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    Flying Wing Aircraft having a Compact Storage Configuration
    1.
    发明申请
    Flying Wing Aircraft having a Compact Storage Configuration 审中-公开

    公开(公告)号：US20200017213A1

    公开(公告)日：2020-01-16

    申请号：US16031786

    申请日：2018-07-10

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Levi Charles Hefner ,  Dakota Charles Easley

    IPC: B64C39/02 ,  B64D27/26

    Abstract: An unmanned aircraft system includes a flying wing airframe having leading and trailing edges with respective sweep angles. A thrust array is coupled to the airframe and includes first and second motor mounts each selectively rotatably coupled to the leading edge by a locking joint. Each motor mount has first and second propulsion assemblies coupled to respective first and second distal ends thereof. A power system is operably associated with the thrust array and is operable to provide power to each propulsion assembly. A flight control system is operably associated with the thrust array and is operable to independently control the speed of each propulsion assembly. In a flight configuration, each motor mount is locked substantially perpendicular with the leading edge by the respective locking joint. In a compact storage configuration, each motor mount is locked substantially parallel with the leading edge the respective locking joint.

    Flying Wing Aircraft having a Two-dimensional Thrust Array
    3.
    发明申请
    Flying Wing Aircraft having a Two-dimensional Thrust Array 审中-公开

    公开(公告)号：US20200017212A1

    公开(公告)日：2020-01-16

    申请号：US16031771

    申请日：2018-07-10

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Dakota Charles Easley ,  Levi Charles Hefner

    IPC: B64C39/02 ,  G05D1/08 ,  B64D31/06 ,  B64D27/26

    Abstract: An unmanned aircraft system having a flying wing orientation includes an airframe having leading and trailing edges, a two-dimensional thrust array coupled to the leading edge, a power system and a flight control system operable to independently control the speed of each propulsion assembly of the two-dimensional thrust array. In the flying wing orientation, the two-dimensional distributed thrust array provides airspeed control responsive to collectively changing the speed of each propulsion assembly, pitch authority responsive to differentially changing the speed of the propulsion assemblies above the airframe relative to the propulsion assemblies below the airframe, roll authority responsive to differentially changing the speed of the propulsion assemblies rotating clockwise relative to the propulsion assemblies rotating counterclockwise and yaw authority responsive to differentially changing the speed of the propulsion assemblies on a port side of the airframe relative to the propulsion assemblies on a starboard side of the airframe.

    Foldable Wings for UAS having a Geared Interface
    5.
    发明申请
    Foldable Wings for UAS having a Geared Interface 审中-公开

    公开(公告)号：US20190031316A1

    公开(公告)日：2019-01-31

    申请号：US16148005

    申请日：2018-10-01

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Levi Charles Hefner ,  Dakota Charles Easley ,  Danielle Lynn Moore

    IPC: B64C3/56 ,  B64C11/48 ,  B64C29/02 ,  B64C39/02 ,  B64C39/00

    Abstract: A foldable wing system for an unmanned aerial system having a fuselage includes a left wing frame having an inboard gear rotatably coupled to the fuselage, a right wing frame having an inboard gear rotatably coupled to the fuselage and a wing actuator coupled to a linkage point on at least one of the wing frames. The wing frames are movable between a plurality of positions including a deployed position and a stowed position. The inboard gear of the left wing frame is engaged with the inboard gear of the right wing frame such that the wing frames move symmetrically between the plurality of positions in response to movement of the linkage point by the wing actuator.

    Flying Wing Aircraft having Flight and Storage Configurations
    6.
    发明申请
    Flying Wing Aircraft having Flight and Storage Configurations 审中-公开

    公开(公告)号：US20200017211A1

    公开(公告)日：2020-01-16

    申请号：US16031741

    申请日：2018-07-10

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Levi Charles Hefner ,  Dakota Charles Easley

    IPC: B64C39/02 ,  B64D27/26 ,  B64D31/06

    Abstract: An unmanned aircraft system includes a flying wing airframe having leading and trailing edges with respective sweep angles. A thrust array is coupled to the airframe and includes first and second motor mounts each rotatably coupled to the leading edge. Each motor mount has first and second propulsion assemblies coupled to respective first and second distal ends thereof. A power system is operably associated with the thrust array and is operable to provide power to each propulsion assembly. A flight control system is operably associated with the thrust array and is operable to independently control the speed of each propulsion assembly. In a flight configuration of the system, each motor mount is substantially perpendicular with the leading edge such that the thrust array forms a two-dimensional thrust array. In a compact storage configuration of the system, each motor mount is substantially parallel with the leading edge.

    Airbag to secure payload
    7.
    发明授权
    Airbag to secure payload 有权

    公开(公告)号：US10906520B2

    公开(公告)日：2021-02-02

    申请号：US16041687

    申请日：2018-07-20

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Levi Charles Hefner ,  John Richard McCullough

    IPC: B60V3/08 ,  B64C27/08 ,  B64B1/62 ,  B64D9/00 ,  B64C39/04 ,  B64C3/30 ,  B64C1/34 ,  B64C39/02 ,  B64C37/00

    Abstract: Systems and methods include providing vertical takeoff and landing (VTOL) aircraft with a cargo pod having a selectively inflatable bladder system that firmly secures a payload disposed within the cargo pod when the bladder system is pressurized. The bladder system also controls the location, position, and/or orientation of the payload in order to adjust, control, and/or maintain the center of gravity of the aircraft during flight. The aircraft includes an impact protection system that further pressurizes the bladder system to protect the payload and/or that disperses a flame-retardant fluid into the cargo pod to protect electrical components of the aircraft. The aircraft is fully autonomous and self-directed via a preprogrammed location-based guidance system to allow for accurate delivery of the payload to its intended destination. The bladder system is depressurized in response to a landing event to allow for e f the payload from the cargo pod.

    AIRBAG TO SECURE PAYLOAD
    9.
    发明申请
    AIRBAG TO SECURE PAYLOAD 审中-公开

    公开(公告)号：US20200023829A1

    公开(公告)日：2020-01-23

    申请号：US16041687

    申请日：2018-07-20

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Levi Charles Hefner ,  John Richard McCullough

    IPC: B60V3/08 ,  B64C39/02 ,  B64C27/08 ,  B64B1/62 ,  B64C37/00

    Abstract: Systems and methods include providing vertical takeoff and landing (VTOL) aircraft with a cargo pod having a selectively inflatable bladder system that firmly secures a payload disposed within the cargo pod when the bladder system is pressurized. The bladder system also controls the location, position, and/or orientation of the payload in order to adjust, control, and/or maintain the center of gravity of the aircraft during flight. The aircraft includes an impact protection system that further pressurizes the bladder system to protect the payload and/or that disperses a flame-retardant fluid into the cargo pod to protect electrical components of the aircraft. The aircraft is fully autonomous and self-directed via a preprogrammed location-based guidance system to allow for accurate delivery of the payload to its intended destination. The bladder system is depressurized in response to a landing event to allow for e f the payload from the cargo pod.

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