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公开(公告)号:CA2652777C
公开(公告)日:2012-11-06
申请号:CA2652777
申请日:2006-05-19
Applicant: BELL HELICOPTER TEXTRON INC
Inventor: RAUBER RICHARD , STAMPS FRANK B , BRASWELL JAMES LEE JR
Abstract: A constant-velocity drive system for a rotary-wing aircraft rotor comprising a differential torque-splitting mechanism and a gimbal mechanism is disclosed. A rotary-wing aircraft having a rotary-wing aircraft rotor comprising a differential torque- splitting mechanism and a gimbal mechanism is disclosed.
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公开(公告)号:CA2831584A1
公开(公告)日:2012-11-01
申请号:CA2831584
申请日:2011-04-26
Applicant: BELL HELICOPTER TEXTRON INC
Inventor: YUCE MITHAT , POPELKA DAVID A , STAMPS FRANK B , WIINIKKA MARK A
IPC: B64C27/51
Abstract: A dual series damper includes a fluid damper portion and a elastomeric damper portion. The fluid damper portion includes a first housing, a first connection member, and a piston coupled to the first connection member. The piston divides an interior of the first housing into a first fluid chamber and a second fluid chamber. The piston has a fluid passage in the piston, the fluid passage being configured to provide fluid communication between the first fluid chamber and the second fluid chamber. The elastomeric damper portion includes a second housing, a second connection member coupled to the second housing, and an elastomer between the first housing and the second housing. When a lead/lag force is introduced to the dual series damper, the fluid damper portion behaves rigidly so that the elastomeric damper portion dampens the lead/lag oscillation.
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公开(公告)号:CA2662744C
公开(公告)日:2012-04-17
申请号:CA2662744
申请日:2006-06-20
Applicant: BELL HELICOPTER TEXTRON INC
Inventor: STAMPS FRANK B , RAUBER RICHARD
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.
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公开(公告)号:CA2665676C
公开(公告)日:2012-01-31
申请号:CA2665676
申请日:2006-12-08
Applicant: BELL HELICOPTER TEXTRON INC
Inventor: STAMPS FRANK B , RAUBER RICHARD , POPELKA DAVID A , TISDALE PATRICK R , CAMPBELL THOMAS C , BRASWELL JAMES L JR , STANNEY KEITH , WASIKOWSKI MARK , DONOVAN TOM , BASKIN BRYAN , SMITH RYAN , CORRIGAN JOHN J III
Abstract: A pitch control system for blades on a rotor of an aircraft has a gimballing rotor hub (31) and a plurality of step-over arms (61) connected to the hub and capable of pivoting relative to the hub about a pivot axis. Each of a plurality of pitch links (55) connects one of the step-over arms (61) to a flight control system for pivoting the connected step-over arm (61) about the pivot axis and relative to the hub in response to inputs from the control system. Each of a plurality of step-over links (69) connects one of the step-over arms (61) to one of the blades for rotating the associated blade about the pitch axis in response to pivoting of the associated step-over arm.
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公开(公告)号:BRPI0621904A2
公开(公告)日:2011-12-20
申请号:BRPI0621904
申请日:2006-08-17
Applicant: BELL HELICOPTER TEXTRON INC
Inventor: STAMPS FRANK B , RAUBER RICHARD , POPELKA DAVID , TISDALE PATRICK R , CAMPBELL THOMAS C , BRASWELL JAMES LEE JR
IPC: B64C27/35
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.
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公开(公告)号:BRPI0621713A2
公开(公告)日:2011-12-20
申请号:BRPI0621713
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.
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公开(公告)号:CA2592644C
公开(公告)日:2011-10-11
申请号:CA2592644
申请日:2006-01-24
Applicant: BELL HELICOPTER TEXTRON INC
Inventor: STAMPS FRANK B , TISDALE PATRICK R , SHERRILL PAUL , RAUBER RICHARD , CAMPBELL THOMAS C , BRASWELL JAMES LEE JR , MEASOM RON , HIROS TRICIA , POPELKA DAVID A , SOUTHERLAND MICHAEL J , STANNEY KEITH , WASIKOWSKI MARK , LEDBETTER TIM
IPC: B64C27/473 , B64C27/46
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.
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公开(公告)号:CA2789340A1
公开(公告)日:2011-08-25
申请号:CA2789340
申请日:2011-02-15
Applicant: BELL HELICOPTER TEXTRON INC
Inventor: SMITH MICHAEL R , STAMPS FRANK B
IPC: B64D27/00
Abstract: A variable stiffness liquid inertia vibration isolation device includes a liquid inertia vibration elimination isolator and a variable stiffness spring operably associated with the liquid inertia vibration elimination isolator for varying the stiffness of the liquid inertia vibration isolator. The variable stiffness spring may include an elastomeric pad exhibiting a first stiffness along a first axis and a second stiffness, significantly greater than the first stiffness, along a second axis that is perpendicular to the first axis.
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公开(公告)号:CA2780953A1
公开(公告)日:2011-06-09
申请号:CA2780953
申请日:2009-12-01
Applicant: BELL HELICOPTER TEXTRON INC
Inventor: SMITH MICHAEL R , STAMPS FRANK B
IPC: F16F7/10
Abstract: A vibration isolator having an upper housing defining an upper fluid chamber, a lower housing defining a lower fluid chamber, a piston resiliently disposed within the upper housing and the lower housing, a tuning passage defined by the piston, for providing fluid communication between the upper fluid chamber and the lower fluid chamber, a tuning fluid disposed within the tuning passage, the upper fluid chamber, and the lower fluid chamber. A reservoir in fluid communication with the upper fluid chamber for providing pressurization control of the vibration isolator. An expanded accumulator region for providing Increased pressure retention during maintenance and operation of the vibration isolator.
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公开(公告)号:DE09169365T1
公开(公告)日:2010-11-25
申请号:DE09169365
申请日:2003-09-24
Applicant: BELL HELICOPTER TEXTRON INC
Inventor: SMITH MICHAEL R , STAMPS FRANK B , LEE TAEOH , HEVERLY DAVID E JR , PASCAL ROBERT J
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