[특허]Wing pivot structures for tiltrotor aircraft

Bell Helicopter Textron Inc.

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Wing pivot structures for tiltrotor aircraft

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-003/56 B64C-029/00 B64C-011/28 B64C-005/10 B64C-005/02
출원번호	US-0271717 (2016-09-21)
등록번호	US-10220936 (2019-03-05)
발명자 / 주소	Kooiman, James Everett McCullough, John Richard Obert, Brian Dale
출원인 / 주소	Bell Helicopter Textron Inc.
대리인 / 주소	Lawrence Youst PLLC
인용정보	피인용 횟수 : 0 인용 특허 : 8

초록
▼

A wing pivot apparatus for rotating a wing between a flight orientation and a stowed orientation relative to a fuselage of a tiltrotor aircraft. The apparatus includes a guide ring that is fixably coupled to the fuselage. Forward and aft wing attach assemblies are coupled respectively to forward and aft spars of the wing and are moveably supported by the guide ring. Forward and aft wing support fittings are coupled respectively to the forward and aft spars of the wing and are selectively securable respectively to first and second fore-aft beams of the fuselage. A plurality of lock assemblies selectively secures the wing support fittings to the fore-aft beams of the fuselage when the wing is in the flight orientation. An actuator coupled to the fuselage is operable to reversibly rotate the wing between the flight orientation and the stowed orientation.

대표
청구항
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1. A wing pivot apparatus for rotating a wing between a flight orientation and a stowed orientation relative to a fuselage of a tiltrotor aircraft, the wing having forward and aft spars and the fuselage having first and second fore-aft beams, the apparatus comprising: a guide ring fixably coupled to the fuselage;forward wing attach assemblies coupled to the forward spar of the wing and moveably supported by the guide ring;aft wing attach assemblies coupled to the aft spar of the wing and moveably supported by the guide ring;first and second forward wing support fittings coupled to the forward spar of the wing and selectively securable respectively to the first and second fore-aft beams of the fuselage at locations forward of the guide ring;first and second aft wing support fittings coupled to the aft spar of the wing and selectively securable respectively to the first and second fore-aft beams of the fuselage at locations aft of the guide ring;a plurality of lock assemblies selectively securing the wing support fittings to the fore-aft beams of the fuselage when the wing is in the flight orientation; andan actuator coupled to the fuselage operable to reversibly rotate the wing between the flight orientation and the stowed orientation. 2. The apparatus as recited in claim 1 wherein the guide ring further comprises a rail. 3. The apparatus as recited in claim 2 wherein the wing attach assemblies each further comprise at least one roller bearing operable to engage the rail. 4. The apparatus as recited in claim 1 wherein the guide ring is securably coupled to the first and second fore-aft beams of the fuselage. 5. The apparatus as recited in claim 1 wherein the lock assemblies selectively secure the wing support fittings directly to the fore-aft beams of the fuselage. 6. The apparatus as recited in claim 1 further comprising a plurality of forward devises securably coupled to the fore-aft beams of the fuselage forward of the guide ring and plurality of aft devises securably coupled to the fore-aft beams of the fuselage aft of the guide ring and wherein, the wing support fittings each include at least one lug that is operable to sweep through the forward and aft clevises such that the lock assemblies are operable to selectively secure the forward wing support fittings to the fore-aft beams of the fuselage forward of the guide ring and the aft wing support fittings to the fore-aft beams of the fuselage aft of the guide ring when the wing is in the flight orientation and such that the actuator is operable to reversibly rotate the wing between the flight orientation and the stowed orientation when the lock assemblies are disengaged. 7. The apparatus as recited in claim 1 wherein the lock assemblies further comprise actuated pins. 8. The apparatus as recited in claim 1 wherein the actuator further comprises a rotary actuator. 9. The apparatus as recited in claim 8 wherein the rotary actuator further comprises a capstan actuator. 10. The apparatus as recited in claim 8 wherein the rotary actuator further comprises a gear driven actuator. 11. The apparatus as recited in claim 1 wherein the actuator further comprises a linear actuator. 12. A tiltrotor aircraft having a VTOL flight mode, a forward flight mode and a storage mode, the aircraft comprising: a fuselage;a wing rotatably mounted to the fuselage, the wing reversibly rotatable between a flight orientation, substantially perpendicular to the fuselage, in the flight modes, and a stowed orientation, substantially parallel to the fuselage, in the storage mode;a wing pivot apparatus disposed between the fuselage and the wing, the wing pivot apparatus including:a guide ring fixably coupled to the fuselage;forward wing attach assemblies coupled to the forward spar of the wing and moveably supported by the guide ring;aft wing attach assemblies coupled to the aft spar of the wing and moveably supported by the guide ring;first and second forward wing support fittings coupled to the forward spar of the wing and selectively securable respectively to the first and second fore-aft beams of the fuselage at locations forward of the guide ring;first and second aft wing support fittings coupled to the aft spar of the wing and selectively securable respectively to the first and second fore-aft beams of the fuselage at locations aft of the guide ring;a plurality of lock assemblies selectively securing the wing support fittings to the fore-aft beams of the fuselage when the wing is in the flight orientation; andan actuator coupled to the fuselage operable to reversibly rotate the wing between the flight orientation and the stowed orientation. 13. The aircraft as recited in claim 12 wherein the guide ring further comprises a rail. 14. The aircraft as recited in claim 13 wherein the wing attach assemblies each further comprise at least one roller bearing operable to engage the rail. 15. The aircraft as recited in claim 12 wherein the lock assemblies selectively secure the wing support fittings directly to the fore-aft beams of the fuselage. 16. The aircraft as recited in claim 12 further comprising a plurality of forward devises securably coupled to the fore-aft beams of the fuselage forward of the guide ring and plurality of aft devises securably coupled to the fore-aft beams of the fuselage aft of the guide ring and wherein, the wing support fittings each include at least one lug that is operable to sweep through the forward and aft devises such that the lock assemblies are operable to selectively secure the forward wing support fittings to the fore-aft beams of the fuselage forward of the guide ring and the aft wing support fittings to the fore-aft beams of the fuselage aft of the guide ring when the wing is in the flight orientation and such that the actuator is operable to reversibly rotate the wing between the flight orientation and the stowed orientation when the lock assemblies are disengaged. 17. The aircraft as recited in claim 12 wherein the lock assemblies further comprise actuated pins. 18. The aircraft as recited in claim 12 wherein the actuator is selected from the group consisting of a rotary actuator, a capstan actuator, a gear driven actuator and a linear actuator.

이 특허에 인용된 특허 (8)

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특허 상세정보

Wing pivot structures for tiltrotor aircraft

초록
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이 특허에 인용된 특허 (8)

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IPC 상세정보(version : 201201)

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특허 상세정보

Wing pivot structures for tiltrotor aircraft

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이 특허에 인용된 특허 (8)

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

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