[특허]Elastomeric bearing system motion limiter

Elastomeric bearing system motion limiter 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-005/30 B64C-027/33 B64C-027/35
출원번호	US-0139015 (2008-12-11)
등록번호	US-9884680 (2018-02-06)
국제출원번호	PCT/US2008/086365 (2008-12-11)
§371/§102 date	20110610 (20110610)
국제공개번호	WO2010/068209 (2010-06-17)
발명자 / 주소	Meyer, Leon M. Lay, Richard C. Schmaling, David N.
출원인 / 주소	Sikorsky Aircraft Corporation
대리인 / 주소	Carlson, Gaskey & Olds, P.C.
인용정보	피인용 횟수 : 0 인용 특허 : 56

초록

The invention relates to a backing plate used for an elastomeric bearing system, the backing plate comprising a plate which defines an at least partial annulus about an axis, a motion limiter and a redundant pivot which extend from the plate so as to respond to a retainer plate disbond.

대표청구항 ▼

1. A tail rotor blade assembly comprising: a flexbeam;a torque tube defined at least partially around said flexbeam;a retainer mounted to said flexbeam;an elastomeric bearing having an inner race and an outer race defined along an axis, said inner race mounted to said retainer, wherein said elastomeric bearing includes an outer damper portion adjacent said outer race, an inner snubber portion adjacent said inner race, and a rigid transition layer between said outer damper portion and said inner snubber portion;a backing plate mountable to said outer race, said torque tube between said backing plate and said outer race;wherein said backing plate includes a redundant pivot generally opposite a motion limiter;wherein said motion limiter is outboard of said redundant pivot; andwherein a surface of said rigid transition layer contacts a wall of said motion limiter in a retainer disbond condition. 2. The assembly as recited in claim 1, wherein the inner race is spherical in shape and the outer race is a planar plate shape. 3. The assembly as recited in claim 2, wherein the inner snubber portion includes concentric semi-spherical laminates to accommodate blade pitch and flap change. 4. The assembly as recited in claim 2, wherein the outer damper portion includes generally flat laminates to accommodate in-plane, lead-lag motions. 5. The assembly as recited in claim 1, wherein said plate defines an annulus radial opening located generally at zero degrees, said motion limiter located generally at 90 degrees and said redundant pivot located generally at 270 degrees. 6. The assembly as recited in claim 1, wherein said redundant pivot includes a cylinder with a semi-spherical end section. 7. A tail rotor blade assembly comprising: a backing plate comprising: a plate which defines an at least partial annulus about an axis;a motion limiter which extends from said plate generally parallel to said axis;a redundant pivot which extends from said plate generally parallel to said axis;wherein said plate defines an annulus radial opening located generally at zero degrees, said motion limiter located generally at 90 degrees, and said redundant pivot located generally at 270 degrees; andan elastomeric bearing comprising: an inner race and an outer race defined along an axis, wherein the inner race is spherical in shape and the outer race is a planar plate shape, and wherein said plate is attached to said outer race;an outer damper portion adjacent said outer race, wherein the outer damper portion includes generally flat laminates;an inner snubber portion adjacent said inner race, wherein the inner snubber portion includes semi-spherical laminates; anda rigid transition layer between said outer damper portion and said inner snubber portion, wherein a surface of said rigid transition layer contacts a wall of said motion limiter in a retainer disbond condition. 8. The backing plate as recited in claim 7, wherein said plate is semi-annular. 9. The backing plate as recited in claim 8, wherein said plate defines a “C” shape. 10. The backing plate as recited in claim 7, wherein said redundant pivot includes a cylinder with a semi-spherical end section. 11. The backing plate as recited in claim 7, wherein said plate defines a plurality of apertures about said axis. 12. The backing plate as recited in claim 11, further comprising a nut cage adjacent each of said multiple of apertures.

이 특허에 인용된 특허 (56)

Stableford William E. (Woodford GBX), Aircraft flying control systems.
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Byrnes Francis E. (White Plains NY) Hibyan Edward S. (Trumbull CT) Noehren William L. (Trumbull CT), Articulated helicopter rotor within an improved blade-to-hub connection.
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Niwa Yoshiyuki (Tachikawa JPX) Kashiwagi Masahiro (Tachikawa JPX) Yasue Masahiro (Funabashi JPX) Bandoh Shunichi (Kakamigahara JPX) Kakinuma Asao (Kakamigahara JPX) Wakatsuki Tadashi (Gifu JPX), Bearingless hub structure for rotary-wing aircrafts.
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Van Zanten David A. (Clawson MI) Lichtenberg Norman B. (Troy MI), Cable assembly for heater air control.
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Van Zanten David A. (Clawson MI) Nagle James J. (Birmingham MI), Cable assembly for heater air control.
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Pohling John G., Cable control system having stored energy fail-safe mechanism.
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Noehren William Lawrence (Huntington CT) Hibyan Edward Stanley (Trumbull CT), Composite helicopter spar and means to alleviate stress concentration.
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Neathery William D. (Fort Worth TX) Broekhuizen Willem (Arlington TX) Schellhase Ernst C. (Forth Worth TX), Constant velocity elastomeric bearing joint.
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Huling Don W. (Kent WA), Control cable fail safe device.
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Ferris ; Donald Leroy, Cross beam rotor.
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Kluting Bernd-Alfred,DEX ; Menten Klaus,DEX ; Osterkamp Heinrich,DEX, Detachable door hinge for a motor vehicle door.
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Desjardins Rene A. (Newton Square PA) McArdle Francis H. (Norristown PA), Ducted fan and pitch controls for tail rotor of rotary wing aircraft.
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Byrnes Francis E. (White Plains NY) Ferris Donald L. (Newtown CT) Hibyan Edward S. (Trumbull CT) Noehren William L. (Trumbull CT) Ogle Peter C. (Woodbridge CT), Elastomeric high torque, constant velocity joint.
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Beno Edward A. (Stratford CT) Noehren William L. (Trumbull CT), External wrap of composite flexbeam.
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Cholakon Rifka (Stow OH) Errera Tracy C. (Mogadore OH) Zeno Joseph R. (Cuyahoga Falls OH), Fast-make coupler for attaching a work implement to a prime mover.
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Byrnes Francis E. (White Plains NY) D\Anna Frank P. (Seymour CT), Flexbeam helicopter rotor with improved snubber-vibration damper between the torque tube and the flexible spar member.
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Jones Peter J., Fluid damper including flexible damping plate.
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Bowden James M. (Lakewood CA) Cook ; deceased Thomas A. (late of Garden Grove CA by Anita D. Cook ; heir ) Dailey Donald L. (Irvine CA), Hardover protection system for an aircraft.
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Head, Robert E.; Banerjee, Debashis, Helicopter tail rotor of the elastomerically-mounted composite flexbeam type.
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