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 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

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.