Auxiliary fuel tank systems for aircraft and methods for their manufacture and use
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F16K-021/18
F16K-021/00
출원번호
US-0768242
(2004-01-29)
등록번호
US-7357149
(2008-04-15)
발명자
/ 주소
Howe,Mark E.
출원인 / 주소
The Boeing Company
대리인 / 주소
Perkins Coie LLP
인용정보
피인용 횟수 :
12인용 특허 :
39
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 inc
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.
대표청구항▼
I claim: 1. An aircraft fuel outlet manifold comprising: a first duct having a first fuel inlet positioned to draw fuel out of a sump region of a tank, the first duct further having a first fuel outlet that transfers fuel through a first outlet aperture in an end wall of the tank; a first valve ass
I claim: 1. An aircraft fuel outlet manifold comprising: a first duct having a first fuel inlet positioned to draw fuel out of a sump region of a tank, the first duct further having a first fuel outlet that transfers fuel through a first outlet aperture in an end wall of the tank; a first valve assembly operably coupled to the first duct and positioned proximate to the sump region of the tank, wherein the first valve assembly is configured to at least reduce the flow of fuel through the first fuel inlet when fuel in the tank drops to or below a selected level; a second duct spaced apart from the first duct and having a second fuel inlet positioned to draw fuel out of the sump region of the tank, the second duct further having a second fuel outlet spaced apart from the first fuel outlet, wherein the second fuel outlet transfers fuel through a second outlet aperture spaced apart from the first outlet aperture in the end wall of the tank; and a second valve assembly spaced apart from the first valve assembly and operably coupled to the second duct, wherein the second valve assembly is positioned proximate to the sump region of the tank, and wherein the second valve assembly is configured to at least reduce the flow of fuel through the second fuel inlet when fuel in the tank drops to or below the selected level. 2. The fuel outlet manifold of claim 1 wherein the first valve assembly is configured to be positioned in the tank at least proximate to the first fuel inlet. 3. The fuel outlet manifold of claim 1 wherein the first valve assembly includes: a first valve movably positioned in the first duct; and a fuel level sensor operably coupled to the first valve, wherein the fuel level sensor is configured to close the first valve and at least reduce the flow of fuel through the first inlet when fuel in the tank drops to or below the selected level. 4. The fuel outlet manifold of claim 1 wherein the first valve assembly includes: a valve rotatably mounted in the first duct; and a float operably coupled to the valve, wherein movement of the float causes the valve to rotate between a first position in which the first duct is at least approximately open and a second position in which the first duct is at least approximately closed. 5. The fuel outlet manifold of claim 1 wherein the fist valve assembly includes: a valve rotatably mounted in the first duct; a float operably coupled to the valve, wherein the float is configured to move toward an upper position causing the valve to rotate in a first direction to at least approximately open the first duct when fuel in the tank is at or above a first level, and wherein the float is further configured to move from the upper position toward a lower position causing the valve to rotate in a second direction to at least approximately close the first duct when fuel in the tank drops from the first level toward a second level. 6. The fuel outlet manifold of claim 1 wherein the tank is a first tank, and wherein the fuel outlet manifold further comprises: a third duct having a third fuel inlet configured to draw fuel out of a second tank positioned adjacent to the first tank; and a third valve assembly operably coupled to the third duct, wherein the third valve assembly is configured to at least reduce the flow of fuel through the third fuel inlet when fuel in the second tank drops to or below a selected level. 7. The fuel outlet manifold of claim 1 wherein the first valve assembly includes: a first valve movably positioned in the first duct; and a float operably coupled to the first valve, wherein movement of the float causes the first valve to move between a first position in which the first duct is at least approximately open and a second position in which the first duct is at least approximately closed. 8. The fuel outlet manifold of claim 7 wherein the float is mechanically coupled to the valve. 9. The fuel outlet manifold of claim 7 wherein the float is electronically coupled to the valve. 10. An aircraft system comprising: a first tank body configured to hold liquid fuel in a fuselage, the first tank body having a first end wall extending vertically between an upper wall and a lower wall; a second tank body positioned adjacent to the first tank body, the second tank body having a second end wall facing the first end wall; and a fuel outlet manifold extending through the first end wall of the first tank body and the second end wall of the second tank body, the fuel outlet manifold including: a first duct in the first tank body, the first duct being configured to transfer liquid fuel out of the first tank body via a first liquid fuel inlet; a first valve assembly operably coupled to the first duct in the first tank body, wherein the first valve assembly is configured to at least reduce the flow of liquid fuel through the first duct when liquid fuel in the first tank body drops to or below a selected level; a second duct in the second tank body, the second duct being configured to transfer liquid fuel out of the second tank body via a second liquid fuel inlet; and a second valve assembly operably coupled to the second duct in the second tank body, wherein the second valve assembly is configured to at least reduce the flow of liquid fuel through the second duct when liquid fuel in the second tank body drops to or below a selected level. 11. The aircraft system of claim 10 wherein the first tank body includes beveled corner portions configured to at least approximately follow the contour of a cargo compartment of the fuselage. 12. The aircraft system of claim 10 wherein the first fuel inlet is positioned at least proximate to a sump portion of the first tank body, the sump portion defining a lowermost fuel-carrying portion of the first tank body. 13. The aircraft system of claim 10 wherein the first valve assembly includes: a valve movably positioned in the first duct; and a float movably positioned in the first tank body and operably coupled to the valve, wherein movement of the float causes the valve to move between a first position in which the first duct is at least approximately open and a second position in which the first duct is at least approximately closed. 14. The aircraft system of claim 10, further comprising the fuselage. 15. A system for providing fuel to at least one of an engine and an aerial refueling manifold on an aircraft, the system comprising: a fuel tank for carrying fuel in an aircraft; first duct means for transferring fuel from the fuel tank to at least one of the engine and the aerial refueling manifold through a first outlet aperture in an end wall of the fuel tank; a first fuel inlet positioned in the fuel tank and operably coupled to the first duct means; first pump means positioned in the fuel tank and operably coupled to the first duct means for moving fuel through the first fuel inlet; first valve means for automatically closing the first duct means before fuel in the fuel tank drops below the first fuel inlet to avoid ingesting a gaseous substance into the first duct means; second duct means for transferring fuel from the fuel tank to at least one of the engine and the aerial refueling manifold through a second outlet aperture in the end wall of a second fuel inlet positioned in the fuel tank and operably coupled to the second duct means; second pump means positioned in the fuel tank and operably coupled to the second duct means for moving fuel through the second fuel inlet; and second valve means for automatically closing the second duct means before fuel in the fuel tank drops below the second fuel inlet to avoid ingesting a gaseous substance into the second duct means. 16. The system of claim 15, further comprising pump means for pumping fuel out of the fuel tank via the first and second duct means, wherein the pump means is positioned in the fuel tank and operably coupled to the first and second duct means. 17. The system of claim 15 wherein the fuel tank is a first fuel tank, and wherein the system further comprises: a second fuel tank for carrying fuel in the aircraft; third duct means for transferring fuel from the second fuel tank to at least one of the engine and the aerial refueling manifold via a third fuel inlet positioned in the second fuel tank; and third valve means for automatically closing the third duct means before fuel in the second fuel tank drops below the third fuel inlet to avoid ingesting a gaseous substance into the third duct means. 18. The system of claim 15 wherein the fuel tank is a first fuel tank, and wherein the system further comprises: a second fuel tank for carrying fuel in the aircraft; third duct means for transferring fuel from the second fuel tank to at least one of the engine and the aerial refueling manifold via a third fuel inlet positioned in the second fuel tank; and third valve means for automatically closing the third duct means before fuel in the second fuel tank drops below the third fuel inlet to avoid ingesting a gaseous substance into the third duct means, wherein the first fuel tank is removably positioned in a fuselage of the aircraft and the second fuel tank is removably positioned in the fuselage at least proximate to the first fuel tank. 19. The system of claim 15 wherein the fuel tank is a first fuel tank, and wherein the system further comprises: a second fuel tank for carrying fuel in the aircraft; third duct means for transferring fuel from the second fuel tank to at least one of the engine and the aerial refueling manifold via a third fuel inlet positioned in the second fuel tank; and third valve means for automatically closing the third duct means before fuel in the second fuel tank drops below the third fuel inlet to avoid ingesting a gaseous substance into the third duct means, wherein the first, second and third duct means are operably coupled to a common manifold means.
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이 특허에 인용된 특허 (39)
Coloney Wayne H. (P.O. Box 668 Tallahasse FL 32302), Aircraft fuel tank.
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Wittko Joseph N. (Old Westbury NY) Harding David G. (Brookhaven PA) Schneider John J. (Media PA) Gonsalves Joseph E. (Springfield PA), Hammock supported fuel tank.
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