[특허]Auxiliary fuel tank systems for aircraft and methods for their manufacture and use

The Boeing Company

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

검색도움말
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

연합인증

연합인증 가입 기관의 연구자들은 소속기관의 인증정보(ID와 암호)를 이용해 다른 대학, 연구기관, 서비스 공급자의 다양한 온라인 자원과 연구 데이터를 이용할 수 있습니다.

이는 여행자가 자국에서 발행 받은 여권으로 세계 각국을 자유롭게 여행할 수 있는 것과 같습니다.

연합인증으로 이용이 가능한 서비스는 NTIS, DataON, Edison, Kafe, Webinar 등이 있습니다.

한번의 인증절차만으로 연합인증 가입 서비스에 추가 로그인 없이 이용이 가능합니다.

다만, 연합인증을 위해서는 최초 1회만 인증 절차가 필요합니다. (회원이 아닐 경우 회원 가입이 필요합니다.)

연합인증 절차는 다음과 같습니다.

최초이용시에는
ScienceON에 로그인 → 연합인증 서비스 접속 → 로그인 (본인 확인 또는 회원가입) → 서비스 이용

그 이후에는
ScienceON 로그인 → 연합인증 서비스 접속 → 서비스 이용

연합인증을 활용하시면 KISTI가 제공하는 다양한 서비스를 편리하게 이용하실 수 있습니다.

특허 상세정보

MyON담기

내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Auxiliary fuel tank systems for aircraft and methods for their manufacture and use

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64D-037/14 B64D-037/00
미국특허분류(USC)	244/135.R; 244/135.C; 137/263; 137/571; 060/734
출원번호	UP-0441492 (2006-05-26)
등록번호	US-7568660 (2009-08-24)
발명자 / 주소	Howe, Mark E.
출원인 / 주소	The Boeing Company
대리인 / 주소	Perkins Coie LLP
인용정보	피인용 횟수 : 2 인용 특허 : 47

초록
▼

Auxiliary fuel tank systems for aircraft and methods for their manufacture and use. In one embodiment, an aircraft can include a fuselage, at least one engine, and a fuel system configured to distribute fuel to at least one of the engine and an aerial refueling manifold. The aircraft can further include an auxiliary fuel tank system operably coupled to the fuel system. The auxiliary fuel tank system can include a master tank assembly and at least one slave tank assembly. The master tank assembly can be removably installed in the fuselage, and can include a master tank body configured to hold fuel. The master tank body can be configured to pass through a door in the fuselage without disassembly. The slave tank assembly can be removably installed in the fuselage at least proximate to the master tank assembly, and can include a slave tank body configured to hold fuel.

대표
청구항
▼

I claim: 1. A method on an aircraft for providing fuel to at least one of an engine and an aerial refueling manifold during flight, the method comprising: at least partially filling a first tank assembly with fuel in a fuselage of the aircraft by flowing fuel through a dual purpose inlet/outlet duct coupled to the first "tank assembly and positioned at least partially withen the first tank assembly;" at least partially filling a second tank assembly with fuel in the fuselage of the aircraft by flowing fuel through the dual purpose inlet/outlet duct; drawing fuel from the first tank assembly by operating a fuel transfer pump positioned in the first tank assembly; while drawing fuel from the first tank assembly, drawing fuel through an inlet positioned in the second tank assembly by operating the fuel transfer pump positioned in the first tank assembly; passing the fuel drawn from the first and second tank assemblies through the fuel transfer pump: and after passing the fuel drawn from the first and second tank assemblies through the fuel transfer pump, flowing the fuel out of the first and second tank assemblies to at least one of the engine and the aerial refueling manifold through the dual purpose inlet/outlet duct, wherein the dual purpose inlet/outlet duct is configured to transfer fuel from, and provide fuel to, the first and second tank assemblies. 2. The method of claim 1, wherein at least partially filling a first tank assembly with fuel includes at least partially filling a first tank assembly removably installed in a fuselage of the aircraft, and wherein at least partially filling a second tank assembly with fuel includes at least partially filling a second tank assembly removably installed in the fuselage at least proximate to the first tank assembly. 3. The method of claim 1, wherein at least partially filling the first and second tank assemblies with fuel before takeoff includes at least approximately simultaneously filling the first tank assembly and the second tank assembly. 4. The method of claim 1, further comprising: removably installing the first tank assembly in a fuselage of the aircraft, the first tank assembly having a first aperture in a first end wall; removably installing the second tank assembly in the fuselage of the aircraft, the second tank assembly having a second aperture in a second end wall, the second end wall of the second tank assembly facing the first end wall of the first tank assembly; and extending a portion of a fuel duct through the first and second apertures. 5. A method on an aircraft for providing fuel to at least one of an engine and an aerial refueling manifold during flight, the method comprising: at least partially filling a first tank assembly with fuel in a fuselage of the aircraft by flowing fuel through a dual purpose inlet/outlet duct coupled to the first "tank assembly and positioned at least partially withen the first tank assembly;" at least partially filling a second tank assembly with fuel in the fuselage of the aircraft by flowing fuel through the dual purpose inlet/outlet duct; drawing fuel from the first tank assembly through a first inlet operably coupled to a first portion of a fuel duct positioned in the first tank assembly; while drawing fuel from the first tank assembly, drawing fuel from the second tank assembly through a second inlet operably coupled to a second portion of the fuel duct positioned in the second tank assembly: passing the fuel drawn from the second tank assembly through the first tank assembly; and after drawing the fuel from the first and second tank assemblies, transferring the fuel drawn from the first and second tank assemblies to at least one of the engine and the aerial refueling manifold through the dual purpose inlet/outlet duct, wherein the dual purpose inlet/outlet duct is configured to transfer fuel from, and provide fuel to, the first and second tank assemblies. 6. The method of claim 5, wherein passing the fuel drawn from the second tank assembly through the first tank assembly includes passing the fuel drawn from the second tank assembly through a tank interconnect bridging a gap between the first and second tank assemblies. 7. The method of claim 5, wherein passing the fuel drawn from the second tank assembly through the first tank assembly includes passing the fuel drawn from the second tank assembly through a first aperture in a first end wall of the first tank assembly and a second aperture in a second end wall of the second tank assembly. 8. A method on an aircraft for providing fuel to at least one of an engine and an aerial refueling manifold during flight, the method comprising: at least partially filling a first tank assembly with fuel in a fuselage of the aircraft by flowing fuel through a dual purpose inlet/outlet duct positioned at least partially within the first tank assembly; at least partially filling a second tank assembly with fuel in the fuselage of the aircraft by flowing fuel through the dual purpose inlet/outlet duct; drawing fuel from the first tank assembly; while drawing fuel from the first tank assembly, drawing fuel from the second tank assembly; and after drawing the fuel from the first and second tank assemblies, transferring the fuel drawn from the first and second tank assemblies to at least one of the engine and the aerial refueling manifold through the dual purpose inlet/outlet duct positioned at least partially within the first tank assembly, wherein the dual purpose inlet/outlet duct is configured to transfer fuel from, and provide fuel to, the first and second tank assemblies. 9. The method of claim 8, wherein drawing fuel from the first tank assembly includes drawing fuel through a first portion of a first outlet duct operably coupled to a first branch of the dual purpose inlet/outlet manifold, and drawing fuel through a second portion of a second outlet duct operably coupled to a second branch of the dual purpose inlet/outlet manifold. 10. A method on an aircraft for providing fuel to at least one of an engine and an aerial refueling manifold during flight, the method comprising: at least partially filling a first tank assembly with fuel in a fuselage of the aircraft; at least partially filling a second tank assembly with fuel in the fuselage of the aircraft; drawing fuel from the first tank assembly; while drawing fuel from the first tank assembly, drawing fuel through an inlet positioned in the second tank assembly by operating a fuel transfer pump positioned in the first tank assembly; passing the fuel drawn from the first and second tank assemblies through the fuel transfer pump; and after passing the fuel drawn from the first and second tank assemblies through the fuel transfer pump, transferring the drawn fuel to at least one of the engine and the aerial refueling manifold through a dual purpose "inlet/outlet duct positioned at least partially within the first tank assembly, wherein the dual purpose inlet/outlet manifold is" configured to transfer fuel from, and provide fuel to, the first and second tank assemblies. 11. The method of claim 10, wherein at least partially filling a first tank assembly with fuel includes at least partially filling a first tank assembly removably installed in a fuselage of the aircraft, and wherein at least partially filling a second tank assembly with fuel includes at least partially filling a second tank assembly removably installed in the fuselage at least proximate to the first tank assembly. 12. The method of claim 10, wherein drawing fuel from the first tank assembly includes drawing fuel through a first inlet of an outlet manifold, the first inlet being positioned in the first tank assembly, and wherein drawing fuel from the second tank assembly includes drawing fuel through a second inlet of the outlet manifold, the second inlet being positioned in the second tank assembly. 13. The method of claim 10, further comprising passing the fuel drawn from the second tank assembly through a portion of a fuel duct positioned in the first tank assembly. 14. The method of claim 10, further comprising: removably installing the first tank assembly in a fuselage of the aircraft, the first tank assembly having a first aperture in a first end wall; removably installing the second tank assembly in the fuselage of the aircraft, the second tank assembly having a second aperture in a second end wall, the second end wall of the second tank assembly facing the first end wall of the first tank assembly; and extending a portion of a fuel duct through the first and second apertures, wherein drawing fuel from the second tank assembly includes drawing fuel through the fuel duct. 15. A method on an aircraft for providing fuel to at least one of an engine and an aerial refueling manifold during flight, the method comprising: removably installing a first tank assembly in a fuselage of the aircraft, the first tank assembly having a first aperture in a first end wall; removably installing a second tank assembly in the fuselage of the aircraft, the second tank assembly having a second aperture in a second end wall, the second end wall of the second tank assembly facing the first end wall of the first tank assembly; extending a fuel duct through the first and second apertures and into the first and second tank assemblies; operably coupling the fuel duct to a dual purpose inlet/outlet duct positioned in the first tank assembly, wherein the dual purpose inlet/outlet duct is configured to transfer fuel from, and provide fuel to, the first and second tank assemblies; at least partially filling the first tank assembly with fuel by flowing fuel through the dual purpose inlet/outlet duct; at least partially filling the second tank assembly with fuel by flowing fuel through the dual purpose inlet/outlet duct; drawing fuel from the first tank assembly through a first inlet operably coupled to a first portion of the fuel duct positioned in the first tank assembly; while drawing fuel from the first tank assembly, drawing fuel from the second tank assembly through a second inlet operably coupled to a second portion of the fuel duct positioned in the second tank assembly, and passing the fuel drawn from the second tank assembly through the first and second apertures via the fuel duct; transferring the fuel drawn from the first and second tank assemblies to the dual purpose inlet/outlet duct via the fuel duct; and transferring the fuel from the dual purpose inlet/outlet duct to at least one of the engine and the aerial refueling manifold. 16. The method of claim 15, further comprising: operably coupling a fuel transfer pump to the fuel duct in the first tank assembly, wherein drawing fuel from the first and second tank assemblies includes operating the fuel transfer pump to draw the fuel through the first and second inlets.

이 특허에 인용된 특허 (47)

이 특허를 인용한 특허 피인용횟수: 2

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

연합인증

특허 상세정보

Auxiliary fuel tank systems for aircraft and methods for their manufacture and use

초록
▼

대표
청구항
▼

이 특허에 인용된 특허 (47)

이 특허를 인용한 특허 피인용횟수: 2

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

ScienceON Chatbot

연합인증

특허 상세정보

Auxiliary fuel tank systems for aircraft and methods for their manufacture and use

초록 ▼

대표청구항 ▼

이 특허에 인용된 특허 (47)

이 특허를 인용한 특허 피인용횟수: 2

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

초록
▼

대표
청구항
▼