AERIAL REFUELING SYSTEM

• US 20090032645A1
• Filed: 10/16/2008
• Published: 02/05/2009
• Est. Priority Date: 06/10/2005
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Shelly, Mark A., Cutler, Theron L.
• Granted Patent: US 7,665,479 B2
• Time in Patent Office: Days
• US Class Current: 244/135.A
• CPC Class Codes: B64D 39/00 Refuelling during flight filling or emptying fuel tanks B64D37/14
• CPC Class Codes: Y10T 137/0318 Processes
• CPC Class Codes: Y10T 137/4673 Plural tanks or compartments with parallel flow
• CPC Class Codes: Y10T 137/4857 With manifold or grouped outlets

Abstract

A method for operating an aircraft refueling system, where the aircraft refueling system has a computer system, a plurality of fuel tanks containing a fuel, a plurality of fuel pumps, a plurality of motor operated valves, and at least one refueling connection. The method may involve using the computer system to signal at least one of the motor operated valves to open; initiating a flow of the fuel to the at least one of the refueling connections using at least one of the pumps; sensing a flow condition of the fuel; signaling the flow condition to the computer system; and varying an operating quantity of the pumps in response to the flow condition.

Claims

1. A method for operating an aircraft refueling system, the aircraft refueling system having a computer system, a plurality of fuel tanks containing a fuel, a plurality of fuel pumps, a plurality of motor operated valves, and at least one refueling connection, the method comprising:

using the computer system to signal at least one of the motor operated valves to open;

initiating a flow of the fuel to the at least one of the refueling connections using at least one of the pumps;

sensing a flow condition of the fuel;

signaling the flow condition to the computer system; and

varying an operating quantity of the pumps in response to the flow condition.

2. The method of claim 1, further comprising connecting the plurality of fuel tanks using a single wall manifold by operation of first ones of the valves.

3. The method of claim 1, further comprising joining individual ones of the fuel tanks located in manned spaces of an aircraft to the single wall manifold using a double wall pipe by opening second ones of the valves.

4. The method of claim 1, further comprising connecting a flow meter to the computer system prior to the signaling step.

5. The method of claim 1, further comprising further comprising connecting a pressure transducer to the computer system prior to the signaling step.

6. The method of claim 1, further comprising shutting off the at least one of the pumps upon completion of a refueling operation.

7. The method of claim 1, further comprising controlling a center of gravity of the aircraft by transferring the fuel into select ones of the fuel tanks.

8. A method for operating an aircraft refueling system, the method comprising:

connecting a first wing tank and a second wing tank by a connecting header;

connecting a forward auxiliary fuel tank to the connecting header;

connecting a center wing tank to the connecting header;

connecting a rear auxiliary fuel tank to the connecting header;

using a refueling connection located remotely from the wing tanks, the forward auxiliary fuel tank, the center wing tank, and the rear auxiliary wing tank, to discharge fuel from at least one said fuel tanks through the refueling connection;

monitoring a flow of said fuel out from at least one of the fuel tanks; and

controlling at least one fuel pump in communication with one of the fuel tanks in accordance with a monitored fuel flow in said connecting header to transfer said fuel from said one fuel tank to the refueling connection.

9. The method of claim 8, further comprising controlling a second fuel pump associated with a different one of said fuel tanks besides said one fuel tank, simultaneously with said at least one fuel pump, to supply said fuel through said connecting header to said refueling connection.

10. The method of claim 8, further comprising using a retractable refueling hose in communication with said refueling connection to dispense said fuel.

11. The method of claim 10, further comprising using a valve operably associated with said refueling hose and controlled by a controller to drain fuel from said refueling hose back into said connecting header.

12. The method of claim 8, further comprising using at least one electrically controlled valve to control a flow of said fuel through said connecting header.

13. The method of claim 8, wherein said monitoring a flow of said fuel comprises using a controller to control said one electrically controlled valve in accordance with said monitored fuel flow to control fuel discharged from said connecting header to said refueling connection.

14. The method of claim 10, further comprising using a float associated with said at least one fuel pump to monitor a level of said fuel within said one fuel tank, and enabling manual overriding operation of said pump by an operator.

15. The method of claim 9, further comprising controlling operation of said fuel pumps to control a center of gravity of said aircraft.

16. A method for operating an aircraft refueling system having a computer system, plurality of independent fuel tanks containing a fuel, a plurality of fuel pumps, a plurality of motor operated valves, and at least one refueling connection, the method comprising:

using the computer system to control a plurality of the motor controlled valves to open and close, and a plurality of said pumps to being pumping;

initiating a flow of said fuel to said at least one refueling connection using at least one of the pumps from at least one of the fuel pumps of a specified one of said fuel tanks;

monitoring a flow of said fuel to said one refueling connection; and

controlling operation of said motor controlled valves and said fuel pumps to redistribute a volume of fuel in said fuel tanks between selected one of said fuel tanks to balance the weight of said fuel tanks and to control a center of gravity of said aircraft.

17. The method of claim 16, further comprising using a double walled wall pipe to connect a selected one of said fuel tanks that is located in a manned space of said aircraft with a manifold, where the manifold is in communication with said refueling connection.

18. The method of claim 16, further comprising enabling a mechanical override of at least one of said fuel pumps.

19. The method of claim 16, further comprising using a refueling hose assembly in communication with said refueling connection to dispense said fuel.

20. The method of claim 19, further comprising providing a valve controlled by a controller to enable fuel within said refueling hose assembly to be drained therefrom back into at least one said fuel tanks.