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    TEETERING TAIL ROTOR YOKE
    21.
    发明申请
    TEETERING TAIL ROTOR YOKE 审中-公开

    公开(公告)号：US20180290739A1

    公开(公告)日：2018-10-11

    申请号：US15482616

    申请日：2017-04-07

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Hassan A. Mughal ,  Jared Addison Hallett ,  Andrew Paul Haldeman

    IPC: B64C27/45 ,  B64C27/82 ,  F16C23/04

    Abstract: In one embodiment, a rotorcraft can include a teetering tail rotor assembly. The teetering tail rotor assembly can include one or more multi-bearing yokes. Each yoke can include three or more spherical bearings evenly spaced apart from each other. The teetering tail rotor assembly can include a tail rotor blade affixed to each yoke arm through the three or more spherical bearings. The physical dimensions of the three-bearing yoke can be 10% smaller than a two bearing yoke that can support an equivalent load. For example, the length of each three bearing yoke can be 28 inches, the thickness can be 0.85 inches, and the width can be 3.250 inches.

    Tail rotor cyclic control for pitch attitude adjustment
    22.
    发明授权
    Tail rotor cyclic control for pitch attitude adjustment 有权

    公开(公告)号：US11117654B2

    公开(公告)日：2021-09-14

    申请号：US16277504

    申请日：2019-02-15

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Aaron Alexander Acee ,  Andrew Paul Haldeman ,  Colin John Thomas

    IPC: B64C27/82 ,  B64C27/78 ,  B64C27/08

    Abstract: A method of controlling a tail rotor system includes pivoting a swashplate of the tail rotor system about an axis passing through a diameter of the swashplate. Pivoting the swashplate causes a first linkage of a first pair of linkages coupled between the swashplate and a collective crosshead to move in a first direction and a second linkage of the first pair of linkages coupled between the swashplate and the collective crosshead to move in a second direction that is opposite the first direction. The movement of the first and second linkages causes a plane of rotation of a pair of rotors of the tail rotor system to cant relative to a centerline of a mast of the tail rotor system. A tail rotor system is also disclosed.

    Tail rotor housing
    23.
    发明授权
    Tail rotor housing 有权

    公开(公告)号：US10814971B2

    公开(公告)日：2020-10-27

    申请号：US15949660

    申请日：2018-04-10

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Dalton T. Hampton ,  Andrew Paul Haldeman ,  Aaron Alexander Acee ,  Matthew John Hill

    IPC: B64C27/82 ,  B64C27/06

    Abstract: Systems and methods include providing an aircraft with a tail rotor system having a tail rotor housing that forms a cambered airfoil between an upper cambered surface and a lower cambered surface of the tail rotor housing. The cambered airfoil design of the tail rotor housing is capable of providing sufficient lifting force of an aircraft to offload the tail rotor during forward flight, thereby eliminating the need for a traditional vertical stabilizer or fin. The tail rotor blades of the tail rotor system are disposed within an aperture in the tail rotor housing, which minimizes or preferably eliminates exposure of the tail rotor blades to edgewise airflow typically encountered during forward flight, thereby allowing rigid rotor hubs, both in-plane and out-of-plane, to be used in the tail rotor system while also reducing noise output of the tail rotor system.

    DUCTED ROTOR STATORS
    25.
    发明申请
    DUCTED ROTOR STATORS 审中-公开

    公开(公告)号：US20200247535A1

    公开(公告)日：2020-08-06

    申请号：US16266086

    申请日：2019-02-03

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Aaron Alexander Acee ,  Andrew Paul Haldeman

    IPC: B64C27/12 ,  F04D29/58 ,  B64C27/20 ,  B64D33/08

    Abstract: Systems and methods include providing an aircraft with a ducted rotor assembly. The ducted rotor assembly includes a housing having a duct, a rotor drive mechanism coupled to a rotor system, and a plurality of stators that both structurally support the rotor drive mechanism within the duct of the housing and carry a fluid through internal fluid passages in the plurality of stators to provide cooling to the rotor drive mechanism. Some of the stators carry fluid to the rotor drive mechanism, where the fluid absorbs heat from the rotor drive mechanism, and some of the stators carry fluid away from the rotor drive mechanism. The rotor system generates an airflow over the stators carrying fluid away from the rotor drive mechanism to effect transfer between the fluid and the airflow.

    Low moment rotor hub
    26.
    发明授权
    Low moment rotor hub 有权

    公开(公告)号：US10597143B2

    公开(公告)日：2020-03-24

    申请号：US15683621

    申请日：2017-08-22

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Andrew Paul Haldeman ,  Frank B. Stamps ,  James Donn Hethcock

    IPC: B64C11/02 ,  B64C27/35 ,  B64C11/04 ,  B64C11/06 ,  B64C27/39 ,  B64C27/12 ,  B64C27/32 ,  B64C27/59 ,  B64C27/78

    Abstract: In one embodiment, a rotor hub comprises a hub body, and a plurality of blade grips configured for attaching a plurality of rotor blades. The rotor hub further comprises a plurality of centrifugal force bearings coupled to the plurality of blade grips, wherein a focus of the plurality of centrifugal force bearings is aligned with a centerline of a rotor mast. The rotor hub further comprises a plurality of drive links configured to transfer torque to the plurality of rotor blades, wherein the plurality of drive links is positioned to correspond with a leading edge side of the plurality of rotor blades. The rotor hub further comprises a plurality of pitch horns configured to adjust a pitch of the plurality of rotor blades.

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