[특허]Folding wing tip device with rotatable lock

AIRBUS OPERATIONS LIMITED

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특허 상세정보

MyON담기

내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Folding wing tip device with rotatable lock

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-003/56 B64C-023/06
출원번호	US-0152765 (2016-05-12)
등록번호	US-10137978 (2018-11-27)
우선권정보	GB-1508421.3 (2015-05-15)
발명자 / 주소	Harding, Matt
출원인 / 주소	AIRBUS OPERATIONS LIMITED
대리인 / 주소	Nixon & Vanderhye P.C.
인용정보	피인용 횟수 : 0 인용 특허 : 6

초록
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The invention relates to a locking mechanism for a folding wing tip. The locking mechanism has a locked configuration, in which a first part is received in a second part such that the first part may not be withdrawn from the second part along the longitudinal axis of the locking mechanism, and an unlocked configuration, in which the first part is received in the second part such that the first part may be withdrawn from the second part along the longitudinal axis of the locking mechanism, wherein the locking mechanism is moved between the locked configur...

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청구항
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1. An aircraft, comprising: an aircraft wing, the aircraft wing comprising a fixed wing and a wing tip device at the tip thereof, wherein the wing tip device is configurable between:(i) a locked flight configuration for use during flight and (ii) a ground configuration for use during ground-based operations, in which ground configuration the wing tip device is moved away from the locked flight configuration such that the span of the aircraft wing is reduced, the aircraft wing further comprising a locking mechanism for locking the wing tip device in the locked flight configuration, the locking mechanism having a longitudinal axis and comprising a first part associated with one of the fixed wing and the wing tip device, and a second part associated with the other of the fixed wing and wing tip device,the locking mechanism having a locked configuration, in which the first part is received in the second part such that the first part is prevented from being withdrawn from the second part along the longitudinal axis of the locking mechanism, and an unlocked configuration, in which the first part is received in the second part such that the first part is free to be withdrawn from the second part along the longitudinal axis of the locking mechanism, wherein the locking mechanism is moved between the locked configuration and the unlocked configuration by rotation of at least one of the first part or second part around the longitudinal axis of the locking mechanism,wherein the first part is a male locking pin having a longitudinal axis shared with the locking mechanism, with one or more flanges extending in a direction perpendicular to the longitudinal axis of the locking pin,wherein the second part is a female receiving portion, with an opening aperture shaped to allow passage of the male locking pin in a longitudinal direction when the locking mechanism is in the unlocked configuration, andwherein the female receiving portion comprises at least one internal receiving chamber, the receiving chamber arranged to receive a flange of the male locking pin and prevent longitudinal movement of the male locking pin when the locking mechanism is in the locked configuration. 2. The aircraft as claimed in claim 1, wherein the flange of the male locking pin is configured to be moved into and out of the internal receiving chamber by rotational movement of at least one of the male locking pin and female receiving member around the longitudinal axis of the locking mechanism. 3. The aircraft as claimed in claim 1, wherein the internal receiving chamber decreases in dimensions in the direction of rotation of the male locking pin when moving into the locked configuration. 4. The aircraft as claimed in claim 1, wherein the male locking pin comprises two, three, four, or five flanges extending in a direction perpendicular to the longitudinal axis of the locking pin. 5. The aircraft as claimed in claim 4, further comprising a female receiving portion comprising a corresponding number of internal receiving chambers, each chamber arranged to receive individual flanges when the locking mechanism is in the locked configuration. 6. The aircraft as claimed in claim 5, wherein the female receiving portion comprises an opening aperture with two, three, four, or five sections shaped to correspond to, and allow passage of, the flanges extending from the male locking pin. 7. The aircraft as claimed in claim 1, wherein the female receiving portion comprises one or more internal receiving chambers with at least a partial thread. 8. The aircraft as claimed in claim 1, wherein the first part and/or second part includes a toothed surface suitable for being driven by a similarly toothed drive unit. 9. The aircraft as claimed in claim 1, wherein the first part comprises a male locking pin comprising one or more locking channels. 10. The aircraft as claimed in claim 9, wherein the second part comprises one or more internal pins arranged to engage with a corresponding locking channel. 11. The aircraft as claimed in claim 9, wherein the one or more locking channels extend initially in a longitudinal direction and then in a direction perpendicular to the longitudinal direction. 12. An aircraft wing, comprising: a fixed wing and a wing tip device at the tip thereof,wherein the wing tip device is configurable between: (i) a locked flight configuration for use during flight and (ii) a ground configuration for use during ground-based operations, in which ground configuration the wing tip device is moved away from the locked flight configuration such that the span of the aircraft wing is reduced, the aircraft wing further comprising a locking mechanism for locking the wing tip device in the locked flight configuration, the locking mechanism having a longitudinal axis and comprising a first part associated with one of the fixed wing and the wing tip device, and a second part associated with the other of the fixed wing and wing tip device, the locking mechanism having a locked configuration, in which the first part is received in the second part such that the first part is prevented from being withdrawn from the second part along the longitudinal axis of the locking mechanism, and an unlocked configuration, in which the first part is received in the second part such that the first part is free to be withdrawn from the second part along the longitudinal axis of the locking mechanism, wherein the locking mechanism is moved between the locked configuration and the unlocked configuration by rotation of at least one of the first part or second part around the longitudinal axis of the locking mechanism, wherein the first part is a male locking pin having a longitudinal axis shared with the locking mechanism, with one or more flanges extending in a direction perpendicular to the longitudinal axis of the locking pin,wherein the second part is a female receiving portion, with an opening aperture shaped to allow passage of the male locking pin in a longitudinal direction when the locking mechanism is in the unlocked configuration, andwherein the female receiving portion comprises at least one internal receiving chamber, the receiving chamber arranged to receive a flange of the male locking pin and prevent longitudinal movement of the male locking pin when the locking mechanism is in the locked configuration. 13. A method of locking a wing tip device on an aircraft as claimed in claim 1, the method comprising the steps of moving the wing tip device into the flight configuration, such that the first part is received within the second part of the locking mechanism, and rotating the first part and/or second part relative to the longitudinal axis of the locking mechanism such that corresponding elements of the first part and second part obstruct each other, thereby preventing relative movement of the first part and second part in the longitudinal direction. 14. A method of unlocking a wing tip device on an aircraft as claimed in claim 1, the method comprising the steps of rotating the first part and/or second part relative to the longitudinal axis of the locking mechanism such that corresponding elements of the first part and second part do not obstruct each other, thereby allowing relative movement of the first part and second part in the longitudinal direction.

이 특허에 인용된 특허 (6)

이 특허와 함께 이용한 콘텐츠

[특허] Powered hinge with automatic locking feature at opposite ends of permissible relative angular displacement of the hinge sections 함께 이용한 콘텐츠

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특허 상세정보

Folding wing tip device with rotatable lock

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이 특허에 인용된 특허 (6)

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Folding wing tip device with rotatable lock

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이 특허에 인용된 특허 (6)

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IPC 상세정보(version : 201201)

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