公开(公告)号：DE06851653T1

公开(公告)日：2009-07-30

申请号：DE06851653

申请日：2006-06-20

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： STAMPS FRANK B ,  RAUBER RICHARD

IPC: B63H1/00

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：BRPI0606617A2

公开(公告)日：2009-07-07

申请号：BRPI0606617

申请日：2006-04-19

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： RAUBER RICHARD ,  STAMPS FRANK B

IPC: B64C27/02 ,  B64C27/52

Abstract: A torque coupling (13) for a rotor head (11) of a rotary-wing aircraft has upper and lower plates (29, 31) configured for rotation with a rotor mast (19). Drive links (33) pivotally connected to the upper and lower plates (29, 31) pivot about a pivot axis generally parallel to and radially offset from an axis of rotation of the plates. Each link (33) is engaged with adjacent drive links (33) to form a continuous ring of links, such that motion of one link (33) about its pivot axis causes motion in an opposite direction of each adjacent link (33) about its pivot axis. Drive elements (25) connect the drive links (33) to an assembly configured to receive rotor blades. The drive elements (25) may be components of a universal joint, a multiple trailing-link configuration, a pad-bearing configuration, or another type of articulating assembly.

公开(公告)号：DE60134767D1

公开(公告)日：2008-08-21

申请号：DE60134767

申请日：2001-09-26

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： SMITH MICHAEL R ,  STAMPS FRANK B ,  PASCAL ROBERT J

IPC: F16F7/10 ,  B64C27/00

公开(公告)号：CA2665700A1

公开(公告)日：2008-04-17

申请号：CA2665700

申请日：2006-10-12

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： SMITH MICHAEL R ,  STAMPS FRANK B

IPC: B64C27/12 ,  B64C27/04 ,  F16F7/10

Abstract: A preferred embodiment of a pylon has six pylon mounting links for mounti ng the pylon to an airframe. Each link is considered "near-rigid" and has a spherical-bearing rod-end on both ends such that the link can only transmit axial loads. At least one of the links has a mass carried within the link an d selectively moveable by an actuating means along the axis of the link in a n oscillatory manner for attenuating vibrations traveling axially through th e link. The actuating means may be an electromechanical, hydraulic, pneumati c, or piezoelectric system. By mounting each link in a selected orientation relative to the other links, the actuating means may be operated in a manner that attenuates axial vibration that would otherwise be transmitted through the link and into the airframe.

公开(公告)号：DE04819036T1

公开(公告)日：2007-04-05

申请号：DE04819036

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: B64C27/51 ,  B60G13/00 ,  B60G15/00 ,  B64C20060101 ,  B64C27/22 ,  F16D20060101 ,  F16F5/00 ,  F16F7/00 ,  F16F9/00 ,  F16F9/10 ,  F16F9/34 ,  F16F11/00 ,  F16F13/08 ,  F16F13/24 ,  F16F13/26

公开(公告)号：CA2610853A1

公开(公告)日：2006-12-14

申请号：CA2610853

申请日：2005-06-07

Applicant: BELL HELICOPTER TEXTRON INC

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

IPC: F16D3/48

Abstract: A constant-velocity 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 link couple the yoke to the driver, each ling 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：BRPI0413123A

公开(公告)日：2006-10-03

申请号：BRPI0413123

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

公开(公告)号：CA2369837A1

公开(公告)日：2002-08-16

申请号：CA2369837

申请日：2002-01-30

Applicant: BELL HELICOPTER TEXTRON INC

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

IPC: B64C27/08 ,  B64C27/37 ,  B64C27/605 ,  B64C29/00 ,  B64C27/28 ,  B64C27/39

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 whi le 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 o f 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 i n a rotor disk position which is substantially transverse to the craft body; (2) a helicopt er 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 fligh t.

公开(公告)号：CA2995295C

公开(公告)日：2020-07-21

申请号：CA2995295

申请日：2018-02-14

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： MILLER GARY ,  STAMPS FRANK B ,  CHOI JOUYOUNG JASON ,  PARHAM THOMAS C ,  EWING ALAN ,  RAUBER RICHARD E

IPC: B64C27/37 ,  B64C11/06 ,  B64C11/12 ,  B64C27/54

Abstract: An aircraft rotor assembly includes a central hub, and rotor blades coupled to the hub for rotation with the hub about an axis. Each blade has a Lock number of approximately 5 or greater. A discrete hinge for each blade allows for out-of-plane motion. A lead-lag pivot for each blade formed by a flexure couples the associated blade to the hub. Each pivot is a radial distance from the axis and allows for in-plane lead-lag motion of the associated blade relative to the hub. Each pivot allows for in-plane motion from a neutral position of at least 1 degree in each of the lead and lag directions. Elastic deformation of the flexure produces a biasing force for biasing the associated blade toward the neutral position. The biasing force is selected to achieve a first in-plane frequency of greater than 1/rev for each blade.

公开(公告)号：CA2596322C

公开(公告)日：2016-09-13

申请号：CA2596322

申请日：2006-01-24

Applicant: BELL HELICOPTER TEXTRON INC

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

IPC: B64C27/33 ,  B64C27/51

Abstract: An assembly for providing flexure to a blade of a rotary blade system, the assembly including 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 having a layer of cushioning material positioned thereon and secured thereto. The layer of cushioning material extending along and following the general contour of yoke surface, and the layer of cushioning material directly contacting a support plate. Another embodiment is 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.