Bladders, storage containers, and aircraft fuel systems
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B65D-088/18
B64D-037/06
B65D-088/24
출원번호
US-0370129
(2012-02-09)
등록번호
US-9352845
(2016-05-31)
발명자
/ 주소
Albert, Jeremie J.
Andrews, Martin G.
Firko, Jason L.
출원인 / 주소
THE BOEING COMPANY
대리인 / 주소
Parsons Behle & Latimer
인용정보
피인용 횟수 :
1인용 특허 :
10
초록▼
A storage container, which may be a fuel bladder, includes a container wall configured to retain a fluid within the container and an opening through the container wall. The container includes a rim of the container wall surrounding the opening and a non-planar flex region of the container wall adjac
A storage container, which may be a fuel bladder, includes a container wall configured to retain a fluid within the container and an opening through the container wall. The container includes a rim of the container wall surrounding the opening and a non-planar flex region of the container wall adjacent to the rim. The flex region includes at least one resilient crease in the container wall and the rim is between the flex region and the opening. A portion of the container wall surrounds the flex region. The flex region exhibits the property of allowing movement of the rim with respect to the portion of the container wall.
대표청구항▼
1. A fuel bladder comprising: two sections co-planar with one another; anda non-planar flex region separating the two co-planar sections and exhibiting the property of allowing movement of the bladder relative to an external bladder attachment, the two co-planar sections and the non-planar flex regi
1. A fuel bladder comprising: two sections co-planar with one another; anda non-planar flex region separating the two co-planar sections and exhibiting the property of allowing movement of the bladder relative to an external bladder attachment, the two co-planar sections and the non-planar flex region being directly connected to one another or integrally formed, the two co-planar sections and the non-planar flex region containing the same material, and the non-planar flex region extending radially between the two co-planar sections of the fuel bladder,wherein the fuel bladder is comprised by an aircraft fuel system. 2. The fuel bladder of claim 1, wherein the two co-planar sections are non-contiguous. 3. The fuel bladder of claim 1, wherein one of the two co-planar sections is concentric to the other. 4. The fuel bladder of claim 1, wherein the flex region includes a plurality of concentric corrugations. 5. A fuel bladder comprising: a bladder wall configured to retain a fluid within the bladder;an opening through the bladder wall;a rim of the bladder wall surrounding the opening, the rim being configured to attach an interconnect to the bladder wall;a non-planar flex region of the bladder wall adjacent the rim, the flex region including at least one resilient crease in the bladder wall and the rim being between the flex region and the opening; anda portion of the bladder wall surrounding the flex region and being substantially co-planar with the opening when no force is applied to the rim, the flex region exhibiting the property of allowing movement of the rim with respect to the portion of the bladder wall and the flex region extending radially from the rim to the portion of the bladder wall. 6. The bladder of claim 5 wherein the bladder wall is configured to retain a liquid aircraft fuel within the bladder. 7. The bladder of claim 5 wherein the bladder is comprised by an aircraft fuel system that further comprises an aircraft fuel housing and a rigid interconnect extending from the housing to the rim. 8. The bladder of claim 7 wherein the rigid interconnect is axially aligned with the opening, the interconnect extending orthogonally from the opening. 9. The bladder of claim 5 wherein the rim is planar, the rim being substantially co-planar with the portion of the bladder wall when no force is applied to the rim. 10. The bladder of claim 5 further comprising a ring-shaped interconnect mount attached to the rim, the mount being configured to attach a housing an interconnect to the bladder wall. 11. The bladder of claim 10 wherein the rim, the mount, and the crease are circular. 12. The bladder of claim 5 wherein the flex region exhibits a surface length along a radius from a center of the opening that is greater than its aerial length along the radius. 13. The bladder of claim 5 wherein the at least one resilient crease comprises a plurality of resilient, concentric corrugations. 14. The bladder of claim 5 wherein the at least one resilient crease continuously surrounds the rim. 15. A fuel bladder comprising: a bladder wall configured to retain a fluid within the bladder;an opening through the bladder wall;a rim of the bladder wall surrounding the opening;a non-planar flex region of the bladder wall adjacent the rim, the flex region including at least one resilient crease in the bladder wall and the rim being between the flex region and the opening; anda portion of the bladder wall surrounding the flex region, the flex region exhibiting the property of allowing movement of the rim with respect to the portion of the bladder wall, the bladder being comprised by an aircraft fuel system that further includes an aircraft fuel housing and a rigid interconnect extending from the housing to the rim, the interconnect being selected from among a fuel line, a fill port, an access port, a vent, and a cell leveling port. 16. A storage container comprising: a container wall configured to retain a fluid within the container;an orifice through a portion of the container wall;a plurality of resilient, concentric corrugations in the portion of the container wall adjacent the orifice, individual corrugations continuously surrounding the orifice; anda planar section of the portion of the container wall surrounding the plurality of corrugations and being substantially co-planar with the orifice, the plurality of corrugations exhibiting the property of allowing translational movement of the orifice with respect to the planar section of the portion of the container wall and the plurality of corrugations extending radially from adjacent the orifice to the planar section of the portion of the container wall. 17. The container of claim 16 wherein the container is a bladder and the bladder is configured to retain a liquid aircraft fuel within the bladder. 18. The container of claim 16 wherein the container is comprised by an aircraft fuel system. 19. The container of claim 16 wherein the corrugations are circular. 20. The container of claim 16 wherein the corrugations exhibit a surface length along a radius from a center of the orifice that is greater than their aerial length along the radius. 21. An aircraft fuel system comprising an aircraft fuel housing, a fuel bladder inside the housing, and a rigid interconnect extending from the housing to the bladder, the bladder including: a bladder wall configured to retain fuel within the bladder, the housing having an interior profile and the bladder wall being configured to correspond with the interior profile;an opening through the bladder wall;a rim of the bladder wall surrounding the opening;an interconnect mount attached to the rim, the mount in turn attaching the interconnect to the bladder;at least one resilient, ring-shaped corrugation in the bladder wall adjacent to and continuously surrounding the rim; anda portion of the bladder wall surrounding the corrugation and being substantially co-planar with the opening when no force is applied to the rim, the corrugation exhibiting the property of allowing movement of the rim with respect to the surrounding portion of the bladder wall and the at least one corrugation extending radially from the rim to the portion of the bladder wall. 22. The system of claim 21 wherein the mount is a circular ring. 23. The system of claim 21 wherein the at least one resilient corrugation comprises a plurality of concentric corrugations. 24. The system of claim 21 wherein the interconnect is axially aligned with the opening, the interconnect extending orthogonally from the opening, and wherein the entire fuel bladder is configured to correspond with the interior profile.
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이 특허에 인용된 특허 (10)
Kirk Kenneth G. (Placerville CA) Baxter Kris E. (El Dorado Hills CA), Compliant mount for neck of compressed gas cylinder.
Furs Stanley (East Haven CT) Grom Glen (Fairfield CT) Miller Paul W. (Milford CT) Wang David E. (Newton CT) Berardi Arthur F. (Seymour CT), Method for removing a fuel cell.
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