Auxiliary fuel tank systems for aircraft and methods for their manufacture and use
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-001/22
B64C-001/00
B64D-001/00
출원번호
US-0768267
(2004-01-29)
발명자
/ 주소
Howe,Mark E.
출원인 / 주소
The Boeing Company
대리인 / 주소
Perkins Coie LLP
인용정보
피인용 횟수 :
8인용 특허 :
27
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 comprising: a fuselage; at least one engine configured to provide propulsive thrust; a fuel system configured to distribute fuel to at least one of the engine and an aerial refueling manifold; and an auxiliary fuel tank system operably coupled to the fuel system, the auxili
I claim: 1. An aircraft comprising: a fuselage; at least one engine configured to provide propulsive thrust; a fuel system configured to distribute fuel to at least one of the engine and an aerial refueling manifold; and an auxiliary fuel tank system operably coupled to the fuel system, the auxiliary fuel tank system including: a first tank assembly removably installed in the fuselage, the first tank assembly including a first tank body configured to hold fuel; at least a second tank assembly removably installed in the fuselage at least proximate to the first tank assembly, the second tank assembly including a second tank body configured to hold fuel, the second tank body being at least approximately identical to the first tank body; and at least one fuel transfer pump operably coupled to a fuel outlet manifold and configured to draw fuel from the first and second tank assemblies, wherein the fuel outlet manifold includes a first fuel inlet positioned in the first tank assembly and a second fuel inlet positioned in the second tank assembly. 2. The aircraft of claim 1 wherein the fuselage includes at least one door, and wherein the first and second tank bodies are configured to pass through the door. 3. The aircraft of claim 1 wherein the auxiliary fuel tank system further comprises a fuel inlet manifold configured to flow fuel into the first and second tank assemblies via a first fuel outlet positioned in the first tank assembly and a second fuel outlet positioned in the second tank assembly. 4. The aircraft of claim 1 wherein the auxiliary fuel tank system further comprises a third tank assembly removably installed in the fuselage at least proximate to the second tank assembly, the third tank assembly including a third tank body that is at least approximately identical to the second tank body. 5. The aircraft of claim 1 wherein the fuel outlet manifold includes a first manifold portion positioned in the first tank assembly and a second manifold portion positioned in the second tank assembly, and wherein the first and second manifold portions are at least approximately identical. 6. The aircraft of claim 1 wherein the auxiliary fuel tank system further comprises a fuel inlet manifold configured to flow fuel into the first and second tank assemblies, wherein the fuel inlet manifold includes a first manifold portion positioned in the first tank assembly and a second manifold portion positioned in the second tank assembly, and wherein the first and second manifold portions are at least approximately identical. 7. The aircraft of claim 1 wherein the auxiliary fuel tank system further comprises a vent manifold configured to vent the first and second tank assemblies, wherein the vent manifold includes a first manifold portion positioned in the first tank assembly and a second manifold portion positioned in the second tank assembly, and wherein the first and second manifold portions are at least approximately identical. 8. The aircraft of claim 1 wherein each of the first and second tank assemblies includes a common tank body, the common tank body having a first end wall and an opposite second end wall, wherein the first end wall includes at least a first aperture and the second end wall includes at least a second aperture, and wherein the first and second apertures are configured to accommodate at least one of the fuel outlet manifold and a fuel inlet manifold extending through the common tank body. 9. The aircraft of claim 1 wherein each of the first and second tank assemblies includes a common tank body, the common tank body having a first end wall and an opposite second end wall, wherein the first end wall includes at least a first aperture and the second end wall includes at least a second aperture, wherein the first and second apertures are configured to accommodate at least one of the fuel outlet manifold and a fuel inlet manifold extending through the common tank body, and wherein the first and second apertures are at least approximately axially aligned. 10. The aircraft of claim 1 wherein the first tank body is configured to hold at least about 250 gallons of fuel and the second tank body is configured to hold at least about 250 gallons of fuel. 11. An aircraft comprising: a fuselage; at least one engine configured to provide propulsive thrust; a fuel system configured to distribute fuel to at least one of the engine and an aerial refueling manifold; and an auxiliary fuel tank system operably coupled to the fuel system, the auxiliary fuel tank system including: a first tank assembly removably installed in the fuselage, the first tank assembly including a first tank body configured to hold fuel; at least a second tank assembly removably installed in the fuselage at least proximate to the first tank assembly, the second tank assembly including a second tank body configured to hold fuel, the second tank body being at least approximately identical to the first tank body; and at least one fuel transfer pump positioned in the first tank assembly, wherein the fuel transfer pump is operably coupled to a fuel outlet manifold and configured to draw fuel from the first and second tank assemblies. 12. The aircraft of claim 11 wherein the first tank assembly is a first master tank assembly and the second tank assembly is a first slave tank assembly, wherein the first master and slave tank assemblies are positioned in a forward compartment of the fuselage, and wherein the auxiliary fuel tank system further comprises: a second master tank assembly removably installed in an aft compartment of the fuselage, the second master tank assembly including a second master tank body configured to hold fuel, the second master tank body configured to pass through an aft fuselage door without disassembly; and at least a second slave tank assembly removably installed in the aft compartment of the fuselage at least proximate to the second master tank assembly, the second slave tank assembly including a second slave tank body configured to hold fuel, the second slave tank body being at least approximately identical to the second master tank body. 13. The aircraft of claim 12 wherein each of the first master tank assembly, the second master tank assembly, the first slave tank assembly, and the second slave tank assembly include a common tank body. 14. The aircraft of claim 12 wherein the first master tank assembly is at least approximately identical to the second master tank assembly, and wherein the first slave tank assembly is at least approximately identical to the second slave tank assembly. 15. An aircraft comprising: a fuselage; at least one engine configured to provide propulsive thrust; a fuel system configured to distribute fuel to at least one of the engine and an aerial refueling manifold; and an auxiliary fuel tank system operably coupled to the fuel system, the auxiliary fuel tank system including: a first tank assembly removably installed in the fuselage, the first tank assembly including a first tank body configured to hold fuel; at least a second tank assembly removably installed in the fuselaae at least proximate to the first tank assembly, the second tank assembly including a second tank body configured to hold fuel, the second tank body being at least approximately identical to the first tank body; a third tank assembly removably installed in the fuselage at least proximate to the second tank assembly; and at least one fuel transfer pump operably coupled to a fuel outlet manifold and configured to draw fuel from the first, second, and third tank assemblies, wherein the fuel outlet manifold includes a first fuel inlet positioned in the first tank assembly, a second fuel inlet positioned in the second tank assembly, and a third fuel inlet positioned in the third tank assembly. 16. An aircraft comprising: a fuselage; at least one engine configured to provide propulsive thrust; a fuel system configured to distribute fuel to at least one of the engine and an aerial refueling manifold; and an auxiliary fuel tank system operably coupled to the fuel system, the auxiliary fuel tank system including: a first tank assembly removably installed in the fuselage; and at least a second tank assembly removably installed in the fuselage at least proximate to the first tank assembly, wherein each of the first and second tank assemblies includes a common tank body configured to hold fuel, the common tank body having a first end wall and an opposite second end wall, wherein the first end wall includes at least first and second apertures and the second end wall includes at least third and fourth apertures, wherein the first and third apertures are configured to accommodate a fuel inlet manifold extending continuously through the common tank body, and wherein the second and fourth apertures are configured to accommodate a fuel outlet manifold extending continuously through the common tank body. 17. An aircraft comprising: a fuselage; at least one engine configured to provide propulsive thrust; a fuel system configured to distribute fuel to at least one of the engine and an aerial refueling manifold; and an auxiliary fuel tank system operably coupled to the fuel system, the auxiliary fuel tank system including: a first tank assembly removably installed in the fuselage; and at least a second tank assembly removably installed in the fuselage at least proximate to the first tank assembly, wherein each of the first and second tank assemblies includes a common tank body configured to hold fuel, the common tank body having a first end wall and an opposite second end wall, wherein the first end wall includes at least first and second apertures and the second end wall includes at least third and fourth apertures, wherein the first and third apertures are configured to accommodate a fuel inlet manifold extending continuously through the common tank body, wherein the second and fourth apertures are configured to accommodate a fuel outlet manifold extending continuously through the common tank body, and wherein the third aperture is at least approximately axially aligned with the first aperture and the fourth aperture is at least approximately axially aligned with the second aperture. 18. An aircraft comprising: a fuselage; at least one engine configured to provide propulsive thrust; a fuel system configured to distribute fuel to at least one of the engine and an aerial refueling manifold; and an auxiliary fuel tank system including: a first tank assembly removably installed in the fuselage; at least a second tank assembly removably installed in the fuselage at least proximate to the first tank assembly; and a fuel outlet manifold operably coupling the first and second tank assemblies to the fuel system, wherein the fuel outlet manifold is configured to drain fuel from the first tank assembly and the second tank assembly at least approximately simultaneously, wherein the fuel outlet manifold includes at least a first fuel inlet and an associated first shutoff valve positioned in the first tank assembly and a second fuel inlet and an associated second shutoff valve positioned in the second tank assembly, wherein the first shutoff valve is configured to close the first fuel inlet when fuel in the first tank assembly drops to or below a first fuel level, and wherein the second shutoff valve is configured to close the second fuel inlet when fuel in the second tank assembly drops to or below a second fuel level. 19. The aircraft of claim 18 wherein the fuselage includes at least one door, wherein the first tank assembly includes a first tank body configured to hold fuel, wherein the second tank assembly includes a second tank body configured to hold fuel, and wherein the first and second tank bodies are configured to pass through the fuselage door without disassembly. 20. The aircraft of claim 18 wherein the first and second tank assemblies share a common tank body. 21. The aircraft of claim 18 wherein the second fuel level in the second tank assembly is at least approximately equivalent to the first fuel level in the first tank assembly. 22. The aircraft of claim 18 wherein the auxiliary fuel tank system further comprises at least one fuel transfer pump operably coupled to the fuel outlet manifold, the fuel transfer pump being positioned within the first tank assembly. 23. The aircraft of claim 18 wherein the auxiliary fuel tank system further comprises a third tank assembly removably installed in the fuselage at least proximate to the second tank assembly, wherein the fuel outlet manifold is configured to drain fuel from the first, second, and third tank assemblies at least approximately simultaneously. 24. An aircraft comprising: a fuselage; at least one engine configured to provide propulsive thrust; a fuel system configured to distribute fuel to at least one of the engine and an aerial refueling manifold; and an auxiliary fuel tank system including: a first tank assembly removably installed in the fuselage; at least a second tank assembly removably installed in the fuselage at least proximate to the first tank assembly; and a fuel inlet manifold operably coupling the first and second tank assemblies to the fuel system, wherein the fuel inlet manifold is configured to flow fuel into the first tank assembly and the second tank assembly at least approximately simultaneously, and wherein the fuel inlet manifold extends continuously through at least the second tank assembly. 25. The aircraft of claim 24 wherein the fuselage has at least one door, wherein the first tank assembly includes a first tank body configured to hold fuel, wherein the second tank assembly includes a second tank body configured to hold fuel, and wherein the first and second tank bodies are configured to pass through the fuselage door without disassembly. 26. The aircraft of claim 24 wherein the first and second tank assemblies share a common tank body. 27. The aircraft of claim 24 wherein the fuel inlet manifold includes at least a first fuel outlet positioned in the first tank assembly and a second fuel outlet positioned in the second tank assembly. 28. The aircraft of claim 24 wherein the auxiliary fuel tank system further comprises a third tank assembly removably installed in the fuselage at least proximate to the second tank assembly, and wherein the fuel inlet manifold is configured to flow fuel into the first, second, and third tank assemblies at least approximately simultaneously.
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이 특허에 인용된 특허 (27)
Coloney Wayne H. (P.O. Box 668 Tallahasse FL 32302), Aircraft fuel tank.
Caniglia Joseph E. (5368 E. 134th St. Garfield Heights OH 44125) Caniglia Roberto G. (5368 E. 134th St. Garfield Heights OH 44125), Bladder for fuel tank.
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.
Chan Allan L. ; Connors James J. ; Epstein Kenneth W. ; Heath Robert M. ; Ogden Gene Spencer ; Prewitt Michael B. ; Wong Michael ; Szeto Edward W. ; Kennon David P. ; Vogel Michael J. ; Hsu Larry Y. , Orbital assist module and interstage.
Richardson Walter R. (Pointe Claire CA CAX) Oakes Harry (Arcadia CA) Bernstein Saul (Montreal MO CAX) Handleman Avrom R. (St. Louis MO), Powder and water mixing and dropping system onboard an aircraft.
Barbosa, Weber de Brito; Hasmann, Paulo Henrique; Assao, Regis, Aircraft fuel tanks, systems and methods for increasing an aircraft's on-board fuel capacity.
Bistuer, Olivier; Mougin, Stephane; Klos, Sebastien, Rotorcraft having fuel tanks mounted in suspension under a load-bearing middle floor of the fuselage of the rotorcraft.
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