公开(公告)号：CA2665700C

公开(公告)日：2013-11-19

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 mounting 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 and selectively moveable by an actuating means along the axis of the link in an oscillatory manner for attenuating vibrations traveling axially through the link. The actuating means may be an electromechanical, hydraulic, pneumatic, 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：CA2806277A1

公开(公告)日：2013-08-24

申请号：CA2806277

申请日：2013-02-15

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： FOSKEY CHRISTOPHER ,  STAMPS FRANK B

IPC: B64C27/32 ,  B64C11/04

Abstract: A tiltrotor rotor hub comprises first and second configurations of yokes arranged in two parallel and axially offset planes, each having an equal number of two or more yokes substantially equally spaced about a mast, wherein a portion of each yoke overlaps with a portion of each azimuthally adjacent yoke. Another tiltrotor rotor hub is selectively positionable for operation in helicopter/airplane/transition modes and comprises substantially parallel and axially offset first and second planes, each containing a plurality of blade yokes arranged about a central axis and a portion of each yoke overlaps with a portion of each azimuthally adjacent yoke. Another tiltrotor rotor hub is coupled to a tiltrotor mast and comprises a stacked arrangement of blade yokes wherein a portion of each yoke overlaps with a portion of each azimuthally adjacent yoke, and a plurality of mounting components coupling each yoke to the overlapping azimuthally adjacent yoke.

公开(公告)号：CA2805889A1

公开(公告)日：2013-08-21

申请号：CA2805889

申请日：2013-02-12

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： STAMPS FRANK B ,  MARSHALL BRYAN W ,  THOMPSON TERRY K ,  BRAZIEL ORION ,  POPELKA DAVID ,  TISDALE PATRICK

IPC: B64C27/32 ,  B64C11/06 ,  B64C27/48

Abstract: A rotary system includes a retention member and a flexible yoke having an opening forming a bridge. The rotary system is further provided with two bearing assemblies, a first bearing assembly extending through the opening of the yoke and configured to secure a rotor blade to the retention member and a second bearing assembly extending through the opening of the flexible yoke and configured to secure the rotor blade to the bridge. The second bearing element includes a bearing element having a first surface forming a spherical contouring and an opposing integral second surface forming a conical contouring.

公开(公告)号：CA2800439A1

公开(公告)日：2013-06-28

申请号：CA2800439

申请日：2012-12-20

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： BISER JOSEPH ,  DAY CLIFTON B ,  STAMPS FRANK B ,  SPIVEY DANIEL

IPC: B64C27/605 ,  B64C11/32 ,  F16C7/06

Abstract: According to one embodiment, a pitch link includes a first link, a second link coupled to a first end of the first link, a third link coupled to a second end of the first link opposite the first end, and a first bearing housing having a first bearing and a second bearing housing having a second bearing. The first bearing housing is removably coupled to the second link. The second link separates the first bearing housing from the first link. The second bearing housing is removably coupled to the third link. The third link separates the second bearing housing from the first link.

公开(公告)号：CA2794039A1

公开(公告)日：2013-05-16

申请号：CA2794039

申请日：2012-11-01

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： STAMPS FRANK B ,  TISDALE PATRICK ,  CORRIGAN JOHN J III

IPC: B64C27/51 ,  B64C11/06 ,  B64C27/37 ,  B64C27/635 ,  F16F9/44

Abstract: A rotor hub assembly and method for controlling movement of a rotor blade relative to a swashplate. The hub assembly having an attachment device operably associated with the rotor blade and the swashplate. The attachment device provides pivot and rotational blade movement relative to the swashplate. A dual spring-rate damper is operably associated with the attachment device. The damper switches between a first spring rate and a second spring rate during flight to control movement of the rotor blade. The method includes the process of switching the damper between the first spring rate and the second spring rate during flight.

公开(公告)号：CA2789472A1

公开(公告)日：2013-05-11

申请号：CA2789472

申请日：2012-09-07

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： LEE TAEOH ,  SMITH MICHAEL R ,  STAMPS FRANK B ,  HEVERLY DAVID E JR

IPC: F16F9/46 ,  B64C11/04 ,  B64C27/51 ,  F16F9/18 ,  F16F9/34

Abstract: A vibration isolator includes a housing having an upper fluid chamber, a lower fluid chamber, a piston, a tuning passage, and a linear inductance motor assembly for changing the isolation frequency of the vibration isolator. The piston is resiliently disposed within the housing. A vibration tuning fluid is located in the upper fluid chamber, the lower fluid chamber, and the tuning passage. The linear inductance motor assembly includes a magnet member and an inductance coil at least partially surrounding the magnet member. A control system is configured to selectively actuate the magnet member; wherein selective actuation of the magnet member selectively imparts a pumping force on the tuning fluid, thereby changing the isolation frequency.

公开(公告)号：CA2792226A1

公开(公告)日：2013-04-28

申请号：CA2792226

申请日：2012-10-11

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： STAMPS FRANK B ,  MARSHALL BRYAN W

IPC: B64C11/04 ,  B64C11/06 ,  B64C27/37 ,  F16C11/06

Abstract: A rotary system and method to control feathering movement of a rotor blade. The system having a yoke arm configured to rotate a rotor blade. A first bearing and a second bearing are utilized to secure the rotor blade to the yoke arm and are configured to restrict longitudinal and transverse movement, while allowing feathering movement of the rotor blade relative to yoke arm.

公开(公告)号：CA2667607C

公开(公告)日：2013-02-19

申请号：CA2667607

申请日：2006-11-14

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： STAMPS FRANK B ,  SMITH DUDLEY ,  KILMAIN CHARLES J ,  EHINGER RYAN ,  COLLINS BOB

IPC: B64D35/00 ,  B64C27/00

Abstract: A transmission for a rotary-wing aircraft has a differential torque-splitting mechanism associated with an input shaft. The differential has a drive disk coaxial with the shaft and integral in rotation with the shaft, a first driven member coaxial with the shaft and generally adjacent the drive disk, and a second driven member coaxial with the shaft and generally adjacent the drive disk. At least one pin engages each of the drive disk, the first driven member, and the second driven member. The first driven member is configured to drive a first transfer gear, and the second driven member is configured to drive a second transfer gear for supplying torque to a bull gear associated with a rotor mast.

公开(公告)号：CA2838512A1

公开(公告)日：2013-01-03

申请号：CA2838512

申请日：2011-06-29

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： STAMPS FRANK B ,  TISDALE PATRICK R ,  YUCE MITHAT

IPC: B64C27/37

Abstract: A rotor hub has a yoke with radial arms allowing flapping of connected blades about a flap axis. A grip is rigidly attached to each blade, and a lead-lag bearing connects each grip to one of the arms, the bearing defining a lead-lag axis outboard of the flap axis. Each arm has a pair of straps located on opposite sides of the rotor plane for transferring centrifugal force from the blades to the central portion of the yoke. A pair of lead-lag dampers is provided for each grip, the dampers of each pair being located on opposite sides of the rotor plane and connecting an inboard end portion of the grip to the adjacent strap. In-plane motion of a blade causes rotation of the attached grip about the lead-lag axis, causing opposite motion of an inboard end portion of the grip. The dampers act to oppose rotation of the grip.

公开(公告)号：CA2835401A1

公开(公告)日：2012-11-29

申请号：CA2835401

申请日：2011-05-20

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： STAMPS FRANK B

IPC: B64C27/02

Abstract: A blade-pitch control system for controlling a pitch angle of blades on a rotor has an input swashplate assembly having non-rotating and rotating portions, the rotating portion being operably connected to blade grips. A feedback swashplate assembly has non-rotating and rotating portions, the rotating portion being connected to the yoke for movement with the yoke during flapping of the yoke. Linear actuators connect the non-rotating portion of the input swashplate assembly to the non-rotating portion of the feedback swashplate assembly. Motion of the yoke during flapping causes a corresponding motion of the feedback swashplate assembly and input swashplate assembly for providing selected pitch-flap coupling between flapping motion of the yoke and pitch motion of the grips.