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    HYDRAULIC INERTIAL VIBRATION ISOLATOR
    231.
    发明公开
    HYDRAULIC INERTIAL VIBRATION ISOLATOR 失效
    液压振动惯性调节器

    公开(公告)号：EP0749540A4

    公开(公告)日：1998-06-24

    申请号：EP95914831

    申请日：1995-03-31

    Applicant: BELL HELICOPTER TEXTRON INC

    Inventor： STAMPS FRANK B ,  SMITH MICHAEL R ,  MCKEOWN WILLIAM L

    IPC: F16F15/02 ,  F16F7/10 ,  F16F9/18 ,  F16F13/08 ,  F16F15/023

    CPC classification number: F16F13/08 ,  F16F7/10 ,  F16F7/1011

    Abstract: A hydraulic inertial vibration isolator (1) is connected between a vibrating body (3) and an isolated body (5). The vibration isolator (1) comprises a cylinder (7) which includes two chambers (35, 37) and a piston (9) therebetween. The chambers (35, 37) are connected by a tuning passage (31) in which a solid tuning slug (33) is slidably disposed. The chambers (35, 37) and the tuning passage (31) are filled with liquid. Bypass passages (57, 61) connecting the tuning passage (31) to the chambers (35, 37) allows the liquid pressure in the chambers (35, 37) to equalize when the amplitude of the tuning slug's oscillatory motion is sufficiently large, thereby limiting the tuning slug's amplitude. Dashpots (45, 47) axially disposed adjacent to either end of the tuning slug (33) act to damp excessive tuning slug motion and to bias the tuning slug (33) toward the center of the tuning passage (31). An electronic control system (69) is used to supply alternate current to magnetic coils (67) adjacent to the tuning slug (31), thereby matching the isolation frequency to the vibration frequency.

    STIFF-IN-PLANE ROTOR CONFIGURATION
    232.
    发明公开
    STIFF-IN-PLANE ROTOR CONFIGURATION 有权
    配置硬增强转子

    公开(公告)号：EP2387531A4

    公开(公告)日：2014-11-12

    申请号：EP09838518

    申请日：2009-01-19

    Applicant: BELL HELICOPTER TEXTRON INC

    Inventor： STAMPS FRANK B ,  TISDALE PATRICK R ,  DONOVAN TOM ,  RAUBER RICHARD E

    IPC: B64C27/33 ,  B64C27/32

    CPC classification number: B64C27/35 ,  B64C27/32 ,  B64C27/33 ,  B64C27/39 ,  B64C27/48

    Abstract: A rotor assembly (11) for a rotary-wing aircraft, the rotor having a central hub assembly with a flexure-type, twist-shank yoke with multiple arms (19), each arm (19) being adapted for a rotor blade to be mounted thereto. The arms (19) provide for pitch changes of blades (15) attached to the yoke through twisting of portions of the arms about a corresponding pitch axis. An inboard pitch bearing (37) associated with each arm (19) is attached to the hub assembly and allows for rotation of the attached blade about the pitch axis, the inboard pitch bearing (37) also allowing for out-of-plane motion of the arm relative to the hub assembly about a flapping axis. An outboard pitch bearing (35) associated with each arm is attached to the associated arm a selected distance from the inboard pitch bearing and allows for rotation of the attached blade about the pitch axis.

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