公开(公告)号：CA2650355C

公开(公告)日：2012-04-17

申请号：CA2650355

申请日：2007-05-14

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： STAMPS FRANK B ,  RAUBER RICHARD E ,  CAMPBELL THOMAS C ,  DONOVAN TOM ,  TISDALE PATRICK R ,  BRASWELL JAMES LEE JR

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：BRPI0621698A2

公开(公告)日：2011-12-20

申请号：BRPI0621698

申请日：2006-05-19

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： RAUBER RICHARD ,  STAMPS FRANK B ,  BRASWELL JAMES LEE JR

IPC: B64C27/22

Abstract: An aircraft rotor constant-velocity drive system having a differential mechanism that includes a drive disk configured to be integral in rotation with a mast, an upper member at least partially located above the drive disk, a lower member at least partially located below the drive disk, and at least one link connecting the upper member and the lower member to the drive disk such that the drive disk drives the upper member and the lower member in rotation with the drive disk and that the upper member and the lower member are allowed to rotate differently with respect to the drive disk. The link having opposing end joints and a central joint that pivotally engages the drive disk. The system also having a gimbal device configured to drive a rotor hub and to allow gimbaling of the rotor hub with respect to a mast.

公开(公告)号：BRPI0620973A2

公开(公告)日：2011-11-29

申请号：BRPI0620973

申请日：2006-01-13

Applicant: BELL HELICOPTER TEXTRON INC

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

IPC: B64C27/48

公开(公告)号：BRPI0710976A2

公开(公告)日：2011-05-31

申请号：BRPI0710976

申请日：2007-05-14

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： STAMPS FRANK B ,  RAUBER RICHARD E ,  BRASWEELL JAMES L JR ,  CAMPBELL THOMAS C ,  DONOVAN TOM ,  TISDALE PATRICK R

IPC: B64C27/33

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：CA2776045A1

公开(公告)日：2011-04-21

申请号：CA2776045

申请日：2009-10-13

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： STAMPS FRANK B ,  TISDALE PAT ,  MARSHALL BRYAN ,  CAMPBELL TOM

IPC: B64C27/00

Abstract: A method of making a composite rotor yoke includes preparing a molded rotor yoke in a closed cavity tool and possibly machining at least one portion of the molded rotor yoke to form the rotor yoke. In the preferred embodiment, preparing the molded rotor yoke is accomplished by applying layers of uncured low-flow composite material and a layer of uncured high-flow adhesive; substantially enclosing the uncured molded rotor yoke in the closed cavity tool; applying pressure so as to compress the uncured molded rotor yoke; and curing the uncured molded rotor yoke. During the curing process, the high-flow adhesive bleeds out of the molded rotor yoke, thereby preventing marcels from forming through movement of the low-flow composite material.

公开(公告)号：DE07861293T1

公开(公告)日：2011-01-27

申请号：DE07861293

申请日：2007-04-24

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： RAUBER RICHARD E ,  POPELKA DAVID A ,  STAMPS FRANK B

IPC: B64C27/32 ,  F16C15/00

公开(公告)号：CA2746048A1

公开(公告)日：2010-06-24

申请号：CA2746048

申请日：2008-12-18

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： SMITH MICHAEL R ,  STAMPS FRANK B

IPC: F16M1/00

Abstract: A tunable vibration isolator having a housing, fluid chamber, and at least one tuning passage. A piston assembly is resiliently disposed within the housing. A vibration isolation fluid is allowed to flow from the fluid chambers through the tuning passage. A metering valve is actuated up and down in order to change the effective diameter of the tuning passage, resulting in a change to the isolation frequency.

公开(公告)号：CA2533201C

公开(公告)日：2010-06-22

申请号：CA2533201

申请日：2004-08-27

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： STAMPS FRANK B ,  SMITH MICHAEL R ,  BOTHWELL CHRISTOPHER M ,  CORSO LAWRENCE M ,  BRASWELL 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

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 piston, 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 from 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 second spring rate due to a fluid force required to cause bulging deflection of the seals.

公开(公告)号：CA2533523C

公开(公告)日：2010-03-30

申请号：CA2533523

申请日：2004-08-27

Applicant: BELL HELICOPTER TEXTRON INC

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

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 rotation of the blades. The pivoting allows for in-plane motion of the blades relative 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：DE06838841T1

公开(公告)日：2009-12-03

申请号：DE06838841

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

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.