公开(公告)号：CA3017372A1

公开(公告)日：2019-03-22

申请号：CA3017372

申请日：2018-09-13

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： MARSHALL BRYAN ,  WIINIKKA MARK A ,  SHERRILL PAUL ,  STAMPS FRANK BRADLEY

IPC: B64C27/48 ,  B64C27/51 ,  B64C27/54 ,  F16F7/00

Abstract: An aircraft rotor assembly has a yoke defining a plurality of bearing pockets. Each bearing pocket houses an axisymmetric elastomeric spherical bearing at least partially therein. The axisymmetric elastomeric spherical bearings comprise flap, lead-lag, and pitch hinges for rotor blades coupled thereto. The rotor blades maintain a first in-lane frequency of less than 1/rev through the use of damper assemblies coupled between adjacent blades.

公开(公告)号：CA2805481C

公开(公告)日：2015-11-24

申请号：CA2805481

申请日：2013-02-08

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： WIINIKKA MARK ,  STAMPS FRANK BRADLEY ,  SOTTIAUX DANIEL P ,  DAILEY ZACH

IPC: B64C27/54 ,  B64C11/06 ,  B64C27/48 ,  B64C27/605

Abstract: A rotary system including a yoke having an opening forming a bridge for receiving a spoke extending therethrough. A rotor blade couples to the spoke and a pitch horn positioned outside the opening pitches the rotor blade during flight. A bearing assembly attaches the spoke and the pitch horn to the bridge and control blade forces exerted against the hub assembly during flight.

公开(公告)号：CA2712638C

公开(公告)日：2015-05-12

申请号：CA2712638

申请日：2008-01-31

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： HIROS TRICIA ,  STAMPS FRANK BRADLEY ,  TISDALE PAT ,  MEASOM RON ,  BRASWELL JIM ,  CAMPBELL TOM ,  OLDROYD PAUL K ,  BARBOUR RICHARD

IPC: B64C27/32 ,  B29C43/10 ,  B29C43/12

Abstract: A method of making a rotor yoke includes preparing a cured composite rotor yoke preform on a single-sided curing tool and machining at least one portion of the cured rotor yoke preform to form a rotor yoke. In one embodiment, preparing the cured composite rotor yoke is accomplished by applying successive layers of uncured polymeric composite material to a single-sided tool in a configuration to produce an uncured rotor yoke preform; disposing a semi-rigid caul to an untooled side of the uncured rotor yoke preform; enclosing the uncured rotor yoke preform and the semi-rigid caul by substantially hermetically sealing a vacuum bag to the tool; substantially evacuating a volume defined by the vacuum bag and the tool of air; and heating the uncured rotor yoke preform, sometimes under pressure, to form the cured composite rotor yoke preform.

公开(公告)号：CA2606976C

公开(公告)日：2014-11-04

申请号：CA2606976

申请日：2006-03-17

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： STAMPS FRANK BRADLEY ,  SMITH MICHAEL REAUGH ,  LEE TAEOH

IPC: F16F13/10 ,  F16F9/52 ,  F16F13/24

Abstract: A vibration isolator for connecting a first body and a second body includes a housing having a first chamber (22) , a second chamber (26) , and a port (24) connecting the first chamber (22) to the second chamber (26) and permitting fluid (34) to flow between the first chamber (22) and the second chamber (26). The first and second chambers (22), (26) and the port (24) defining a fluid reservoir (27) . The isolator (10) includes a gas-to-fluid accumulator (30) in fluid communication with the fluid reservoir (27) through a first one-way valve (140) and a second one-way valve (142) . The first one-way valve (140) allows fluid (34) to pass only from the fluid reservoir (27) to the accumulator (30) and the second one-way valve (142) allows fluid (34) to pass only from the accumulator (30) to the fluid reservoir (27). At least one of the first and second one-way valves (140), (142) being preloaded to a predetermined force to permit fluid flow through the at least one-way valve (140), (142) only when fluid pressure exceeds the predetermined force.

公开(公告)号：CA2830006A1

公开(公告)日：2014-04-23

申请号：CA2830006

申请日：2013-10-11

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： SUTTON DREW ,  VO LOAN THANH ,  STAMPS FRANK BRADLEY ,  PHILLIPS NOLAN

IPC: B32B1/00 ,  B64C3/20 ,  B64C11/26 ,  B64C27/473 ,  B64F5/00

Abstract: A method of constructing a composite component includes at least one of laterally and longitudinally aligning a material strip relative to a concavity of a layup tool, at least one of laterally and longitudinally extending the material strip to a predetermined location relative to the layup tool, wherein the material strip is substantially rectangular, and vertically abutting the material strip to the concavity of the layup tool, wherein the longitudinally extending the material strip includes at least one of (1) measuring a longitudinal distance of the material strip and (2) aligning a longitudinal end of the material strip with a longitudinal distance indicium and wherein the laterally extending the material strip includes at least one of (1) measuring a lateral distance of the material strip and (2) aligning a lateral end of the material strip with a lateral distance indicium.

公开(公告)号：CA2431191C

公开(公告)日：2008-12-09

申请号：CA2431191

申请日：2001-12-12

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： MARTIN RONNIE LEE ,  BRASWELL JAMES LEE JR ,  STAMPS FRANK BRADLEY

IPC: G01L7/06 ,  F16F9/10 ,  F16F9/32 ,  F17C13/02 ,  G01L7/08 ,  G01L19/10 ,  G01L19/12

Abstract: A pressure indicator (106) according to the present invention monitors the pressure of the fluid in a vessel (102). One embodiment of the present invention comprises a closed pressurized gas volume (210) behind a dimpled metal diaphragm (208). In normal operation, the force of the fluid pressure acting on the external surface of the diaphragm (208) to hold the diaphragm (208) in a concave geometry. In the event of a sufficient loss of fluid pressure, the force of the gas pressure acting on the internal surface of th e diaphragm (208) will overcome the force of the fluid pressure acting on the external surface of the diaphragm (208), thereby moving the diaphragm (208) into a convex geometry. A viewing window (110) disposed in the side of the vessel (102) can be used to view the pressure indicator (106) and determine the shape of the indicator diaphragm (208).

公开(公告)号：AT348965T

公开(公告)日：2007-01-15

申请号：AT01939332

申请日：2001-05-23

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： STAMPS FRANK BRADLEY ,  SMITH MICHAEL REAUGH ,  BRASWELL JAMES LEE JR ,  LEDBETTER TIMOTHY KENT

IPC: F16F1/38 ,  F16F9/06 ,  F16F13/18 ,  F16F13/24

公开(公告)号：CA2982110C

公开(公告)日：2020-09-22

申请号：CA2982110

申请日：2017-10-10

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： CHOI JOUYOUNG JASON ,  MILLER GARY ,  RAUBER RICHARD ERLER ,  PARHAM THOMAS CLEMENT ,  EWING ALAN CARL ,  STAMPS FRANK BRADLEY

IPC: B64C27/39 ,  B64C11/02 ,  B64C11/26 ,  B64C27/28 ,  B64C27/473 ,  B64C27/54

Abstract: A proprotor system for tiltrotor aircraft having a helicopter mode and an airplane mode. The proprotor system includes a hub and a plurality of proprotor blades coupled to the hub such that each proprotor blade is operable to independently flap relative to the hub and independently change pitch. In the airplane mode, the proprotor blades have a first in-plane frequency greater than 2.0/rev.

公开(公告)号：CA2983143C

公开(公告)日：2019-05-07

申请号：CA2983143

申请日：2017-10-19

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： PARHAM THOMAS CLEMENT ,  CHOI JOUYOUNG JASON ,  MILLER GARY ,  STAMPS FRANK BRADLEY ,  RAUBER RICHARD ERIER

IPC: B64C27/51 ,  B64C11/06 ,  B64C27/28 ,  B64C27/48 ,  B64C27/59

Abstract: A soft-in-plane proprotor system for a tiltrotor aircraft having a helicopter mode and an airplane mode. The proprotor system comprises a hub, and proprotor blades coupled to the hub to independently flap relative to the hub, and independently change pitch. A plurality of loop yokes coupling one of the proprotor blades with the hub and including first and second longitudinal sections extending between inboard and outboard arcuate sections. A bearing assembly disposed between the inboard and outboard arcuate sections of each loop yoke. Each bearing assembly includes a flapping bearing disposed generally within the inboard arcuate section and coupled to the hub, a lead-lag damper coupled to the hub, a centrifugal force bearing disposed generally within the outboard arcuate section, and a blade anchor positioned between the lead-lag damper and the centrifugal force bearing. The blade anchor is coupled to the respective proprotor blade inboard of the centrifugal force bearing.

公开(公告)号：CA2974257A1

公开(公告)日：2018-07-09

申请号：CA2974257

申请日：2017-07-20

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： SUTTON DREW ALAN ,  STAMPS FRANK BRADLEY

IPC: B64C27/59 ,  B64C27/37 ,  B64C27/82

Abstract: The present invention includes a rotor hub system (200), comprising: a teetering rotor hub (204, 206) disposed about a mast (202), the teetering rotor hub (204, 206) comprising: a first (208) and a second (218) yoke; each connected to a set of rotor blades (210, 212, 220, 222), wherein the second set of rotor blades (220, 222) and the first set of rotor blades (210, 212) are disposed in a common plane, but the first (208) and the second (218) yoke do not come in contact.