中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

25 records (took 0.029 seconds)

    VARIABALE STIFFNESS LIQUID INERTIA VIBRATION ELIMINATOR
    1.
    发明申请
    VARIABALE STIFFNESS LIQUID INERTIA VIBRATION ELIMINATOR 审中-公开
    VARIABALE柔性液体动力学振动消除器

    公开(公告)号：WO2011103078A1

    公开(公告)日：2011-08-25

    申请号：PCT/US2011/024858

    申请日：2011-02-15

    Applicant: BELL HELICOPTER TEXTRON INC. ,  SMITH, Michael R. ,  STAMPS, Frank B.

    Inventor： SMITH, Michael R. ,  STAMPS, Frank B.

    IPC: B64D27/00

    CPC classification number: B64C27/001 ,  B64C2027/004 ,  F16F7/1034 ,  F16F13/08 ,  F16F2228/066

    Abstract: A variable stiffness liquid inertia vibration isolation device includes a liquid inertia vibration elimination isolator and a variable stiffness spring operably associated with the liquid inertia vibration elimination isolator for varying the stiffness of the liquid inertia vibration isolator. The variable stiffness spring may include an elastomeric pad exhibiting a first stiffness along a first axis and a second stiffness, significantly greater than the first stiffness, along a second axis that is perpendicular to the first axis.

    Abstract translation: 可变刚度液体惯性隔振装置包括液体惯性消振隔离器和可变刚度弹簧，可变刚度弹簧与液体惯性消除隔振器可操作地相关联，用于改变液体惯性隔振器的刚度。 可变刚度弹簧可以包括沿着垂直于第一轴线的第二轴线呈现沿着第一轴线的第一刚度和显着大于第一刚度的第二刚度的弹性体垫片。

    STEP-OVER BLADE-PITCH CONTROL SYSTEM
    5.
    发明公开
    STEP-OVER BLADE-PITCH CONTROL SYSTEM 有权
    STEP-OVER BLADE-PITCH控制系统

    公开(公告)号：EP2089274A2

    公开(公告)日：2009-08-19

    申请号：EP06838841.2

    申请日：2006-12-08

    Applicant: Bell Helicopter Textron Inc.

    Inventor： STAMPS, Frank B. ,  RAUBER, Richard E. ,  POPELKA, David A. ,  TISDALE, Patrick R. ,  CAMPBELL, Thomas C. ,  BRASWELL, James L. Jr. ,  STANNEY, Keith ,  WASIKOWSKI, Mark ,  DONOVAN, Tom ,  BASKIN, Bryan ,  SMITH, Ryan ,  CORRIGAN, John J. III.

    IPC: B64C27/54 ,  F03B3/14

    CPC classification number: B64C11/30 ,  B64C27/605 ,  B64C29/0033

    Abstract: A pitch control system for blades on a rotor of an aircraft has a gimballing rotor hub (31) and a plurality of step-over arms (61) connected to the hub and capable of pivoting relative to the hub about a pivot axis. Each of a plurality of pitch links (55) connects one of the step-over arms (61) to a flight control system for pivoting the connected step-over arm (61) about the pivot axis and relative to the hub in response to inputs from the control system. Each of a plurality of step-over links (69) connects one of the step-over arms (61) to one of the blades for rotating the associated blade about the pitch axis in response to pivoting of the associated step-over arm.

    Abstract translation: 一种用于飞机转子上的叶片的桨距控制系统具有一个万向球转子轮毂（31）和多个连接到该轮毂并且能够围绕枢转轴线相对于轮毂枢转的跨接臂（61）。 多个俯仰连杆（55）中的每一个将所述跨接臂（61）中的一个连接到飞行控制系统，用于响应于输入使所连接的跨接臂（61）绕枢转轴线并且相对于轮毂枢转 来自控制系统。 多个跨接连杆（69）中的每一个将一个跨接臂（61）连接到叶片中的一个，以响应于相关联的跨接臂的枢转而使关联的叶片绕俯仰轴线旋转。

    CF BEARING WITH STEADY PITCHING MOMENT
    6.
    发明公开
    CF BEARING WITH STEADY PITCHING MOMENT 有权
    与SAME EXCESSIVE倾覆力矩离心轴承

    公开(公告)号：EP2032427A2

    公开(公告)日：2009-03-11

    申请号：EP06851653.3

    申请日：2006-06-20

    Applicant: Bell Helicopter Textron Inc.

    Inventor： STAMPS, Frank B. ,  RAUBER, Richard

    IPC: B63H1/00

    CPC classification number: B64C27/35 ,  F16F1/40

    Abstract: A centrifugal force bearing having a means for providing a steady pitching moment is disclosed. The centrifugal force bearing may optionally comprise a coning means. A rotor system having the centrifugal force bearing is disclosed. A rotary-wing aircraft having the centrifugal force bearing is disclosed.

    ADAPTABLE ROTOR CONTROL SYSTEM FOR A VARIABLE NUMBER OF BLADES
    9.
    发明公开
    ADAPTABLE ROTOR CONTROL SYSTEM FOR A VARIABLE NUMBER OF BLADES 审中-公开

    公开(公告)号：EP3450308A1

    公开(公告)日：2019-03-06

    申请号：EP17195083.5

    申请日：2017-10-05

    Applicant: Bell Helicopter Textron Inc.

    Inventor： MILLER, Gary ,  STAMPS, Frank B.

    IPC: B64C27/605

    CPC classification number: B64C11/32 ,  B64C11/06 ,  B64C11/30 ,  B64C27/605 ,  B64C29/0033 ,  B64C2027/7216 ,  B64C2027/7255

    Abstract: In one embodiment, a rotor hub comprises a yoke (202) for attaching a plurality of rotor blades, a constant velocity joint (206) to drive torque from a mast (201) to the yoke (202) and to enable the yoke (202) to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate (210), a phase adapter fulcrum (212), a plurality of actuators (221a-c) controlled based on a flight control input, a plurality of lower pitch links (222) configured to transfer motion between the plurality of actuators (221a-c) and the swashplate (210), a plurality of phase adjustment levers (213) configured to adjust a control phase associated with motion transferred between the plurality of actuators (221a-c) and the plurality of lower pitch links (222), and a plurality of upper pitch links (224) configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links (224) than lower pitch links (222).

    ROTOR ASSEMBLY WITH HIGH LOCK-NUMBER BLADES
    10.
    发明公开
    ROTOR ASSEMBLY WITH HIGH LOCK-NUMBER BLADES 审中-公开

    公开(公告)号：EP3345829A1

    公开(公告)日：2018-07-11

    申请号：EP17154785.4

    申请日：2017-02-06

    Applicant: Bell Helicopter Textron Inc.

    Inventor： STAMPS, Frank B. ,  MILLER, Gary

    IPC: B64C27/35 ,  B64C27/33

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

    Abstract: An aircraft rotor assembly (15) has a central yoke (21) and a plurality of rotor blades (17) coupled to the yoke (21) for rotation with the yoke (21) about an axis, each blade (17) having a Lock number of approximately 5 or greater. A lead-lag pivot for each blade (17) is a radial distance from the axis and allows for in-plane lead-lag motion of the associated blade (17) relative to the yoke (21), 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 (17) is opposed by a biasing force that biases the associated blade (17) 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 (17).

Patent Agency Ranking