Refueling booms with multiple couplings and associated methods and systems

• US 7,188,807 B2
• Filed: 03/11/2005
• Issued: 03/13/2007
• Est. Priority Date: 03/11/2005
• Status: Expired due to Fees

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Smith, Jerell L.
• Primary Examiner(s): BAREFOOT, GALEN L
• Application Number:
  US11/078,210
• Publication Number:
  US 20060214059A1
• Time in Patent Office: 732 Days
• Field of Search: 244/135.A, 244/135.R, 141/98, 141/231, 141/387
• US Class Current: 244/135.00A
• CPC Class Codes: B64D 39/06 Connecting hose to aircraft; Disconnecting hose therefrom

Abstract

Refueling booms with multiple couplings, and associated methods and systems, are disclosed. A system in accordance with one embodiment of the invention includes a deployable boom carrying a refueling passage. A first coupler carried by the boom can be operatively coupleable to the refueling passage. The first coupler can be configured to be releasably connected to a receiver aircraft during refueling. A second coupler can be carried by the boom and can be operatively coupleable to the refueling passage, with the second coupler being configured to be releasably connected to a receiver aircraft during refueling. In particular embodiments, the first and second couplers can have different configurations so as to be compatible with aircraft having different refueling arrangements.

Claims

1. An in-flight refueling system, comprising:

a deployable boom carrying a refueling passage;

a first coupler carried by the boom and operatively coupleable to the refueling passage, the first coupler being configured to be releasably connected to a receiver aircraft during refueling; and

a second coupler carried by the boom and operatively coupleable to the refueling passage, the second coupler being configured to be releasably connected to a receiver aircraft during refueling.

2. The system of claim 1 wherein the boom includes a first portion and a second portion that is rotatable relative to the first portion, the second portion having a cross-sectional shape that is elongated and tapered, the second portion including a housing in which the first and second couplers are movably carried, and wherein the system further comprises:

a drive unit operatively coupled to the first and second couplers, the drive unit being configured to selectively move one of the first and second couplers at a time between a stowed position and a deployed position; and

an actuator operatively coupled between the first and second portions to rotate the second portion relative to the first portion about an axis generally aligned with the refueling line;

wherein the first coupler is positioned below the second coupler and includes a probe configured to be received in a corresponding receptacle of a receiver aircraft; and

wherein the second coupler is positioned above the first coupler and includes a hose and drogue, the hose being flexible, the drogue being configured to receive a probe of a receiver aircraft.

3. The system of claim 1 wherein the first and second couplers are positioned so as to preclude simultaneous coupling to two corresponding receiver aircraft.

4. The system of claim 1 wherein the first coupler is configured to be received at least partially within a corresponding receptacle of a receiver aircraft, and wherein the second coupler is configured to receive a corresponding connector of a receiver aircraft at least partially within the second coupler.

5. The system of claim 1 wherein at least a portion of the boom has a cross-sectional shape that is elongated and tapered in a generally upward direction.

6. The system of claim 1, further comprising an aircraft carrying the boom.

7. The system of claim 1, further comprising a valve carried by the boom, the valve being positioned to selectively couple the first coupler to the refueling passage in a first mode, and selectively couple the second coupler to the refueling passage in a second mode.

8. The system of claim 1 wherein the boom is elongated along a boom axis and includes a first portion coupleable to a refueling aircraft, and a second portion coupled to the first portion, the second portion carrying the first and second couplers and being rotatable relative to the first portion about an axis generally aligned with the boom axis.

9. The system of claim 1 wherein the first coupler and second coupler are connected to a common drive unit to move from a stowed position to a deployed position, and wherein the drive unit is configured to move one coupler at a time.

10. The system of claim 1 wherein the boom includes a housing and wherein at least one of the first and second couplers is movable relative to the housing between a stowed position and a deployed position, and wherein the at least one coupler is positioned to refuel a receiver aircraft when in the deployed position.

11. The system of claim 1 wherein:

the first coupler include first means for coupling the refueling passage to a receiver aircraft during refueling; and

the second coupler includes second means for coupling the refueling passage to a receiver aircraft during refueling.

12. An in-flight refueling system, comprising:

a deployable boom carrying a refueling passage and being elongated along a boom axis, the boom having an external contour, and wherein a cross-sectional shape of the external contour is elongated along a contour axis extending generally transverse to the boom axis; and

at least one coupler carried by the boom and configured to be releasably connected to a receiver aircraft during refueling.

13. The system of claim 12 wherein the at least one coupler includes a first coupler and a second coupler, and wherein the deployable boom includes a first portion and a second portion, the second portion having the elongated cross-sectional shape and being rotatable relative to the first portion about a rotation axis that is at least approximately aligned with the boom axis, the second portion including a housing in which the first and second couplers are movably carried, and wherein the system further comprises:

a drive unit operatively coupled to the first and second couplers, the drive unit being configured to selectively move one of the first and second couplers at a time between a stowed position and a deployed position; and

an actuator operatively coupled to between the first and second portions to rotate the second portion relative to the first portion about the rotation axis;

wherein the first coupler is positioned below the second coupler and includes a probe configured to be received in a corresponding receptacle of a receiver aircraft; and

wherein the second coupler is positioned above the first coupler and includes a hose and drogue, the hose being flexible, the drogue being configured to receive a probe of a receiver aircraft.

14. The system of claim 12 wherein the cross-sectional shape is tapered in a direction generally aligned with the contour axis.

15. The system of claim 12 wherein the deployable boom includes a first portion and a second portion, the second portion having the elongated cross-sectional shape and being rotatable relative to the first portion about a rotation axis that is at least approximately aligned with the boom axis.

16. The system of claim 12 wherein the deployable boom includes a first portion and a second portion, the second portion having the elongated cross-sectional shape and being rotatable relative to the first portion about a rotation axis that is at least approximately aligned with the boom axis, and wherein the second portion is coupled to a boom steering control device.

17. The system of claim 12 wherein the cross-sectional shape is generally symmetric about the contour axis.

18. The system of claim 12, further comprising movable control surfaces coupled to the boom.

19. The system of claim 12 wherein the cross-sectional shape has a leading edge portion and a trailing edge portion, and wherein the leading edge portion is blunter than the trailing edge portion.

20. A method for refueling aircraft in flight, comprising:

deploying a generally rigid boom from a refueling aircraft;

releasably connecting a first coupler carried by the boom to a first receiver aircraft;

refueling the first receiver aircraft via the first coupler;

releasing the connection between the first coupler and the first receiver aircraft;

releasably connecting a second coupler carried by the boom to a second receiver aircraft;

refueling the second receiver aircraft via the second coupler; and

releasing the connection between the second coupler and the second receiver aircraft.

21. The method of claim 20 wherein refueling the first receiver aircraft includes refueling the first receiver aircraft with a first coupler having a first configuration and wherein refueling the second receiver aircraft includes refueling the second receiver aircraft with a second coupler having a second configuration different than the first configuration.

22. The method of claim 20 wherein releasably connecting the second coupler includes releasably connecting the second coupler without landing the aircraft between the time the connection between the first coupler and the first receiver aircraft is released and the time the second coupler is connected.

23. The method of claim 20 wherein releasably connecting the second coupler includes releasably connecting the second coupler without stowing the boom between the time the connection between the first coupler and the first receiver aircraft is released and the time the second coupler is connected.

24. The method of claim 20 wherein the boom is elongated along a boom axis and wherein the boom includes a first portion and a second portion that is rotatable relative to the first portion, the second portion having a cross-sectional shape that is elongated and tapered in a generally upward direction, the second portion including a housing in which the first and second couplers are movably carried, and wherein the method further comprises:

independently moving the first and second couplers between stowed and deployed positions with a common drive unit; and

rotating the second portion relative to the first portion about a rotation axis that is generally parallel to the boom axis to impart aerodynamic forces on the boom that move the boom toward a selected position;

wherein releasably connecting a first coupler includes releasably connecting a first coupler positioned below the second coupler and wherein releasably connecting a first coupler includes inserting a probe into a corresponding receptacle of the first receiver aircraft; and

wherein releasably connecting a second coupler includes deploying a flexible hose and drogue and receiving a probe of the second receiver aircraft in the drogue.

25. The method of claim 20, further comprising:

moving the first coupler from a stowed position to a deployed position prior to releasably connecting the first coupler;

moving the first coupler from the deployed position to the stowed position after releasing the connection between the first coupler and the first receiver aircraft;

moving the second coupler from a stowed position to a deployed position prior to releasably connecting the second coupler; and

moving the second coupler from the deployed position to the stowed position after releasing the connection between the second coupler and the second receiver aircraft.