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    GEARBOX INTERNAL SENSOR INTEGRATION
    212.
    发明申请
    GEARBOX INTERNAL SENSOR INTEGRATION 有权

    公开(公告)号：US20210217255A1

    公开(公告)日：2021-07-15

    申请号：US16743988

    申请日：2020-01-15

    Applicant: Bell Textron Inc.

    Inventor： Scott David POSTER ,  Brian Edward TUCKER

    IPC: G07C5/08 ,  B64C27/12 ,  B64D45/00

    Abstract: An exemplary internal wireless sensor monitoring system includes a wireless sensor positioned inside of an enclosed housing to monitor a condition in the housing, a wireless gateway positioned outside of the housing, a gateway antenna located in the housing configured to wirelessly communicate with the wireless sensor, and a conductor extending through a penetration in the housing and connecting the gateway antenna and the wireless gateway.

    System and method for adjustable ballast
    214.
    发明授权
    System and method for adjustable ballast 有权

    公开(公告)号：US11001373B2

    公开(公告)日：2021-05-11

    申请号：US16555515

    申请日：2019-08-29

    Applicant: Bell Textron Inc.

    Inventor： Derek William Heard ,  Richard Theodore Perryman ,  Nathan Craig Clark ,  Joshua Andrew Emrich ,  Yann Lavallee ,  Ralph Michael Gannarelli

    IPC: B64C17/00 ,  B64C27/04

    Abstract: A movable ballast system for an aircraft includes first and second ballast docks secured to the aircraft. The first ballast dock includes a first housing and a first ballast tray secured within the first housing. The first ballast tray includes a plurality of channels. The second ballast dock is positioned aft of a CG of the aircraft and includes a second housing and a second ballast tray secured within the second housing. The second ballast tray includes a plurality of channels. The movable ballast system includes a plurality of movable ballasts, each movable ballast of the plurality of movable ballasts being configured to fit within at least one channel of each of the plurality of channels of the first and second ballast trays.

    Elastomeric pitch lock restraint
    215.
    发明授权
    Elastomeric pitch lock restraint 有权

    公开(公告)号：US10994837B1

    公开(公告)日：2021-05-04

    申请号：US16655855

    申请日：2019-10-17

    Applicant: Bell Textron Inc.

    Inventor： Kyle Thomas Cravener ,  Andrew Maresh ,  Mark Adam Wiinikka

    IPC: B64C11/32 ,  B64C27/57 ,  B64C29/00 ,  B64C27/80 ,  B64C11/28 ,  B64C27/605

    Abstract: An exemplary pitch lock for a tiltrotor aircraft to enable and disable a pitching degree of freedom of a rotor blade assembly includes a first tab coupled to a blade stop assembly, the first tab having a first ramp surface, a second tab coupled to a blade cuff, the second tab having a second ramp surface, a hasp having a central opening to receive the first and the second tab and rollers rotatably coupled to the hasp on opposite sides of the central opening, where the rollers engage the first and second ramp surfaces and retain the first and the second tabs in the central opening.

    Convertible Biplane Aircraft for Autonomous Cargo Delivery
    216.
    发明申请
    Convertible Biplane Aircraft for Autonomous Cargo Delivery 有权

    公开(公告)号：US20210122468A1

    公开(公告)日：2021-04-29

    申请号：US17005704

    申请日：2020-08-28

    Applicant: Bell Textron Inc.

    Inventor： Kevin Morris ,  Nicholas Brodeur ,  Pascal Flynn-Robitaille ,  Mathieu Beland

    IPC: B64D1/10 ,  B64C29/02 ,  B64C39/08 ,  B64C1/00 ,  B64C1/22 ,  B64C1/14 ,  B64D27/24 ,  B64C39/02 ,  B64D41/00 ,  G05D1/10 ,  E05F15/00

    Abstract: An autonomous cargo delivery aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes a fuselage having an aerodynamic shape with a leading edge, a trailing edge and first and second sides. First and second wings are coupled to the fuselage proximate the first and second sides, respectively. A distributed thrust array includes a first pair of propulsion assemblies coupled to the first wing and a second pair of propulsion assemblies coupled to the second wing. A flight control system is operably associated with the distributed thrust array and configured to independently control each of the propulsion assemblies. The first side of the fuselage includes a door configured to provide access to a cargo bay disposed within the fuselage from an exterior of the aircraft with a predetermined clearance relative to the first pair of propulsion assemblies.

    AIRCRAFT WITH DISPLACEABLE CONTROL SURFACE
    217.
    发明申请
    AIRCRAFT WITH DISPLACEABLE CONTROL SURFACE 有权

    公开(公告)号：US20210122458A1

    公开(公告)日：2021-04-29

    申请号：US16661740

    申请日：2019-10-23

    Applicant: Bell Textron Inc.

    Inventor： Pascal Flynn-Robitaille

    IPC: B64C9/08 ,  B64C29/02 ,  B64C13/38

    Abstract: An aircraft includes a wing and a rotor pod mounted to the wing. The rotor pod includes a body having a forward end and an aft end. A propeller is mounted to the body of the rotor pod at the forward end. A control surface is mounted to the body of the rotor pod between the forward and aft ends and extends outwardly from the body. The control surface is displaceable relative to the body between a first control configuration and a second control configuration to control an attitude of the aircraft. The control surface in the first control configuration is closer to the propeller than the control surface in the second control configuration.

    Modular Tandem Tiltrotor Aircraft
    218.
    发明申请
    Modular Tandem Tiltrotor Aircraft 有权

    公开(公告)号：US20210114723A1

    公开(公告)日：2021-04-22

    申请号：US17081654

    申请日：2020-10-27

    Applicant: Bell Textron Inc.

    Inventor： John Robert Wittmaak, JR. ,  Steven M. Loveland ,  Joshua Allan Edler ,  Alan Hisashi Steinert ,  Stephen Yibum Chung ,  Matthew Edward Louis

    IPC: B64C29/00

    Abstract: A modular tandem tiltrotor aircraft in which the tiltrotor assemblies are operably coupled at the forward and aft ends of the fuselage of the aircraft is disclosed. The modular tandem tiltrotor assemblies are capable of rotating between a vertical lift position and a horizontal flight position. The modular tandem tiltrotor aircraft can be structurally more efficient and lower drag than a conventional tiltrotor, has better control authority and lifting capacity than hybrid-quads and tail-sitters, and has more range than a helicopter or multi-rotor. The modular tandem tiltrotor aircraft can orbit and search over a broad area, or can hover for long periods, depending on the application. Instead of providing a multi-function tandem tiltrotor aircraft that is generally suited for all applications, but not optimized for any, the modular tandem tiltrotor aircraft allows for customized configuration to optimize the aircraft for a particular application.

    Light Communication Slip Ring
    220.
    发明申请
    Light Communication Slip Ring 有权

    公开(公告)号：US20210094684A1

    公开(公告)日：2021-04-01

    申请号：US16584240

    申请日：2019-09-26

    Applicant: Bell Textron Inc.

    Inventor： Michael Raymond Hull ,  Daniel Duane Donley

    IPC: B64C27/72 ,  H04B10/116

    Abstract: Embodiments are directed to a rotor system for an aircraft comprising a gearbox configured to receive torque from a drive train, a mast having a first end and a second end, wherein the first end is attached to the gearbox and the mast configured to rotate in response to the torque from the drive train, a rotor hub attached to the second end of the mast, a first light transceiver mounted adjacent to the first end of the mast, wherein the first light transceiver is does not rotate relative to the mast, and a second light transceiver mounted adjacent to the second end of the mast, wherein the second light transceiver rotates with the mast.

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