High lift system for an aircraft with two separate drive units

Patent metadata

Field	Value
Publication number	US-9682769-B2
Application number	US-201313832483-A
Country	US
Kind code	B2
Filing date	Mar 15, 2013
Priority date	Oct 5, 2010
Publication date	Jun 20, 2017
Grant date	Jun 20, 2017

Abstract

A high-lift system on a wing of an aircraft is provided. The wing includes a right-hand and a left-hand wing half with movably held high-lift flaps and the right-hand and left-hand wing half are attached to an aircraft fuselage, thus forming a wing root. Each wing half in a region in close proximity to the wing root, includes a drive unit. In each case this drive unit is joined to a transmission shaft mechanically connected to the respective drive unit, which transmission shaft extends from the drive unit in the direction of the end of the respective wing half and is designed to mechanically move the high-lift flaps arranged in the respective wing half. By means of such an arrangement it is possible to do without deflection gear arrangements from a central drive unit to the individual wing halves.

First claim

What is claimed is:

1. A high-lift system on a wing of an aircraft, which wing comprises a left-hand wing half with a first plurality of movably held high-lift flaps and a right-hand wing half with a second plurality of movably held high-lift flaps and is attached to an aircraft fuselage thus forming a wing root, comprising:
a first and a second independently operable drive unit arranged in the left-hand wing half and right-hand wing half, respectively, in a region in close proximity to the wing root, the first and second drive units being joined to a first and a second transmission shaft respectively, the first and second transmission shafts being mechanically coupled to the respective first and second drive units and extending from the first and second drive units in the direction of the end of the left-hand wing half and right-hand wing half respectively and are configured to mechanically move the first and second pluralities of high-lift flaps arranged in the left-hand wing half and right-hand wing half respectively.

2. The high-lift system of claim 1 , further comprising at least first and second actuator devices in the left-hand wing half and right-hand wing half, respectively, mechanically connected to the first and second transmission shafts and to the first and second pluralities of high-lift flaps to be moved,
wherein the first and second drive units, when viewed in the direction of the wingspan, are arranged closer to the wing root than the at least first and second actuator devices.

3. The high-lift system of claim 1 , further comprising two or more actuator devices, wherein the drive unit, when viewed in the direction of the wingspan, is arranged between a first actuator device and a second actuator device.

4. The high-lift system of claim 1 , further comprising first and second control computers that are independent of each other, which are both connected to the first and second drive units, and are configured to acquire current desired positions and actual positions of the high-lift flaps to be moved and to control the respective drive unit to equalize the actual positions to the target positions.

5. The high-lift system of claim 1 , further comprising a roll compensation unit connected to the drive units and configured to superimpose differential rolling moments by a difference in the actuating distance from respective target positions.

6. An aircraft, comprising:
a fuselage;
a wing with a left-hand wing half and a right-hand wing half that are each attached to the fuselage to form a wing root;
a first plurality of high-lift flaps movably coupled to the left-hand wing half and a second plurality of high-lift flaps movably coupled to the right-hand wing half; and
a first and a second independently operable drive unit arranged in the left-hand wing half and right-hand wing half, respectively, in a region in close proximity to the wing root, the first and second drive units being joined to a first and a second transmission shaft, respectively, the first and second transmission shafts coupled to the first and second drive units, respectively, and extending from the first and second drive units in the direction of the end of the left-hand wing half and right-hand wing half and are configured to mechanically move the first and the second pluralities of high-lift flaps arranged in the left-hand wing half and right-hand wing half, respectively.

7. The aircraft of claim 6 , further comprising at least first and second actuator devices in the left-hand wing half and right-hand wing half, respectively, mechanically connected to the first and second transmission shafts and to the first and second pluralities of high-lift flaps to be moved,
wherein the first and second drive units, when viewed in the direction of the wingspan, are arranged closer to the wing root than the at least first and second actuator devices.

8. The aircraft of claim 6 , further comprising two or more actuator devices, wherein the drive unit, when viewed in the direction of the wingspan, is arranged between a first actuator device and a second actuator device.

9. The aircraft of claim 6 , further comprising first and second control computers that are independent of each other, which are both connected to the first and second drive units, and are configured to acquire current desired positions and actual positions of the high-lift flaps to be moved and to control the respective drive unit to equalize the actual positions to the target positions.

10. The aircraft of claim 6 , further comprising a roll compensation unit that is connected to the drive units and that is designed to superimpose differential rolling moments by means of a difference in the actuating distance from respective target positions.

11. The high-lift system of claim 1 , wherein the first drive unit is mechanically coupled exclusively to the first transmission shaft, and
wherein the second drive unit is mechanically coupled exclusively to the second transmission shaft.

Assignees

• Airbus Operations Gmbh

Inventors

• Richter Martin

Classifications

• B64C13/30 Primary

  using cable, chain, or rod mechanisms · CPC title

• Y02T50/44

  Cross-Sectional Technologies · mapped topic

• B64D2045/001

  for indicating symmetry of flaps deflection · CPC title

• B64D45/0005

  Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear · CPC title

• B64C13/28 Primary

  mechanical · CPC title