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    83.
    发明专利
    未知

    公开(公告)号：DE60200897D1

    公开(公告)日：2004-09-16

    申请号：DE60200897

    申请日：2002-02-15

    Applicant: BELL HELICOPTER TEXTRON INC

    Inventor： COVINGTON CECIL E ,  STAMPS FRANK B ,  BRASWELL JR ,  POPELKA DAVID A ,  BENNET RICHARD L ,  SETTLE JR ,  COVINGTON CHARLES E

    IPC: B64C27/08 ,  B64C27/37 ,  B64C27/605 ,  B64C29/00 ,  B64C27/28

    Abstract: An aircraft with a tilt rotor assembly comprising a craft body, a plurality of rotor blades which are subject to three modes of flight operation, a tilting mast coupling the plurality of rotor blades to the craft body and for selectively moving the plurality of rotor blades between the three modes of flight operation, a hub coupling the plurality of rotor blades to the tilting mast in a manner which transfers torque and thrust while allowing tilting of a rotor thrust vector, a main swashplate for tilting in response to operator input to control the direction of the rotor thrust vector, a plurality of pitch horns, each mechanically coupled to a particular one of the plurality of rotor blades and to the main swashplate, for communicating swashplate input to each of the plurality of rotor blades, a plurality of links coupling the main swashplate to the plurality of pitch horns, wherein each of the plurality of pitch horns is mechanically coupled to a particular one of the plurality of rotor blades by one of the plurality of links in a particular position which yields a delta-3 value which is not optimum, and a feedback swashplate and cooperating feedback links for receiving disk tilting input from the plurality of rotor blades during flight, and for supplying a mechanical input to the main swashplate to compensate for the less than optimum delta-3 coupling between the plurality of pitch horns and the plurality of links. The three modes of flight include: (1) an airplane mode of flight with the plurality of rotor blades in a rotor disk position which is substantially transverse to the craft body; (2) a helicopter mode of flight with the plurality of rotor blades in a rotor disk position substantially parallel to the craft body with direction of flight being controlled by a rotor thrust vector; and (3) a transition mode of flight with the plurality of rotor blades moving between the rotor disk positions associated with the airplane mode of flight and the helicopter mode of flight.

    HYDRAULIC INERTIAL VIBRATION ISOLATOR
    85.
    发明专利
    HYDRAULIC INERTIAL VIBRATION ISOLATOR 未知

    公开(公告)号：CA2186453A1

    公开(公告)日：1995-10-12

    申请号：CA2186453

    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

    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 file 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.

    RETRACTABLE AND DEPLOYABLE FLIGHT ROTOR SYSTEM
    86.
    发明专利
    RETRACTABLE AND DEPLOYABLE FLIGHT ROTOR SYSTEM 未知

    公开(公告)号：CA3007823C

    公开(公告)日：2021-01-26

    申请号：CA3007823

    申请日：2018-06-11

    Applicant: BELL HELICOPTER TEXTRON INC

    Inventor： LOUIS MATTHEW E ,  RYAN MICHAEL JOHN ,  ROBERTSON DANIEL B ,  STAMPS FRANK B

    IPC: B64C27/30 ,  B64C11/28 ,  B64C27/12 ,  B64C27/26 ,  B64C27/50

    Abstract: An apparatus includes a shaft comprising a spiral spline along a length of the shaft. A rotor comprising a blade extending from the rotor and a tubular hole extending into the rotor. The tubular hole comprises a spiral groove configured to mate with the spiral spline on the shaft. Relative rotation between the spiral spline and the spiral groove causes the rotor to linearly move along the shaft. A cam surface comprises a recession. The blade nesting in the recession constrains rotation of the rotor about the shaft in a first rotational direction, and allows linear movement of the rotor along the shaft in a second rotational direction.

    WING EXTENSION CONTROL SURFACE
    87.
    发明专利
    WING EXTENSION CONTROL SURFACE 未知

    公开(公告)号：CA2754206C

    公开(公告)日：2019-04-09

    申请号：CA2754206

    申请日：2009-03-12

    Applicant: BELL HELICOPTER TEXTRON INC

    Inventor： COLLINS BOB ,  STAMPS FRANK B ,  CORRIGAN JOHN J ,  DREIER MARK E

    IPC: B64C27/22 ,  B64C29/00

    Abstract: A tiltrotor aircraft includes a rotatable nacelle that supports a rotor assembly and is pivotally attached to the aircraft's fuselage. A wing extension attaches to an outboard section of the nacelle. The wing extension provides additional yaw control during helicopter mode and additional lift during airplane mode. A method for controlling at least a portion of yaw movement includes positioning the rotor assembly in helicopter mode, creating rotor wash with the rotor assembly, and pivotally rotating the wing extension in the rotor wash.

    ROTOR HUB DAMPER FOR A ROTORCRAFT
    88.
    发明专利
    ROTOR HUB DAMPER FOR A ROTORCRAFT 未知

    公开(公告)号：CA2863707C

    公开(公告)日：2019-01-08

    申请号：CA2863707

    申请日：2014-09-16

    Applicant: BELL HELICOPTER TEXTRON INC

    Inventor： STAMPS FRANK B ,  SOTTIAUX DANIEL P

    IPC: F16F13/16 ,  B64C27/39 ,  B64C27/51 ,  F16F9/34

    Abstract: A damper for a rotor hub for a rotorcraft can include a housing, a piston resiliently coupled to the housing with a first elastomeric member and a second elastomeric member, a plurality of conical members, a fluid, and an orifice. The conical members may be coupled between the housing and the piston in a compressive state, such that a relative motion between the piston and the housing causes the conical members to flex by a compressive load change produced by the relative motion between the piston and the housing. The elastomeric members, the piston, the housing, and the conical members form inner chambers between the conical members and the piston and outer chambers between the conical members and the housing, each comprising an at least partially conical shape, Flexure of the conical members pumps the fluid through the orifice.

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