Foldable wing and actuator arrangement

Patent metadata

Field	Value
Publication number	US-10676174-B2
Application number	US-201715619031-A
Country	US
Kind code	B2
Filing date	Jun 9, 2017
Priority date	Jun 9, 2016
Publication date	Jun 9, 2020
Grant date	Jun 9, 2020

Abstract

A wing (9) having a base section (11) and a tip section (13) pivotably connected to the base section (11) such that the tip section (13) is pivotable between a deployed position and a stowed position in which the spanwise length of the wing (9) is smaller than in the deployed position. The wing arrangement also has an actuating arrangement (19) including a linear hydraulic actuator (21) coupled between the base section (11) and the tip section (13) such that it is operable to selectively move the tip section (13) between the deployed position and the stowed position, a first and a second hydraulic connection portion (79a, 79b) connected to the linear hydraulic actuator (21) such that they are in fluid communication with different chamber sections (27a, 27b) of a cylinder (25) of the linear hydraulic actuator (21), and a first hydraulic subsystem (81a) and a second hydraulic subsystem (81b).

First claim

The invention claimed is:

1. A wing arrangement for an aircraft comprising:
a wing having:
a base section having a first end portion and an opposite second end portion, wherein the first end portion is adapted to be secured to a fuselage of the aircraft, and
a tip section having a third end portion and an opposite fourth end portion, wherein the third end portion is pivotably connected to the second end portion such that the tip section is pivotable about a pivot axis between a deployed position and a stowed position in which the spanwise length of the wing is smaller than in the deployed position, and
an actuating arrangement including:
a linear hydraulic actuator, which comprises a cylinder defining a cylinder chamber and a piston movably arranged in the cylinder chamber and sealingly dividing the cylinder chamber into a first chamber section and a second chamber section, wherein the linear hydraulic actuator is coupled between the base section and the tip section such that the linear hydraulic actuator is operable to selectively move the tip section between the deployed position and the stowed position,
a first hydraulic connection portion connected to the linear hydraulic actuator such that the first hydraulic connection portion is in fluid communication with the first chamber section,
a second hydraulic connection portion connected to the linear hydraulic actuator such that the second hydraulic connection portion is in fluid communication with the second chamber section, and
a first hydraulic subsystem and a second hydraulic subsystem, each connected to and branching off the first and second hydraulic connection portions, and each operable to supply pressurized hydraulic fluid to the first and second hydraulic connection portions, wherein
a first shut-off valve is located between the first hydraulic subsystem and the first and second hydraulic connection portions, and is operable to selectively separate the first hydraulic subsystem from the first and second hydraulic connection portions,
the first hydraulic subsystem comprises a first hydraulic supply including a first connector assembly adapted to be connected to a first hydraulic system of an aircraft which first hydraulic system is operable to supply a plurality of consumers of the aircraft with pressurized hydraulic fluid, and
the second hydraulic subsystem comprises a motor and a pump, wherein the motor is coupled via a motor shaft to the pump such that motor is operable to drive the pump to pump hydraulic fluid contained in the second hydraulic subsystem to the first and second hydraulic connection portions.

2. The wing arrangement according to claim 1 , wherein the linear hydraulic actuator is the only linear hydraulic actuator coupled between the base section and the tip section and operable to move the tip section between the deployed and stowed positions.

3. The wing arrangement according to claim 1 , wherein the pivot axis is oriented in a direction extending between a first edge and a second edge of the wing opposite to each other in a chord direction of the wing.

4. The wing arrangement according to claim 1 , wherein each of the first and second hydraulic subsystems is adapted to effect movement of the tip section between the deployed and stowed positions independent of the other one of the first and second subsystems.

5. The wing arrangement of claim 1 , wherein
a second shut-off valve is located between the second hydraulic subsystem and the first and second hydraulic connection portions, and is operable to selectively separate the second hydraulic subsystem from the first and second hydraulic connection portions, or
a clutch is provided between the motor shaft and the pump.

6. The wing arrangement of claim 1 , wherein
the pump and the motor are bidirectional such that the hydraulic fluid contained in the second hydraulic subsystem is pumped to the first hydraulic connection portion or to the second hydraulic connection portion depending on the direction in which the pump is driven by the motor, or
the pump and the motor are unidirectional and the second hydraulic subsystem further includes a selection valve which can be selectively switched between a first position in which the hydraulic fluid contained in the second hydraulic subsystem is pumped to first hydraulic connection portion and a second position in which the hydraulic fluid contained in the second hydraulic subsystem is pumped to second hydraulic connection portion.

7. The wing arrangement according to claim 1 , wherein the motor is an electric motor.

8. The wing arrangement according to claim 7 , wherein the second hydraulic subsystem comprises a hydraulic accumulator and a separation valve connected between the hydraulic accumulator and the suction side of the pump, wherein the separation valve is controllable to open when the second hydraulic subsystem is active to thereby connect the suction side of the pump to the hydraulic accumulator, wherein the hydraulic accumulator is connected to the first hydraulic supply via a check valve, such that hydraulic fluid is provided to the hydraulic accumulator by the first hydraulic supply if the hydraulic pressure provided by the first hydraulic supply is higher than the pressure inside the hydraulic accumulator.

9. The wing arrangement according to claim 1 , wherein
the second hydraulic subsystem comprises a second hydraulic supply including a second connector assembly separate from the first connector assembly and adapted to be connected to a second hydraulic system of an aircraft which second hydraulic system is operable to supply a plurality of consumers of the aircraft with pressurized hydraulic fluid, and
the motor is a hydraulic motor connected to the second hydraulic supply and operable to be driven by pressurized hydraulic fluid supplied by the second hydraulic supply.

10. The wing arrangement of claim 9 , wherein the second hydraulic subsystem comprises a hydraulic accumulator and a pressure relief valve connectable between the hydraulic accumulator and the suction side of the hydraulic pump, wherein the pressure relief valve is normally closed and adapted to open when a predetermined hydraulic pressure is exceeded to thereby connect the suction side of the pump to the hydraulic accumulator.

11. The wing arrangement of claim 10 , wherein the hydraulic accumulator is connected via separate check valves to the first and second hydraulic connection portions, so that the hydraulic accumulator is operable to serve as a source of pressurized hydraulic fluid in case the hydraulic pressure at the suction side of the hydraulic pump is lower than the hydraulic pressure in the hydraulic accumulator.

12. The wing arrangement according to claim 1 , further comprising
a latching device having at least one latching element which is selectively movable between a latching position and a release position, wherein
when the tip section is in the deployed position and the at least one latching element is moved from the release position to the latching position the at least one latching element engages one of the tip section and the base section and thereby prevents the tip section from moving out of the deployed position, and
when the tip section is in the deployed position and the at least one latching element is moved from the latching position to the release position the tip section or the base section is able to disengage from the at least one latching element, so that the tip section is able to move from the deployed position into the stowed position,
at least one first hydraulic latching actuator and at least one second hydraulic latching actuator, each operable to move the at least one latching

Assignees

• Airbus Operations Gmbh

Inventors

• Winkelmann Christoph
• Rupp Johannes

Classifications

• Y02T50/14

  Cross-Sectional Technologies · mapped topic

• B64C2201/102

  Operations & Transport · mapped topic

• B64C3/56 Primary

  Folding or collapsing to reduce overall dimensions of aircraft · CPC title

• F15B9/10

  in which the controlling element and the servomotor each controls a separate member, these members influencing different fluid passages or the same passage · CPC title

• Y02T50/10

  Drag reduction · CPC title