[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 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-037/00
미국특허분류(USC)	244/135.R
출원번호	US-0042731 (2005-01-24)
발명자 / 주소	Howe,Mark E.
출원인 / 주소	The Boeing Company
대리인 / 주소	Perkins Coie LLP
인용정보	피인용 횟수 : 9 인용 특허 : 28

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. An aircraft system comprising: a first tank body having a first end wall and an opposite second end wall; a fuel inlet manifold portion positioned at least partially in the first tank body and having at least one fuel inlet duct configured to flow fuel into the first tank body; a first manifold interconnect operably coupled to the fuel inlet manifold portion and positioned toward the first end wall; and a second manifold interconnect operably coupled to the fuel inlet manifold portion and positioned toward the second end wall, wherein the first manifold interconnect is configured to operably connect the fuel inlet manifold portion to a second manifold portion associated with a second tank body, and wherein the second manifold interconnect is configured to operably connect the fuel inlet manifold portion to a third manifold portion associated with a third tank body. 2. The aircraft system of claim 1 wherein the first end wall has at least a first aperture and the second end wall has at least a second aperture, and wherein the first manifold interconnect extends at least partially through the first aperture and the second manifold interconnect extends at least partially through the second aperture. 3. The aircraft system of claim 1 wherein the first end wall has at least a first aperture and the second end wall has at least a second aperture, wherein the first manifold interconnect extends at least partially through the first aperture and the second manifold interconnect extends at least partially through the second aperture, and wherein the first and second apertures are axially aligned with each other. 4. The aircraft system of claim 1 wherein the first manifold interconnect is configured to operably connect the first tank body to the second tank body when the second tank body is positioned at least proximate to the first end wall in a fuselage of the aircraft, and wherein the second manifold interconnect is configured to operably connect the first tank body to the third tank body when the third tank body is positioned at least proximate to the second end wall in the fuselage of the aircraft. 5. The aircraft system of claim 1 further comprising a fuel outlet manifold portion having at least one fuel outlet duct configured to withdraw fuel from the first tank body. 6. The aircraft system of claim 1, further comprising a fuselage, wherein the first tank body is positioned in the fuselage. 7. The aircraft system of claim 1 wherein at least the first and second end walls are double-wall construction and include an inner tank skin spaced apart from an outer tank skin. 8. An aircraft system comprising: a first tank body having a first end wall and an opposite second end wall; a vent manifold portion positioned at least partially in the first tank body and having at least one vent duct configured to vent the first tank body; a first manifold interconnect operably coupled to the vent manifold portion and positioned toward the first end wall; and a second manifold interconnect operably coupled to the vent manifold portion and positioned toward the second end wall, wherein the first manifold interconnect is configured to operably connect the vent manifold portion to a second manifold portion associated with a second tank body, and wherein the second manifold interconnect is configured to operably connect the vent manifold portion to a third manifold portion associated with a third tank body. 9. The aircraft system of claim 8 further comprising a fuel inlet manifold portion positioned at least partially in the first tank body, the fuel inlet manifold portion having at least one fuel inlet duct configured to flow fuel into the first tank body. 10. An aircraft system comprising: a first tank body having a first end wall and an opposite second end wall; a first fuel outlet manifold portion positioned at least partially in the first tank body and having at least one fuel outlet duct configured to withdraw fuel from the first tank body; a first manifold interconnect operably coupled to the first fuel outlet manifold portion and positioned toward the first end wall; a second manifold interconnect operably coupled to the first fuel outlet manifold portion and positioned toward the second end wall, wherein the first manifold interconnect is configured to operably connect the first fuel outlet manifold portion to a second fuel outlet manifold portion associated with a second tank body, and wherein the second manifold interconnect is configured to operably connect the first fuel outlet manifold portion to a third fuel outlet manifold portion associated with a third tank body; a first fuel inlet manifold portion positioned at least partially in the first tank body, the first fuel inlet manifold portion having at least one fuel inlet duct configured to flow fuel into the first tank body; a third manifold interconnect operably coupled to the first fuel inlet manifold portion and positioned toward the first end wall; and a fourth manifold interconnect operably coupled to the first fuel inlet manifold portion and positioned toward the second end wall, wherein the third manifold interconnect is configured to operably connect the first fuel inlet manifold portion to a second fuel inlet manifold portion associated with the second tank body, and wherein the fourth manifold interconnect is configured to operably connect the first fuel inlet manifold portion to a third fuel inlet manifold portion associated with the third tank body. 11. The aircraft system of claim 10 wherein at least the first and second end walls are double-wall construction and include an inner tank skin spaced apart from an outer tank skin. 12. The aircraft system of claim 10 wherein the first end wall has at least a first aperture and the second end wall has at least a second aperture, and wherein the first manifold interconnect extends at least partially through the first aperture and the second manifold interconnect extends at least partially through the second aperture. 13. The aircraft system of claim 10 wherein the first end wall has at least a first aperture and the second end wall has at least a second aperture, wherein the first manifold interconnect extends at least partially through the first aperture and the second manifold interconnect extends at least partially through the second aperture, and wherein the first and second apertures are axially aligned with each other. 14. The aircraft system of claim 10 wherein the first manifold interconnect is configured to operably connect the first tank body to the second tank body when the second tank body is positioned at least proximate to the first end wall in a fuselage of the aircraft, and wherein the second manifold interconnect is configured to operably connect the first tank body to the third tank body when the third tank body is positioned at least proximate to the second end wall in the fuselage of the aircraft. 15. An aircraft system comprising: a first tank body having a first end wall and an opposite second end wall; a fuel outlet manifold portion positioned at least partially in the first tank body and having at least one fuel outlet duct configured to withdraw fuel from the first tank body; a first manifold interconnect operably coupled to the fuel outlet manifold portion and positioned toward the first end wall; a second manifold interconnect operably coupled to the fuel outlet manifold portion and positioned toward the second end wall, wherein the first manifold interconnect is configured to operably connect the fuel outlet manifold portion to a second manifold portion associated with a second tank body, and wherein the second manifold interconnect is configured to operably connect the fuel outlet manifold portion to a third manifold portion associated with a third tank body; a fuel inlet manifold portion positioned at least partially in the first tank body, the fuel inlet manifold portion having at least one fuel inlet duct configured to flow fuel into the first tank body; and a vent manifold portion having at least one vent duct configured to vent the first tank body. 16. The aircraft system of claim 15 wherein at least the first and second end walls are double-wall construction and include an inner tank skin spaced apart from an outer tank skin. 17. The aircraft system of claim 15 wherein the first end wall has at least a first aperture and the second end wall has at least a second aperture, and wherein the first manifold interconnect extends at least partially through the first aperture and the second manifold interconnect extends at least partially through the second aperture. 18. The aircraft system of claim 15 wherein the first manifold interconnect is configured to operably connect the first tank body to the second tank body when the second tank body is positioned at least proximate to the first end wall in a fuselage of the aircraft, and wherein the second manifold interconnect is configured to operably connect the first tank body to the third tank body when the third tank body is positioned at least proximate to the second end wall in the fuselage of the aircraft. 19. An aircraft system comprising: a first tank body having a first end wall and an opposite second end wall; a first fuel outlet manifold portion positioned at least partially in the first tank body and having at least one fuel outlet duct configured to withdraw fuel from the first tank body; a first manifold interconnect operably coupled to the first fuel outlet manifold portion and positioned toward the first end wall; a second manifold interconnect operably coupled to the first fuel outlet manifold portion and positioned toward the second end wall, wherein the first manifold interconnect is configured to operably connect the first fuel outlet manifold portion to a second fuel outlet manifold portion associated with a second tank body, and wherein the second manifold interconnect is configured to operably connect the first fuel outlet manifold portion to a third fuel outlet manifold portion associated with a third tank body; a first fuel inlet manifold portion positioned at least partially in the first tank body, the first fuel inlet manifold portion having at least one fuel inlet duct configured to flow fuel into the first tank body; a first vent manifold portion having at least one vent duct configured to vent the first tank body; a third manifold interconnect operably coupled to the first fuel inlet manifold portion and positioned toward the first end wall; a fourth manifold interconnect operably coupled to the first fuel inlet manifold portion and positioned toward the second end wall, wherein the third manifold interconnect is configured to operably connect the first fuel inlet manifold portion to a second fuel inlet manifold portion associated with the second tank body, and wherein the fourth manifold interconnect is configured to operably connect the first fuel inlet manifold portion to a third fuel inlet manifold portion associated with the third tank body; a fifth manifold interconnect operably coupled to the first vent manifold portion and positioned toward the first end wall; and a sixth manifold interconnect operably coupled to the first vent manifold portion and positioned toward the second end wall, wherein the fifth manifold interconnect is configured to operably connect the first vent manifold portion to a second vent manifold portion associated with the second tank body, and wherein the sixth manifold interconnect is configured to operably connect the first vent manifold portion to a third vent manifold portion associated with the third tank body. 20. The aircraft system of claim 19 wherein the first, second, third, and fourth manifold interconnects are at least generally similar in structure and function.

인용문헌 (28)

이 특허를 인용한 특허 (9)

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
▼

인용문헌 (28)

이 특허를 인용한 특허 (9)

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 ▼

인용문헌 (28)

이 특허를 인용한 특허 (9)

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

초록
▼

대표
청구항
▼