System and method for aerial refueling door actuation

Patent metadata

Field	Value
Publication number	US-10981665-B2
Application number	US-201815864883-A
Country	US
Kind code	B2
Filing date	Jan 8, 2018
Priority date	Jan 8, 2018
Publication date	Apr 20, 2021
Grant date	Apr 20, 2021

Abstract

A device includes a drive link coupled to an actuator and a first link coupled to the drive link, the first link and the drive link forming a first pivot point. The device also includes a second link coupled to the first link and a support shaft coupled to second link. The second link and the first link form a second pivot point and the second link is configured to rotate about the support shaft. The device further includes a third link coupled to the second link and includes a fourth link coupled to third link and coupled to a door assembly. The third link and the second link form a third pivot point, and the fourth link and the third link form a fourth pivot point. When the door assembly is in an open position, the support shaft, the third pivot point, and the fourth pivot point are aligned.

First claim

What is claimed is:

1. An aircraft comprising:
a torque transfer shaft;
a door assembly;
door linkages coupled to the door assembly and the torque transfer shaft;
an actuator including a driveshaft, wherein the actuator is configured to open and close the door assembly via the door linkages; and
a double on-center mechanical linkage coupled to the torque transfer shaft and the actuator, wherein the double on-center mechanical linkage is configured to have a first set of links in an on-center configuration when the door assembly is in an open state and a second set of links in an on-center configuration when the door assembly is in a closed state.

2. The aircraft of claim 1 , wherein the actuator comprises a rotary electric actuator, and wherein the rotary electric actuator is located within a pressurized portion of the aircraft.

3. The aircraft of claim 1 , wherein the door assembly is located in proximity to a nose of the aircraft, wherein the door assembly corresponds to an aerial refueling door, and wherein the door assembly is curved and configured to open outwards with respect to the aircraft.

4. The aircraft of claim 1 , further comprising a controller configured to control operation of the actuator and to control a state of the door assembly.

5. The aircraft of claim 1 , further comprising a limit switch coupled to the aircraft, the limit switch configured to generate a signal configured to cause deactivation of the actuator based on contact with a portion of the double on-center mechanical linkage.

6. The aircraft of claim 1 , wherein the door assembly includes an aerial refueling door and further comprising:
a fuel intake nozzle housed within a compartment partially enclosed by the door assembly;
one or more fuel tanks in fluid connection with the fuel intake nozzle; and
a refueling boom in fluid connection with the one or more fuel tanks, the refueling boom configured to refuel other aircraft in flight.

7. The aircraft of claim 1 , wherein the double on-center mechanical linkage comprises:
a drive link mechanically coupled to the actuator, wherein the drive link is configured to rotate about the driveshaft of the actuator;
a first link rotatably coupled to the drive link, wherein the first link and the drive link form a first pivot point;
a second link rotatably coupled to the first link, wherein the second link and the first link form a second pivot point;
a support shaft coupled to second link, wherein the second link is configured to rotate about the support shaft;
a third link rotatably coupled to the second link, wherein the third link and the second link form a third pivot point; and
a fourth link rotatably coupled to third link and mechanically coupled to the door assembly, wherein the fourth link and the third link form a fourth pivot point, and wherein, when the door assembly is in the open state, the support shaft, the third pivot point, and the fourth pivot point are aligned.

8. The aircraft of claim 7 , wherein, when the door assembly is in the closed state, the driveshaft, the first pivot point, and the second pivot point are aligned.

9. The aircraft of claim 7 , wherein, when the door assembly is in the open state, the second pivot point is further aligned with the support shaft, the third pivot point, and the fourth pivot point.

10. The aircraft of claim 7 , wherein the door assembly further comprises:
a first door;
a second door;
a first door driving linkage coupled to the first door and coupled to the fourth link via a shaft, wherein the first door driving linkage is configured to open and close the first door; and
a second door driving linkage coupled to the second door and coupled to the fourth link via a shaft, wherein the second door driving linkage is configured to open and close the second door.

11. The aircraft of claim 10 , wherein the first door driving linkage includes:
an input link;
a coupler link rotatably coupled to the input link; and
an output link rotatably coupled to the coupler link and coupled to the first door via an output shaft.

12. The aircraft of claim 7 , wherein the actuator comprises a rotary electric actuator.

13. The aircraft of claim 7 , wherein the support shaft coupled to the second link forms a bound pivot point, and wherein the support shaft is configured to absorb loads when the door assembly is in the open state and in the closed state.

14. The aircraft of claim 7 , wherein the first pivot point, the second pivot point, and the third pivot point are moveable pivot points.

15. The aircraft of claim 7 , wherein the first link, the second link, the third link, and the fourth link are substantially straight and move substantially in the same plane, and wherein the drive link, the first link, the second link, the third link, and the fourth link comprise the double on-center mechanical linkage.

16. A method of operating an aerial refueling door, the method comprising:
responsive to rotation of a driveshaft of an actuator in a first direction, opening a door assembly via door linkages based on rotation of a torque transfer shaft coupled to the driveshaft of the actuator by a double on-center mechanical linkage, wherein opening the door assembly includes rotating a drive link about the driveshaft to drive a first link, rotating a second link about a support shaft, driving a third link, and rotating a fourth link mechanically coupled to the torque transfer shaft, and wherein the second link and the third link are aligned on-center when the door assembly is in an open state; and
responsive to rotation of the driveshaft in a second direction, closing the door assembly via the door linkages based on rotation of the torque transfer shaft, wherein closing the door assembly includes rotating the drive link about the driveshaft to drive the first link, rotating the second link about the support shaft, driving the third link, and rotating the fourth link, and wherein the first link and at least a portion of the drive link are aligned on-center when the door assembly is in a closed state.

17. The method of claim 16 , wherein the door assembly is located on an aircraft and is opened during flight, wherein the door assembly being in the open state enables access to a fuel intake nozzle, and further comprising, prior to closing the door assembly, receiving fuel from another aircraft via the fuel intake nozzle.

18. The method of claim 17 , further comprising transferring the received fuel to an operational fuel tank, a refueling tank, or a fuel storage tank.

19. The method of claim 17 , further comprising transferring the received fuel to a third aircraft via a refueling boom.

20. The method of claim 16 , further comprising, when the door assembly is in the open state:
receiving a load at the door assembly; and
transferring the load to the support shaft.

Assignees

• Boeing Co

Inventors

• Arany-Kovacs Steven T
• Blohm Eric D

Classifications

• B64D39/06 Primary

  Connecting hose to aircraft; Disconnecting hose therefrom · CPC title

• B64C1/14

  Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens {accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers}(fairings movable in conjunction with undercarriage elements B64C25/16; bomb doors B64D1/06) · CPC title

• B64C1/1407

  Doors; surrounding frames · CPC title