[특허]Adjustable fittings for attaching support members to fluid conduits, including aircraft fuel conduits, and associated systems and methods

The Boeing Company

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Adjustable fittings for attaching support members to fluid conduits, including aircraft fuel conduits, and associated systems and methods

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64D-039/06 B64D-039/00
미국특허분류(USC)	244/135.R; 248/062; 248/068.1; 248/074.1; 285/061; 138/103; 244/118.1; 244/129.1
출원번호	UP-0440726 (2006-05-24)
등록번호	US-7581700 (2009-09-16)
발명자 / 주소	Carns, James A. Cutler, Theron L. Shelly, Mark A. Van Kampen, Benjamin P.
출원인 / 주소	The Boeing Company
대리인 / 주소	Perkins Coie LLP
인용정보	피인용 횟수 : 4 인용 특허 : 68

초록
▼

Adjustable fittings for attaching support members to fluid conduits, including aircraft fuel conduits, are disclosed herein. An aircraft system in accordance with one embodiment of the invention includes a fluid conduit carried by an aircraft and a housing fixedly attached to the fluid conduit. The housing can include a first attachment feature having one of a projection extending outwardly from the housing or an aperture extending at least partially through the housing. The system further includes a support member having an attachment portion positioned proximate to the attachment feature. The attachment portion includes a support member aperture positioned over at least a portion of the first attachment feature. An adjustable fitting couples the support member to the housing. The adjustable fitting can include a first side, a second side opposite the first side, and an engagement portion at the second side positioned within at least a portion of the support member aperture. The fitting can also include a second attachment feature mated with the first attachment feature. The second attachment feature includes the other one of the projection or the aperture. The second attachment feature has a center point eccentrically offset from a center point of the fitting.

대표
청구항
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We claim: 1. An aircraft system, comprising: a fluid conduit carried by an aircraft; a first housing fixedly attached to the fluid conduit, the first housing including a first attachment feature having a projection extending outwardly from the housing; a second housing fixedly attached to the fluid conduit and spaced apart from the first housing, the second housing including another first attachment feature; a support member having a first attachment portion positioned proximate to the first housing and a second attachment portion proximate to the second housing, the first attachment portion including a first support member aperture positioned over at least a portion of the first attachment feature and the second attachment portion including a second support member aperture positioned over at least a portion of the other first attachment feature; and a first adjustable fitting coupling the first attachment portion of the support member to the first housing, and a second adjustable fitting coupling the second attachment portion of the support member to the second housing, each adjustable fitting including a first side; a second side opposite the first side, the second side including an engagement portion positioned within at least a portion of the corresponding support member aperture; and a second attachment feature mated with the corresponding first attachment feature, the second attachment feature having an aperture, and wherein the second attachment feature has a center point eccentrically offset from a center point of the adjustable fitting. 2. The system of claim 1 wherein each adjustable fitting is rotatable with respect to the respective first attachment feature to secure the adjustable fitting in place against the support member and the respective housing. 3. The system of claim 2 wherein: the projection of each first attachment feature includes a generally arcuate end portion with a first center point defined at least in part by the end portion; and the aperture of each second attachment feature includes a second center point, and wherein the second center point is at least partially eccentrically offset from the first center point when each adjustable fitting is secured in place against the respective housing. 4. The system of claim 1 wherein: the first and second attachment portions of the support member have a first diameter; and each adjustable fitting includes a generally annular fitting having an outer diameter generally corresponding to the first diameter of the attachment portions. 5. The system of claim 1, further comprising: one or more first fasteners releasably coupling the adjustable fittings to the respective attachment portions of the support member; and a second fastener extending through the aperture and releasably coupling the adjustable fittings to the respective attachment features. 6. The system of claim 1 wherein the fining aperture extends completely through each adjustable fitting from the second side to the first side. 7. The system of claim 1 wherein the fitting aperture extends partially through each adjustable fitting from the second side to an intermediate depth between the first side and the second side. 8. The system of claim 1 wherein the first side of each adjustable fitting comprises a first annular portion having a first dimension and a second annular portion having a second dimension less than the first dimension. 9. The system of claim 1 wherein the first adjustable fitting has a first eccentric orientation relative to the first attachment feature, and the second adjustable fitting has a second eccentric orientation different than the first orientation relative to the other one of the first attachment features. 10. The system of claim 1 wherein the support member is configured to receive imposed surge loads and pressure loads from the fluid conduit. 11. The system of claim 1 wherein each adjustable fitting is configured to be installed with and uninstalled from the respective housing and the support member using common hand tools. 12. The system of claim 1 wherein the aircraft comprises: a fuselage portion; a wing portion; and a fuel tank carried by at least one of the fuselage portion and the wing portion, and wherein the fluid conduit is operably coupled to the fuel tank. 13. The system of claim 12, further comprising: a plurality of fluid conduits operably coupled to the fuel tank; a plurality of housings fixedly attached to corresponding fluid conduits, the individual housings including first attachment features; a plurality of support members positioned proximate to corresponding housings, the individual support members including attachment portions having support member apertures positioned over at least a portion of corresponding first attachment features, and wherein the individual support members are generally identical; and a plurality of adjustable fittings coupling the attachment portions of the support members to corresponding first attachment features on each housing, wherein two or more adjustable fittings have different eccentric orientations relative to the corresponding first attachment features.

이 특허에 인용된 특허 (68)

이 특허를 인용한 특허 피인용횟수: 4

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특허 상세정보

Adjustable fittings for attaching support members to fluid conduits, including aircraft fuel conduits, and associated systems and methods

초록
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대표
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이 특허에 인용된 특허 (68)

이 특허를 인용한 특허 피인용횟수: 4

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특허 상세정보

Adjustable fittings for attaching support members to fluid conduits, including aircraft fuel conduits, and associated systems and methods

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대표청구항 ▼

이 특허에 인용된 특허 (68)

이 특허를 인용한 특허 피인용횟수: 4

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

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