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公开(公告)号：US20190039727A1
公开(公告)日：2019-02-07
申请号：US15666449
申请日：2017-08-01
Applicant: Bell Helicopter Textron Inc.
Inventor： Mark Adam Wiinikka , Nathan Patrick Green , John R. McCullough
Abstract: A centrifugal force (CF) bearing for a rotorcraft rotor assembly includes an inner-member, an outer-member, and an elastic member interposed between the inner- and outer-members. The outer-member includes an upper flange extension and a lower flange extension for location to and engagement with a grip. The upper flange extension is disposed over an upper surface portion of the elastic member, and the lower flange extension is disposed under a lower surface portion of the elastic member. The CF bearing is configured for attachment to a grip of the rotor assembly. The outer-member is configured to communicate mechanical loads (e.g., centrifugal force, lateral shear, vertical shear) from the grip to the yoke during operation of the rotor assembly.
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公开(公告)号：US10239609B2
公开(公告)日：2019-03-26
申请号：US15656929
申请日：2017-07-21
Applicant: Bell Helicopter Textron Inc.
Inventor： Hunter Jay Davis , Mark Adam Wiinikka
IPC: B64C27/54 , B64C27/605 , F16C7/06
Abstract: A system and method for measuring, or otherwise determining pitch length adjustments to a pitch link coupled to a rotor blade in a rotorcraft includes vertical track adjustment indicators machined onto an exterior of the tube of the pitch link and a vertical reference indicator machined onto an exterior of the upper or the lower rod of the pitch link. A metric of a pitch length adjustment can be determined by tracking or counting how many track adjustment indicators pass the reference indicator while the tube of the pitch link is being turned in either direction for increasing or decreasing the pitch length. The track adjustment indicators can be relied upon to track one or a series of adjustments for tracking a rotor blade installed in a rotor assembly.
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公开(公告)号：US20200001991A1
公开(公告)日：2020-01-02
申请号：US16022375
申请日：2018-06-28
Applicant: Bell Helicopter Textron Inc.
Inventor： Mark Adam Wiinikka , Matthew Curtis Ledbetter
IPC: B64C27/32
Abstract: A rotorcraft having a rotor system including a yoke, a plurality of grip assemblies, each of which is hingedly attach a rotor blade to the yoke, a plurality of flap stops, each flap stop attached to a respective grip assembly, a channel bounded by an upper and lower retaining surfaces, and a droop ring slideably disposed in the channel of the droop limiting system. The droop ring has a body with an inner surface, an outer surface, and a first end surface between the inner surface and the outer surface. The droop ring further has a first wear element removably disposed at the first end surface and extending above the first end surface and spaces the first end surface apart from the channel. Each flap stop is arranged to contact the outer surface of the droop ring and limit a downward droop of the respective rotor blade.
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公开(公告)号：US11643197B2
公开(公告)日：2023-05-09
申请号：US16210489
申请日：2018-12-05
Applicant: Bell Helicopter Textron Inc.
Inventor： Scott David Poster , Charles Hubert Speller , Mark Adam Wiinikka
IPC: B64C27/605 , F01D5/02
CPC classification number: B64C27/605 , F01D5/02
Abstract: A swashplate assembly includes: a mounting sleeve configured for coupling to and around an upper portion of a gearbox, wherein the mounting sleeve extends downwards from the upper portion of the gearbox; a tilt sleeve coupled to the mounting sleeve, wherein the tilt sleeve has a curved exterior surface; a non-rotating swashplate ring positioned around the tilt sleeve, wherein the non-rotating swashplate ring has a first set of pitch control connectors and an anti-rotation connector; a rotating swashplate ring rotatable about the non-rotating swashplate ring, wherein the rotating swashplate ring has a second set of pitch control connectors and a drive link connector; and a first bearing system mounted between the non-rotating swashplate ring and the rotating swashplate ring.
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Patent Agency Ranking
公开(公告)号：US20180339773A1
公开(公告)日：2018-11-29
申请号：US15606275
申请日：2017-05-26
Applicant: Bell Helicopter Textron Inc.
Inventor： John Richard McCullough , Paul K. Oldroyd , Mark Adam Wiinikka , Jouyoung Jason Choi
Abstract: A rotor assembly for an aircraft is operable to generate a variable thrust vector. The rotor assembly includes a mast that is rotatable about a mast axis. A ball joint is positioned about and non rotatable with the mast. A tilt control assembly is positioned on and has a tilting degree of freedom relative to the ball joint. The tilt control assembly is non rotatable with the mast. A rotor hub is rotatably coupled to the tilt control assembly. The rotor hub is rotatable with the mast in a rotational plane and tiltable with the tilt control assembly. The rotor hub includes a plurality of grips each coupled to a rotor blade. Actuation of the tilt control assembly changes the rotational plane of the rotor hub relative to the mast axis, thereby generating the variable thrust vector.
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公开(公告)号：US20200180757A1
公开(公告)日：2020-06-11
申请号：US16210489
申请日：2018-12-05
Applicant: Bell Helicopter Textron Inc.
Inventor： Scott David Poster , Charles Hubert Speller, JR. , Mark Adam Wiinikka
IPC: B64C27/605 , F01D5/02
Abstract: A swashplate assembly includes: a mounting sleeve configured for coupling to and around an upper portion of a gearbox, wherein the mounting sleeve extends downwards from the upper portion of the gearbox; a tilt sleeve coupled to the mounting sleeve, wherein the tilt sleeve has a curved exterior surface; a non-rotating swashplate ring positioned around the tilt sleeve, wherein the non-rotating swashplate ring has a first set of pitch control connectors and an anti-rotation connector; a rotating swashplate ring rotatable about the non-rotating swashplate ring, wherein the rotating swashplate ring has a second set of pitch control connectors and a drive link connector; and a first bearing system mounted between the non-rotating swashplate ring and the rotating swashplate ring.
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公开(公告)号：US20190382107A1
公开(公告)日：2019-12-19
申请号：US16012094
申请日：2018-06-19
Applicant: Bell Helicopter Textron Inc.
Inventor： Glenn Alan SHIMEK , Mark Adam Wiinikka , Michael Dean Dearman
IPC: B64C27/605 , B64F5/40
Abstract: An example rotating swashplate ring to rotor mast connection includes a polygon-shaped drive tube secured to the rotor mast and a gimbal joint connected between the rotating swashplate ring and the polygon-shaped drive tube, wherein the gimbal joint rotates with the rotor mast and can translate axially along the polygon-shaped drive tube.
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公开(公告)号：US20190031328A1
公开(公告)日：2019-01-31
申请号：US15659272
申请日：2017-07-25
Applicant: Bell Helicopter Textron Inc.
Inventor： John McCullough , Mark Adam Wiinikka , Matthew Curtis Ledbetter
Abstract: A centrifugal force (CF) bearing for a rotorcraft rotor assembly includes an inner-member, an outer-member, and an elastic member interposed between the inner- and outer-members. The inner-member includes a boss configured for location to and engagement with a yoke. The boss includes a tapered profile (e.g., conic) portion. A tapered recess region of the yoke includes a profile that is substantially matched to receive and contact the tapered profile of the boss. The CF bearing is configured for attachment to a grip of the rotor assembly. The boss is configured to communicate mechanical loads (e.g., centrifugal force, lateral shear, vertical shear) from the grip to the yoke during operation of the rotor assembly.
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公开(公告)号：US20180327089A1
公开(公告)日：2018-11-15
申请号：US15590736
申请日：2017-05-09
Applicant: Bell Helicopter Textron Inc.
Inventor： Glenn Alan Shimek , Nathan Patrick Green , Robert Alan Self , Mark Adam Wiinikka
Abstract: A system and method for attaching a damper to a tail rotor blade includes a cuff that is integral with the rotor blade. The cuff has upper and lower lugs formed by extending a skin over a blade core of the rotor blade. The skin extends past the blade core to the root end of the rotor blade. The rod end of the damper is inserted into an opening between the lugs. The rod end of the damper is coupled to the blade with a bolt through aligned holes in the lugs. The cuff also couples the rotor blade to the grip inside the cuff. The cuff includes a same material as that forming the skin. Sacrificial buffer pads are applied to interior faces of the lugs. The buffer pads permit a distance between the lugs to be machined within a tolerance without removing skin from the cuff.
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