[특허]Aircraft and fuel venting system therefor

Airbus UK Limited

검색어에 아래의 연산자를 사용하시면 더 정확한 검색결과를 얻을 수 있습니다.
검색연산자

검색연산자	기능	검색시 예
()	우선순위가 가장 높은 연산자	예1) (나노 (기계 \| machine))
공백	두 개의 검색어(식)을 모두 포함하고 있는 문서 검색	예1) (나노 기계) 예2) 나노 장영실
\|	두 개의 검색어(식) 중 하나 이상 포함하고 있는 문서 검색	예1) (줄기세포 \| 면역) 예2) 줄기세포 \| 장영실
!	NOT 이후에 있는 검색어가 포함된 문서는 제외	예1) (황금 !백금) 예2) !image
*	검색어의 *란에 0개 이상의 임의의 문자가 포함된 문서 검색	예) semi*
""	따옴표 내의 구문과 완전히 일치하는 문서만 검색	예) "Transform and Quantization"

과학기술 지식인프라 ScienceON

안녕하세요!
ScienceON 챗봇입니다.
궁금한 것은 저에게 물어봐주세요.

특허 상세정보

MyON담기

내보내기

Aircraft and fuel venting system therefor

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64D-037/04 B64D-037/00
미국특허분류(USC)	244/135.R; 137/589; 137/899.2
출원번호	UP-0112859 (2005-04-22)
등록번호	US-7621483 (2009-12-02)
우선권정보	GB-0409593.1(2004-04-29)
발명자 / 주소	Cozens, Simon John Brown, Jeffrey Mark Van, Michel Tran
출원인 / 주소	Airbus UK Limited
대리인 / 주소	Patterson, Thuente, Skaar & Christensen, P.A.
인용정보	피인용 횟수 : 7 인용 특허 : 1

초록

An aircraft comprising a plurality of fuel tanks in each wing is arranged such that each fuel tank is provided with a venting pipe connected to a single venting chamber. The venting chamber is itself located in a central fuel tank located in the wing centre-box and is thus located inwardly of at least two of the fuel tanks. The venting chamber has two venting pipes each being connected via a respective surge tank in each wing to the exterior of the aircraft.

대표
청구항
▼

The invention claimed is: 1. An aircraft comprising a plurality of fuel storage chambers located within said aircraft, at least one of said fuel storage chambers being located within a wing of said aircraft, said wing having an outward portion associated with the wingtip and an inward portion, each of at least two of the fuel storage chambers being provided with a venting conduit for permitting fluid communication with a venting chamber of a venting chamber system, wherein the venting chamber is located inwardly of said at least one fuel storage chamber and has a venting outlet for permitting fluid communication between the venting chamber and the exterior of the aircraft, the aircraft comprising a venting chamber conduit provided between the venting outlet of the venting chamber and an overflow chamber, the overflow chamber being provided with an overflow venting outlet for permitting fluid communication between the overflow chamber and the exterior of the aircraft, the overflow chamber being located in the outward portion of the wing. 2. An aircraft according to claim 1, wherein the venting chamber is located inward of said at least two fuel storage chambers. 3. An aircraft according to claim 1, wherein the venting chamber is disposed within a fuel storage chamber located centrally relative to the wings of the aircraft. 4. An aircraft according to claim 1, wherein each of said at least two fuel storage chambers is associated with a mutually different wing of the aircraft. 5. An aircraft according to claim 1, wherein the venting chamber system comprises a plurality of venting regions in fluid communication with each other, but arranged such that during level flight of the aircraft the flow of fuel, if any is present, from one of the venting regions to another of the venting regions is restricted. 6. An aircraft according to claim 5, wherein at least two of the venting regions are defined within the venting chamber by one or more substantially liquid-impermeable partitions that allow venting gases to flow from one venting region to another. 7. An aircraft according to claim 5, wherein the venting chamber system comprises only one venting chamber, with the venting regions being defined within the venting chamber. 8. An aircraft according to claim 5, wherein the venting chamber system comprises a plurality of venting chambers wherein each of at least two of the venting regions is located within a separate venting chamber. 9. An aircraft according to claim 5, wherein each of the venting regions is associated with one or more fuel storage chambers, the fuel storage chambers associated with one of the venting regions all being located in one wing and the fuel storage chambers associated with another of the venting regions all being located in a different wing. 10. An aircraft according to claim 9, wherein each venting region may be provided with a separate venting chamber outlet for permitting fluid communication between the venting region and the exterior of the aircraft. 11. An aircraft according to claim 1, wherein one of said venting conduits includes a valve arrangement that is arranged to restrict the overflow of fuel into the venting conduit. 12. An aircraft according to claim 1, wherein one of said venting conduits includes a fuel storage chamber venting outlet located towards the trailing edge of said wing, said venting conduit connecting said venting outlet via a forwardly extending portion and via an inwardly extending portion to the venting chamber system, the portions being arranged in series and within the fuel storage chamber. 13. A fixed-wing aircraft with two anhedral wings, said aircraft comprising a plurality of fuel tanks located within said aircraft, each of said wings having an outward portion associated with the wingtip and an inward portion, each of at least two of the fuel tanks being located within mutually different wings of the aircraft and being provided with a venting conduit for permitting fluid communication with a venting chamber of a venting chamber system, wherein the venting chamber is disposed within a fuel tank located centrally relative to the wings of the aircraft and is located inwardly of said at least two fuel storage tanks and has a venting outlet for permitting fluid communication between the venting chamber and the exterior of the aircraft, wherein the aircraft further comprises two surge tanks, the surge tanks being located in the outward portion of mutually different wings of the aircraft, a venting chamber conduit being provided between the venting outlet of the venting chamber and each surge tank, each surge tank being provided with an overflow venting outlet for permitting fluid communication between the surge tank and the exterior of the aircraft.

이 특허에 인용된 특허 (1)

Vardaman Billy G. (Albany GA) Meyer Corwin W. (Ocala FL). Fuel system for Canard aircraft. USP1990044913380.

이 특허를 인용한 특허 피인용횟수: 7

IPC 상위 출원인

내보내기

상세정보
내보내기 구분	파일저장 인쇄 메일전송
구성항목	관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표IPC 관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 공고번호, 공고일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표출원인, 출원인국적, 출원인주소, 발명자, 발명자E, 발명자코드, 발명자주소, 발명자 우편번호, 발명자국적, 대표IPC, IPC코드, 요약, 미국특허분류, 대리인주소, 대리인코드, 대리인(한글), 대리인(영문), 국제공개일자, 국제공개번호, 국제출원일자, 국제출원번호, 우선권, 우선권주장일, 우선권국가, 우선권출원번호, 원출원일자, 원출원번호, 지정국, Citing Patents, Cited Patents
저장형식	Text(ASCII format) Excel format PIAS분석(.xls)
메일정보	받는사람 (필수) @ 보내는사람 (선택) @ 제목 내용 KISTI 검색결과 이메일 서비스
안내	> 총 건의 자료가 검색되었습니다. > 다운받으실 자료의 인덱스를 입력하세요. (1-10,000) > 검색결과의 순서대로 최대 10,000건 까지 다운로드가 가능합니다. > 데이타가 많을 경우 속도가 느려질 수 있습니다.(최대 2~3분 소요) > 다운로드 파일은 UTF-8 형태로 저장됩니다. 파일의 내용이 제대로 보이지 않을실 때는 웹브라우저 상단의 보기 -> 인코딩 -> 자동선택 여부를 확인하십시오 > ~ > Text(ASCII format) Excel format

과학기술 지식인프라 ScienceON

ScienceON Chatbot

특허 상세정보

Aircraft and fuel venting system therefor

초록

대표
청구항
▼

이 특허에 인용된 특허 (1)

이 특허를 인용한 특허 피인용횟수: 7

IPC 상위 출원인

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

ScienceON Chatbot

특허 상세정보

Aircraft and fuel venting system therefor

초록

대표청구항 ▼

이 특허에 인용된 특허 (1)

이 특허를 인용한 특허 피인용횟수: 7

IPC 상위 출원인

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

대표
청구항
▼