中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

136 records (took 0.018 seconds)

    Rotor Assembly with High Lock-Number Blades
    112.
    发明申请
    Rotor Assembly with High Lock-Number Blades 审中-公开

    公开(公告)号：US20190061929A9

    公开(公告)日：2019-02-28

    申请号：US15398919

    申请日：2017-01-05

    Applicant: Bell Helicopter Textron, Inc.

    Inventor： Gary Miller ,  Frank B. Stamps

    IPC: B64C27/35 ,  B64C27/48

    CPC classification number: B64C27/35 ,  B64C27/33 ,  B64C27/48 ,  B64C27/51 ,  B64C27/54

    Abstract: An aircraft rotor assembly has a central yoke and a plurality of rotor blades coupled to the yoke for rotation with the yoke about an axis, each blade having a Lock number of approximately 5 or greater. A lead-lag pivot for each blade is a radial distance from the axis and allows for in-plane lead-lag motion of the associated blade relative to the yoke, each pivot allowing for in-plane motion from a neutral position of at least 1 degree in each of the lead and lag directions. Lead and lag motion of each blade is opposed by a biasing force that biases the associated blade toward the neutral position, and the biasing force is selected to achieve a first in-plane frequency of greater than 1/rev for each blade.

    LOW MOMENT ROTOR HUB
    113.
    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.

    ACTIVE VIBRATION CONTROL SYSTEM WITH NON-CONCENTRIC REVOLVING MASSES
    114.
    发明申请
    ACTIVE VIBRATION CONTROL SYSTEM WITH NON-CONCENTRIC REVOLVING MASSES 审中-公开

    公开(公告)号：US20180370621A1

    公开(公告)日：2018-12-27

    申请号：US16054606

    申请日：2018-08-03

    Applicant: Bell Helicopter Textron Inc.

    Inventor： David E. Heverly, II ,  Jeremy DeWaters ,  Frank B. Stamps

    IPC: B64C27/00 ,  B64C29/00

    CPC classification number: B64C27/001 ,  B64C29/0033 ,  B64C2027/003

    Abstract: A vibration control system for a rotor hub provides vibration attenuation in an aircraft by reducing the magnitude of rotor induced vibratory. The system can include a force generating device attached to a rotor hub which rotates along with the rotor at the rotational speed of the rotor. Vibratory shear force is generated by rotating unbalanced weights each about an axis non-concentric with the rotor hub axis at high speed to create large centrifugal forces. The rotational speed of the weights can be a multiple of the rotor rotational speed to create shear forces for canceling rotor induced vibrations. The amplitude of the generated shear force is controlled by indexing the positions of the unbalanced weights relative to each other, while the phase of the shear force is adjusted by equally phasing each weight relative to the rotor.

    Constant velocity joint with spring rate control mechanism
    117.
    发明授权
    Constant velocity joint with spring rate control mechanism 有权

    公开(公告)号：US09878783B2

    公开(公告)日：2018-01-30

    申请号：US14258187

    申请日：2014-04-22

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Drew Sutton ,  Frank B. Stamps ,  Christopher Foskey

    IPC: B64C27/41 ,  B64C27/32 ,  F16D3/33 ,  F16D3/28 ,  F16D3/30

    CPC classification number: B64C27/41 ,  B64C27/32 ,  F16D3/28 ,  F16D3/30 ,  F16D3/33

    Abstract: According to one embodiment, a constant velocity (CV) joint includes a first yoke, a second yoke, and three bearings. The first yoke is configured to be rotatably coupled to an input device about a first axis and configured to receive the input device through a first opening. The second yoke is rotatably coupled to the first yoke about a second axis and rotatably coupled to an output device about a third axis. The first bearing is disposed about the first axis adjacent to the first yoke, the second bearing is disposed about the second axis adjacent to the first yoke or the second yoke, and the third bearing disposed about the third axis adjacent to the second yoke. The first and third bearings torsionally constrain movement the first yoke and the second yoke so as to achieve a substantially CV characteristic between the input device and the output device.

    Tiltrotor control system with two rise/fall actuators
    120.
    发明授权
    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：US09567070B2

    公开(公告)日：2017-02-14

    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: B64C27/10 ,  B64C29/00 ,  B64C11/32 ,  B64C27/605

    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。

Patent Agency Ranking