公开(公告)号：CA2830374C

公开(公告)日：2016-03-22

申请号：CA2830374

申请日：2013-10-16

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： STAMPS FRANK B ,  RAUBER RICHARD E

IPC: B64C27/605 ,  B64C27/635

Abstract: The present application includes a blade-pitch control system with an indexing swashplate. A swashplate assembly has a non-rotating portion and a rotating portion and an indexing portion of the mast. The swashplate assembly is translatably affixed to the indexing portion. A pitch link connects the rotating portion of the swashplate assembly to each blade. Translation of the swashplate assembly along the indexing portion causes a change in pitch of the blades and a corresponding indexing of the rotating portion of the swashplate assembly relative to the mast, the indexing causing a change in an angular orientation of each pitch link, thus providing for selected pitch-flap coupling between flapping motion of the yoke and pitch motion of the blades.

公开(公告)号：CA2816509C

公开(公告)日：2016-02-23

申请号：CA2816509

申请日：2010-11-12

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： SHERRILL PAUL B ,  STAMPS FRANK B ,  MEASOM RONALD J

IPC: B64C27/473 ,  B29C70/30 ,  B64C11/26 ,  F01D5/14 ,  F03D1/06 ,  F16F15/32

Abstract: A rotor blade for an aircraft includes a composite portion having fiber-reinforced resin material, the composite portion having an outside surface that forms at least a partial airfoil shape. The weighted portion includes a plurality of weighted material layers and a plurality of fiber-reinforced resin material layers. Weighted material is configured to be compatible with and integrated into composite manufacturing processes used to fabricate the rotor blade. The weighted portion has a higher density than the composite portion and positioned to produce desired mass balance characteristics of the rotor blade.

公开(公告)号：CA2704734C

公开(公告)日：2015-11-24

申请号：CA2704734

申请日：2007-09-27

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： WARD EMERY N ,  SMITH MICHAEL R ,  STAMPS FRANK B ,  HAYNIE DAVID ,  THOMPSON TERRY K ,  SHIPMAN DAVID P ,  WILSON JAMES A

IPC: F16F9/58 ,  B64D27/26 ,  F16F5/00 ,  F16F7/112 ,  F16F9/24 ,  F16F9/36

Abstract: A vibration isolator is disclosed having a housing which defines a fluid chamber. A piston, which is movable to and from a down position, is disposed within the housing. A vibration isolation fluid is disposed within the fluid chamber. A passage having a predetermined diameter extends through the piston to permit the vibration isolation fluid to flow from one fluid chamber to the other. An elastic element is provided for reducing transmission of vibrations from the piston to the housing when the piston is at the down position.

公开(公告)号：IN2746DEN2012A

公开(公告)日：2015-09-18

申请号：IN2746DEN2012

申请日：2012-03-30

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：CA2832669C

公开(公告)日：2015-09-08

申请号：CA2832669

申请日：2013-11-05

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： THOMPSON GEORGE M ,  STAMPS FRANK B ,  SHIMEK GLENN A

IPC: B64C27/605

Abstract: According to one embodiment, a rotor system includes an anti-rotation sleeve featuring an outer recess portion and a tilt sleeve positioned about the anti- rotation sleeve and having an opening therethrough. A first swashplate ring is positioned about the tilt sleeve and features an inner recess portion. An anti-rotation mechanism is disposed through the opening and at least partially in the outer recess portion and the inner recess portion. The anti-rotation mechanism is operable to prevent the first swashplate ring from rotating about the anti-rotation sleeve. A second swashplate ring is positioned about the first swashplate ring and rotatable about the anti- rotation sleeve.

公开(公告)号：CA2773175C

公开(公告)日：2015-09-08

申请号：CA2773175

申请日：2012-03-29

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： SOTTIAUX DANIEL P ,  STAMPS FRANK B

IPC: F16B11/00 ,  B64C13/24 ,  C09J5/00 ,  F16L13/10

Abstract: A tube form assembly includes an inner member and an outer member. Each of the inner and outer members has an offset which creates a cavity therebetween. During assembly of the tube form assembly, an adhesive is located in the cavity and squeezed out and through the adjacent bond lines between the inner member and outer member. The pressurization and flow of adhesive outward from the cavity facilitates removal of air bubbles, as well as prevents the introduction of air bubbles into the bond line.

公开(公告)号：CA2749118C

公开(公告)日：2015-09-08

申请号：CA2749118

申请日：2009-01-19

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： STAMPS FRANK B ,  TISDALE PATRICK R ,  DONOVAN TOM ,  RAUBER RICHARD E

IPC: B64C27/48 ,  B64C27/33

Abstract: A rotor assembly for a rotary-wing aircraft, the rotor having a central hub assembly with a flexure-type, twist-shank yoke with multiple arms, each arm being adapted for a rotor blade to be mounted thereto. The arms provide for pitch changes of blades attached to the yoke through twisting of portions of the arms about a corresponding pitch axis. An inboard pitch bearing associated with each arm is attached to the hub assembly and allows for rotation of the attached blade about the pitch axis, the inboard pitch bearing also allowing for out-of-plane motion of the arm relative to the hub assembly about a flapping axis. An outboard pitch bearing associated with each arm is attached to the associated arm a selected distance from the inboard pitch bearing and allows for rotation of the attached blade about the pitch axis.

公开(公告)号：CA2841971C

公开(公告)日：2015-08-04

申请号：CA2841971

申请日：2013-08-14

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： SMITH MICHAEL R ,  STAMPS FRANK B ,  GRIFFIN MAURICE D

IPC: F16F9/32 ,  B64C27/00 ,  F16F9/06

Abstract: In accordance with one embodiment of the present disclosure, a system includes a first housing, a second housing, a seal, and a spring system. The first housing includes a first volume of fluid. The first housing is capable of connecting to a first element and to a second element, and is also capable of reducing an amount of movement transferred from the first element to the second element. The second housing is connected to the first housing. The second housing includes a second volume of fluid and a volume of gas. The first volume of fluid is in fluid communication with the second volume of fluid. The seal is capable of separating the second volume of fluid from the volume of gas. The spring system is capable of applying pressure to the first volume of fluid and the second volume of fluid.

公开(公告)号：CA2754205C

公开(公告)日：2015-05-19

申请号：CA2754205

申请日：2009-03-12

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： SMITH MICHAEL R ,  STAMPS FRANK B

IPC: F16F9/44 ,  B64C27/51 ,  F16F9/14 ,  F16F9/34

Abstract: A vibration isolator having a housing defining a fluid chamber, piston assembly, tuning passage, and a switchable fluid path assembly for changing the isolation frequency of the vibration isolator. The piston assembly is resiliently disposed within the housing. A vibration tuning fluid is allowed to flow within the housing. Actuation of a valve in the switchable fluid path assembly selectively controls fluid flow within the fluid path of the switchable fluid path assembly.

公开(公告)号：CA2794228C

公开(公告)日：2015-04-07

申请号：CA2794228

申请日：2012-11-02

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： RAUBER RICHARD E ,  STAMPS FRANK B ,  POPELKA DAVID A ,  TISDALE PATRICK R ,  WOOD TOMMIE L

IPC: B64C11/06 ,  B64C11/48 ,  B64C27/28 ,  B64C27/37 ,  B64C27/50

Abstract: The present application includes a main rotor assembly for an aircraft. The rotor assembly has a main rotor mast configured for rotation about a mast axis and two yokes pivotally connected to the mast for rotation therewith about the mast axis. Each yoke is independently pivotable relative to the mast about at least one flap axis that is generally perpendicular to the mast axis. A torque splitter is rotatably attached directly to the mast and disposed between the two yokes. The torque splitter is configured to transfer rotational movement to the two yokes while also allowing limited movement of the two yokes relative to each other. Each yoke is configured for the attachment of rotor blades extending generally radially relative to the mast axis.