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公开(公告)号：CA2801296C
公开(公告)日：2014-12-30
申请号：CA2801296
申请日：2013-01-09
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： SOTTIAUX DANIEL P , STAMPS FRANK B , TISDALE PATRICK R , THOMPSON TERRY K , VO LOAN THANH
Abstract: According to one embodiment, a method comprises calendering an elastomeric material into an elastomeric layer having a thickness that is more uniform than the elastomeric material prior to the calendaring. After calendaring, the elastomeric layer is vulcanized to a composite shim comprising at least one reinforcement layer and at least one layer of adhesive.
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公开(公告)号：CA2794805C
公开(公告)日：2014-10-14
申请号：CA2794805
申请日：2012-11-06
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： STAMPS FRANK B
Abstract: The present application includes a blade-pitch control system for controlling a pitch angle of each of a plurality of blades on an aircraft rotor. A feedback lever associated with each blade is pivotally mounted to the rotating portion of a swashplate assembly. A pitch link connects an output arm of a lever to a pitch horn of a corresponding blade, and a feedback link connects the input arm of the lever to a yoke. Flapping motion of the yoke causes motion of the feedback link, and this motion causes corresponding rotation of the lever. Rotation of the lever causes motion of the pitch link, which changes the pitch angle of the attached blade. This provides for selected pitch-flap coupling between flapping motion of the yoke and pitch motion of the blades.
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公开(公告)号：CA2844214A1
公开(公告)日：2014-09-15
申请号：CA2844214
申请日：2014-02-26
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： MODRZEJEWSKI BRIAN , JUDD BRYAN , SOTTIAUX DAN , STAMPS FRANK B , SCHOFIELD EMILY
Abstract: A damper includes a housing that forms a fluidly sealed cavity for receiving a fluid therein. The fluid is configured to change fluid properties as electrical energy is induced. An electrical subsystem provides electrical energy to the fluid, which is monitored with a control subsystem. The method includes inducing the fluid with electrical energy to change the dampening effects of the damper in real time.
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公开(公告)号：CA2749119C
公开(公告)日：2014-05-27
申请号：CA2749119
申请日：2009-01-19
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： STAMPS FRANK B , RAUBER RICHARD E
IPC: B64C27/605 , B64C27/32
Abstract: A blade-pitch control system has a swashplate configured for continuous rotation with an associated rotor and mast, and at least one link connects the swashplate to each blade of the rotor. The swashplate provides for collective control of the pitch angle of the blades through selective rotation of the swashplate about a swashplate axis while the swashplate is rotating with the rotor and mast. The system can be configured to provide for cyclic control of the pitch angle of the blades through planar translation of the swashplate or through tilting of the swashplate about axes generally perpendicular to the swashplate axis.
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公开(公告)号：CA2832784A1
公开(公告)日：2014-05-09
申请号：CA2832784
申请日：2013-11-05
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： SUTTON DREW A , FOSKEY CHRISTOPHER , SMITH DUDLEY , STAMPS FRANK B
Abstract: According to one embodiment, a constant velocity (CV) joint includes a first yoke, a second yoke, and a control mechanism. The first yoke is configured to be rotatably coupled to an input device about a first axis and configured to receive the input device through a first opening. The second yoke is rotatably coupled to the first yoke about a second axis and rotatably coupled to an output device about a third axis. The control mechanism is adapted to constrain the first yoke and the second yoke so as to achieve a substantially CV characteristic between the input device and the output device.
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Patent Agency Ranking
公开(公告)号：CA2685025C
公开(公告)日：2014-03-11
申请号：CA2685025
申请日：2007-04-24
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： RAUBER RICHARD E , POPELKA DAVID A , STAMPS FRANK B
Abstract: A vibration attenuator for an aircraft has at least one weight mounted in a rotating system of a rotor hub of the aircraft, each weight being rotatable about an axis of rotation of the hub relative to the hub and to each other weight. Drive means are provided for rotating each weight about the axis of rotation at a selected speed for creating oscillatory shear forces that oppose and attenuate rotor-induced vibrations having a selected frequency.
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公开(公告)号：CA2711149C
公开(公告)日：2013-10-29
申请号：CA2711149
申请日：2008-01-04
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： STAMPS FRANK B , TISDALE PATRICK R
Abstract: A constant-velocity drive system for an aircraft rotor has a gimbal mechanism and a differential torque-combining mechanism. The gimbal mechanism has gimbals driven in rotation by a rotor mast about a mast axis, the gimbals providing for gimballing relative to the mast about gimbal axes generally perpendicular to the mast axis. The differential torque-combining mechanism is connected to the gimbal mechanism and configured to be driven in rotation about the mast axis by the gimbal mechanism. The differential mechanism is capable of gimballing relative to the mast about the gimbal axes, the differential torque-combining mechanism having an output component attached to a yoke of the rotor for driving the yoke in rotation with the differential torque-combining mechanism.
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公开(公告)号：CA2808987A1
公开(公告)日：2013-10-18
申请号：CA2808987
申请日：2013-03-05
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： SEIFERT MICHAEL , STAMPS FRANK B , SMITH MICHAEL R , HEVERLY DAVID E
Abstract: A system and method to adjustably create a reacting force in response to a vibrating force of a vibrating structure. The system includes an adjustable vibration absorber that creates a range of reacting forces. The method includes continuously monitoring the reacting force and the vibrating force with a sensor system operably associated with a control unit having an algorithm to determine if adjustment of the vibration absorber is required. If required, the control unit commands a driver to selectively adjust the vibration absorber such that the reacting force equals the vibrating force.
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公开(公告)号：CA2799697A1
公开(公告)日：2013-06-26
申请号：CA2799697
申请日：2012-12-19
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： RAUBER RICHARD , STAMPS FRANK B , POPELKA DAVID , TISDALE PATRICK , DONOVAN TOM
Abstract: A rotary system and method to control feathering and centrifugal forces of a rotor blade during flight. The rotary system having a hub assembly, which includes a hollow yoke arm to receive a spindle section of the rotor blade. A tension-torsion strap extends through the hollow yoke arm and couples the rotor blade and the hub assembly. The method includes allowing the spindle section of the rotor blade to pivot within the hollow yoke arm and controlling rotational and centrifugal movement of the rotor blade with the tension-torsion strap.
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公开(公告)号：CA2790085A1
公开(公告)日：2013-04-03
申请号：CA2790085
申请日：2012-09-13
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： SCOTTIAUX DANIEL P , STAMPS FRANK B
IPC: F16C27/06 , B64C27/32 , B64C27/35 , B64C27/37 , B64C27/48 , B64C27/51 , F16C7/04 , F16C17/04 , F16C27/08
Abstract: The centrifugal force bearing includes a plurality of tapered metal shims such that the thicker end of each tapered metal shim near the inner portion of bearing. The bearing can include a plurality of tapered elastomeric members that are consequently tapered so that the inner portions are narrower than the outer portions. The tapered metal shims can increase the axial stiffness in the direction of the centrifugal force, thereby reducing the axial deflection under loading, as compared to non-tapered shims. Further, reducing axial deflection reduces clearance issues that may arise when the rotor blade is allowed to axial deflect significant distances. As such, the tapered metal shims can increase the capacity of the bearing. Tapering the metal shims can decrease the compression induced shear strain near the outer portions of the elastomeric member, where loads are typically higher.
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