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    METHODS FOR FORMING ROTOR BLADES HAVING FOAM CORES
    2.
    发明申请
    METHODS FOR FORMING ROTOR BLADES HAVING FOAM CORES 审中-公开

    公开(公告)号：US20200094450A1

    公开(公告)日：2020-03-26

    申请号：US16141127

    申请日：2018-09-25

    Applicant: Bell Helicopter Textron Inc.

    Inventor： James A. Cordell ,  Suvankar Mishra ,  Andrew Paul Haldeman ,  Jesse J. Wrabel ,  Dalton T. Hampton

    IPC: B29C44/18 ,  B64C11/26 ,  B29C44/34 ,  B29C44/42 ,  B29C44/60

    Abstract: A method is provided in one example embodiment and may include positioning at least one nozzle within a hollow portion of a rotor blade at a distance associated with a span of the rotor blade and providing, via the at least one nozzle, a liquid foam mixture in the hollow portion, wherein the liquid foam expands and becomes a solid foam material that fills the hollow portion of the rotor blade. Another method is provided in another example embodiment and may include providing a plurality of openings for a rotor blade that are positioned proximate to a hollow portion of the rotor blade and providing a liquid foam mixture in the hollow portion of the rotor blade through at least one opening of the rotor blade, wherein the liquid foam mixture expands and becomes a solid foam material that fills the hollow portion of the rotor blade.

    Articulated Rotor Systems with Blade-to-Blade Damping
    4.
    发明申请
    Articulated Rotor Systems with Blade-to-Blade Damping 审中-公开

    公开(公告)号：US20190322363A1

    公开(公告)日：2019-10-24

    申请号：US15961713

    申请日：2018-04-24

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Andrew Paul Haldeman ,  Dalton T. Hampton ,  Frank Bradley Stamps

    IPC: B64C27/51 ,  B64C27/48

    Abstract: A rotor system includes a yoke, a plurality of blade grip assemblies and a plurality of centrifugal force bearings coupling the blade grip assemblies with the yoke. A plurality of rotor blades are coupled to the blade grip assemblies such that each rotor blade has a coincident hinge and such that each rotor blade has three independent degrees of freedom including blade pitch about a pitch change axis, blade flap about a flapping axis and lead-lag about a lead-lag axis. A blade-to-blade damping ring includes a plurality of damper anchors each coupled to one of the blade grip assemblies along the respective pitch change axis and a plurality of lead-lag dampers each coupled between adjacent damper anchors. During blade pitch operations, each blade grip assembly is operable to rotate relative to the respective damper anchor, such that the blade-to-blade damping ring is operable to provide pitch independent lead-lag damping.

    TAIL ROTOR CYCLIC CONTROL FOR PITCH ATTITUDE ADJUSTMENT
    6.
    发明申请
    TAIL ROTOR CYCLIC CONTROL FOR PITCH ATTITUDE ADJUSTMENT 审中-公开

    公开(公告)号：US20200262552A1

    公开(公告)日：2020-08-20

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

    Abstract: A method of controlling a tail rotor system of a helicopter 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.

    LOW MOMENT ROTOR HUB
    10.
    发明申请
    LOW MOMENT ROTOR HUB 审中-公开

    公开(公告)号：US20190061926A1

    公开(公告)日：2019-02-28

    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: B64C27/32 ,  B64C27/78 ,  B64C27/59 ,  B64C27/12

    CPC classification number: B64C27/32 ,  B64C27/12 ,  B64C27/35 ,  B64C27/39 ,  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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