[특허]Rotor system with pitch flap coupling

Sikorsky Aircraft Corporation

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특허 상세정보

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Rotor system with pitch flap coupling

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-005/00
미국특허분류(USC)	416/001; 416/024
출원번호	UP-0560008 (2006-11-15)
등록번호	US-7841829 (2011-01-31)
발명자 / 주소	Schmaling, David N. Cabrera, Pedro L.
출원인 / 주소	Sikorsky Aircraft Corporation
대리인 / 주소	Carlson Gaskey & Olds PC
인용정보	피인용 횟수 : 5 인용 특허 : 5

초록
▼

An articulated rotor system with a servo-flap rotor control system locates the focal point of a blade retention spherical elastomeric bearing inboard of a joint in the servo-flap pitch control tube which separates the flap hinge and supports the servo-flap pitch control tube on a single pivot bearing within a blade retention spindle. Rotor blade flapping produces relative movements between the servo-flap pitch control tube and the blade retention spindle which is converted through a servo-flap drive linkage into servo-flap pitch motions to provide flap/p...

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청구항
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What is claimed is: 1. A rotor blade assembly comprising: a rotor blade bearing housing; a blade pitch control coupling mounted within said rotor blade bearing housing for rotation about a blade hub axis; an elastomeric bearing mounted to said rotor blade bearing housing; a blade spindle mounted to said elastomeric bearing to define a blade spindle flapping focal point; a spherical bearing mounted within said blade spindle; and a servo-flap pitch control tube mounted within said spherical bearing for rotation about a servo-flap pitch control tube axis, said servo-flap pitch control tube mounted to said blade pitch control coupling at a joint which defines a servo-flap pitch control tube pivot point, said servo-flap pitch control tube pivot point offset from said blade spindle flapping focal point, said servo-flap pitch control tube drives a servo-flap assembly relative a rotor blade. 2. The assembly as recited in claim 1, wherein said servo-flap pitch control tube pivot point is outboard of said blade spindle flapping focal point. 3. The assembly as recited in claim 1, wherein said servo-flap pitch control tube rotates about said servo-flap pitch control tube axis to drive a servo-flap drive linkage mounted to a rotor blade cuff. 4. The assembly as recited in claim 3, wherein said servo-flap drive linkage drives a push-pull link. 5. The assembly as recited in claim 4, wherein said push-pull link actuates a servo-flap. 6. The assembly as recited in claim 4, wherein said push-pull link actuates a servo-flap linkage which pitches said servo-flap relative said rotor blade. 7. The assembly as recited in claim 1, wherein said rotor blade bearing housing is foldable about a fold axis. 8. The assembly as recited in claim 1, further comprising a rotor blade cuff mounted to said blade spindle. 9. The assembly as recited in claim 8, further comprising a main rotor blade mounted to said rotor blade cuff. 10. The assembly as recited in claim 1, wherein said elastomeric bearing is an elastomeric spherical bearing. 11. A servo-flap rotor blade assembly comprising: a rotor blade bearing housing; an elastomeric bearing mounted to said rotor blade bearing housing; a blade spindle mounted to said elastomeric bearing to define a blade spindle flapping focal point; a blade cuff mounted to said blade spindle; a rotor blade mountable to said blade cuff; a spherical bearing mounted within said blade spindle; a servo-flap pitch control tube mounted within said spherical bearing for rotation about a servo-flap pitch control tube axis, said servo-flap pitch control tube mounted at a joint which defines a servo-flap pitch control tube pivot point, said servo-flap pitch control tube pivot point offset from said blade spindle flapping focal point; and a servo-flap pitchable relative to said rotor blade in response to rotation of said servo-flap pitch control tube. 12. The assembly as recited in claim 11, wherein said servo-flap pitch control tube rotates about said servo-flap pitch control tube axis to drive a servo-flap drive linkage mounted to said rotor blade cuff. 13. The assembly as recited in claim 12, wherein said servo-flap drive linkage includes a slotted interface between said servo-flap pitch control tube and said servo-flap drive linkage. 14. The assembly as recited in claim 13, wherein said servo-flap drive linkage drives a push-pull link. 15. A method of pitch/flap coupling for a rotor blade assembly of a rotary-wing aircraft comprising the steps of: (A) flapping a rotor blade spindle about a blade spindle flapping focal point; (B) flapping a servo-flap pitch control tube about a servo-flap pitch control tube pivot point offset from the blade spindle flapping focal point; and (C) tilting the servo-flap pitch control tube relative the blade spindle in response to said step (B) to pitch a servo-flap relative a rotor blade. 16. A method as recited in claim 15, wherein said step (C) further comprises: (a) tilting the servo-flap pitch control tube in response to flap-up motion of the rotor blade spindle to pitch down the servo-flap to obtain a pitch/flap (Delta-3) coupling. 17. A method as recited in claim 15, further comprising the step of: (D) folding a rotor blade bearing assembly which supports the rotor blade spindle inboard of an elastomeric bearing mounted within the rotor blade bearing assembly relative a rotor hub about a fold axis. 18. A rotor blade assembly comprising: a rotor blade; a servo-flap movable relative to said rotor blade; a blade spindle mounted to said rotor blade, said blade spindle defines a blade spindle flapping focal point; and a servo-flap pitch control tube mounted at least partially through said blade spindle, said servo-flap pitch control tube defines a servo-flap pitch control tube pivot point offset from said blade spindle flapping focal point, said servo-flap pitch control tube free to tilt about said servo-flap pitch control tube pivot point relative to said blade spindle as said rotor blade flaps about said blade spindle flapping focal point such that said servo-flap pitch control tube pitches said servo-flap relative to said rotor blade to generate a stabilizing pitch-flap coupling. 19. The assembly as recited in claim 18, further comprising a spherical bearing mounted within said blade spindle to define said servo-flap pitch control tube pivot point. 20. The assembly as recited in claim 19, wherein said spherical pivot bearing is axially adjustable. 21. The assembly as recited in claim 18, further comprising a rotor blade cuff mounted to said blade spindle to support said rotor blade. 22. The assembly as recited in claim 21, wherein said servo-flap pitch control tube is rotatable about a servo-flap pitch control tube axis to drive a servo-flap drive linkage mounted to said rotor blade cuff. 23. The assembly as recited in claim 21, wherein tilt of said servo-flap pitch control tube tilts about said servo-flap pitch control tube pivot point relative to said blade spindle to drive a servo-flap drive linkage mounted to said rotor blade cuff. 24. The assembly as recited in claim 23, wherein said servo-flap drive linkage drives a push-pull link to pitch said servo-flap such that flapping up produces a tension in said push/pull link to pitch said servo-flap up to provide a pitch-down movement in said rotor blade and flapping down produces a compression in said push/pull link to pitch said servo-flap down to provide a pitch-up movement in said rotor blade.

인용문헌 (5)

이 특허를 인용한 특허 (5)

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특허 상세정보

Rotor system with pitch flap coupling

초록
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청구항
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인용문헌 (5)

이 특허를 인용한 특허 (5)

IPC 상위 출원인

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IPC 상세정보(version : 201201)

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특허 상세정보

Rotor system with pitch flap coupling

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인용문헌 (5)

이 특허를 인용한 특허 (5)

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

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