公开(公告)号：DE60233129D1

公开(公告)日：2009-09-10

申请号：DE60233129

申请日：2002-04-19

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： SEHGAL AJAY ,  COVINGTON CECIL E ,  SMITH MICHAEL R ,  STAMPS FRANK B ,  MARSHALL BRYAN

IPC: B64C27/51 ,  B64C27/00

Abstract: A rotor system vibration absorber for use with a helicopter of other rotorcraft is disclosed in which spring forces are provided by a plurality of elongated rods arranged in a selected pattern. The rods are coupled at one end to a fixed base that is coupled to a rotor hub, and at the other end to a tuning weight.

公开(公告)号：BRPI0520263A2

公开(公告)日：2009-04-28

申请号：BRPI0520263

申请日：2005-06-07

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： STAMPS FRANK B ,  ZIERER JOE J ,  HAYNIE DAVID A ,  RAUBER RICHARD E ,  CAMPBELL THOMAS C ,  TISDALE PATRICK R ,  BRASWELL JAMES L JR ,  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：DE05759330T1

公开(公告)日：2008-08-21

申请号：DE05759330

申请日：2005-06-07

Applicant: BELL HELICOPTER TEXTRON INC

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

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：CA2662744A1

公开(公告)日：2008-04-24

申请号：CA2662744

申请日：2006-06-20

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： RAUBER RICHARD ,  STAMPS FRANK B

IPC: B64C27/35 ,  F16F1/40

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

公开(公告)号：AU2006350121A1

公开(公告)日：2008-04-24

申请号：AU2006350121

申请日：2006-06-20

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： RAUBER RICHARD ,  STAMPS FRANK B

IPC: B64C27/51

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.

公开(公告)号：AU2006347271A1

公开(公告)日：2008-02-21

申请号：AU2006347271

申请日：2006-08-17

Applicant: BELL HELICOPTER TEXTRON INC

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

IPC: B64C27/12

Abstract: A torque coupling for a rotor head of a rotary-wing aircraft is configured 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 radially. Pad-bearing assemblies each have a central member coupled to one of the trunnions with a laminated spherical bearing and have laminated pad bearings affixed to opposing sides of the central member. The laminated bearings have alternating rigid and elastomeric layers. A bearing mount is affixed to each pad bearing and is connected to a yoke for rotating the yoke with the mast. The pad-bearing assemblies allow for relative motion between each central member and the associated trunnion and between each central member and the bearing mounts through elastic shear deformation, and this allows for gimballing of the attached yoke relative to the mast.

公开(公告)号：DE04786599T1

公开(公告)日：2007-02-22

申请号：DE04786599

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 ,  POPELKA DAVID A ,  SCHELLHASE ERNST C ,  HOLLIMON CHARLES L ,  NEWMAN THOMAS J ,  BASKIN BRYAN ,  CAMPBELL THOMAS C ,  ROBERTSON DANIEL B

IPC: F16F9/14 ,  B60G13/00 ,  B60G15/00 ,  B64C20060101 ,  B64C11/04 ,  B64C27/51 ,  F16D20060101 ,  F16F5/00 ,  F16F7/00 ,  F16F9/00 ,  F16F9/10 ,  F16F9/34 ,  F16F9/36 ,  F16F11/00 ,  F16F13/08 ,  F16F13/24 ,  F16F13/26

公开(公告)号：CA2485830C

公开(公告)日：2007-02-06

申请号：CA2485830

申请日：1994-12-01

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： STAMPS FRANK B ,  SMITH MICHAEL R

IPC: F16F15/16 ,  B64C27/00 ,  B64C27/51 ,  F16F9/10 ,  F16F13/08 ,  F16F13/24 ,  F16F15/00

Abstract: A tunable dual-axis live isolator (31) with a vertical single-axis isolator (33) and a horizontal single-axis isolator (35) with cruciform member (41) serving as pistons for both single-axis isolators (33-35). The isolator (31) is tuned by a sleeve (83) within the cruciform member (41) for varying the dimension of the tuning passage (75). The isolator (31) minimizes the transfer of vibration forces and moments from a vibrating body to a body attached thereto.

公开(公告)号：CA2596322A1

公开(公告)日：2006-08-17

申请号：CA2596322

申请日：2006-01-24

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： ZIERER JOSEPH J ,  REDDY D J ,  LEDBETTER TIMOTHY K ,  TISDALE PATRICK R ,  STAMPS FRANK B ,  WIINIKKA MARK A ,  OLDROYD PAUL ,  HIROS TRICIA ,  MEASOM RON ,  MARTIN RONNIE L ,  CAMPBELL TOM ,  BRASWELL JAMES L ,  BASKIN CHARLES L JR ,  HARSE JIM ,  MULLINS BOB ,  SADLER STANLEY GENE ,  HAYNIE DAVID A

IPC: B64C27/33 ,  B64C27/51

Abstract: An assembly for providing flexure to a blade of a rotary blade system includes an upper support plate having an upper curved surface, a lower support plate having a lower curved surface, and a yoke positioned therebetween. At least one of the upper and lower yoke surfaces has a layer of cushioning material positioned thereon and secured thereto. An alternate embodiment includes an assembly for providing flexure to a blade of a rotary blade system, including, an upper support plate having an upper curved surface, a lower support plate having a lower curved surface, and a yoke positioned therebetween and directly contacting the support plates wherein one of the curved surfaces is a non-circular arc that does not form part of the circumference of a circle. Another alternate embodiment includes a similar assembly having a twist-shank type of yoke for providing rotation of attached blades about their respective pitch axes.

公开(公告)号：DE60200897T2

公开(公告)日：2005-09-22

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.