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    Inboard bearing assemblies for proprotor systems
    11.
    发明授权
    Inboard bearing assemblies for proprotor systems 有权

    公开(公告)号：US10472059B2

    公开(公告)日：2019-11-12

    申请号：US15648650

    申请日：2017-07-13

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Kyle Thomas Cravener ,  Amarjit Kizhakkepat ,  Ken Shundo ,  Jared Mark Paulson ,  Tyler Wayne Baldwin

    IPC: B64C27/35 ,  B64C29/00 ,  F16C23/04 ,  F16C27/02 ,  F16C33/20

    Abstract: A proprotor system for a tiltrotor aircraft having a helicopter flight mode and an airplane flight mode. The proprotor system includes a yoke having a plurality of blade arms with inboard pockets. A centrifugal force and shear bearing assembly is disposed in each of the inboard pockets of the yoke. Each of a plurality of proprotor blades is coupled to the yoke by one of the bearing assemblies such that each proprotor blade has a pitch change degree of freedom about a pitch change axis and a tilting degree of freedom about a focal point. Each bearing assembly includes a centrifugal force bearing coupled to the yoke, a shear bearing coupled to the yoke and an inboard beam coupled between the centrifugal force bearing and the shear bearing. Each inboard beam is coupled to a respective proprotor blade.

    Soft in-plane and stiff out-of-plane rotor system
    12.
    发明授权
    Soft in-plane and stiff out-of-plane rotor system 有权

    公开(公告)号：US10543916B2

    公开(公告)日：2020-01-28

    申请号：US15603019

    申请日：2017-05-23

    Applicant: BELL HELICOPTER TEXTRON INC.

    Inventor： Ken Shundo ,  Mithat Yuce ,  Frank B. Stamps

    IPC: B64C27/80 ,  B64C27/52 ,  B64C27/10 ,  B64C27/32 ,  B64C27/35 ,  B64C27/48 ,  B64C27/51

    Abstract: A rotor assembly includes a yoke operably associated with a rotor blade. The yoke includes a first device and a second device that attach the rotor blade to the yoke. The first device is configured to allow transverse movement of the rotor blade about a chord axis and rotational movement about a pitch-change axis. The second device is configured to allow rotational movement of the rotor blade solely about the pitch-change axis. The method includes rotating rotor assembly about a first plane of rotation, while retaining a relatively stiff out-of-plane rotation and a relatively soft in-plane rotation during flight.

    Inboard Bearing Assemblies with Anti-Rotation Features
    13.
    发明申请
    Inboard Bearing Assemblies with Anti-Rotation Features 审中-公开

    公开(公告)号：US20190017543A1

    公开(公告)日：2019-01-17

    申请号：US15698796

    申请日：2017-09-08

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Glenn Alan Shimek ,  Amarjit Olenchery Kizhakkepat ,  Ken Shundo ,  Michael Dean Dearman ,  Kyle Thomas Cravener ,  Michael Christopher Burnett

    IPC: F16C27/06 ,  B64C29/00

    Abstract: A bearing assembly for coupling a proprotor blade to a yoke in a proprotor system. The bearing assembly is positionable within an inboard pocket of a blade arm of the yoke. The proprotor system is operable for use on a tiltrotor aircraft having helicopter and airplane flight modes. The bearing assembly includes a centrifugal force bearing and a shear bearing having an inboard beam coupled therebetween. The centrifugal force bearing has a mating surface, a lateral movement constraint feature and at least one radially extending anti-rotation feature. The inboard beam has a mating surface in a contact relationship with the mating surface of the centrifugal force bearing, a lateral movement constraint feature operably associated with the lateral movement constraint feature of the centrifugal force bearing and at least one radially extending anti-rotation feature that corresponds with the at least one radially extending anti-rotation feature of the centrifugal force bearing.

    VARIABLE HUB-TO-HUB PHASING ROTOR SYSTEM
    15.
    发明申请
    VARIABLE HUB-TO-HUB PHASING ROTOR SYSTEM 有权
    可变的HUB-TO-HUB相位转子系统

    公开(公告)号：US20150217863A1

    公开(公告)日：2015-08-06

    申请号：US14174004

    申请日：2014-02-06

    Applicant: BELL HELICOPTER TEXTRON INC.

    Inventor： Brian Modrzejewski ,  Ken Shundo ,  Frank B. Stamps ,  David Popelka

    IPC: B64C27/00 ,  F16F15/22

    CPC classification number: B64C27/001 ,  B64C11/50 ,  B64C27/30 ,  B64C2027/004 ,  G10K11/178 ,  G10K2210/123 ,  G10K2210/1281

    Abstract: An aircraft includes a first rotor assembly, a second rotor assembly, and a rotor phase angle control system. The system includes a phase adjustor operably associated with the first rotor assembly and the second rotor assembly. The method includes sensing vibrations exerted on the aircraft and offsetting a phase angle of the first rotor assembly and the second rotor assembly to minimize the vibrations.

    Abstract translation: 飞机包括第一转子组件，第二转子组件和转子相位角控制系统。 该系统包括可操作地与第一转子组件和第二转子组件相关联的相位调节器。 该方法包括感测施加在飞行器上的振动并抵消第一转子组件和第二转子组件的相位角以最小化振动。

    Tiltrotor Control System With Two Rise/Fall Actuators
    16.
    发明申请
    Tiltrotor Control System With Two Rise/Fall Actuators 有权
    具有两个上升/下降执行器的倾翻机控制系统

    公开(公告)号：US20140271204A1

    公开(公告)日：2014-09-18

    申请号：US13835705

    申请日：2013-03-15

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Ken Shundo ,  Carlos A. Fenny ,  Frank B. Stamps

    IPC: B64C29/00 ,  B64C11/32

    CPC classification number: B64C29/0033 ,  B64C11/32 ,  B64C27/605

    Abstract: A rotor system for rotor aircraft comprises a rotor hub comprising a plurality of rotor blades, a rotatable rotor mast coupled to the rotor hub, a swashplate assembly comprising a non-rotating ring engaged with a rotatable ring, a plurality of pitch links mechanically coupling the rotatable ring to the plurality of rotor blades, and a swashplate actuator system. The rotatable ring is configured to rotate with the rotor mast, and the non-rotating ring is configured to engage and guide the rotatable ring. The pitch links are configured to control the pitch angle of each rotor blade. The swashplate actuator system consists of: a first actuator and a second actuator, where the first actuator and the second actuator are mechanically coupled to a stationary surface and the non-rotating ring.

    Abstract translation: 用于转子飞行器的转子系统包括转子毂，该转子毂包括多个转子叶片，连接到转子毂的可旋转转子柱塞，包括与可旋转环接合的非旋转环的斜盘组件，多个螺距连杆， 可旋转环到多个转子叶片，以及斜盘致动器系统。 可旋转环被构造成与转子桅杆一起旋转，并且非旋转环被构造成接合和引导可旋转环。 俯仰连杆构造成控制每个转子叶片的俯仰角。 斜盘致动器系统包括：第一致动器和第二致动器，其中第一致动器和第二致动器机械地联接到固定表面和非旋转环。

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