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公开(公告)号：CA2863707A1
公开(公告)日：2015-06-20
申请号：CA2863707
申请日：2014-09-16
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： STAMPS FRANK B , SOTTIAUX DANIEL P
Abstract: A damper for a rotor hub for a rotorcraft can include a housing, a piston resiliently coupled to the housing with a first elastomeric member and a second elastomeric member, a plurality of conical members, a fluid, and an orifice.
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公开(公告)号：CA2789472C
公开(公告)日：2015-03-24
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
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.
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公开(公告)号：CA2790435C
公开(公告)日：2014-11-18
申请号：CA2790435
申请日：2012-09-06
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： STAMPS FRANK B , POPELKA DAVID A , COVINGTON CHARLES ERIC , PARHAM THOMAS C
Abstract: A system and method for adjusting a rotor blade upon detection of a harmful force exerted on an aircraft wing includes a sensor attached to the wing and a subsystem operably associated with the sensor. The method includes sensing the force exerted on the wing with the sensor and determining whether the sensed force is potentially harmful to the structural integrity of the wing. The method further includes counteracting the harmful force by adjusting the rotor blade movement.
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公开(公告)号：CA2805894A1
公开(公告)日：2013-09-16
申请号：CA2805894
申请日：2013-02-12
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： BOSWORTH JEFFREY , YUCE MITHAT , STAMPS FRANK B , SMITH MICHAEL R
Abstract: A dual frequency damper includes a liquid inertia vibration eliminator (LIVE) portion and a fluid damper portion. LIVE portion and fluid damper portion operate in series and function so that dual frequency damper is optimized in both stiffness and damping at multiple frequencies. LIVE portion acts as a frequency dependent switch to selectively cause low frequency oscillatory forces to be treated primarily by the high spring rate and high damping rate characteristics of the fluid damper portion, and also to select high frequency oscillatory forces to be primarily treated by the low spring rate and low damping rate characteristics of the LIVE unit portion.
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公开(公告)号：CA2794805A1
公开(公告)日：2013-06-14
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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Patent Agency Ranking
公开(公告)号：CA2794228A1
公开(公告)日：2013-06-13
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
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. In at least one embodiment, a torque splitter connects the yokes and allows for limited rotation of the yokes relative to each other about the mast axis. Each yoke is configured for the attachment of rotor blades extending generally radially relative to the mast axis.
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公开(公告)号：CA2790846A1
公开(公告)日：2013-04-03
申请号：CA2790846
申请日：2012-09-25
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： SOTTIAUX DANIEL P , STAMPS FRANK B
Abstract: The bearing assembly includes one or more elastomeric members loaded in a precompression by a shim that includes a shape memory alloy. The shape memory alloy is configured to generate the precompression in the elastomeric members upon a temperature change.
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公开(公告)号：DE06844162T8
公开(公告)日：2011-11-17
申请号：DE06844162
申请日：2006-08-17
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： STAMPS FRANK B , RAUBER RICHARD E , POPELKA DAVID A , TISDALE PATRICK R , CAMPBELL THOMAS C , BRASWELL JUN
IPC: B64C27/12
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公开(公告)号：DE08713528T1
公开(公告)日：2011-04-07
申请号：DE08713528
申请日：2008-01-04
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： STAMPS FRANK B , TISDALE PATRICK R
IPC: B64C27/00
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公开(公告)号：CA2369837C
公开(公告)日：2009-12-08
申请号：CA2369837
申请日：2002-01-30
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： STAMPS FRANK B , BRASWELL JAMES L JR , POPELKA DAVID A , COVINGTON CECIL E , BENNETT RICHARD L , COVINGTON CHARLES E , SETTLE THOMAS B JR
Abstract: An aircraft with a tilt rotor assembly comprising a craft body, a plurality of rotor blades which are subject to three modes of flight operation, a tilting mast coupling the plurality of rotor blades to the craft body and for selectively moving the plurality of rotor blades between the three modes of flight operation, a hub coupling the plurality of rotor blades to the tilting mast in a manner which transfers torque and thrust whi le allowing tilting of a rotor thrust vector, a main swashplate for tilting in response to operator input to control the direction of the rotor thrust vector, a plurality of pitch horns , each mechanically coupled to a particular one of the plurality of rotor blades and to the main swashplate, for communicating swashplate input to each of the plurality of rotor blades, a plurality of links coupling the main swashplate to the plurality of pitch horns, wherein each o f the plurality of pitch horns is mechanically coupled to a particular one of the plurality of rotor blades by one of the plurality of links in a particular position which yields a delta- 3 value which is not optimum, and a feedback swashplate and cooperating feedback links for receiving disk tilting input from the plurality of rotor blades during flight, and for supplying a mechanical input tothe main swashplate to compensate for the less than optimum delta-3 coupling between the plurality of pitch horns and the plurality of links. The three modes of flight include: (1) an airplane mode of flight with the plurality of rotor blades i n a rotor disk position which is substantially transverse to the craft body; (2) a helicopt er mode of flight with the plurality of rotor blades in a rotor disk position substantially parallel to the craft body with direction of flight being controlled by a rotor thrust vector; and (3) a transition mode of flight with the plurality of rotor blades moving between the rotor disk positions associated with the airplane mode of flight and the helicopter mode of fligh t.
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