Devices, systems and methods for refueling air vehicles

Patent metadata

Field	Value
Publication number	US-11834192-B2
Application number	US-202117497514-A
Country	US
Kind code	B2
Filing date	Oct 8, 2021
Priority date	Jan 4, 2012
Publication date	Dec 5, 2023
Grant date	Dec 5, 2023

Abstract

A variety of refueling devices, systems and methods are disclosed for use in in-flight refueling. In one example one such device is towed by a tanker aircraft via a fuel hose at least during in-flight refueling, and has a boom member with a boom axis. The boom member enables fuel to be transferred from the fuel hose to a receiver aircraft along the boom axis during in-flight refueling. The device maintains a desired non-zero angular disposition between the boom axis and a forward direction at least when the refueling device is towed by the tanker aircraft in the forward direction via the fuel hose.

First claim

The invention claimed is:

1. A refueling device for use in in-flight refueling operation between a tanker aircraft and a receiver aircraft, the refueling device comprising:
a selectively steerable body having a longitudinal axis and configured to be towed by a tanker aircraft via a fuel hose at least during in-flight refueling, the selectively steerable body including a boom member having a boom axis and configured to enable fuel to be transferred from said fuel hose to a receiver aircraft along said boom axis during said in-flight refueling operation;
wherein said boom member is pivotably mounted with respect to said body, and pivotable between a retracted position and a deployed position, wherein in said retracted position said boom axis is at a smaller angular disposition with respect to said longitudinal axis than in said deployed position; and
a controller configured for selectively steering the body to an engagement enabling position spaced with respect to the receiver aircraft and for aligning said boom axis in an engagement enabling orientation at said spaced position, and for subsequently moving the boom member along said boom axis towards the receiver aircraft for enabling fuel communication therebetween.

2. The refueling device according to claim 1 , wherein in said retracted position said boom axis is at an angular disposition with respect to said longitudinal axis of between 0° and 15°, and wherein in said deployed position, said angular disposition is greater than 15°.

3. The refueling device according to claim 1 , wherein in said deployed position said boom axis is at an angular disposition with respect to said longitudinal axis between 20° to 40°.

4. The refueling device according to claim 1 , wherein at least during said in-flight refueling the boom axis is at a non-zero angular displacement with respect to the longitudinal axis.

5. The refueling device according to claim 1 , the boom member comprising a fuel delivery nozzle, and the receiver aircraft comprising a fuel receptacle configured for engaging with the fuel delivery nozzle to enable refueling of the receiver aircraft.

6. The refueling device according to claim 1 , comprising a spatial control system configured for selectively ensuring maintaining a desired non-zero angular disposition between said boom axis and a forward direction at least when said refueling device is towed by the tanker aircraft in said forward direction via said fuel hose.

7. The refueling device according to claim 6 , wherein said spatial control system comprises selectively controllable aerodynamic control system.

8. The refueling device according to claim 7 , wherein said selectively controllable aerodynamic control system comprises a forward set of aerodynamic control surfaces mounted to said body, and an aft set of aerodynamic control surfaces mounted to said body in longitudinally aft spaced relationship with respect to said forward set of aerodynamic control surfaces.

9. The refueling device according to claim 6 , wherein said spatial control system is configured for enabling the refueling device to be steered in one, or two, or three degrees of freedom in translation, and in one, or two, or three degrees of freedom in rotation, independently of the tanker aircraft or of the refueling aircraft.

10. The refueling device according to claim 6 , further comprising an aerodynamic stabilizer arrangement, different from the spatial control system.

11. The refueling device according to claim 10 , wherein said aerodynamic stabilizer arrangement is in the form of a drogue structure having a stowed configuration, in which drogue structure generates a minimum drag, and a deployed configuration in drogue structure generates greater drag than in the inactive configuration.

12. The refueling device according to claim 1 , further comprising a force generating arrangement configured for selectively generating a force along said boom axis in a direction towards said fuel delivery nozzle.

13. The refueling device according to claim 12 , wherein said force generating arrangement is configured for selectively generating said force along said boom axis in a direction towards said fuel delivery nozzle responsive to said fuel delivery nozzle positioned in said engagement enabling position wherein to force said fuel delivery nozzle into engagement with the fuel receptacle.

14. The refueling device according to claim 1 , said body comprising a fuel delivery lumen configured for fluid communication with said fuel hose and said boom member at least during the in-flight refueling operation, wherein said body comprises a coupling having a hose interface configured for connecting said lumen to the fuel hose, said coupling configured for allowing relative rotation between the hose and said body in at least one degree of freedom while maintaining said fuel communication.

15. The refueling device according to claim 1 , further comprising a data acquisition system configured for providing spatial data relating to a relative spatial disposition between said fuel delivery nozzle and said fuel receptacle, to enable selectively controlling the refueling device to provide automatic or autonomous or manual engagement of the fuel delivery nozzle to the fuel receptacle of the receiver aircraft.

16. The refueling device according to claim 15 , wherein said data acquisition system comprises or is operatively connected to a computing system configured for identifying a fuel receptacle of a receiver aircraft within said field of regard from said image data, and for determining a spatial disposition of said fuel delivery nozzle with respect to the fuel receptacle.

17. A refueling system comprising a refueling fuel reservoir connected to a refueling device via a hose, the refueling device defined in claim 2 .

18. A tanker aircraft comprising at least one refueling system as defined in claim 17 .

Assignees

• Israel Aerospace Ind Ltd

Inventors

• Rix Ohad
• Gur Joshua
• Litvak Michael
• Koskas Elie

Classifications

• B64D39/06 Primary

  Connecting hose to aircraft; Disconnecting hose therefrom · CPC title

• B64D3/00

  Aircraft adaptations to facilitate towing or being towed · CPC title

• B64D39/00

  Refuelling during flight · CPC title

• B64D39/04

  Adaptations of hose construction · CPC title

• G05D1/0094

  involving pointing a payload, e.g. camera, weapon, sensor, towards a fixed or moving target · CPC title