公开(公告)号：DE60329196D1

公开(公告)日：2009-10-22

申请号：DE60329196

申请日：2003-09-24

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： SMITH MICHAEL R ,  STAMPS FRANK B ,  LEE TAEOH ,  HEVERLY DAVID E ,  PASCAL ROBERT J

IPC: F16F7/10 ,  B64C27/00 ,  F16F7/108 ,  F16F13/08 ,  F16F13/24 ,  F16F13/26 ,  F16F15/00 ,  F16F15/027

公开(公告)号：CA2716358A1

公开(公告)日：2009-09-03

申请号：CA2716358

申请日：2008-02-28

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： MEASOM RONALD J ,  STAMPS FRANK B

IPC: D07B1/02 ,  D07B1/14 ,  D07B5/08

Abstract: A resin-impregnated, structural fiber rope includes a plurality of tows disposed in a bundle, each of the plurality of tows including a plurality of structural fibers, and uncured polymeric resin impregnated into the bundle. Each of the plurality of structural fibers defines an angle with respect to a central axis of the rope of no more than about 10 degrees.

公开(公告)号：CA2711149A1

公开(公告)日：2009-07-16

申请号：CA2711149

申请日：2008-01-04

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： STAMPS FRANK B ,  TISDALE PATRICK R

IPC: B64C27/28 ,  B64C27/00 ,  B64C29/00

Abstract: A constant-velocity drive system for an aircraft rotor has a gimbal mechanism and a differential torque-combining mechanism. The gimbal mechanism has gimbals driven in rotation by a rotor mast about a mast axis, the gimbals providing for gimballing relative to the mast about gimbal axes generally perpendicular to the mast axis. The differential torque-combining mechanism is connected to the gimbal mechanism and configured to be driven in rotation about the mast axis by the gimbal mechanism. The differential mechanism is capable of gimballing relative to the mast about the gimbal axes, the differential torque-combining mechanism having an output component attached to a yoke of the rotor for driving the yoke in rotation with the differential torque- combining mechanism.

公开(公告)号：DE06849210T1

公开(公告)日：2009-01-29

申请号：DE06849210

申请日：2006-01-13

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： STAMPS FRANK B ,  RAUBER RICHARD E ,  CAMPBELL THOMAS C ,  BRASWELL JAMES L JR ,  POPELKA DAVID A ,  STANNEY KEITH ,  SOUTHERLAND MICHAEL J ,  TISDALE PATRICK R ,  WASIKOWSKI MARK

IPC: B64C27/32

公开(公告)号：CA2662833A1

公开(公告)日：2008-02-21

申请号：CA2662833

申请日：2006-08-17

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： STAMPS FRANK B ,  RAUBER RICHARD ,  POPELKA DAVID ,  TISDALE PAT ,  BRASWELL JAMES LEE JR ,  CAMPBELL TOM

IPC: B64C27/35

Abstract: A torque coupling for a rotor head of a rotary-wing aircraft is configure d for rotation with a mast and for causing rotation of an attached yoke. The coupling has trunnions that rotate with the mast and extend generally radia lly. Pad-bearing assemblies each have a central member coupled to one of the trunnions with a laminated spherical bearing and have laminated pad bearing s affixed to opposing sides of the central member. The laminated bearings ha ve alternating rigid and elastomeric layers. A bearing mount is affixed to e ach pad bearing and is connected to a yoke for rotating the yoke with the ma st. The pad-bearing assemblies allow for relative motion between each centra l member and the associated trunnion and between each central member and the bearing mounts through elastic shear deformation, and this allows for gimba lling of the attached yoke relative to the mast.

公开(公告)号：CA2650355A1

公开(公告)日：2007-11-22

申请号：CA2650355

申请日：2007-05-14

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： CAMPBELL THOMAS C ,  DONOVAN TOM ,  TISDALE PATRICK R ,  POPELKA DAVID A ,  STAMPS FRANK B ,  RAUBER RICHARD E

IPC: B64C27/32 ,  B64C27/00 ,  B64C27/54

Abstract: A yoke for a rotary wing aircraft rotor system has a plurality of arms, each arm having a root. Each root has a notched portion configured to allow passage of a portion of a blade-pitch control system through the notched portion.

公开(公告)号：AU2005332627A1

公开(公告)日：2006-12-14

申请号：AU2005332627

申请日：2005-06-07

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： TISDALE PATRICK R ,  BRASWELL JAMES L JR ,  STAMPS FRANK B ,  CAMPBELL THOMAS ,  RAUBER RICHARD E ,  ZIERER JOE J ,  HAYNIE DAVID A ,  BASKIN CHARLES L

IPC: F16D3/48

Abstract: A joint is configured for use with a rotary-wing aircraft having at least one engine. A driver is coupled to an output shaft of the engine, the driver being rotatable about an axis. A yoke is at least partially rotatable relative to the driver about a first center of rotation, the center of rotation being located on the axis. A plurality of upright links couple the yoke to the driver, each link being translatable relative to the yoke, the driver, or both. Each link is also rotatable relative to the yoke, the driver, or both, about a second center of rotation.

公开(公告)号：BRPI0413189A

公开(公告)日：2006-10-03

申请号：BRPI0413189

申请日：2004-08-27

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： STAMPS FRANK B ,  SMITH MICHAEL R ,  BOTHWELL CHRISTOPHER M ,  CORSO LAWRENCE M ,  BRASWLL JAMES L JR ,  POPELKA DAVID A ,  SCHELLHASE ERNST C ,  HOLLIMON CHARLES L ,  NEWMAN THOMAS J ,  BASKIN BRYAN ,  CAMPBELL THOMAS C ,  ROBERTSON DANIEL B

IPC: B60G13/00 ,  B60G15/00 ,  B64C20060101 ,  B64C27/51 ,  F16D20060101 ,  F16F5/00 ,  F16F7/00 ,  F16F9/00 ,  F16F9/10 ,  F16F9/34 ,  F16F11/00 ,  F16F13/08 ,  F16F13/24 ,  F16F13/26

公开(公告)号：CA2533523A1

公开(公告)日：2005-06-02

申请号：CA2533523

申请日：2004-08-27

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： BASKIN BRYAN ,  SCHELLHASE ERNST C ,  NEWMAN THOMAS J ,  HOLLIMON CHARLES L ,  CAMPBELL THOMAS C ,  POPELKA DAVID A ,  ROBERTSON DANIEL B ,  BRASWELL JAMES L JR ,  STAMPS FRANK B ,  SMITH MICHAEL R ,  BOTHWELL CHRISTOPHER M ,  CORSO LAWRENCE M

IPC: B64C27/51 ,  B60G13/00 ,  B60G15/00 ,  B64C20060101 ,  F16D20060101 ,  F16F5/00 ,  F16F7/00 ,  F16F9/00 ,  F16F9/10 ,  F16F9/34 ,  F16F11/00 ,  F16F13/08 ,  F16F13/24 ,  F16F13/26

Abstract: A rotor hub assembly for a rotary-wing aircraft has a central member and a plurality of blade grips adapted for attaching rotor blades to the central member. The blade grips are pivotally attached to the central member and are capable of pivoting about a pivot axis generally normal to a plane of rotati on of the blades. The pivoting allows for in-plane motion of the blades relativ e to the central member. A damper is operably connected to each blade grip for damping the in-plane motion of the associated blade, each damper being selectively switchable between at least two spring rates.

公开(公告)号：CA2533201A1

公开(公告)日：2005-03-10

申请号：CA2533201

申请日：2004-08-27

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： SMITH MICHAEL R ,  STAMPS FRANK B ,  ROBERTSON DANIEL B ,  SCHELLHASE ERNST C ,  CAMPBELL THOMAS C ,  BRASWELL JAMES L JR ,  CORSO LAWRENCE M ,  POPELKA DAVID A ,  NEWMAN THOMAS J ,  BOTHWELL CHRISTOPHER M ,  HOLLIMON CHARLES L ,  BASKIN BRYAN

IPC: B60G13/00 ,  B60G15/00 ,  B64C20060101 ,  B64C27/51 ,  F16D20060101 ,  F16F5/00 ,  F16F7/00 ,  F16F9/00 ,  F16F9/10 ,  F16F9/34 ,  F16F11/00 ,  F16F13/08 ,  F16F13/24 ,  F16F13/26

Abstract: A damper has a piston having an axis, an outer surface, and opposing ends. Elastomeric seals are in sealing contact with the outer surface of the pisto n, the seals being coaxial with the piston and limiting movement of the piston to a path along the axis of the piston. The seals also define fluid chambers adjacent the ends of the piston. A primary passage communicates the fluid chambers, and a selectively switchable valve for controls a flow of fluid fr om one of the chambers to another of the chambers through the primary passage. When the flow of fluid through the primary passage is permitted, movement of the piston is resisted by a first spring rate due to a shear force required to cause shear deflection of the seals. When the flow of fluid through the primary passage is restricted, movement of the piston is resisted by a secon d spring rate due to a fluid force required to cause bulging deflection of the seals.