High lift system for an aircraft and aircraft having such a high lift system

Patent metadata

Field	Value
Publication number	US-9868511-B2
Application number	US-201514608271-A
Country	US
Kind code	B2
Filing date	Jan 29, 2015
Priority date	Jan 29, 2014
Publication date	Jan 16, 2018
Grant date	Jan 16, 2018

Abstract

A high lift system for an aircraft comprises a wing structure and a leading edge slat movably supported relative to a leading edge of the wing structure, the leading edge slat comprises a leading edge and a trailing edge, wherein the trailing edge is configured to take different positions to form a gap between the leading edge slat and the wing structure, a skin and enclosing an interior space of the leading edge slat, the skin having a flexible leading skin section facing away from the wing structure, a flexible trailing skin section facing towards the wing structure, at least one actuation arrangement arranged inside the interior space for selectively introducing a normal force onto at least one of the leading skin section and the trailing skin section.

First claim

What is claimed is:

1. A high lift system for an aircraft, comprising a wing structure and a leading edge slat movably supported relative to a leading edge of the wing structure, the leading edge slat comprising:
a leading edge and a trailing edge, wherein the trailing edge is configured to take different positions to form a gap between the leading edge slat and the wing structure,
a skin enclosing an interior space of the leading edge slat, the skin having a flexible leading skin section facing away from the wing structure, and a flexible trailing skin section facing towards the wing structure, and
at least one actuation arrangement arranged inside the interior space for selectively introducing normal forces onto the leading skin section and the trailing skin section,
wherein said normal forces change the profile of the skin in such a way that the trailing edge changes its position relative to the wing structure to selectively close or open the gap between the leading edge slat and the wing structure,
wherein the at least one actuation arrangement comprises a rotary actuator, which is coupled with at least one lever, pivotably attached to a joint on the inside of the trailing skin section and to a joint on the inside of the leading skin section, wherein the rotary actuator, the at least one lever, and the joints are arranged inside the interior space, and
wherein the rotary actuator comprises a pair of bevel gears, couplable with a first spindle screw, which engages with a first screw nut coupled to the trailing skin section by a first coupling element, and couplable with a second spindle screw, which engages with a second screw nut coupled to the leading skin section by a second coupling element, wherein the pair of bevel gears, the spindle screws, the screw nuts, and the coupling elements are arranged inside the interior space.

2. The high lift system of claim 1 ,
wherein the at least one actuation arrangement is configured for introducing normal force in a region distant from the trailing edge, such that due to the change in the profile pulling forces act onto the trailing edge through the skin.

3. The high lift system of claim 1 ,
wherein the at least one actuation arrangement is configured for bending at least one of the leading skin section and the trailing skin section towards the interior space when normal force is introduced.

4. The high lift system of claim 1 ,
wherein the at least one actuation arrangement is configured for bending the trailing skin section towards the leading skin section, and
wherein the trailing edge of the skin is urged towards the leading edge of the wing structure upon bending the trailing skin section.

5. The high lift system of claim 1 ,
wherein the at least one actuation arrangement comprises a release means, which is configured for abruptly releasing normal force introduced by the at least one actuation arrangement.

6. The high lift system of claim 1 ,
wherein the rotary actuator comprises a motor, a clutch and a gearbox, and
wherein the gearbox is selectively couplable to the motor through the clutch.

7. The high lift system of claim 6 ,
further comprising a brake, which is coupled with the clutch and the gearbox for selectively arresting the gearbox such that a profile shape is maintainable without the clutch coupling the motor and the gearbox.

8. The high lift system of claim 6 ,
wherein the gearbox comprises a continuously variable transmission gear.

9. The high lift system of claim 1 ,
wherein the rotary actuator comprises a motor, a brake and a gearbox, and
wherein the gearbox is permanently coupled with the motor.

10. The high lift system of claim 1 ,
further comprising a friction ring clutch arranged between the first screw nut and the first coupling element.

11. The high lift system of claim 1 ,
wherein the at least one actuation arrangement is configured for introducing a normal force onto both of the leading skin section and the trailing skin section at the same time, such that a distance between the leading skin section and the trailing skin section is decreased upon introducing the normal force.

12. The high lift system of claim 1 ,
comprising a plurality of actuation arrangements, which are driven by a single shaft, which is extending along a nose region of the slat.

13. A high lift system for an aircraft, comprising a wing structure and a leading edge slat movably supported relative to a leading edge of the wing structure, the leading edge slat comprising:
a leading edge and a trailing edge, wherein the trailing edge is configured to take different positions to form a gap between the leading edge slat and the wing structure,
a skin enclosing an interior space of the leading edge slat, the skin having a flexible leading skin section facing away from the wing structure, and a flexible trailing skin section facing towards the wing structure, and
at least one actuation arrangement arranged inside the interior space for selectively introducing a normal force onto at least one of the leading skin section and the trailing skin section,
wherein said normal force changes the profile of the skin in such a way that the trailing edge changes its position relative to the wing structure to selectively close or open the gap between the leading edge slat and the wing structure,
wherein the at least one actuation arrangement comprises a rotary actuator, which is coupled with a first lever pivotably attached to a first joint on the inside of at least one of the trailing skin section and the leading skin section, and which is coupled with a second lever pivotably attached to a second joint on the inside of at least one of the trailing skin section and the leading skin section, wherein the rotary actuator, the levers, and the joints being arranged inside the interior space, and
wherein the rotary actuator comprises a single transmission shaft coupled to a first pair of bevel gears and to a second pair of bevel gears, the first pair of bevel gears couplable with a first spindle screw, which engages with a first screw nut coupled to the at least one of the trailing skin section and the leading skin section by a first coupling element, and the second pair of bevel gears couplable with a second spindle screw, which engages with a second screw nut coupled to the at least one of the trailing skin section and the leading skin section by a second coupling element, wherein the single transmission shaft, the pairs of bevel gears, the spindle screws, the screw nuts, and the coupling elements are arranged inside the interior space.

14. A high lift system for an aircraft, comprising a wing structure and a leading edge slat movably supported relative to a leading edge of the wing structure, the leading edge slat comprising:
a leading edge and a trailing edge, wherein the trailing edge is configured to take different positions to form a gap between the leading edge slat and the wing structure,
a skin enclosing an interior space of the leading edge slat, the skin having a flexible leading skin section facing away from the wing structure, and a flexible trailing skin section facing towards the wing structure, and
at least one actuation arrangement arranged inside the interior space for selectively introducing normal forces onto the leading skin section and the trailing skin section,
wherein said normal forces change the profile of the skin in such a way that the trailing edge changes its position relative to the wing structure to selectively close or open the gap between the leading edge slat and the wing structure,
wherein the at least one actuation arrangement comprises a rotar

Assignees

• Airbus Operations Gmbh

Inventors

• Henning Frieder
• Zantz Tanno
• Brady Michael

Classifications

• B64C2009/143

  comprising independently adjustable elements for closing or opening the slot between the main wing and leading or trailing edge flaps · CPC title

• B64C9/22 Primary

  at the front of the wing · CPC title

• B64C9/24

  by single flap · CPC title

• B64C13/50

  using electrical energy · CPC title

• Y02E10/721

  Cross-Sectional Technologies · mapped topic