward of the pod assembly and the second wing is aft of the pod assembly. In a forward flight mode, the first wing is below the pod assembly and the second wing is above the pod assembly. In both the VTOL flight mode and the forward flight mode, a first pair of symmetrically disposed propulsion assemblies generates thrust having a first direction while a second pair of symmetrically disposed propulsion assemblies generates thrust having a second direction that is different from the first direction.

    Rotor assembly having collective pitch control
    25.
    发明授权
    Rotor assembly having collective pitch control 有权

    公开(公告)号：US11505302B2

    公开(公告)日：2022-11-22

    申请号：US16421371

    申请日：2019-05-23

    Applicant: Textron Innovations Inc.

    Inventor： John Richard McCullough ,  Paul K. Oldroyd

    IPC: B64C27/605 ,  B64C3/10 ,  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 a High Efficiency Forward Flight Mode
    26.
    发明申请
    Aircraft having a High Efficiency Forward Flight Mode 有权

    公开(公告)号：US20220212785A1

    公开(公告)日：2022-07-07

    申请号：US17706445

    申请日：2022-03-28

    Applicant: Textron Innovations Inc.

    Inventor： John Richard McCullough ,  Paul K. Oldroyd

    IPC: B64C29/00 ,  B64C11/28 ,  B64D35/00 ,  B64C27/50 ,  B64C39/02 ,  B64C29/02 ,  B64C39/06 ,  B64D1/08

    Abstract: An aircraft having a high efficiency forward flight mode. The aircraft includes an airframe having at least one wing. A distributed propulsion system is attached to the airframe and includes a first plurality of propulsion assemblies and a second plurality of propulsion assemblies. A flight control system is operably associated with the distributed propulsion system and is operable to independently control each of the propulsion assemblies. The aircraft is configured for thrust-borne lift in a vertical takeoff and landing flight mode and wing-borne lift in the forward flight mode. In the vertical takeoff and landing flight mode, each of the propulsion assemblies is configured to generate vertical thrust. In the forward flight mode, the propulsion assemblies of the first plurality of propulsion assemblies are configured to generate forward thrust and the propulsion assemblies of the second plurality of propulsion assemblies are configured to shut down.

    Aircraft having Multiple Independent Yaw Authority Mechanisms
    28.
    发明申请
    Aircraft having Multiple Independent Yaw Authority Mechanisms 有权

    公开(公告)号：US20210300580A1

    公开(公告)日：2021-09-30

    申请号：US17225778

    申请日：2021-04-08

    Applicant: Textron Innovations 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.

    Line replaceable propulsion assemblies for aircraft
    29.
    发明授权
    Line replaceable propulsion assemblies for aircraft 有权

    公开(公告)号：US11104446B2

    公开(公告)日：2021-08-31

    申请号：US16154326

    申请日：2018-10-08

    Applicant: Textron Innovations Inc.

    Inventor： John Richard McCullough ,  Paul K. Oldroyd

    IPC: B64D31/06 ,  B64C29/02 ,  B64C27/52 ,  B64D27/24 ,  B64D27/26 ,  G05D1/00 ,  B64C11/46 ,  B64D31/14

    Abstract: A propulsion assembly for an aircraft includes a nacelle having a rapid connection interface, at least one battery disposed within the nacelle, a speed controller coupled to the battery and a propulsion system coupled to the speed controller and the battery. The propulsion system includes an electric motor having an output drive and a rotor assembly having a plurality of rotor blades that are rotatable with the output drive of the electric motor in a rotational plane to generate thrust. The electric motor is operable to rotate responsive to power from the battery at a speed responsive to the speed controller. The rapid connection interface of the nacelle is couplable to a rapid connection interface of an airframe nacelle station to provide structural and electrical connections therebetween that are operable for rapid in-situ assembly.

    Convertible biplane aircraft for capturing drones
    30.
    发明授权
    Convertible biplane aircraft for capturing drones 有权

    公开(公告)号：US11084579B2

    公开(公告)日：2021-08-10

    申请号：US16743203

    申请日：2020-01-15

    Applicant: Textron Innovations Inc.

    Inventor： Steven Ray Ivans ,  Jason Paul Hurst ,  Brent Chadwick Ross ,  John Richard McCullough ,  Paul K. Oldroyd

    IPC: B64C29/02 ,  B64D3/00 ,  G05D1/00 ,  B64C39/02 ,  B64D1/08 ,  B64C39/06 ,  B64D25/12

    Abstract: An aircraft for capturing drones includes an airframe having a drone channel with first and second wings extending outboard thereof. A two-dimensional distributed thrust array includes a plurality of propulsion assemblies coupled to each of the first and second wings such that the rotor disc of each propulsion assembly is outboard of the drone channel. A flight control system is coupled to the airframe and is operable to independently control each of the propulsion assemblies. A mesh bag is coupled to the drone channel forming a drone capture net. The aircraft is configured to convert between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft is also configured to overtake a drone during flight in the biplane orientation such that the drone passes through the drone channel into the mesh bag, thereby capturing the drone in the drone capture net.

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